FAS Military AnalysisNetwork

Russian Missiles

S-25SA-1 GUILD

The S-25 SA-1 GUILD was the first surface-to-air strategic airdefense system deployed by the Soviet Union These R-113 missileswere deployed in a ring around Moscow, and remained in servicethrough the mid-1980s. The SA-1 system entered operationalservice in the late 1950s, and was deployed around Moscow in adense complex of 56 sites arranged in two concentric rings. Therewere 22 sites in the inner ring at about 25 nm radius from the centerof Moscow and 34 sites on the outer ring at about 45 nm radius. Atypical site had 60 launch positions joined by a road network.

The V-301 missile, as originally designed for use with this system,was unboosted and employed a single liquid sustainer motor.Although its maximum speed was on the order of Mach 2.5, it had alow initial velocity which limited its engagement capability againstsupersonic targets. Its maximum intercept range varied dependingupon the approach and type of target; for example, against a directlyincoming, high-flying B-252 its range was on the order of 20 n.m.This missile ccould carry an HE or nuclear payload of 450-700pounds and its CEP was estimated to be 65-120 feet. It was believedto be capable of interceptions from a minimum altitude of 3,000 feetup to 60,000 feet, with some additional capability up to about

80,000 feet, particularly if equipped with a nuclear warhead.

The B-200 guidance system at each site employed a track-while-scan radar (designated"Yo-Yo" by US intelligence) having about 54° coverage in both the vertical andhorizontal planes. The system also incorporated fire control equipment which enabledeach site to engage as many as 20 targets simultaneously. This capability, with thespacing of adjacent sites for mutual support and the inner ring of sites for backup, enablesthe system to direct an extremely high rate of fire against incoming targets.

Because of its' cost, immobility, and inflexibility, the SA-1 system was not deployedelsewhere in the Soviet Union apart from Moscow.

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V-75SA-2 GUIDELINEHQ-1 / HQ-2 (Chinese versions)Tayir as Sabah (Egyptian versions)

The V-75 (SA-2) surface-to-air missile system was designedfor the defense of both fixed targets and field forces. The V-75was designed to cope with the threat posed by small groups ofaircraft rather than massed raids. Flexibility and mobility are itschief advantages over the SA-1. In contrast to the massive SA-1 sites, each of which is capable of defending only a limitedsector around the target area, each SA-2 site is capable of 360°coverage. This flexibility is obtained at the expense of targethandling capacity and rate of fire relative to the SA-1.

Although there are a variety of arrangement patterns, all sitesconsist of six launching positions -- usually revetted - deployedaround a guidance radar and linked by service roads tofacilitate loading. While the sites were permanent installations,all operating components of the system are mounted onwheeled vehicles and are capable of movement by road or raiL

The V-75 was the basic missile defense system for criticalurban-industrial areas in the USSR, other than Moscow. The V-75 deployment began on a wide scale since early 1958, with

sites located throughout the western part of the Soviet Union and Warsaw Pact countries.Deployment patterns and levels of concentration varied according to the geography, size,and shape of the target area, and the Soviet estimate of the worth of individual targets.Between mid-1958 and 1964 more than 600 SA-2 sites were identified by US intelligencein the USSR, mostly in defense of population centers, industrial complexes, andgovernment control centers.Most SA-2 sites defended major centers of population and industry. SA-2 defenses werealso deployed for the special protection of nuclear materials production and storagefacilities. In addition, some key Soviet field forces and long range bomber bases wereincluded in the SA-2 deployment pattern. The construction of sites and the training andactivation of firing units was seasonal, with activity at a minimum during the wintermonths.The sites in the Moscow area, located within the inner ring of SA-1 sites, were intendedto supplement the existing defenses. Deployment of SA-2 installations around Moscowincluded seven sites as of 1964 as part of a program to supplement the SA-1 system.

Missile defenses were provided for most of the Soviet cities with populations greater than200,000. SA-2 sites were emplaced at some smaller urban areas which containedgovernment control centers or other installations of critical importance. They were alsodeployed for defense of naval and port facilities, nuclear production and weapon storageInstallations, missile test ranges, and Industrial facilities. Other major militaryinstallations, such as long-range missile sites and alrfields of the long-range air force, arealso defended by SA-2. A number of sites in border areas, which were unrelated tospecific targets, were part of the deployment of peripheral defenses which eventuallyextended from the Kola Peninsula along the western and southern borders of the USSRinto central Asia. Deployment in the Baltic coastal area was particularly dense. In mid-1962 about 750 sites were operational in defense of more than 200 target areas in theUSSR. The Soviets eventually deployed roughly a thousand SA-2 sites in the USSR, withthe major portion of the deployment completed by the mid-1960s.

Some SA-2 units were deployed in support of Soviet field forces in East Germany and inthe USSR. Although SA-2 units assigned to Soviet field forces were normally emplacedat fixed installations, the system is transportable by road and SA-2 units were observed infield exercises. However, SA-2 units have a limited ability to follow a fast moving frontbecause of the requirement for good roads and the time required to displace to newpositions. SA-2 missile defenses for field forces were primarily assigned to such targetsas major headquarters, logistic centers, and airfields.

Deployment of SA-2 sites for defense of Warsaw Pact targets began in 1960. Theheaviest deployment has occurred in East Germany. About half of the sites were mannedby East German troops, and the remainder by units of the Soviet field forces. The EastGerman sites were located in the vicinity of Berlin and in the northern portion of EastGermany. The Soviet sites were deployed to defend important Soviet militaryinstallations such as major headquarters and airfields.

China

Suspension of Soviet assistance limited the extent of SA-2 deployment in China. Onlyabout a half dozen sites were initially deployed in China, three of them at Beijing. Thesesites contained Soviet manufactured equipment. The Chinese license-built version of theV-75 was designated the HQ-1. The People's Republic of China developed its ownmodified version of the V-750 under the designation HQ-2 (Hong Qian = Red Leader),with the Western designation CSA-1.

According to a China sales brochure, the FT-2000A SAM will use a highly-modifiedHQ-2/ CSA-1 missile that has been equipped with a passive radio frequency homingseeker operating in the 2- to 6-GHz band. The FT-2000A also will contain a newmillimeter-wave band fuze, a new guidance-and-control section, and a new 60 kgfragmentation warhead. The missile has a cutoff valve for thrust adjustment while inflight, probably to extend its range. The missile seeker is loaded with the target aircraft’sradio frequency (RF) signature before launch and relies on this information for tracking

and intercept. The missile has an estimated maximum range of 60 km, with a maximumaltitude of 18,000 meters.

A stand-alone FT-2000A battery consists of a central control station and twelvelaunchers, each holding one missile. The central control station has one master passivesensor and three auxiliary passive sensors. The auxiliary passive sensors coordinate withthe master passive sensor through triangulation to determine angle and range of targetsemitting in the 2- to 6-GHz band. This configuration is totally passive, relying on the RFemissions of the target.

A composite fire unit consists of FT-2000A launchers and missiles, integrated withstandard SAM components like those of the HQ-2, SA-2, or SA-3. Although a specialfire control unit and launcher are required, this configuration allows anti-jammingmissiles to replace several of the command guided missiles normally associated withthese SAMs.

Egypt

Egyptian technicians have reverse engineered and modified two Soviet SAMs -- the Aynas Saqr (a version of the SA-7) and the Tayir as Sabah (a version of the SA-2).

V-75 Missile System

The V-75 SA-2 GUIDELINE is a medium to high altitude surface-to-air missile system.This two-stage missile has a large solid propellant booster stage fitted with four verylarge delta fins. The core stage consists of a storable liquid propellant sustainer rocketmotor using inhibited red fuming nitric acid oxidizer and kerosene fuel. A set of fourcropped delta-shaped wings are located near the mid-section, with a second in-line set ofsmaller fixed fins at the nose, and a third in-line set of slightly larger powered control finsat the tail.

The guidance system at an SA-2 site can handle only one target at a time, but can directthree missiles against a target simultaneously. Additional missiles could be fired againstthe same target after one or more missiles of the first salvo had completed their run. TheSoviets apparently believed they must program three or four missiles against each targetin order to achieve acceptable kill probabilities.

The 295 kg nuclear warhead used only on the SA-2E variant is believed to have a yield of15 kT. The other V-75 variants have an internally grooved fragmentation warhead weighs195 kg (130 kg of which is high explosive) with proximity, contact and command fusingavailable. This conventional warhead is fitted forward of the main fins and behind thenose-mounted guidance assembly. At medium and low altitudes the kill radius is about 65meters and the blast radius for severe damage is 100-120 meters. The maximum blastradius against a high altitude target is approximately 250 meters, due to the rarefiedatmosphere. The weapon has a accuracy of 75 meters with the large blast radiuscompensating for system inaccuracies.

The V-75 system is designed to be simple and easy to operate with the minimum ofspecialized training. The standard deployment pattern of a battalion site consists of sixsemi-fixed trainable single rail launchers are deployed in the familiar hexagonarrangement about 60-100 meters apart. The launchers may be dug into pits, left atground level or hardened in concrete revetments. The battery command post fire controlteam and its computer, the Fan Song missile control radar, the P-12 Spoon Rest earlywarning radar, and typically six reload rounds on their articulated trailers are all locatedin the center of the launchers array.

The Spoon Rest A-band warning and target acquisition radar has a range of 275 km usinga large Yagi antenna array.

SPOON RESTFunction: Target acquisition, early warningRange 275 kmFrequency A versions: A band (VHF)

B versions: VHF below A bandComments Power 314kw, BW 6x22.5

PRF 310-400ppsPW 4-6usMax Alt 32kmScan 2-6rpm

Associated weapon system SA-2 GUIDELINEFAN SONG fire control radar

Recognition Six yagi array with bisecting crossbarMast mounted on 6x6 truckIn transit, two truck carry array andgenerator

KNIFE RESTType KNIFE REST A KNIFE REST B/CRussian Designation P-8 Dolfin P-10Function Early WarningFrequency A-band A-bandRange 75 km 70 km

Comment 75kw powerPW 4-12us

Associated weaponsystem

SA-2

Recognition

The maximum radar range of the E-band Fan Song A/B/F radar varies between 60-120km depending upon target type, altitude and operating conditions. The G-band Fan SongD/E maximum range is extended to between 75-145 km under equivalent conditions.

FAN SONGFAN SONG A/B FAN SONG C/E FAN SONG F

Function: Fire Control & TrackingCan track six targets simultaneously

Range 60-120km (A/Bversions)

70-145km (D/E/F versions)

Frequency E/F bands (A/Bversions)

G band (C/Eversions)

E/F bands (Fversion)

Comments 600kw powerVert Ant BW 1010x2degHort Ant BW2x10degScan 15.5-17HZ

1.0mw powerVert Ant BW7.5x1.5degHort Ant BW11.5x7.5Scan 15.5-17HZPRF 828-1440Search1656-2880 TrkPW .4-1.2ms us2-.9ms us

600kw powerVert Ant BW 1010x2degHort Ant BW2x10degScan 15.5-17HZ(guidance): PRF44pps

Associated weaponsystem

SA-2 GUIDELINE SAM,SPOON REST target acquisition radar

Recognition Trailer-mounted with tilting superstructureTwo orthogonal antennas(lewis scanners)

E version have 2 additional parabolic dishesScanners exhibit 'flapping' motion in operation

SIDE NET PRV-11Function HeightRange 28 km

32km Max altitudeFrequency E-bandAssociated weapon system SA-2/3/5Recognition

At regimental HQ there is a fourth Spoon Rest, a van-mounted P-15 Flat Face 250 kmrange C-band search and tracking radar with two elliptical parabolic reflectors and aPRV-11 Side Net 180 km range E-band nodding height-finder radar mounted on a box-bodied trailer. There is also a radar control truck and a Mercury Grass truck-mountedcommand communications system for linking the HQ to the three battalions.

Some countries which deploy early versions of the V-75 use the older ground-mounted P-8 Dolphin Knife Rest-A truck-mounted P-10 Knife Rest-B/C radars instead of the SpoonRest. These A-band radars have an operating range of about 150-200 km.

The People's Republic of China has deployed a modified version of the V-75 under thedesignation HQ-2. The license-built version was the HQ-1.

SpecificationsDOI 1959

Status Standard

Length (m) 10.60

Diameter (m) .70

Weight at launch (kg) 2,300

Propulsion system

Booster Solid

Sustainer Liquid

Launch rails/tubes Single rail, ground mounted (not mobile)

Guidance Command

Warhead (type) HE 200kg (295kg SA-2E) 188kg (HQ-2B/F/J/P),possible nuclear

Performance:

Max. velocity (Mach) 4.0 B/C/D, 4.5 E/F Mach

Effective altitude 27 B/C/F & HQ-2B/F/J/P, 40 D/E km

Maximum range (km) 35km B/F, 44km C, 50km D/E35km HQ-2B, 50km HQ-2J

Minimum range (km) 7-9

Kill Radius 65 m

Reload time (min) 10

Associated radars FAN SONG, SPOON REST

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HQ-1 / HQ-2 (Chinese versions)

SJ-202 Radar

S-125 SA-3 GOAThe S-125 SA-3 GOA medium altitude surface-to-air missile systemuses a two-stage, solid-fuel missile built by the Isayev OKB. The S-125missile includes a large 2.6 second burn-time solid propellant boosterwith rectangular fins that rotate through 90º at launch. The smallermain stage has an 18.7 second burn-time solid propellant sustainermotor, and has four aft fixed fins and four forward movable control.Following booster jettison the missile is tracked by the system's radarwith guidance signals sent to an antenna on the rear fins.

US intelligence imagery at Kapustin Yar in late 1959 revealed twoprobable R&D sites, each of which consisted of four launch pads. Apossible launcher on one of the pads held two missile-like objects about20 feet long. US intelligence subsequntly identified more than 35 sitesof this type in the USSR between late 1961 and 1964, usually near SA-1 or SA-2 sites. The initial SA-3A GOA Mod 0, deployed in 1961,includes command guidance throughout the missile's flight. The

subsequent SA-3B GOA Mod 1, first deployed in 1964, incorporated an improvedguidance system. The missile's ability to dive allows it to be used against surface targetsand naval vessels.

Long-range surveillance and target acquisition is handled by the van-mounted P-15FLAT FACE) radar. The P-15 radar has been replaced in many S-125 units by the P-15MSQUAT EYE radar, which has the antenna mounted on a 20-30 m mast for improved lowaltitude coverage. The accompanying PRV-11 SIDE NET E-band height-finding radarhas a range of 180 km covering targets at altitudes of up to 32000 meters.

FLAT FACE P-15

Function: Target acquisitionRange 200-250 kmFrequency C band (UHF)Associated weapon system SA_3 GOA possibly SA-8 GECKO SAM,

LOW BLOW missile control radarComments Can guide three missiles simultaneosly

Power 380kw,BW AZ 4.3deg-ELEV 4.3 degPW 2us,PRF 200-700pps,70km range at 300m alt,accuracy 650m range, 1.8 deg AZ

Recognition: Van mountedTwo eliptical parabolic reflectors

measuring 11x5.5 mReflectors arranged one above the other onvan roof

Target data generated by these tracking radars is passed to the battalion's LOW BLOWtrailer-mounted fire control radar. With a maximum acquisition range of 110 km, thetracking range of this I-band system is between 40-85 km, depending on target size andaltitude. The system can simultaneously track six target aircraft and guide one or twomissiles. Improved LOW BLOW radars include TV cameras with a range of 25 km toprovide the fire control team with the data needed to perform a command guidanceintercept in a heavy ECM environment. If the missile fails to intercept it would becommanded to either change trajectory or self-destruct.

LOW BLOWFunction: Fire Control Trk/FC GuidanceFrequency I band I band D bandRange 40 km 40-85 km 29 kmComments Power 250kw

PRF 1750-3500ppsPW .25-5ms(us)BW 12x1.5Scan (trough)16HZ

PRF 3560-3585HZScan (Para)25HZ

Associated weaponsystem

SA-3 GOA SAM, FLAT FACE, SQUAT EYEacquisition radar

Recognition: Four-wheeled trailer-mountedTwo scanning parabolic dishesone above the other

The S-125 is fired from trainable launchers which are normally fixed, but can berelocated. The crew loads the missiles with the aid of a conveyor onto the ground-mounted, trainable launcher for firing, with both twin and quadruple launchers in use. Apair of missiles are carried in tandem on a modified truck or tracked vehicle. The S-125 isnormally transported from battalion storage areas on modified ZIL-131 (6 x 6) or ZIL-157 (6 x 6) trucks and loaded onto the launchers. Approximately one minute is requiredto load the missiles onto the launch rails, but nearly an hour is required between missilelaunches due to missile preparation, truck transit and other reloading procedures.

SQUAT EYE P-15M(2)FunctionRange 128 kmFrequency C-bandAssociated weapon system SA-3/5Recognition Power 380kw

SIDE NET PRV-11Function HeightRange 28 km

32km Max altitudeFrequency E-bandAssociated weapon system SA-2/3/5Recognition

Specifications

Missile Characteristics:

DOI 1961

Status Standard

Length (m) 6.70

Diameter (m) .60

Weight at launch (kg) 400

Propulsion system

Booster Solid

Sustainer Solid

Launch rails/tubes 2 or 4 rails, ground mounted (notmobile)

Guidance Command, (poss. IR terminal homing)

Warhead (type) HE

Kill Radius 12.5 m

Performance:

Max. velocity (Mach) 3+

Max. altitude (m) 25,000

Min altitude (m) 100

Operational range (km) 25

Minimum range (km) 6

Reload time (min) 50

Associated radars FLAT FACE, LOW BLOW, SQUAT

EYE

SA-4 GANEF

SA-4 GANEF is a medium to high altitude surface-to-air missile system. Over the yearsat least four variants of the missile have been produced, designated 9M8, 9M8M, 9M8M1and 9M8M2, though external differences are minimal. The 9M8M1 and 9M8M2 variantsare the primary types in service. The 9M8M1, introduced in 1967, is a 8.8 meter long-nosed version (the SA-4a) with effective range limits of 8 to 55 km and effective altitudelimits of 100 to 27000 m. The 9M8M2, introduced in 1973, is the short-nosed 8.3 mversion (SA-4b or GANEF Mod 1). It has improved close-range performance to reducethe dead zone above the TEL at the expense of losing some 3000 m in altitude and 5-10km in maximum range capabilities. Both versions have a fuselage diameter of 0.86 m, awing span of 2.3 m and a tail span of 2.73 m. The HE warhead weighs 135 kg and isdetonated by a proximity fuse.

The missile is launched by four solid booster rockets mounted externally on the body.The missile is armed 300 meters from the launcher. After launch the boosters burn forabout 15 seconds and then fall away when the fueled ramjet kerosene sustainer motorignition speed of over Mach 1 is attained at about 9 km from the TEL. The four fins arefixed and the four wings, in two pairs, are hydraulically operated.

A battery typically has one TEL fitted with the 9M8M2 and two TELs with the 9M8M1missile, although some TELs may carry one missile of each type. An electro-optical firecontrol system is fitted for use in a heavy ECM environment. Targets are initiallydetected by the long range LONG TRACK early warning E-band radar, which has a 150km range and 30 km maximum altitude coverage. LONG TRACK is mounted on alengthened version of the AT-T heavy artillery tractor with a large van body added, and isalso used for the SA-6 SAM.

This system passes data to the SA-4 GANEF battery where the H-band PAT HANDcontinuous wave fire control and command guidance radar takes over. The PAT HANDradar is mounted on the same chassis as the GANEF launcher, with the whole assemblycollapsed flat and a grill raised in front of the radar for road transit. This radar acquiresthe target at about 120-130 km and when it is within the 80-90 km tracking range a singlemissile is launched and guided to the target by the guidance beam with a semi-activeterminal homing phase for the final stage. The missile is tracked in flight by a continuouswave radar transponder beacon attached to one of the tail fins. If required the PATHAND can handle two missiles per target in order to increase the kill probability.

Target altitude information is also provided by the 240 km range THIN SKIN truck- ortrailer-mounted height-finder H-band radar.

The SA-4 TEL (Industrial Index designation 2P24) consists of a tracked armored chassison top of which is mounted a hydraulically operated turntable carrying two missiles. Thelauncher can be traversed by 360º with the missiles being elevated up to an angle of 45ºon their launcher arms for launching. The vehicle's engine is to the right of the driverwith the remainder of the space in the vehicle taken up by the crew and electronics.

Hatches for the other crew members are on either side of the missile turntable. Thetorsion bar suspension consists of seven dual rubber-tired road wheels with the drivesprocket at the front and the idler at the rear, and four track return rollers. The vehicle hasan air filtration and overpressure NBC system and an IR night vision system for thecommander and driver but no amphibious capability.

Reserve missiles are carried on Ural-375 (6 x 6) trucks, and reloading the TEL takesbetween 10 and 15 minutes.

SpecificationsDeployment Russia, 9 other countries

Deployment Year 1967

Length 8.8m (SA-4A), 8.4m (SA-4B)

Body Diameter 86 cm

Launch Weight 2,500 kg

Warhead 135kg HE fragmentation effect

Guidance Radio command, semiactive radar

Propulsion Ramjet sustainer,4 solid rocket boosters

Range 55km (SA-4A), 50km (SA-4B)

Design Lyulev Design Bureau

S-200 SA-5 GAMMONThe S-200 SA-5 GAMMON is a medium tohigh -altitude surface-to-air missile system.The single-stage missile has fourjettisonable, wraparound solid propellantboosters, each of which is is 4.9 m long and0.48 m in diameter with a single fin spanning0.35 m from the booster body. The missile is10.72 m long overall with a wing span of2.85 m. The main body is 0.85 m in diameterand has a solid fuel dual thrust sustainerrocket motor.

Each missile battalion has one 320 km rangeP-35M BARLOCK-B E/F-band target searchand acquisition radar with an integral D-bandIFF system, one 270 km range SQUAREPAIR H-band missile guidance radar, and sixtrainable semi-fixed single rail launchers.

The missile's minimum range of 60 km isdue to the booster burn time and jettisonrequirements, limiting the system toengagements against relatively large

unmaneuverable targets at ranges up to 250 km. Guidance beyond the 60 km boosterjettison point is by course correction command signals from the SQUARE PAIR radarwith the S-200's own active radar terminal homing seeker head activated near theprojected intercept point for final guidance.

The large HE warhead is detonated either by a command signal or the onboard proximityfusing system. When fitted with a nuclear warhead only the command detonation optionis used.

SQUAT EYE P-15M(2)FunctionRange 128 kmFrequency C-bandAssociated weapon system SA-3/5Recognition Power 380kw

TALL KING P-14Function EWRange 605 kmFrequency A BandAssociated weapon system SA-5Recognition Scan 2-6rpm

SIDE NET PRV-11Function HeightRange 28 km

32km Max altitudeFrequency E-bandAssociated weapon system SA-2/3/5Recognition

BACK NETFunction EW/GCI

Range 300 kmFrequency E-bandAssociated weapon system SA-5Recognition 3-6 rpm Scan

BAR LOCK P-35/37Function EWRange 200 kmFrequency E/F-bandsAssociated weapon system SA-5Comments 1 mw/b power

PRF 375pps7 rpm ScanBW .7degPW 1.5, 4.5 usAccuracy range 350m AZ .14 deg

Recognition

SpecificationsMaximum Speed 4 Mach

Effective Altitude 30.5 km

Effective Range 300 km

Warhead HE 215kg

Fuze Proximity and command

Kill Radius Unknown

ZRK-SD Kub 3M9SA-6 GainfulThe SA-6 GAINFUL is a two stage, solid-fuel, low-altitude SAM. It has radio commandguidance with semi-active radar terminal homing. Development of the 3M9 antiaircraftmissile for the Kub [Cube] system ended the career of Ivan Ivanovich Toporov, founderof the OKB-134 Special Engineering Office. The missile designed had not beenexperimentally verified, and it became necessary not only to build the missile but also tosimultaneouly conduct basic research. During the initial test launch in 1961, the 3M9missiles disintegrated in the air. The associated aerodynamic, engine, and guidanceproblems compelled Toporov to ask the Ministry of Armaments to extend the deadlinefor submitting the 3M9 to governmental tests. Toporov was removed from his post ofchief engineer at the end of August 1961, becoming department chairman at the MoscowInstitute of Aviation, and replaced by Andrey Lyapinov as director of the team. This didnot accelerate the work on the 3M9.Finally in 1966 the missile together with all the Kub equipment was certified as anoperational weapon, and it turned out to be one of the most successful Russianantiaircraft missiles. Although it is frequently reported that a naval version of the missileis the SA-N-3 GOBLET, this is evdiently not the case.The SA-6a missile has a length of 5.7 meters, body diameter of 0.335 meters, a wing spanof 1.245 meters, a tail span of 1.524 meters and has a launch weight of 599 kilogramswith a 56 kilogram HE-fragmentation warhead. The proximity and contact fuses arearmed after some 50 meters of flight. The basic SA-6a has a maximum effective range of24,000m and has a minimum effective range of 3,000m, the minimum engagement heightis 100m when using the fire control (STRAIGHT FLUSH) radar and 80m when in theoptical tracking mode, the maximum effective altitude is about 11,000m.A battery is able to relocate to an alternate firing position in approximately 15 minutesfrom systems being shutdown. In 1977, a new version - the SA-6b Gainful, was mountedon an SPU medium-tracked transporter. The SPU carried three SA-6b missiles and alsoan associated FIRE DOME H/I-band missile guidance illuminator radar is fitted on thefront end of the launcher assembly. Reload missiles are carried on modified 6x6 trucksand are loaded manually onto the launcher by a crane carried on the rear of the loadervehicle. Reloading an TEL takes approximately 10 minutes.The STRAIGHT FLUSH fire control radar has a maximum range of 55 - 75km and a10,000m altitude capability depending upon the conditions and target size, and performslimited search, low altitude detection and/or acquisition, pulse Doppler IFF interrogation,target tracking & illumination, missile radar command guidance and secondary radarmissile tracking functions. Some modified fire control (STRAIGHT FLUSH) radars use aTV camera with a 30km range to enable the battery to remain in action even if thevehicle's radar is jammed or forced to shut down due to threats from anti-radiationmissiles. This radar can also be linked to the launch vehicles by either a radio data link ora 10m long cable for direct data input to the launcher's systems. The data link antenna iscarried on the right forward hull corner of the TEL. It also carries the fire controlcomputers for the SA-6 Gainful missile battery.

The foldable 28km range dish antenna is of the conical scanning type and is used for lowaltitude H-band sector search scans, target tracking and target illumination. The lowerparabolic antenna is the G-band medium altitude target acquisition and early warningradar with a 55-75km range, with the lower feed for medium to high altitude coverageand the upper feed for low altitude coverage.The STRAIGHT FLUSH fire control radar can begin target acquisition at its maximumrange of 75km, and begin tracking & illumination at 28km. The STRAIGHT FLUSHradar can only illuminate a single target and control three missiles at any one time sonormal practice when a target track has been initiated is to normally order the launch oftwo and sometimes three weapons from one or more TELs.STRAIGHT FLUSHFunction: Fire control/short range target acquisition

Can guide three missiles simultaneoslyRange 60-90km, 10,000m altFrequency G/H band (acquisition, I band (tracking)Associated weapon system SA-6 GAINFUL and possibly SA-11

GADFLY SAM, LONG TRACK, THINSKIN target acquisition radars

Recognition: Essentially same chassis as SA-612ft long search reflector with 7 ftdiameter fire control parabolic dish on topRadars mounted on heavy turntableReflector backs have hvy pressed metalappearanceRadars can rotate independently of oneanotherAssembly folds flat in transit

With radar up, reaction time from a dormant condition through the target acquisition, IFFinterrogation and lock-on phases to missile launch is about three minutes. If the radarvehicle is already active then the time taken for the sequence is reduced to between 15 to30 seconds. A battery is able to become mobile and relocate to an alternate firing positionin 15 minutes from systems being shutdown.

The LONG TRACK target acquisition radar is also associated with the SA-6 system.After target data has been acquired by the SA-^ regiment's LONG TRACK surveillanceradar, target acquistion and fire control are taken over by the STRAIGHT FLUSH missilesite radars.

LONG TRACK

Function: Target acquisition

Range 150 km+, 30,000+ alt.

Frequency E band (UHF)

Associated weapon system SA-4 GANEF, SA-6 GAINFUL, SA-8GECKO, PAT HAND fire control radar

Recognition: Highly modified AT-T chassisLarge eliptical parabolic antennaOperators' cab at front

The TELAR vehicle is of all-welded construction with the crew compartment at the front,missiles on the turntable immediately behind the crew compartment and the engine at therear. The transmission is at the rear of the hull. The torsion bar suspension systemconsists of six rubber tired road wheels with the drive sprocket at the rear and the idler atthe front. There are no track return rollers. The vehicle has an air filtration and overpressure NBC system and infra-red night vision equipment fitted as standard but thevehicle has no amphibious capability. Three SA-6 Gainful missiles are carried on aturntable which can be traversed through a full 360º with the missiles elevated on theirlaunchers to a maximum of 85º. When traveling the turntable is normally traversed to therear and the missiles are horizontal to reduce the overall height of the vehicle.

Besides being vulnerable to suppresive fires and ECM, the system is slaved to the long-range LONG TRACK radar. Without it the SA-6 is "blind" at high altitudes.

SpecificationsSystem designation Kub (domestic version) or Kvadrat (export version)

Type Mobile tactical air defense complex

Mission

Protection of troops and objects of thereof from low-flying airplanes and helicopters of adversary underconditions of jamming and fire counteraction(The system was reportedly designed to defendadvancing Soviet tank divisions in case of the war)

System DeveloperV.V.Tikhomirov Science and Research Institute ofInstrument-Engineering (NIIP)Chief Designer of the System: Yevgeniy Pigin

Missile Developer State Machine-building Design Bureau «Vympel»(Moscow)

Serial ProductionFacility

Ul'yanovsk Mechanical Plant (for launchers andreconnaissance facility)

CHRONOLOGY

Development started late 1950s

Testing started 1965 (Army)

Serial Productionstarted 1968 [1] or 1967 [3]

Production ceased 1983 [3] or 1985 [1]

PERFORMANCES:

System Composition

One Self-Propelled Reconnaissance and TargetingFacility and 4 Self-propelled SAM Launchers, eachcarrying three missiles (all on tracked chassis). Initialversion of the system carried 3M9 missiles, Kub-M3features 3M9M3 missiles

Probability of kill byone missile (withinthe lethalityenvelope)

To increase Pk target can be engaged by severalmissiles, fired from either single or several Launchers

for «non manueveringaerodynamic target» 0.8-0.9 [1], 0.7-0.8 [2] 0.8-0.95 [3]

for manuevering high-speed target 0.5-0.7 [2]

for cruise missile 0.3-0.4 [1] 0.1-0.3 [2]

Missile Guidance

semi-active radar homing(on recently upgraded complexes TV/optical seekerintroduced)For protection aganst anti-radar missiles seeker of SAMcan lock on target mid-air, after launch

Length: 5.8 m

Diameter: 0.335 m

Wing span: 1.245 m

Max speed: Mach 2.8

Launch weight: 599 kg

Max effective range: 24,000 m24-28 kilometers [1-3] (for M3 and M4 modifications)

Min effective range: 3,700 m3-3.5 kilometers (for M3 and M4 modifications)

Max effectivealtitude:

12,000 m 14 kilometers (for M3 and M4 modifications)

Min effectivealtitude:

(radar mode) 100 m(optical mode) 50 m25 meters (for M3 and M4 modifications)

Propulsion: integral rocket motor/ramjet booster and sustainer motorassembly

Warhead: 59 kg HE fragmentation with contact and proximityfuzes

Reload time (SPU): 10 min

Time of Deploymentfor Combat 5 minutes

Reaction Time 20 [1] or 22 [3] seconds between target detection andmissile firing

OperationalTemperatures

-50 C .. + 50 C

PerformanceUpgrade Activity

«In the interests of foreign customers» NIIP currentlyupgrades the system to increase efficiency of trackingtargets at low altitudes and improve jam-resistance ofillumination channel. Work is also underway to increasecombat performance can be enhanced by inclusion of anewer 9A310M1 Self-propelling Launcher from Buk-M1 (SA-17) system

Exports Was delivered to 22 [1] or 25 [3] countries, including

Syria and Yugoslavia. Extensively used in the 1973Israeli-Arab war (64 airplanes were shot down by 95fired missiles)

SA-N-3

SA-7 GRAIL9K32M Strela-2HN-5 (Hongying 5) ChinaAnza MKI - PakistanAyn as Saqr - EgyptThe SA-7 GRAIL (Strela-2) man-portable, shoulder-fired, low-altitude SAM system issimilar to the US Army REDEYE, with a high explsive warhead and passive infraredhoming guidance. The HN-5 ( Hong Nu = Red Cherry ) is an improved Chinese versionwith upgraded capabilities. The SA-7 was the first generation of Soviet man portablesurface-to-air missiles. Although classed as "fire and forget" types, the missiles wereeasily overcome by solar heat and, when used in hilly terrain, by heat from the ground.

The SA-7 seeker is fitted with a filter to reduce the effectiveness of decoying flares and toblock IR emissions. The system consists of the missile (9K32 & 9K32M), a reloadablegripstock (9P54 & 9P54M), and a thermal battery (9B17). An identification friend or foe(IFF) system can be fitted to the operators helmet. Further, a supplementary earlywarning system consisting of a passive RF antenna and headphones can be used toprovide early cue about the approach and rough direction of an enemy aircraft. Althoughthe SA-7 is limited in range, speed, and altitude, it forces enemy pilots to fly aboveminimum radar limitations which results in detection and vulnerability to regimental anddivisional air defense systems.

The SA-7a (9K32 Strela-2) was introduced for service in 1968, but was soon replaced bythe SA-7b (9K32M Strela-2M) which became the most common production model. TheSA-7b, differs from the SA-7a primarily by using a boosted propellant charge to increaserange and speed. The SA-7a had a slant range of 3.6 km and a kill zone between 15 and1500 meters in altitude, with a speed of about 430 meters per second (Mach 1.4). TheSA-7b has a slant range of about 4.2 km, a ceiling of about 2300 meters, and a speed ofabout 500 meters per second (Mach 1.75). Both the SA-7a and SA-7b are tail-chasemissile systems, and its effectiveness depends on its ability to lock onto the heat source oflow-flying fixed- and rotary-wing aircraft targets.

The Anza anti-aircraft missiles give Pakistan a response to India's superiority in modernaircraft -- India has a numerical superiority in modern fighter aircraft of more than 3 to 1over Pakistan. The Anza MK-1, Anza MK-2, and Anza MK-3 surface to air anti-aircraftmissiles have ranges of 4, 6 and 15 km, respectively. The missiles are manufactured bythe laboratory named after Dr. Abdul Qadeer Khan, the father of Pakistan's nuclearprogram.

The Anza MKI missiles, which have a range of 4.2 km, were manufactured and handedover to the military forces in 1990. It has been reported that the missile was used duringthe Kargil incidents between Pakistan and India. Pakistan downed two of India's militaryplanes, a MIG-21 and a MIG-27, with the Anza MKI missiles for violating its airspace on26 May 1999.

Egyptian technicians have reverse engineered and modified two Soviet SAMs -- the Aynas Saqr (a version of the SA-7) and the Tayir as Sabah (a version of the SA-2). The Aynas Saqr [Falcon Eye] anti-Aircraft missile system is designed to counter air-ground attackby all types of aircraft flying at low and very low altitudes due to its simplicity ofoperation, accuracy, light weight, mobility & versatility (either by one man or to beintegrated into other overall A/D systems). Also it can be mounted on any combatvehicle, light or armored. Moreover the basic equipment can be fitted with IFF & nightvision units.

SpecificationsDate of Introduction 1972

Proliferation Worldwide

Crew 1

Launcher Name 9P54M

Length (m) 1.47

Diameter (mm) 70

Weight (kg) 4.71

Reaction Time 5-10 seconds (acquisition to fire)

Time BetweenLaunches (sec) INA

Reload Time (sec) 6-10

Missile Name 9M32M

Max. Range 5,500 meters

Min. Range 500 meters

Max. Altitude 4,500 meters

Min. Altitude 18 meters

Length (m) 1.40

Diameter (mm) 70

Weight (kg) 9.97

Missile Speed (m/s) 580

Propulsion Solid fuel booster and solid fuel sustainer rocket motor.

Guidance Passive IR homing device (operating in the medium IRrange)

Seeker Field of View 1.9°

Tracking Rate 6°/sec

Warhead Type HE

Warhead Weight (kg) 1.15

Fuze Type Contact (flush or grazing)

Self-Destruct (sec) 15

FIRE CONTROLLauncher has sighting device and a targetacquisitionindicator.The gunner visually identifies and acquires the target.

Gunner Field of View INA

Acquisition Range(m) INA

VARIANTS

SA-N-5 Naval versionHN-5A Chinese versionStrela 2M/A Yugoslavian upgradeSakr Eye Egyptian upgradeMounted in several types of vehicles in four, six, andeight-tube launcher varieties.Can be mounted on several helicopters (Mi-24, S-342Gazelle)

ANZA MK-1 Specifications

Type 2-stage, low altitude

Length (missile, with retracted tail fins) 1.44 m

Weight (total launch assembly in firing condition)15 Kg (Missile at launch) 9.8 Kg

Propulsion solid fuel booster and solid fuel sustainer rocketmotor

Guidance uncooled Pbs passive infrared homing seeker

WarheadHE fragmentation (containing 0.37 Kg HE) withcontactand graze fuzing

Average missilecruise speed 500 m/s

Max missilemanoeuvring 6 g

Self destruction time 14-17 s

Max target speed (receding target) 260 m/s

Max effective slantrange 4,200 m

Min effective slantrange

1,200 m

Max effective altitude 50 m

Weapon reactiontime

less than 5 s

Time from march toready

less than 10 sfor operation

Battery operationtime more than 40 s

HN-5 (Hongying 5)

Anza MK-1

Ayn as Saqr

SA-8 GECKO9K33M3 Osa-AKMThe SA-8 GECKO is a single-stage, solid-fuel, short-range, low-altitude, all-weatherSAM system. The first production version of this system was identified as SA-8a, whichonly had 4 launcher rails and exposed missiles. The SA-8b typically has two BAZ-5937resupply/transloader vehicles, carrying 18 missiles each (boxed in sets of three) thatsupports a battery of four TELARs. A target can be brought under fire both with onemissile as well as a volley of two missiles. This system is also air transportable.

The SA-8a (GECKO Mod 0) high acceleration missile (Factory Index number 9M33) hasa launch weight of about 130 kg. Maximum speed is Mach 2.4, minimum altitude is 25meters, maximum effective altitude 5000 meters. The minimum range is 1500 meters andthe maximum range 12000 meters. The SA-8b or GECKO Mod 1, introduced in 1980, ismounted in a rectangular launch box and incorporates improved guidance and higherspeed providing an increased maximum range of 15000 meters. The warhead of bothmissiles is fitted with proximity and contact fuses, and the 19 kilogram warhead's lethalradius at low altitude is about 5 meters. The system reload time is five minutes, andcombat deployment time is four minutes with system reaction 26 seconds. The LANDROLL conical-scan fire control radar operates in the H-band with a 360º travers, with amaximum range of 35 kilometers and an effective range of around 30 kilometers againsta typical target. LAND ROLL also has a short-range target acquisition capability. Theradar, at the rear of a one-man gunner-radar operator position, folds back 90º to reducethe overall height of the vehicle for air transport and high speed road travel. The pulsed-mode tracking radar operates in the J band with a range of 20 to 25 kilometers. The two I-band guidance radars make it possible to launch two missiles at the same target, each oneresponding to a different frequency to frustrate ECM.

Mounted on top of each missile guidance radar is an low light level TV optical assistsystem for target tracking in low visibility and heavy ECM.

The SA-8 transporter erector launcher and radar (TELAR) vehicle is a six-wheeleddesign designated BAZ-5937. Four command-guided missiles are carried ready to launch,two either side. The driver's compartment at the front of the vehicle has accommodationfor two, the driver and commander, with access via a hatch in the roof. The engine is atthe very rear, and the vehicle is fully amphibious, being propelled in the water by twowater jets at the rear of the hull. The vehicle is fitted with an air filtration andoverpressure NBC system together with IR systems for the commander and driver.

There are at least three major families of SA-8 launch vehicles. The first, a pre-seriesprototype, had a very blunt nose. The standard production model has a sharper nose, andvariants of this vehicle with feature minor changes in the detail of hull fittings. The SA-8b vehicle is basically similar to the SA-8a vehicle aside from the launcher whichaccommodates six missile canisters. Variants of the SA-8b launcher feature a

reconfigured rear end, while some SA-8b TELs include an additional small radar antennafitted above the surveillance radar associated with a newIFF system.

Each battery has two missile transloaders based on the same chassis with a long tarp-covered structure covering the cargo space and crane which slides to the rear whenoperating. A total of 18 reloads in boxed sets of three are transferred to the TELARs bythe centrally-mounted hydraulic crane.

Regimental maintenance batteries include a single radar collimation vehicle using thesame chassis. The collimation antenna lies on both sides of the vehicle and overhangs therear during transit. In operation it is raised and mounted on each side of the hull directlybehind the cab.

SpecificationsDate of Introduction 1980

Proliferation At least 25 countries

Crew 3

Combat Weight (mt) 9

TELAR BAZ-5937 6x6 amphibious cross-country capablevehicle

Length (m) 9.14

Height (m) 4.2 (with surveillance radar folded down)

Width (m) 2.75

Engine Type D20K300 diesel

Cruising Range (km) 500

Max. Road Speed 80 km/h

Max. Swim Speed 8 km/h

Radio R-123M

Protection NBC Protection System

Launcher Name 9P35M2

Length (m) 3.2

Diameter (mm) INA

Weight (kg) 35

Reaction Time (sec) INA

Time Between 4

Launches (sec)

Reload Time (min) 5

Fire on Move No

Emplacement Time(min) 4

Displacement Time(min) Less than 4 (est.)

Missile Name 9M33M3

Max. Range 15,000 meters

Min. Range 200 meters

Max. Altitude 12,000 meters

Min. Altitude 10 meters

Length 3158 mm

Diameter 209.6 mm

Weight 170 kg

Missile Speed 1020 m/s

Propulsion Solid propellant rocket motor

Guidance RF CLOS

Warhead Type Frag-HE

Fuze Type Contact and proximity

Warhead Weight 16 kg

Self-Destruct 25-28 seconds

FIRE CONTROLSights w/MagnificationLLLTV/optical assist (for target tracking in lowvisibility and heavy ECM)

IFF Yes

Radar Name LAND ROLL

Function Target Acquisition

Detection Range (km) 20-30

Tracking Range (km) 20-25

Frequency 6-8 GHz

Frequency Band H

Radar Name Monopulse Target Tracking Radar

Function Target Tracking

Detection Range (km) 20-25

Tracking Range (km) INA

Frequency 14.2-14.8 GHz

Frequency Band J

Missile trackingradars

2

Frequency 10-20 GHz

VARIANTSSA-8a Initial production model that carries fourmissiles on exposed rails.4K33 Osa-M (SA-N-4) Naval variant

SA-9 GASKIN9K31 Strela-1The SA-9 GASKIN is a short-range, low-altitude self-propelled SAM-carrying systembased on the BRDM-2 chassis. The vehicle carries quadruple SA-9 SAM launchers on arevolving mount in place of the KPV/PK machine gun turret. The missiles are usuallyfired in pairs against each target to increase the kill probability, with an interval betweenrounds of about five seconds. Reloading is performed manually and takes about fiveminutes.The 30 kilogram Mach 1.5 Strela-1 missile is 1.8 meters long and 0.12 meters in diameterwith a wing span of 0.375 meters. It carries an HE-fragmentation warhead and proximityfuse with a lethal radius of 5 meters and damage radius of 7.6 meters. The originalversion of the Strela-1 was known as the 9M31 (SA-9A GASKIN Mod 0) and used anuncooled first-generation lead sulfide (PbS) infra-red (IR) seeker operating. This wassupplemented by the 9M31M variant (SA-9B GASKIN Mod 1) which has an improvedseeker providing greater target sensitivity and lock on ability. The minimum range of the9M31 is 800 m and the maximum range 6500 m within altitude limits of 15 to 5200 m.The minimum range of the 9M31M is 560 meters and the maximum range 8000 meters(increasing to a possible 11000 meters when used in a tail-chase engagement) withinaltitude limits of 10 to 6100 meters. When engaging a head-on target the system has aconsiderably reduced range.

One SA-9 TEL (SA-9 Mod A, BRDM-2A1 or SA-9A TEL) in each battery is fitted withFLAT BOX A passive radar detection antenna, one either side of the hull above the frontwheel housings, one under the left launch canisters pointing forward and one mounted ona small frame above the rear engine deck plate pointing rearwards to give 360º coverage.The TEL without the FLAT BOX A system is known as the SA-9 Mod-B, BRDM-2A2or SA-9B.

The BRDM-2 transporter erector launcher (TEL) has the chain-driven belly wheelsremoved and the normal turret replaced by one with four ready to launch SA-9 container-launcher boxes. These are normally lowered to the horizontal when traveling to reducethe overall height of the vehicle. The vehicle crew of three consists of the commander,driver and gunner. An air-filtration and overpressure NBC system are standard.

Missile Specifications

9M31 9M31M

Length: 1.803 m 1.803 m

Diameter: 0.12 m 0.12 m

Wing span: 0.36 0.36

Max speed: Mach 1.8 Mach 1.8

Max target speed: 300 m/s 300 m/s

Launch weight: 32 kg 32 kg

Max effective range: 4,200 m 8,000 m

Min effective range: 800 m 560 m

Max effective altitude: 3,500 m 6,100 m

Min effective altitude: 30 m 10 m

Guidance: 1-3 waveband uncooledPbS passive IR homingseeker

1-5 wavebandcooled PbS passive IRhoming seeker

Propulsion: single-stage solid propellantrocket motor

single-stage solidpropellant rocketmotor

Warhead: 2.6 kg HE fragmentationwith contact and proximityfuzing

2.6 kg HEfragmentation withcontact and proximityfuzing

basic load on vehicle 4

reload time (min) 5

radar(s) Passive radar detection antenna giving 360ºcoverage

emplace/displace time(min)

25895

chassis Modified BRDM-2 chassis

4 wheels

speed, road 100

water 10

road range (kg) 750

crew 3

S-300PMUSA-10 GRUMBLESA-N-6 GRUMBLEHQ-10/15 (Chinese licensed copy)

The S-300PMU [SA-10 land-based, SA-N-6 naval version] surface-to-air missile system is able to engage a number of targets simultaneously,countering intensive aircraft raids at low-to-high altitude. The SA-10offers significant advantages over older strategic surface-to-air missilesystems, including multitarget handling and engagement characteristics,a capability against low altitude targets with small radar cross-sectionssuch as cruise missiles, a capability against tactical ballistic missiles,and possibly a potential to intercept some types of strategic ballisticmissiles.The first SA-10 site became operational in 1980. Over 80 sites wereoperational by 1987, when work was progressing on at least another 20sites. Nearly half of these sites were located near Moscow. Thisemphasis on Moscow as well as the deployment patterns noted for theother SA-10 sites suggested a first priority on terminal defense ofcommand-and-control, military, and key industrial complexes. Aprogram to replace all of the older strategic SAM systems with the SA-10, well under way by 1996, has been considered by experts to be oneof the most successful reequipment programs of the post-Soviet armed

forces.

This vertically launched missile uses a single-stage solid propellant rocket motor. It isnormally armed with a 100 kg HE-fragmentation warhead with a proximity fuse, thougha low yield tactical nuclear type is believed to be an alternative warhead option. Themissile's vertical launch trajectory provides fastest available reaction time capability tocounter targets approaching from any azimuth. Missile engagement altitude extend from25 m up to about 30000 m. The maximum engagement range is stated as at least 90000m, though in practice it is probably greater.

The SA-10A launch complex consists of a missile battery which includes a batterycommand post and engagement control center, the large CLAM SHELL 3D continuouswave pulse Doppler target acquisition radar, the FLAP LID A I-band multi-functionphased-array trailer-mounted engagement radar with digital beam steering in hardenedsites, and up to 12 semi-trailer erector-launchers which mount four tubular missilecontainer-launchers. The towing unit for the semi-trailer erector-launcher is the KrAZ-260V (6 x 6) tractor truck. The launchers are usually positioned on concrete pads with thetrailers being leveled by the use of four hydraulic jacks. An S-300PMU Regimentcomprises three such batteries and employs the BIG BIRD 4 meter tall F-band long-

range, 3D surveillance and tracking radar at the Regimental command post for initialtarget detection.

In the mid-1980s design work on the mobile S-300PMUSA-10B GRUMBLE Mod 1 was completed. This versionof the weapon is carried and vertically launched from adedicated four-round capacity transporter-erector launchervehicle based on the MAZ-7910 (8 x 8) truck chassis. Thecombined engagement radar and control station is mountedon the same chassis. The SA-10B mobile missile batterycomprises the combined FLAP LID B engagement radar

and engagement control/command post station mounted on a MAZ-7910 chassis, up to12 TELs (SPU: mobile launcher unit), a trailer-mounted 36D6; CLAM SHELL 3D 360ºscanning target designation radar, and a maintenance section. The SA-10B Regimentconsists of three such batteries with an additional radar section and a number of TZM(transport-loader vehicles) MAZ-7910 transloaders for resupply purposes. The TELcarries a total of four sealed container-launcher cylinders, each of which is used for thestorage, transport and launching of a missile. When traveling the launcher system iscarriedin the horizontal position but at the launch site is elevated to an angle of 90º.

The combined FLAP LID-B radar/engagement control vehicle has the 2.75 m2 planararray antenna on a box-like antenna mount and support systems container. Whentraveling the array is carried horizontally, and when deployed it is raised above thecontainer to an angle of approximately 60º.

The battery takes only five minutes to deploy once it comes to the halt. The vehicles haveelectronic inter-vehicle communications and data transmission links with elevatable pole-type antenna, and thus it does not require interconnecting vehicle cables. Each of theMAZ-7910 derivative vehicles has four hydraulic jacks positioned either side betweenthe first/second and third/fourth road wheels which are lowered to the ground to provide amore stable and level environment.

Missile guidance is of the Track-Via-Missile (TVM) type with the FLAP LID guidanceradar capable of engaging up to six targets simultaneously, with two missiles assigned pertarget to ensure a high kill probability. Maximum target velocity is stated as 4200 km/hwith the battery capable of firing three missiles per second.

If the battery is employed in rugged terrain or forest then the engagement radar systemcan be mounted on a special trailer-mounted extendible 24.4 m high tower to improveradar coverage. The use of this extended-range radar for low level engagements increasesthe system's range to 43,200 m from the original 32,000 m. In its sealed container-launcher cylinder the missile is considered to be a round of ammunition and is said not torequire any check-ups or adjustments for a period of 10 years.

The S-300PMU1 is an extended range version of S-300PMU with a limited anti-ballisticmissile capability, including capabilities against aerodynamic targets with speeds up to 3kilometers/second.

The S-300PMU2 Favorit variant is a new missile withlarger warhead and better guidance with a range of200 km, versus the 150 km of previous versions.Unveiled at the MAKS'97 exhibition in August 1997,it represents a thorough modification of the S-300PMU1. The first tests were performed on 10August 1995 at the Kapustin Yar firing range. Onenew element is the entirely new 96L6E autonomousmobile radar, which works in conjunction with the

83M6E2 control post and S-300MPU2 launchers. The new 48N6E2 missile, developedby MKB Fakel, weighs 1,800 kg, and is 7.5 m long and 0.5 m in diameter. After a coldstart in the upright position with help of a catapult, the 48N6E2 accelerates up to 1,900m/s in 12 sec time, and then approaches the target from above. The 48N6E2 differs fromthe older 48N6E in having a new warhead specially designed for destroying ballisticmissiles, with a warhead weight of 145 kg versus 70-100 kg.

The S-300PMU2 Favorit can engage targets flying from 10 m to 27 km above the surfaceat a speed of up to 10,000 km/h. It is claimed that it has a kill ratio ranging from 0.8 to0.93 against aircraft and from 0.8 to 0.98 against Tomahawk-class cruise missiles.

Export SalesChinaIn the early 1990s China imported 100-120 S-300 missile systems which aredeployed aroung Bejing, and it has been suggested that China intends to obtain alicense to produce them, with a designation variously reported as either HQ-10 orHQ-15. The first Chinese copy have been tested, but all the components of thefirst copy version were imported from Russia. The October 1999 paradecelebrating the 50th anniversary of the People's Republic of China in Beijingfeatured a large number of truck towed quad-cannister systems associated withthe SA-10.IndiaSince 1995 India has been negotiating with Russia regarding purchase of the S-300, in response to Pakistan's deployment of M-11 missiles from China. In 1995Russian Defense Deputy Minister Kokoshin offered to sell S-300 missiles duringhis trip to India. Following this offer Indian officials started negotiations with theRussian manufacturers, and in August 1995 the Indian Defense SecretaryNambiar went to Russia to observe tests of the missiles near Moscow. The $1billion purchase is said to include six S-300 systems, with each combat systemconsisting of 48 missiles. Reportedly in June 1996 27 S-300 missiles weredelivered to India.Cyprus signed an agreement with Rosvooruzhenie (Russian Armament) statearms-trade agency on 4 January 1996.

South Korea discussed possible purchase of the SA-10, prior to deciding in late1999 to purchase the American Patriot PAC-3.

SpecificationsBuilder Almaz Scientific-Production Association

Lemgth 7.0 m7.5 m - 48N6 S-300PMU1

Diameter 0.45 m0.50 m - 48N6 S-300PMU1

Weight 1,480 kg1,800 kg - 48N6 S-300PMU1

Propulsiom Single-stage, solid-fuel rocket

Range, (km)45 km - 5V55K90 km - 5V55R150-200 km - 48N6 S-300PMU1

Altitude, (m) 30,000 m

Basic load on vehicle

Detection range, km

Reaction time, sec

Speed 1.7 km./sec S-300P2.0 km./sec S-300PMU

Reload time

Warhead 70-100 kg high explosive - 5V55K145 kg high explosive - 48N6 S-300PMU1

Command guidance

Radar(s)Flap Lid or Tombstone engagement radarClam Shell acquisition radarBig Bird designation radar

Emplace/displace time (min)

Support vehicles

Chassis

SA-N-6

SA-11 GADFLY9K37M1 BUK-1MThe SA-11 GADFLY is a medium-range, semi-active, radar-guided missile using solid-rocket propulsion that provides defense against high-performance aircraft and cruisemissiles. The SA-11 represents a considerable improvement over the earlier SA-6GAINFUL system, and can engage six separate targets simultaneously, rather than thesingle target capability of the SA-6. Single-shot kill probability are claimed to be 60-90%against aircraft, 30-70% against helicopters, and 40% against cruise missiles, a significantimprovement over the SA-6. The system is more mobile, taking only about 5 minutes tomove from road march to engagement. The new system also offers significantly greaterresistance to ECM than previous systems. The SA-11 system is comprised of the TELAR(9A310M1), Loader/Launcher (9A39M1), SNOW DRIFT Surveillance Radar (9S18M1),and Command and Control vehicle (9S470M1).The Mach 3 semi-active homing 9M28M1 missile has a maximum slant range of 28 kmand a minimum range of 3 km. It is capable of engaging targets between altitudes of 30and 14000 m and can sustain 23 g maneuvers. The solid fuel missile is 5.6 meters longwith a diameter is 0.4 m and a wing span is 1.2 m. The launch weight is 650 kg, whichincludes a 70 kg HE warhead with a 17 meter lethal radius.The SNOW DRIFT warning and acquisition radar provides target height, bearing andrange data. The SNOW DRIFT has a detection range of 85 km against high-flyingtargets, 35 km against targets at an altitude of 100 meters, and 23 km against targetsflying nap-of-the-earth (NOE). The radar's tracking range extending from 70 km for high-flying targets to 20 km for NOE targets. Tracking of helicopters hovering at 30 m can bemade as far as 10 km. Once a target is identified it is turned over to an TELAR via a datalink for tracking and attack. The SNOW DRIFT receives early warning from brigade-level surveillance radars such as the SPOON REST.

The H/I-band FIRE DOME monopulse guidance and tracking engagement radar has aneffective guidance range of 3-32 km and an altitude envelope 15 meters to 22 km, andcan engage approaching targets moving at a maximum of 3000 km/h (1860 mph). Theradar guides as many as three missiles against a single target.

The SA-11 GADFLY system also can be fitted with a supplementary electro-opticalsighting system for use in a severe jamming environment, which would overwhelm thenormal semi-active radar homing system -- in which case the missile uses radio-command guidance.

The TELAR, based on the GM-569 tracked chassis, carries four ready to fire missiles ona turntable that can traverse a full 360º and FIRE DOME radar. The tracked SurveillanceRadar vehicle uses the same chassis and carries the SNOW DRIFT radar. The Commandand Control vehicle works in conjunction with the SNOW DRIFT radar. TheLoader/Launcher vehicle (LLV) resembles the normal TELAR, but replaces the FIREDOME fire control radar with a hydraulic crane for reloading 9M38 missiles. The LLV

can load itself in rear areas from the 9T229 transporter in 15 minutes, and take thosemissiles to reload the TELAR in about 13 minutes. The LLV can also launch missiles,though it requires radar guidance from a nearby TELAR.

Specifications

SA-11 GADFLY

Missile Characteristics:

DOI 1979

Status Standard

Length (m) 5.7

Diameter (m) 0.13

Weight at launch (kg) 55

Propulsion system

Booster Solid

Sustainer Solid

Launch rails/tubes 2 or 4 canister tubes

Guidance Semiactive radar homing

Warhead (type) HE

Performance:

Max. velocity (Mach) 3 (est.)

Max. altitude (m) 15,000 (est.)

Min altitude (m) 25-30 (est.)

Operational range (km) 30 (est.)

3 (est.)

Reload time (min) INA

Associated radars U/I acquistion radar; U/I trackingradar; possible STRAIGHT FLUSH

Recognition:

Variant ZSU-23-4 chassis

4 missiles mounted side-by-side onlaunch rails

Entire missile system mounted onturntable

Vehicle: Tracked, transporter, erector, andlauncher (TTEL)

S-300VSA-12A GLADIATOR and SA-12BGIANTHQ-18

The S-300V (SA-12) low-to-high Altitude,tactical surface to air missile system also hasanti-ballistic missile capabilities. The HQ-18reportedly the designation of a Chinese copy ofthe Russian S300V, though the details of thisprogram remain rather conjectural. In early 1996Russia astounded the United States Army bymarketing the Russian SA-12 surface-to-airmissile system in the UAE in direct competition

with the United States Army's Patriot system. Rosvooruzheniyeoffered the UAE the highest-quality Russian strategic air defensesystem, the SA-12 Gladiator, as an alternative to the Patriot at halfthe cost. The offer also included forgiveness of some of Russia'sdebt to the UAE.

The S-300V consists of:

9M82 SA-12b GIANT missile 9M83 SA-12a GLADIATOR missile 9A82 SA-12b GIANT TELAR 9A93 SA-12a GLADIATOR TELAR 9A84 GIANT Launcher/Loader Vehicle (LLV) 9A85 GLADIATOR Launcher/Loader Vehicle (LLV) 9S15 BILL BOARD Surveillance Radar system 9S19 HIGH SCREEN Sector Radar system 9S32 GRILL PAN Guidance Radar system 9S457 Command Station

The 9M83 SA-12a GLADIATOR is a dual-role anti-missile and anti-aircraft missile witha maximum range between 75 and 90 km.The 9M82 SA-12b GIANT missile, configured primarily for the ATBM role, is a longerrange system [maximum range between 100 and 200 km] with a longer fuselage withlarger solid-fuel motor.

The 9A82 SA-12b GIANT and 9A93 SA-12a GLADIATOR TELAR vehicles aresimilar, though the 9A83-1 carries four 9M83 SA-12a GLADIATOR missiles, whereasthe 9A82 carries only two 9M82 SA-12b GIANT missiles. The configuration of the

vehicles command radar is also different. On the 9A83-1 the radar is mounted on afolding mast providing 360º coverage in azimuth and full hemispheric coverage inelevation. The radar on the 9M82 TELAR is mounted in a semi-fixed position over thecab, providing 90º coverage on either side in azimuth and 110º in elevation. The TELARsare not capable of autonomous engagements, requiring the support of the GRILL PANradar.

The 9S457-1 Command Post Vehicle is the command and control vehicle for the SA-12system, which is supported by the BILL BOARD A surveillance radar and the HIGHSCREEN sector radar. The CPV and its associated radars can detect up to 200 targets,track as many as 70 targets and designate 24 of the targets to the brigade's four GRILLPAN radar systems for engagement by the SA-12a and SA-12b TELARs.

The BILL BOARD A radar provides general surveillance, with the antenna rotating every6-12 seconds. The radar, which can detect up to 200 targets, provides target coverage of0-55º in elevation and 10-250 km in range with an accuracy is 30-35 min of arc inazimuth and 250 m in range. and.

The HIGH SCREEN sector radar supporst the ATBM role, providing surveillance ofanticipated azimuths of threat missiles. The radar is switches to a tracking mode whenhigh speed targets are detected, automatically transmiting the trajectory parameters to theCommand Post Vehicle. The CPV prioritizes the threat and instructs the HIGH SCREENradar to track specific missiles, with the maximum being 16 simultaneous targets.

The GRILL PAN radar system controls the battery's launcher vehicles (TELARs andLLVs). It can simultaneously track up to 12 targets and control up to six missiles againstthese targets The radar can acquire targets with a radar cross-section of 2m2 at a range of150 km in manual mode and 140 km in automatic mode. The GRILL PAN tracks targetsassigned to it by the CP while simultaneously maintaining a horizon search for newtargets.

The LLVs (9A85 GLADIATOR and 9A83 GLADIATOR) resemble normal TELARs,but with a loading crane rather than command radars. While the primary role of the LLVis to replenish the TELARs, they can also erecting and launch missiles if needed, thoughthey are dependent on the use of command radars from neighboring TELARs.

Specifications

SA-12aRange, (km) 6-75 kmAltitude, (m) 25 kmBasic load onvehicle 4 missiles on launcher

Detection range, kmReaction time, secSpeed 1.7 km./secReload timeWarhead 150 kg, HECommand guidance Combined, inertial with semi-active self-guidance

Radar(s) GRILL PAN missile guidance radar, BILL BOARDsurveillance radar, HIGH SCREEN sector scan radar

Emplace/displacetime (min) 5

Support vehicles TELAR, Transloader, command post

ChassisVariations of the MT-T chassis are used for the launchvehicle, loader-launcher vehicle, missile guidancestation, command post vehicle, and the radars.

Specifications

SA-12bRange, (km) 13-100 kmAltitude, (m) 1-30 kmBasic load onvehicle 2 missiles on launcher

Detection range, kmReaction time, secSpeed 2.4 km./sec.Reload timeWarhead 150 kg, HECommand guidance Combined, inertial with semi-active self-guidance

Radar(s) GRILL PAN missile guidance radar, BILL BOARDsurveillance radar, HIGH SCREEN sector scan radar

Emplace/displacetime (min) 5

Support vehicles TELAR, Transloader, command post

ChassisVariations of the MT-T chassis are used for the launchvehicle, loader-launcher vehicle, missile guidancestation, command post vehicle, and the radars.

SA-13 GOPHERZRK-BD Strela-10The SA-13 GOPHER [ZRK-BD Strela-10] is a short-range, low altitude SAM system.The SA-13 missile (9M37) is 2.2 m long, 0.12 m in diameter with a 0.4 m wingspan andhas a maximum speed of Mach 2. It carries a 5 kg HE warhead and is fitted with either animproved passive lead sulfide all-aspect infra-red seeker unit, or a cryogenically cooledpassive all-aspect infra-red seeker unit. The estimated minimum range of the SA-13 is500 meters and the maximum effective range of 5000 meters with altitude engagementlimits of 10 to 3500 meters.The SA-13 Strela-10M3 variant is designed to defend troops on the march from low levelaircraft and helicopters, precision-guided munitions and reconnaissance RPVs. The majorchange is the adoption of a dual mode guidance system for the missile seeker - optical'photo-contrast' and dual band passive IR. The 9M333 missile weighs 42 kg at launch andwhen in its container-launcher the box-like canister has a total mass of 74 kg. Targetacquisition range using the optical 'photo-contrast' channel is between 2000-8000 meterswhile for the IR channel it is between 2300-5300 meters. Altitude engagement limits arefrom 10 meter up to 3500 meters at a maximum range of 5000 meters. Average missilespeed is 550 m/s. The HE-fragmentation rod warhead weighs 5 kg in total (including 2.6kg of HE) and uses both contact and active laser proximity fusing systems. The actuationradius of the proximity fuse is up to 4 meters. The dual mode passive optical 'photo-contrast/IR seeker ensures good IR decoy counter-countermeasures discriminationcapability and optimum use of the system against extremely low altitude targets and inadverse weather conditions.The SA-13 incorporates the range-only HAT BOX radar which provides the operator thetargets range to the system to prevent wastage of missiles outside the effective range ofthe system. The HAT BOX circular parabolic radar antenna is located between the twopairs of missile canisters.There are two versions of the SA-13 transporter erector launcher and radar (TELAR).The TELAR-1 carries four FLAT BOX B passive radar detection antenna units, one oneither corner of the vehicle's rear deck, one facing aft and one between the driver's visionports at the front, whereas the TELAR-2, which is used by the SA-13 battery commander,has none. The SA-13 TELAR is a modified MT-LB amphibious armored tracked vehiclewith the machine-gun turret removed. The launcher pedestal mounted to the rear of centerof the vehicle is 360º traversable. It incorporates the operators position behind a large,rectangular window at its base.Normally the TELAR carries four ready to fire SA-13 missile container-launchers andeight reloads in the cargo compartment but it can also carry either SA-9 GASKINcontainer-launcher boxes in their place or a mixture of the two. This enables the thecheaper SA-9 (Strela-1) to be used against the easier targets and the more expensive andsophisticated SA-13 (Strela-10) against the difficult targets. The missile mix also allows achoice of infra-red (IR) seeker types on the missiles for use against extremely lowaltitude targets and in adverse weather.

SpecificationsContractor

Entered Service

Total length

Diameter

Wingspan

Weight

Warhead Weight

Propulsion

Maximum Speed

Effective range 600-5000 meters

Altitude 10-3500 meters

Guidance mode IR homing, cooled seeker, dual frequency

Single-shot hitprobability

basic load on vehicle 8

reload time (min) 3

fire control IR homing, cooled seeker, dual frequency

radar(s) SNAP SHOT (range only)

PIE RACK (IFF)

emplace/displace time(min)

40 sec

support vehicles 14631

chassis MT-LB

speed, road 60

water 6

road range (kg) 500

crew 3

SA-14 GREMLIN9K34 Strela-3SA-14 GREMLIN (Strela-3 9K34) man-portable SAM is the successor to the SA-7/SA-7b (Strela-2 9K32 and Strela-2M 9K32M). The system consists of the 9P59 gripstock,9P51 thermal battery/gas reservoir, and 9M36-1 missile. The external appearance of theSA-14 is very similar to the SA-7, and the gripstock, launch canister and aft missile bodyare almost identical. The most significant differences are the new seeker system and thesubstitution of a ball-shaped 9P51 thermal battery and gas reservoir for the SA-7'scanister shaped battery. The SA-14's new nitrogen-cooled lead sulfide seeker allows it tohome in on the exhaust plume of jet engines, turboprop and helicopter gas turbineengines. The enhanced seeker allowed the SA-14 to be fired against targets from muchbroader angles, as well as defeating countermeasures such as exhaust shrouds. Opticalfiltration was added to the seeker to reduce vulnerability to typical IRCM flares. Thewarhead of the SA-14 was nearly doubled in weight over the small warhead of the SA-7.The guidance electronics were reduced in weight and a new solid-propellant motor wasintroduced, compensating for the heavier warhead and improving aerodynamicperformance. The SA-14 has a maximum range of 4500 meters, and a maximum altitudeof 3000 meters.

SpecificationsDesignation 9K34 Strela-3

Date of Introduction 1978

Proliferation Worldwide

Crew 1

Launcher Name 9P59

Dimensions

Length (m) 1.40

Diameter (mm) 75

Weight (kg) 2.95

Reaction Time (sec) 14

Time BetweenLaunches (sec) 35-40

Reload Time (sec) 25

Missile Name 9M36 or 9M36-1

Max. Range (m) 6,000

Min. Range (m) 600

Max. Altitude (m) 6,000

Min. Altitude (m) 50

Length (m) 1.4 m

Diameter (mm) 75 mm

Fin Span (mm) INA

Weight (kg) 10.3

Missile Speed (m/s) 600

Propulsion 2-stage solid-propellant rocket

Guidance passive IR homing

Seeker Field of View INA

Tracking Rate INA

Warhead Type Frag-HE

Warhead Weight (kg) 1.0

Fuze Type Contact/grazing

Self-Destruct (sec) 14-17

FIRE CONTROL Sights w/MagnificationLaunch tube has simple sights

Gunner Field of View( o ) INA

Acquisition Range(m) INA

IFF Yes

VARIANTS Igla 9M39 (SA-N-8) Naval version

9K331 TorSA-15 GAUNTLETSA-N-9HQ-17The 9K331 Tor [SA-15 GAUNTLET land-based, SA-N-9 naval version] low-to-mediumaltitude SAM system is capable of engaging not only aircraft and helicopters but alsoRPVs, precision-guided weapons and various types of guided missiles. The HQ-17 is acopy of Tor-M1, that China will use it to replace the aging HQ-61 SAMs, will enterservice around the year 2005. Although it is an autonomous system it can be interfacedinto an integrated air defense network. SA-15b is designed to be a completelyautonomous air defense system (at division level), capable of surveillance, command andcontrol, missile launch and guidance functions from a single vehicle. The basic combatformation is the firing battery consisting of four TLARs and the Rangir battery commandpost. The TLAR carries eight ready missiles stored in two containers holding fourmissiles each. The SA-15b has the capability to automatically track and destroy 2 targetssimultaneously in any weather and at any time of the day.The single stage solid propellant missile has a maximum speed of 850 m/s and is fittedwith a 15 kg HE-fragmentation warhead detonated by a proximity fusing system. Themissile is approximately 3.5 meters long with a diameter of 0.735 meters and a launchweight 170 kilograms. The cold launch ejection system propels the missile upwards to aheight of 18-20 meters, whereupon thruster jets ignite and turn the weapon to the targetbearing. The main sustainer rocket motor then ignites and the missile is command guidedto the intercept point where the proximity fuse is triggered.Effective range limits are from 1500 to 12000 m with target altitude limits being between10 and 6000 m. The maximum maneuvering load factor limit on the weapon is 30 g.The missile launcher consists of a box container extending down below the level of thehull top, holding two groups of four ready to fire missiles in the vertical position. Eachmissile is in a maintenance-free factory-sealed container-launcher box. The system isreloaded by a dedicated transportation/loader vehicle.

The 3D pulse Doppler electronically beam steered E/F-band surveillance radar providesrange, azimuth, elevation and automatic threat evaluation data on up to 48 targets for thedigital fire control computer processing system. Automatic track initiation can beperformed on the 10 most dangerous targets, which are categorized and prioritized inorder of threat for engagement. The operator reconfirms the highest priority target choiceand tracks this target before firing the missile. The maximum radar range is stated as 25kilometers, but the rapid five to eight second reaction time [including fire control targetprioritization] suggests a somewhat greater range. The radar antenna, on top of the turret,is swung through 90º to the horizontal position for travel. Target radar surveillance iscarried out on the move but the vehicle would normally come to a halt for missile launch.

The phased-array pulse Doppler G/H-band tracking radar is located at the front of theturret. This electronically steered radar is capable of simultaneously tracking two targetstraveling at speeds of up to 700 km/h in all weather conditions, and countering threatECM operations. The antenna assembly can be folded down for travel.Mounted on the top left of this radar is a small vertical pointing antenna which serves toinitially acquire the missile after launch before it is handed over to the maintracking/guidance system. On the lower right side of the tracking radar is an automaticTV tracking system with a range of 20000 m that complements the tracking radar andenables the system to operate in a heavy ECM environment.The Tor is not amphibious although it is airportable. An NBC system is fitted as standardas is a built-in training system. The chassis of the vehicle is almost identical to that usedfor the 2S6 self-propelled hybrid air defense system and is based on the GM-569 trackedvehicle. The three man crew consists of the vehicle commander, system operator andvehicle driver, seated at the front of the vehicle with the large box-like unmanned turretin the center and the engine compartment at the rear. This arrangement is similar to thatof the Kub (SA-6) and Shilka (ZSU-23-4) vehicles. The vehicle suspension consists ofsix dual rubber tired roadwheels with the idler at the front, drive sprocket at the rear andthree return rollers.An auxiliary gas turbine powers a 75 kW generator, allowing the main diesel engine to beshut down when the system is deployed to conserve fuel.The Russian company Antei which produces anti-aircraft missile systems has developeda new efficient system Tor M1. A number of countries have precision weapons and areliable shield is necessary against these weapons. The new Russian anti-aircraft missilesystem Tor is such a shield. The system consists of a special vehicle and two radars todetect targets and to accompany flying targets and missiles, a computer, and equipmentfor launch and navigation. The missile unit is a transportation and launch container withfour missiles. A anti-aircraft guided missile is a one-stage missile with a solid fuelengine. The system is operated by 3 or 4 people. The Tor system ensures reliableprotection for government, industrial and military sites and ground troops from all typesof missiles, unpiloted aircraft, aircraft bombs, aircraft and helicopters with stealthcapabilities. The Tor system is the only system in the world which can detect and identifyvarious targets. It can detect targets at a height ranging from 10 meters to 6 kilometers.The Tor system is autonomous and has short reaction time. The latest technologies ofRussia's defense industry are used in it.

SpecificationsDesignations 9K331 Tor-M1

Date of Introduction 1990

Proliferation At least 5 countries

Crew 3

TLAR 9A331 combat vehicle

Chassis GM-355

Combat Weight (mt) 34

Length (m) 7.5

Height (m) 5.1 (TAR up)

Width (m) 3.3

Engine Type V-12 diesel

Cruising Range (km) 500

Max. RoadSpeed 65 (km/h)

Radio INA

Protection NBC Protection System

Launcher ReactionTime (sec) 5-8

Reload Time (min) 10

Fire on Move Yes

Emplacement Time(min) 5

Displacement Time(min) Less than 5

Missile Name 9M331

Max. Range (m) 12,000

Min. Range (m) 100

Max. Altitude 6,000 (m)

Min. Altitude 10 (m)

Length 2,900 (mm)

Diameter 235 (mm)

Weight (kg) 167

Missile Speed (m/s) 850

Propulsion INA

Guidance Command

Warhead Type Frag-HE

Fuze Type RF Proximity

Warhead Weight (kg) 15

Self-Destruct (sec) INA

FIRE CONTROL Sights w/Magnification

Electro-optical (EO) television system

Range 20 km

IFF Yes

Radar Function Target Acquisition

Detection Range (km) 25

Tracking Range (km) INA

Frequency INA

Frequency Band H-band Doppler

Radar Function Target Tracking and Guidance

Detection Range (km) INA

Tracking Range (km) 25

Frequency INA

Frequency Band K-band Doppler, Phased Array

VARIANTS SA-N-9 Naval version

SA-N-9

SA-16 GIMLETIgla-1 9K310SA-16 GIMLET (Igla-1 9K310) man-portable surface-to-air missile system, a furtherdevelopment from the SA-7 & SA-14 series, is an improved version of the SA-18GROUSE, which was introduced in 1983, three years before the SA-16. The SA-16feattures a new seeker and modified launcher nose cover. Whereas the the SA-18 9M39missile is fitted with an aerodynamic spike on the nose, the 9M310 missile of the SA-16has the spike replaced with an aerodynamic cone held in place with a wire tripod. On theSA-18 the protective cover of the seeker is conical, on the SA-16 it is tubular with aprominent lip at the forward edge. The 9M313 missile of the SA-16 employs an IRguidance system using proportional convergence logic, and an improved two-colorseeker, presumably IR and UV). The seeker is sensitive enough to home in on airframeradiation, and the two-color sensitivity is designed to minimize vulnerability to flares.The SA-16 has a maximum range of 5000 meters and a maximum altitude of 3500meters.

SpecificationsMaximum Speed 2+ Mach

Effective Altitude 3,500 m

Effective Range 500 -- 5,000 m

Altitude 10-3500 m

Warhead HE 2kg

Guidance passive 2-color IR andUV homing

Fuze Contact and graze

Kill Radius Unknown

SA-17 GRIZZLY / Buk-M1-2SA-N-12 GRIZZLY / YezhHQ-16SA-17 GRIZZLY is a new mobile SAM system to augment and eventually replace theSA-11 GADFLY. The new system uses the same launch vehicle chassis, and overall hasa similar configuration to the SA-11 GADFLY. The SNOW DRIFT surveillance radar isalso carried on the modified GM-569 tracked vehicle chassis. Russia is upgrading theBelorussian Buk (NATO: SA-11 Gadfly) air defence missile system at the UliyanovskMechanical Plant. The new Buk-M1-2 (SA-17 Grizzly) system has increased fire power,and guarantees hits against six targets flying simultaneously from different directions andat different altitudes. The Yezh naval version [SA-N-12] of the SA-17 is visually Identicalto SA-N-7.

The HQ-16 is a joint development project between China and Russia that apparentlyrepresents a further evolution of the Russian Grizzly. The system would represent asignificant overall improvement in Chinese air defense capabilities. The HQ-16 willreportedly have a range of 50 miles and the ability to hit both high and low flying targets.

SA-18 GROUSEIgla 9K38SA-N-10 GROUSEIgla-MThe SA-18 GROUSE (Igla 9K38) is an improved variant in the the SA-7 & SA-14 seriesof manportable SAMs. As with the earlier SA-14, the SA-18 uses of a similar thermalbattery/gas bottle, and the SA-18 has the same 2 kilogram high-explosive warhead fittedwith a contact and grazing fuse. But the missile of entirely new design with substantiallyimproved range and speed,. The new seeker and aerodynamic improvements extend itseffective range, and its higher speed enables it to be used against faster targets. The SA-18 has a maximum range of 5200 meters and a maximum altitude of 3500 meters. The9M39 missile SA-18 employs an IR guidance system using proportional convergencelogic. The new seeker offers better protection against electro-optical jammers; theprobability of kill against an unprotected fighter is estimated at 30-48%, and the use ofIRCM jammers only degrades this to 24-30%.

The Igla-M [SA-N-10 ] is the naval version of the SA-18.

SpecificationsContractor

Entered Service

Total length

Diameter

Wingspan

Weight

Warhead Weight

Propulsion

Maximum Speed

Maximum effectiverange 5200 meters

altitude, (m) 10-3500

Guidance mode passive IR homing

emplace/displacetime 13 sec

Single-shot hitprobability

SA-19 GRISOM9M111 Pantsyr S1The SA-19 GRISOM (9M111) is a radar command guided, two-stage surface to airmissile mounted on the 2S6 Integrated Air Defense System. The 2S6 vehicle is fittedwith two banks of four missiles in blocks of two, which can be elevated verticallyindependent of each other. The SA-19 can engage aerial targets moving at a maximumspeed of 500 meters/second at altitudes ranging from 15 to 3,500 meters, and at slantranges from 2400 to 8000 meters. The missile's high-explosive fragmentation warhead isactuated by a proximity fuse if the missile passes within 5 meters of the target. The SA-19 is supported by the HOT SHOT radar system, which consists of a surveillance radarwith a maximum range of 18 km, and a tracking radar with a maximum range of 13 km.The semi-automatic radar to command line-of-sight engagement requires the gunner totrack the target using the roof-mounted stabilized optical sight. The SA-19 is claimed tohave a kill probability of 0.65.

SpecificationsChassis: Ural-53234 8 x 8 truck

Crew 3

Armament 12 57E6 SAMs, 2 2A72 30 mm guns

Missile

Guidance system radio commands with IR or radio direction finding

Maximum speed 1,100 m/sec

Time of flight to 10km range 14 sec

Weight

With container 90 kg

Launch weight 65 kg

Container diameter 170 mm

Length in container 3.2 m

Warhead type: fragmentation rod

Warhead weight 16 kg

Gun

Calibre 30 mm

Total rate of fire 700 rds per minute

Muzzle velocity 960 m/sec

Projectile weight 0.97 kg

Ammunition load 750 rounds

Radar

Range, with targetreflection surface of 2-3 sq cm

Target detection at least 30 km

Target tracking at least 24 km

Kill zone

Missiles

Range 1,000 to 12,000 m

Altitude 5 - 8,000 m

Guns

Range 0.2 - 4,000 m

Altitude 0 - 3,000 m

Number ofsimultaneouslyengaged targets

2

Number of targetshandled per minute 10 - 12

Reaction time 5 - 6 sec

S-400 SA-20 TriumfThe Triumf S-400 is a new generation of air defense and theater anti-missile weapondeveloped by the Almaz Central Design Bureau as an evolution of the S-300PMU [SA-10] family. This new system is intended to detect and destroy airborne targets at adistance of up to 400 km (2- 2.5 times greater than the previous S-300PMU system). TheTriumf system includes radars capable of detecting low-signature targets. And the anti-missile capability of the system has been increased to the limits established by the ABMTreaty demarcation agreements -- it can intercept targets with velocities of up to 4.8km/sec, corresponding to a ballistic missile range of 3,500 km.

The system was developed through the cooperation of the Almaz Central Design Bureau,Fakel Machine Building Design Bureau, Novosibirsk Scientific Research Institute ofInstruments, St. Petersburg Design Bureau of Special Machine Building and otherenterprises.

The Fakel Machine Building Design Bureau has developed two new missiles for Triumf.

The "big" missile [designation otherwise unknown] has a range of up to 400 kmand will be able to engage "over- the-horizon [OTH]" targets using a new seekerhead developed by Almaz Central Design Bureau. This seeker can operate in botha semiactive and active mode, with the seeker switched to a search mode onground command and homing on targets independently. Targets for this missileinclude airborne early warning and control aircraft as well as jammers.

The 9M96 missile is designed to destroy aircraft and air- delivered weapons atranges in excess of 120 km. The missile is small-- considerably lighter than theZUR 48N6Ye used in the S-300PMU1 systems and the Favorit. The missile isequipped with an active homing head and has an estimated single shot killprobability of 0.9 for manned aircraft and 0.8 for unmanned maneuvering aircraft.a gas-dynamic control system enables the 9M96 missile to maneuver at altitudesof up to 35 km at forces of over 20g, which permits engagment of non- strategicballistic missiles. A mockup of the missile was set up at an Athens armsexhibition in October 1998. One 9M96 modification will become the basic long-range weapon of Air Force combat aircraft, and may become the standardizedmissile for air defense SAM systems, ship-launched air defense missile systems,and fighter aircraft.

These new missiles can be accomodated on the existing SAM system launchers of the S-300PMU family. A container with four 9M96's can be installed in place of one containerwith the 5V55 or 48N6 missiles, and thus the the standard launcher intended for four48N6Ye missiles can accommodate up to 16 9M96Ye missiles. Triumf provides for thegreatest possible continuity with systems of the S-300PMU family (PMU1, PMU2),making it possible to smoothly change over to the production of the new generationsystem. It will include the previous control complex, though supporting not six but eight

SAM systems, as well as multifunctional radar systems illumination and guidance,launchers, and associated autonomous detection and target indication systems.

The state tests of the S-400 system reportedly began in 1999, with the initial test on 12February 1999. As of May 1999 the testing of S-400 air defense system was reportedlynearing completion at Kapustin Yar, with the first systems of this kind to be delivered tothe Moscow Air Force and Air Defense District in the fourth quarter of 1999. However,as of August 1999 government testing of the S-400 was slated to begin at the end of1999, with the first system complex slated for delivery in late 2000. The sources of theapparent one-year delay in the program are unclear, though they may involve somecombination of technical and financial problems with this program. Russian air defensetroops conducted a test of the new anti-aircraft missile system S-400 on 07 April 2000. Atthat time, Air Force Commander Anatoly Kornukov said that serial production of the newsystem would begin in June 2000. Kornukov said air defense troops would get one S-400launcher system by the end of 2000, but it would be armed with missiles of the availableS-300 system.

On condition of normal funding, radars with an acquisition range of 500-600 km shouldbecome operational by 2002-2003. However, other sources report that while it wasordered by the Defence Ministry, the military has nothing to pay for it with, so it isunclear when the Russian military will get this new weapon.

The Russian Air Force is studying a reduction in the number of types of air defenseweapons, and it is possible that Triumf will become the only system being developed,providing defense both in the close-range and mid-range as well long-range zones.

SpecificationsContractor Almaz Central Design Bureau

Fakel Machine Building Design Bureau

Entered Service

Total length

Diameter

Wingspan

Weight

Warhead Weight

Propulsion

Maximum Speed

Maximum effectiverange

120 km 9M96 missile400 km "big" missile

Guidance mode

Single-shot hitprobability

SA-X-21 MyskIn 1996 there were reports of that US sources had suggested the fact of the existence of anew Russian SAM system in development with the US designators SA-X-21 and theRussian system nomenclature believed to be Mysk. However, no additional informationhas been forthcoming concerning either a Russian system designated Mysk, or any othersystem that might be associated with the SA-X-21 designator. The Ballistic MissileDefense Simulation Support Center's Extended Air Defense Simulation [EADSIM]modeling database does contain an entry for the SA-21, though publicly available detailsare lacking. The Extended Air Defense Simulation is a system-level simulation used toassess the effectiveness of Theater Missile Defense (TMD) and air defense systemsagainst the full spectrum of extended air defense threats. EADSIM models performanceand predicts effectiveness of ballistic missiles, surface-to-air missiles, aircraft missiles,and cruise missiles in a variety of user defined scenarios. EADSIM is being used by allfour U.S. military services, individually and jointly, at over 300 subscriber sites aroundthe world. It is also being used by the United Kingdom, Israel, Australia, and the SHAPETechnical Center under Memoranda of Agreement with the U.S. Army. EADSIM hasbeen used in support of the TMD Advanced Warfare Experiment, as well as TMD Costand Operational Effectiveness Analysis studies. EADSIM was used successfully by theU.S. Air Force Studies and Analyses Agency to analyze attrition, Suppression of EnemyAir Defense missions, and refueling operations during Desert Shield and Desert Storm.

AA-1 ALKALIK-5 (RS-1U / RS-2)PL-1In 1955 the Kaliningrad (Moscow Oblast) Series Production Plant, which was producinggun turrets for M-4 bomber aircraft and similar equipment, began series production of thefirst K-5 and K-8 guided air-to-air missiles.

The R-55 (K-55, Object 67), a modification of the K-5 missile, was series-producedthroughout the 1967-77 period and quite widely used. By then the Almaz team had givenup work air-to-air missiles, and the development of the K-55 missile was assigned to theengineering office at the Kaliningrad (Moscow Oblast) Series Production Plant. Thisplant was producing aircraft weapons (artillery turrets for M-4 bomber aircraft, sights,etc.), then in 1955 began series production of the first K-5 and K-8 guided air-to-airmissiles. Developing the K-55 missile was the first task ever assigned to this team alone(and the only one concerning air-to-air missiles in the history of this team). Currently thisengineering office in Kaliningrad, under the name Zvezda, is the leading Russian creatorof strategic guided air-to-ground missiles.

During the 1966-168 period the two teams working on air-to-air missiles were renamed --Bisnovat's OKB-4 team was renamed Molniya and Andrey Lyapin's (who replaced IvanToropov in 1961) team was designated Vympel. During later part of the 1960s theVympel team began working on modifications to the R-55 which resulted in the R-55Mmissile, with a cooled homing head, a radio rather than optical closing-in igniter, and amore potent warhead. The PL-1 [Pili = Thunderbolt, or Pen Lung = Air Dragon] mediumrange air-to-air missile was a Chinese copy of the AA-1.

SpecificationsContractor

Entered Service 1957

Total length 2.83 m

Diameter

Wingspan

Weight 83.2 kg

Warhead Weight

Propulsion

Maximum Speed

Maximum effective 2 - 6 km

range

Guidance mode Radio Controlled

Single-shot hitprobability

Carried by MiG-17PFU, MiG-19P, MiG-21F, Yak-25, Yak-28

AA-2 ATOLLK-13 (R-3 or Object 310)PL-2 / PL-3 / PL-5The 24 September 1958 Chinese acquisition of an American AIM-9B Sidewinder missilemarked the beginning of a breakthrough in the development of Soviet air-to-air missiles.The missile, fired from a Taiwanese F-86 Sabre aircraft, lodged without exploding in aChinese MiG-17. The missile was sent to Toropov's engineering office to be copied, andthe product the K-13, long the most popular Soviet air-to-air missile. The Sidewinder hada number of valuable features, not least of which was the modular construction thatfacilitated ease in production and operation. The simplicity of the AIM-9 was in markedcontrast to the complexity of contemporary Soviet missiles. The Sidewinder's infrared-guided homing head contained a free-running gyroscope and was much smaller thanSoviet counterparts, and the steering and in-flight stabilization system were equallysuperior. Gennadiy Sokolovskiy, later chief engineer at the Vympel team, said that "theSidewinder missile was to us a university offering a course in missile constructiontechnology which has upgraded our engineering education and updated our approach toproduction of future missiles."The Soviets soon made advances over the original Sidewinder model, making dozen ofmodifications to the initial design. In 1960 series-production of the K-13 missile (alsocalled R-3 or Object 310) began. In 1962 the R-3S (K13A or Object 310) became the firstversion to be produced in large numbers, though its homing operation took much moretime (22 seconds instead of 11 seconds). In 1961 development began of the high-altitudeK-13R (R-3R or Object 320) with a semiactive radar head, which was entered servicewith combat aircraft in 1966. The training versions were the R-3U missiles ("uchebnaya",barrel with a homing set, not fired from an aircraft) and the R-3P ("prakticheskaya"differing from the combat version by absence of an explosive charge). The RM-3V (RMdenoting "raketa-mishen" [target-missile] served as an aerial target.

During late 1960s the Vympel team began working on the K-13M (R-13M, Object 380)modification of the K-13 missile, which in 1973 was certified as an operational weapon.It has a cooled homing head, a radio rather than optical closing-in igniter, and a morepotent warhead. Analogous modifications of the R-55 resulted in the R-55M missile. Thelast version of the K-13 is the R-13M1 with a mofified steering apparatus.

The K-13 missile was produced in China as the PL-2 (updated versions PL-3 and PL-5)and also in Romania as the A-91. The PL-5E [Pili = Thunderbolt, or Pen Lung = AirDragon] air-to-air missile has a maximum mobility overload of 40g, exceeding the 35g ofthe AIM-9L of the United States. Mobility overload a unit for measuring the mobility ofaircraft. The larger the value the better the aircraft can adapt to violent mid-air mobility.An air-to-air missile with a great overload means that the attacked side is less likely toescape the attack). The speed of the missile is Mach 2.5 (2.5 times sound speed) and itsmaximum range is 14,000 meters.

Specifications

Year 1961

Type short-range missile

ModificationsAA-2 - infra-red guidanceAA-2-2 "Advanced Atoll" - semi-active radarguidance

Wingspan (AA-2) 0.45 m

Wingspan (AA-2-2) 0.53 m

Length (AA-2) 2.8 m

Length (AA-2-2) 3.0 m

Diameter 0.12 m

Launch weight 70 kg

Max. speed 2850 km/h

Maximum range 6.5 km

Propulsion solid propellant rocket motor

Guidance passive infra-red homing or semi-active radar homing

Warhead proximity-fuzed blast fragmentation, 6 kg

Service

USSR, India, South Yemen, Romania, Afghanistan,North Yemen, North Vietnam, Albania, Nigeria,Uganda, Iraq, Poland, Syria, Algeria, Sudan,Morocco, Somalia, Angola, Bangladesh, Peru,Yugoslavia, Mozambique, China, Libya, Hungary,Laos, North Korea, Ethiopia, East Germany, Finland,Czechoslovakia, Cuba, Bulgaria.

AA-2

PL-2

PL-3

PL-5

AA-3 ANABK-8PL-2 [China]In 1955 the Kaliningrad (Moscow Oblast) Series Production Plant, which was producinggun turrets for M-4 bomber aircraft and similar equipment, began series production of thefirst K-5 and K-8 guided air-to-air missiles. The improved version K-8M was certified in1961 as a combat weapon (designated by ordnance as the R-8M; the letter K referring toEngineering Office and the letter R referring to Air Force). This missile operated with theOriol [Eagle] radar set.In January 1960 it was decided to use the homing head of the K-13 missile in K-5 and K-8 missiles to devise a missile for tactical air combat. In 1962 M. Bisnovat's OKB-4Special Engineering Office was testing K-88 missiles, smaller than the K-8 and with a K-13 head, although the K-88 never moved beyond prototype status.

Subsequent modifications of the K-8 missile led to the K-8M (R-8M1, more widelyknown as the K-98 or R-98), equipped with a semiactive radar homing head whichenabled it to attack airborne targets not only from behind but also head on. The firstinterceptor-fighter system using the R-98 missile was the Su-15-98 aircraft. The missilewas subsequently employed on the on the Yak-28P aircraft with the Oriol-D radar set,and later on the Su-15TM aircraft with the Tajfun [Typhoon]-M radar set.

In 1973 production of the R-98 missile shifted to the final variant, the R-98M (K-8M)with improved firing capabilities and greater resistance to countermeasures. The R-98Mmissile remains part of the combat load of the Su-15TM aircraft.

All these missiles were produced in two variants, with radar guidance (suffix R) and aninfrared guidance (suffix T) respectively. The training version is the UR-8M, which firstentered service in 1966.

SpecificationsContractor

Year 1961

Type medium-range intercept missile

Modifications Semi-active I-band and J-band radar guidancePassive infra-red guidance

Wingspan 1.3 m

Length (SARversion) 4.1 m

Length (IR version) 4.0 m

Diameter 0.28 m

Launch weight 275 kg

Max. speed 3420 km/h (Mach=3.0)

Maximum range 19 km

Propulsion single stage solid propellant rocket motor

Guidance semi-active I-band and J-band radar homing or passiveinfra-red homing

Warhead proximity-fuzed high-explosive blast

Carried by Yak-28, Su-15

Service USSR, Bulgaria, Romaina, Poland, East Germany,Hungary, Czechoslovakia

AA-4 AWLK-9 / K-155In the late 1950s the Mikoyan and Gurevich design bureau built the long-range K-9missile, also called the K-155. The prototype of this weapon was displayed publicly in1991 under an E-152A plane, but the missile was not certified as a combat weapon.

AA-5 ASHR-4In 1959 the Bisnovat design team began work on the K-80 missile (Object 36 -- latercalled the R-40) as part of the the Tu-128S-4 interception system. This strategic airdefense system consiste of the Tu-128 long-range interceptor fighter aircraft, a Smerch[Tornado] on-board radar set (the letter S in the system designation), and the R-4 missiles(the digit 4 in Tu-128S-4). Two variants of the R-4 missile were developed: the R-4Rusing a semiactive radar set with a PARG-10-88 homing head and the R-4T usinginfrared homing with the T-80NM seeker head. Apart from the Tu-128, only the MikoyanE-152M experimental aircraft carried the R-4 missiles. The R-4 missile entered series-production in 1963, although significant development efforts remained, as was also thecase with the Smerch radar set. In 1973 production began of the improved K-80M (R-4TM and R-4RM variants) for the Tu-128S-4M system, consisting of the Tu-128Maircraft, the Smerch-M radar set, and the R-4M missile. In the West the K-80 missile andits modifications are called The AA-5 Ash R-4 missile was withdrawn from service alongwith the remaining Tu-128 aircraft around the end of the Cold War.

SpecificationsContractor

Year 1961

Type medium-range missile

Modifications Infra-red guidanceSemi-active radar guidance

Wingspan 1.3 m

Length (SARversion) 5.3 m

Length (IR version) 5.2 m

Diameter 0.31 m

Launch weight 390 kg

Max. speed 1710 km/h

Maximum range(SAR version) 30 km

Maximum range (IRversion)

15 km

Propulsion solid propellant rocket motor

Guidance passive infra-red homing with Cassagrain optics or

semi-active I-band radar homing

Warhead high-explosive blast

Carried by Tu-128

Service USSR, Czechoslovakia, Romania, Bulgaria, EastGermany, Poland.

AA-6 ACRIDR-40In early 1962 the Bisnovat design team began working on the R-40 (K-40), a new long-range missile intended for use with the the MiG-25-40 high- altitude interception system,consisting of the MiG-25 aircraft with Smerch-A radar set and the R-40 missile. Thoughonly slightly larger than the predecessor R-4, the range of the R-40 is over three timesgreater. This missile was produced in two variants: R-40R (Object RD46 with PARG-12head) and R-40T (Object TG-46).

After the defection of a MiG-25P to Japan on 06 September 1976, an extensive redesignof the aircraft was undertaken, resulting in the MiG-25PD interception system. Instead ofthe Smerch-A, a Sapfir-25 radar was installed. The new missile R-40D and its R-40D1update ("dorabotanaya" [more elaborate]) were produced in two variants R-40RD and R-40TD, both featuring improved countermeasures resistance and a more sensitive hominghead to improve performance against low-flying targets. The R-40D1 missile wasdeveloped by the Vympel team, the Molniya team having by that time withdraw fromdevelopment of aircraft missiles. The R-40 is still included among the weapons of MiG-25 and MiG-31 aircraft, although production was discontinued in 1991.

SpecificationsManafacturer

Date Deployed Late 60s

Range 30 km (R-40) 50 km (R-40TD and R-40RD)

Speed Mach 4.5

Propulsion One solid-propellant rocket motor

Fuze Radar and active laser

Guidance Command, inertial and semi-active radar (R-40R)Command, inertial and IR (R-40T)

Warhead 70 kg HE fragmentation

Launch Weight 475 kg

Length 6.2 m

Diameter 355 mm

Fin Span 1.8 m

Platforms Su-15, MiG-25, MiG-31

AA-7 APEXR-23 / R-24In the mid-1960s the Vympel design bureau developed the K-23 intermediate-rangemissile for MiG-23 fighter jet aircraft. While the first units of the K-23 missile weretested with the prototypes the MiG-23 aircraft, the missile was certified as a weapon forthe MiG-23M in 1973. The R-23 comes in two variants: R-23R (Object 340) with radarguidance and R-23T (Object 360) with infrared guidance. There is also the trainingversion R-23UT.

The later MiG-23ML and MiG-23MLD aircraft carry the R-24 missile, a modification ofthe R-23 with various improved characteristics, most importantly a 50 km rather than 35km range. In its external appearance this missile is similar to the predecessor R-23. Foractual use it is available in two variants: R-24R (Object 140) and R-24T (Object 160).The R-23 is produced in Romania under license as the A-911.In 1968 the Soviets acquired an American AIM-7M Sparrow, which was similar to the R-23 class of missiles the under development, and the Vympel team copyied the Sparrowunder the designation K-25. Several of these missiles were tested, but Soviet R-23 missilewas sent to production, and work on the K-25 ended in 1971. The R-23 and R-24 missileswere superior to the K-25 Sparrow-ski in versatility and range, as well as interferenceimmunity, signal processing logic, and other characteristics. Nevertheless, analysis of theSparrow missile design were helpful in later work on the the R-27 missile: on itshydraulically driven closed-loop servomechanisms and aerodynamic system withmovable wings.

SpecificationsContractor

Year 1975

Type medium-range missile

Modifications Semi-active radar guidancePassive infra-red guidance

Wingspan 1.0 m

Length (SARversion) 4.5 m

Length (IR version) 4.2 m

Diameter 0.22 m

Launch weight 320 kg

Max. speed 3420 km/h (Mach=3.0)

Maximum range 35 km

(SAR version)

Maximum range (IRversion) 15 km

Propulsion two stage solid propellant rocket motor

Guidance semi-active radar homing or passive infra-red homing

Warhead proximity-fuzed high-explosive, 40 kg

Carried by MiG-23

Service USSR, Czechoslovakia, Libya, India, East Germany.

AA-8 APHIDK-60 (R-60, Object 62)Toward the end of the 1960s the Molniya design bureau begin working on the firstmissile for tactical air combat, the K-60 (R-60, Object 62), with infrared self-guidance.Series production of this missile began in 1973, with the R-60 missile being certified as aweapon for a variety combat aircraft.

The R-60 missile is an unusually small missile, weighing half as much as the lightestWestern missiles, with a correspondingly small warhead which weighs barely 3.5 kg).The R-60 on attack aircraft such as the MiG-27, Su-24 or Su-25 serves as a self-defensemissile, and on fighter aircraft such as the MiG-23, MiG-25, and Su-15 it is occasionallyused as a supplementary missile. The R-60 missile had an unusually short developmenttime, with only four years passing from the beginning of its design to the beginning of itsproduction -- the normal development process of Soviet air-to-air missiles typicallyrequired 8 to 9 years. This rapid development was facilitated by the availability of awealth of experimental data on the K-13 missile, and no new research was done for theR-60. Further developments of the R-60 include the R-60M missile, the export variant R-60MK, and the UZR-60 training version.

SpecificationsManufacturer

Date Deployed 1975

Range 3 km, 5 km 10 km

Speed Mach 2+

Propulsion One solid-propellant rocket motor

Fuze

Two active radar fuze aerials located aft of themoving control fins, and a single strake runningdown the forward half of the body. Active laser inR-60M

Guidance All aspect Infrared

Warhead 6 kg ( 1.6 kg of which is uranium ) HEfragmentation

Launch Weight 65 kg

Length 2.08 m

Diameter 130 mm

Fin Span 0.43 m

PlatformsMi-24, Su-15bis, Su-17M3, Yak-38, Su-25, Su-24M,MiG-21bis, MiG-23, MiG-25, MiG-27, MiG-29,MiG-31

AA-9 AMOSThe R-33 long-range missile was created for arming MiG-31 fighter-interceptors. Itbecame operational in 1980 and is capable of engaging SR-71 strategic reconnaissanceaircraft, B-52 and B-1 bombers, aircraft of front and transport aviation, and alsohelicopters and cruise missiles. The R-33 may be used at any time of day, under anyweather conditions, in the presence of interference and jamming to engage targets flyingagainst earth and water surfaces. The missile is made in a normal aerodynamic schemeand has a cruciform configuration. Lifting surfaces of the R-33 are made with a lowaspect ratio and two control surfaces are folding for its semirecessed accommodationbeneath the platform's fuselage. Control and stabilization in three angles areaccomplished with the help of four mechanically unconnected (differential) aerodynamicsurfaces activated by gas drives. The missile is equipped with a semiactive radar hominghead that locks onto a target on the trajectory. Guidance of the R-33 to a target is acombination: inertial in the initial phase and homing in the terminal phase.

The R-33 is the first Russian air-to-air missile to use an onboard digital computer, whichhas stable characteristics compared with analogue devices. It is fitted with an active radarproximity fuze and impact fuze as well as with an HE-fragmentation warhead.

SpecificationsManafacturer Vympel

Date Deployed 1985?

Range 160 km

Speed Mach 4.5

Propulsion solid rocket

Fuze Active radar

Guidance Inertial, command updates and semi-active radar

Warhead 47 kg HE fragmentation

Launch Weight 490 kg

Length 4.15 m

Diameter 380mm

Fin Span 1.18 m ( 0.9 m wingspan )

Platforms Mig-31, up to 6 can be carried

AA-10 ALAMO R-27The R-27 medium-range missile is a component of the MiG-29 armament. In its overallcharacteristics the R-27R is generally comparable to the the American AIM-7M Sparrowmissile, which it is said to surpasse it in certain combat capabilities. The R-27 is designedaccording to a modular principle and is the base for a family of missiles equipped withvarious types of homing heads and propulsion systems. Several versions of this missilehave been produced in Russia with infrared, semi-active and active radar guidance. TheAA-10 Alamo-C has a range of 130 km, while other variants have a maximum range ofbetween 70 to 170 kilometers.The R-27 standardized medium-range guided missile became operational in 1985,intended for MiG-29 and Su-27 frontal aviation fighters. The R-27 is capable of engagingmanned and unmanned targets in long-range and close maneuverable air-to-air combat. Itcan be employed both in individual as well as group operations of platform aircraft. Itsupports the intercept of targets moving from different directions against the backgroundof the earth's and water's surface in any weather conditions.

The R-27R is equipped with a semiactive radar homing head. The R-27R is equippedwith an active radar proximity fuze and impact fuze and a continuous-rod warhead. It isguided to the target by a combination method according to the proportional navigationmethod: inertially with radiocorrection of trajectory in the initial flight phase, and homingin the terminal phase. This provides for reliable target lock-on at long ranges from thelaunching aircraft. The missile can be guided along special trajectories to create favorableconditions for homing head and proximity fuze operation. It is capable of going around aplume of passive jamming, of being moved out of the main lobe of the platform's radar,and of approaching a low-flying target from above at a given angle.

The missile has a canard aerodynamic configuration with an axially symmetric cruciformarrangement of aerodynamic surfaces. Control surfaces of original (so-called "butterfly")configuration permit using the same surfaces both for missile yaw and pitch control aswell as for its roll stabilization. Each of the four control surfaces has an independenthydraulic drive with a pump-accumulator system for supplying pressure fluid. Canardsurfaces are mounted ahead of them. Changing their size ensures identical balancecharacteristics of the missile when the homing head is replaced.

SpecificationsContractor Vympel

Date Deployed 1982

Range 2 - 80 km R-27R 70 km R-27T 130 km R-27RE120 km R-27TE

Speed Mach 4

Propulsion One solid-propellant rocket motor

Guidance SARH R-27R, R-27E All-aspect Infrared R-27T,R-27TE

Warhead 39 kg expanding rod

Launch Weight 253 kg R-27R 254 kg R-27T 350 kg R-27RE 343kg R-27TE

Length 3.70 m

Diameter 230 mm

Fin Span 0.77 m

Platforms Su-27, Su-33, Su-35, Mig-29, Yak-141

AA-11 ARCHER R-73Currently the R-73 is the best Russian short range air-to-air missile. Apart from anexceptional maneverability, this missile is also directly connected to the pilot's helmet,which allows engagement of targets lateral to the aircraft, which cannot be engaged bymissiles with a traditional system of targeting and guidance. The R-73A, an earliervariant of this missile, has a 30 km range, while the most recent R-73M can hit targets ata distance of 40 km.

The R-73 short-range, close-combat standardized missile was developed in the VympelMachine Building Design Bureau, and became operational in 1984. The R-73 is includedin the weapon complex of MiG-23MLD, MiG-29 and Su-27 fighters and theirmodifications and also of Mi-24, Mi-28 and Ka-50 helicopters. It also can be employed inflying craft which do not have sophisticated aiming systems.

The missile is used for engaging modern and future fighters, attack aircraft, bombers,helicopters, drones and cruise missiles, including those executing a maneuver with a g-force up to 12. It permits the platform to intercept a target from any direction, under anyweather conditions, day or night, in the presence of natural interference and deliberatejamming. It realizes the "fire and forget" principle.

The missile design features a canard aerodynamic configuration: control surfaces arepositioned ahead of the wing at a distance from the center of mass. The airframe consistsof modular compartments accommodating the homing head, aerodynamic control surfacedrive system, autopilot, proximity fuze, warhead, engine, gas-dynamic control systemand aileron drive system. The lifting surfaces have a small aspect ratio. Strakes aremounted ahead of the aerodynamic control surfaces. The combined aero-gas-dynamiccontrol gives the R-73 highly maneuverable flight characteristics. During flight, yaw andpitch are controlled by four aerodynamic control surfaces connected in pairs and by justas many gas-dynamic spoilers (fins) installed at the nozzle end of the engine. Controlwith engine not operating is provided by aerodynamic control surfaces. Roll stabilizationof the missile is maintained with the help of four mechanically interconnected aileronsmounted on the wings. Drives of all missile controls are gas, powered from a solid-propellant gas generator.

The passive infrared homing head supports target lock-on before launch. Guidance to thepredicted position is by the proportional navigation method. The missile's combatequipment consists of an active proximity (radar or laser) fuze and impact fuze and acontinuous-rod warhead. The engine operates on high-impulse solid propellant and has ahigh-tensile steel case.Russia's Vympel weapons designers have developed a one-of-a-kind air-to-air missile,which NATO has dubbed as AA-11, for use on foreign fighter planes. Techically andmilitarily the new missile, meant for quick-action dogfights, leave its foreign analoguesfar behind. Vympel experts have also made it possible for the new missile to be easilyinstalled on all available types of aircraft. The AA-11 can also be used on older planes

which will now be able to effectively handle the US' highly maneuverable F-15 and F-16jets. The AA-11 missile is based on all-new components, use new high-energy solid fueland an advanced guidance and control system which has made it possible to minimizetheir size. Their exceptionally high accuracy is ensured by the missile's main secret, theso-called transverse control engine, which rules out misses during the final approachtrajectory. The transverse control engine is still without parallel in the world.

Russia has offered the export-version R-7EE air-to-air missile system for sale so that itcan be fitted to foreign-made fighter aircraft. Developed by the Vympel state-sectorengineering and design bureau, the R-7EE is designed for close-quarters aerial combat.Vympel specialists have developed a way of ensuring that the missile system can be fittedto virtually any type of aircraft. It can be fitted to older aircraft, which feature heavily inthird-world countries' air forces.

SpecificationsContractor Vympel

Date Deployed 1980s

Range 20 km (R-73M1) 30 km (R-73M2) 40 km

Speed Mach 2.5

Propulsion One solid-propellant rocket motor

Guidance All aspect Infrared

Warhead 7.4 kg HE expanding rod warhead

Launch Weight 105 kg (R-73M1) 115 kg (R-73M2)

Length 2.9 m

Diameter 170 mm

Fin Span 0.51 m

Platforms Su-27, Su-33, Su-34, Su-35, Su-37, MiG-29, MiG-31, MiG-33, Yak-141, Ka-50, Ka-52

AA-12 ADDERR-77The most recent Russian R-77 medium-range missiles (AA-12 "AMRAAMSKI") issimilar to and in some respects equal to the American AIM-120 AMRAAM missiles. TheR-77 missile has an active radar finder and a maximim range of 90-100 kilometers (50km more than AMRAAM) and flies at four times the speed of sound.The AA-12 has rectangular narrow span wings and a distinctive set of four rectangularcontrol surfaces at the rear. similar to the configuration used on the terminal control finsof the SS-21 'Scarab' and SS-23 'Spider' ballistic missiles. These unique control surfacesfeature reduced flow separation at high angles of attack, producing greater aerodynamicmoment force than conventional control surfaces. The missile's guidance is inertial withmid-course updates from the launch aircraft, followed by a terminal active radar phasefrom an acquisition range of about 20 kilometers. Development of the missile is believedto have begun around in 1982.

SpecificationsLength 3.60 m

Body diameter 200 mm

Wingspan 0.35 m

Launch weight 175 kg

Warhead 30 kg HE fragmentation

Fuze Active radar

Guidance Inertial, command and active radar

Propulsion Solid propellant

Range 50 km

Platforms Su-33, Su-34, Su-35, Su-37, MiG-33, MiG-31M, Yak-141

AS-1 KENNELSSC-2a SALISHSSC-2b SAMLETThe AS-1 air-to-surface missile is a subsonic,turbojet-powered, cruise missile with arange or 35 to 97 nm. It weighs approximately 6030-lb and has a conventional warheadof 2020-lb. For guidance, it uses a preprogrammed autopilot for launch and climb, abeam rider for mid-course, and semi-active radar for terminal flight. It has a CEP of 150ft when used in an anti-ship role and a CEP of 1.0 nm when used against land targets.Two AS-1 missiles are carried on the Badger B aircraft. Production of the AS-1 isestimated to have began in 1953, with IOC reached in 1956. It was first seen in 1961.

Two versions of the SSC-2 were developed from the Soviet "KENNEL" air-to-surfaceanti-shipping missile. They resemble a small jet fighter in appearance and are transportedon one-axle semitrailers. The field missile SSC-2a "SALISH" is launched from itstransport semitrailer which is towed by a KrAZ-214 tractor truck The SSC-2b"SAMLET" coastal missile transport semitrailer is towed by a ZIL-157V tractor truckand is not used for launching. The missile must be removed from the transport semitrailerand placed on a large rail-type launcher for firing. The "SAMLET" coastal defensemissile is the most commonly encountered cruise missile, and has been identified in EastGermany and Poland.

SpecificationsContractor

Initial operationalcapability 1956

Production terminated 1960

First detected 1961

Total length

Diameter

Wingspan

Weight

Warhead Weight

Propulsion

Maximum Speed

Maximum effective

range

Guidance mode

Mikoyan K-10S (AS-2 Kipper)The AS-2 air-to-surface missile is a supersonic, turbojet-powered, low-level run-in,cruise missile with a range of 30 to 100 nm. The K-10S missile (Article 352), developedspecially for the Tu-16K-10 (Badger-C) aircraft as weapon against naval vessels, was inOctober 1961, together with that aircraft certified for ordnance. One K-10S missile issuspended from the aircraft, under the middle section of the fuselage. It carries either aconventional or a nuclear 2200-lb warhead. The missile weighs approximately 9120pounds. For guidance, it uses a preprogrammed autopilot for launch and climb, anautopilot with command correction for mid-course flight, and active radar for terminalflight. The guidance system combines inertial guidance during the initial flight stage andactive-radar homing close to the target. The missile can carry a nuclear warhead. It has aCEP of 150 ft when used in an anti-ship role and a CEP of 1 to 2 nm when used againstland targets.

SpecificationsContractor

Initial operationalcapability 1961

First detected 1961

Productionterminated 1965

Type long-range anti-ship standoff missile

Wingspan 4.6-4.88 m

Length 9.5 m

Diameter 0.9 m

Launch weight 4200 kg

Max. speed 1400 km/h

Ceiling 12000 m

Maximum range 260-350 km

Propulsion Lyulka AL-5 RD-9FK liquid fuel turbojet

Guidance active radar homing

Warhead impact with delay-fuzed high explosive, 1000 kg ornuclear 1000-kg warhead

http://www.fas.org/nuke/guide/russia/bomber/as-2.gif

Kh-20 / AS-3 KANGAROOThe AS-3 air-to-surface missile is a large, supersonic, turbojet-powered, cruise missileweighing approximately 24,500 lb with a range of 100 to 350 nm. It carries a 5000-lbnuclear warhead. For guidance it uses a preprogrammed autopilot for launch and climb,an autopilot with command guidance for mid-course flight, and a preprogrammed dive totarget. It has a CEP of 150 ft when used in an anti-ship role and a CEP of 1 to 3 nm whenused against land targets. One AS-3 is carried aboard the Bear B and Bear C aircraft.

SpecificationsContractor

Type meduim- to long-range standoff missile

Initial operationalcapability 1960

First detected 1961

Productionterminated 1965

Wingspan 9.2 m

Length 14.9 m

Diameter 1.9 m

Launch weight 11000 kg

Max. speed 2280 km/h

Ceiling 18000 m

Maximum range 650 km

Propulsion Tumansky R-11 twin spool turbojet with afterburner,50.9 kN of thrust

Guidance beam riding

Warhead high-explosive, 2300 kg, or thermonuclear, 800 kTyield

http://www.fas.org/nuke/guide/russia/bomber/as-3.gif

Raduga Kh-22 (AS-4 Kitchen)Built by A. Berezhnyak's "Raduga" engineering group for Tu-22 and Tu-22M aircraft,this missile is now also arming modified Tu-95K-22 aircraft. During experimental testsconducted from the late nineteen fifties to the early nineteen sixties the Kh-22B versionhad reached a speed of Mach 6 and an altitude of about 70 km. The "Raduga" DesignBureau, first a branch of Mikoyan's OKB-2-155 Special Design Bureau, became anindependent group in March 1957. Since 1974, after the death of Alexander Berezhnyak,its chief engineer is Igor Seleznyev. The Kh-22 missile comes in three variants: 1. Kh-22N with a nuclear warhead and inertial guidance; 2. Kh-22M with a conventional loadfor use against ships and with an active-radar operating during the final flight stage; 3.Kh-22MP for breaking through enemy air defenses (overcoming enemy radars).

SpecificationsContractor

Type long-range tactical standoff missile

Wingspan 3.0 m

Length 11.3-11.65 m

Diameter 0.92 m

Launch weight 5780-6000 kg

Max. speed 4000 km/h

Ceiling 24000 m

Maximum range 460-500 km

Propulsion liquid propellant rocket motor

Guidance active radar or passive infra-red homing

Warhead high-explosive, 1000 kg, ornuclear, 350 kT yield

KSR-2 / KS-11AS-5 KELTThe AS-5 air-to-surface missile is a small supersonic, liquid-rocket propelled, cruisemissile weighing approximately 7760 lb. It has a maximum speed of Mach 1.2 at analtitude of 30,000 ft. and a range of 80 to 125 nm. It can carry an 1100-lb conventionalwarhead, or a nuclear warhead weighing 850 to 1200 lb. For guidance, it uses active radarhoming from launch to impact when employed in an anti-ship role, and an alternatepassive radar homing system when used in an anti-radar role. It has a CEP of 150 ft whenused in an anti-ship role, and a CEP of 1 to 2 nm when employed against land targets.

The Badger G carries two AS-5 missiles suspended beneath its wings. Production of themissile is estimated to have begun in 1963, with IOC in 1965. It was first seen in 1966.

SpecificationsContractor

Year 1968

Type anti-ship and ground attack standoff cruise missile

Wingspan 4.6 m

Length 9.5 m

Diameter 0.9 m

Launch weight 3000 kg

Max. speed 1080 km/h

Ceiling 18000 m

Maximum range 320 km

Propulsion single stage liquid propellant rocket motor

Guidance active radar or anti-radar seeker

Warhead impact- and direct impact-fuzed high explosive, 1000kg

Service CIS, Egypt

http://www.fas.org/nuke/guide/russia/bomber/as-5.gif

Raduga KSR-5 (AS-6 Kingfish)The AS-6 air-to-surface missile is a supersonic, liquid-rocket propelled, cruise missileweighing approximately 13,000 lb. It has an estimated maximum speed of Mach 3.5 at analtitude of 65,000 ft. and an estimated range of 300 nm. It can carry an 1100-lbconventional or nuclear warhead. For guidance it uses a preprogrammed autopilot forlaunch and climb, an inertial guidance system or an autopilot with radio commandoverride for mid-course, and an active radar system for terminal dive when used in anantiship role. It has a CEP of 150 ft when used in the antiship role, and a CEP of 1 to 2nm when employed against land targets. The AS-6 probably is a follow-on to the AS-2and AS-5.

This is a smaller version of the Kh-22 missile, intended for Tu-16 bomber aircraft. Seriesproduction of the KSR-5 (Article D-5) anti-ship version with active-radar homing beganin 1966. Target indication is given by either a "Rubin" radar of the Tu-16K-26 or a YeNradar of the Tu-16K-10-26. The KSR-SP antiradar missile entered service in 1972, atwhich time was also built the KSR-5N version with a nuclear load. On the basis of theKSR-5 was later built the KSR-5NM airborne target for training exercises. ModifiedBadger C and Badger G aircraft carry two AS-6 missiles. The Backfire may also havebeen an AS-6 carrier, but evidence is lacking to confirm this estimate. Production isestimated to have begun in 1969,with IOC in Badger aircraft in 1970. IOC with Backfireis estimated in 1974.

SpecificationsContractor

operational Badger 1970

operational withBackfire 1974

Type long-range cruise missile

Wingspan 2.5 - 2.61 m

Length 10.0 - 10.52 m

Diameter 0.9 m

Launch weight 3900-4800 kg

Max. speed 3200 - 3400 km/h

Ceiling 20000 m

Maximum range 240-700 km

Propulsion two stage solid propellant rocket motor

Guidance active radar or anti-radar seeker

Warheadproximity-, impact- or impact with delay-fuzed high-explosive, 1000 kg, ornuclear, 350 kT yield 700 kg

Service CIS, Iraq

Zvezda Kh-66 (AS-7 Kerry)Zvezda Kh-23 (AS-7 Kerry)In April 1965, when work on the MiG-23 fighter aircraft began, the "Vympel" [Pennant]OKB-134 Special Design Bureau received an order for a Kh-23 tactical guided air-to-ground missile. The main incentive for developing it was intelligence received about theBullpup missile, a highly effective American one of the same class built several yearsearlier. Right away the engineers faced an obstacle of technological nature: the Russianshad never before built tactical guided missiles and had not acquired any experience withmissile guidance systems. A particularly difficult problem was the stipulation by the AirForce that the missile guidance system fit already existing fighter aircraft and thus besmall. Because the OKB-134 did not meet time schedules, the Air Force in early 1966accepted the proposal from the "Zvezda" small Design Bureau at the Kalinin No 455Series Production Plant near Moscow producing K-5, K-8, and other guided air-to-airmissiles. They proposed to build the first tactical air-to-ground missile with ready-madecomponents of air-to-air missiles.What prompted the "Zvezda" OKB to submit its proposal was that it already had certainexperience in using air-to-air missiles against ground targets. Such tests had beenconducted during late nineteen fifties and early nineteen sixties with K-51 (RS-2US)missiles fired from MiG-19PM fighter aircraft. The main results of these tests indicatedthe feasibility of using these missiles against land and sea targets, though not veryeffectively because of the small warhead.The first Soviet tactical air-to-ground missile was built in 1966 and, therefore, called theKh-66 or Article 66. The key design requirement was that it be able to carry a warheadweighing 100 kg (for comparison, the warhead of the K-5 missile weighed 13 kg). Forpropulsion of the Kh-66 missile the propulsion system of the K-8 was used with only asmall modification of the nozzle. The nozzle had to be split in two, because the K-51(RS-2US) guidance system, also used by the Kh-66 missile, was located in the tail. Usingthe old guidance system had many drawbacks but also offered one great advantage,namely that it could be carried by every aircraft previously carrying a K-5 missile withoutmodifications of the aircraft (except for a new attachment underneath the fuselage). Themissile was produced within a few months and in September 1966 began to be testedwith an MiG-21PFM aircraft. Then in 1968 the Kh-66 was officially certified as weaponof MiG-21 aircraft, supported on the center line beneath the fuselage.The Kh-66 missile was a temporary solution and therefore, work on the Kh-23 missilewas not discontinued but transferred from the "Vympel" OKB to the "Zvezda" OKB.Many components of the Kh-66 missile were used for building the Kh-23 and only thetail carrying the Delta-R1M radio-command guidance system had to be altered.Furthermore, the propulsion fuel was replaced with one having a higher energy content.The first ten experimental Kh-23 units were tested in the beginning of 1968. Due todefects, factory testing continued till the end of 1969. The cause of perturbations in themissile guidance could not be determined for quite a long time. Eventually the cause wasfound to be the wrong location of the smoke tracker allowing it to interfere boththermally and mechanically with the antenna of the guidance system. This problem was

solved by placing the tracker on the tail extension of the missile. The aircraft part of theDelta apparatus was installed either permanently on the aircraft (Delta N and Delta NM)or in containers (Delta NG or Delta NG2 systems). After completion of GovernmentQualification tests on MiG-23S and MiG-23B aircraft in autumn 1973, the Kh-23 missilewas in 1974 officially certified as weapon with the Kh-23M (Article 68M) designation.

SpecificationsVersion Kh-66 Kh-23M

Contractor

Entered Service

Total length 3.63 m 2.49 m

Diameter 0.275 m 0.275 m

Wingspan 0.811 m 0.785 m

Weight 278 kg 286 kg

Warhead Weight 103 kg 111 kg

Propulsion single stage solid propellant rocket motor

Maximum Speed 2340 km/h 2900 km/h

Maximum effectiverange 10 km 10 km

Guidance mode beam riding beam riding

Raduga Kh-28 (AS-9 Kyle)Tactical missiles were also built by A. Berezhnyak's "Raduga" OKB engineering group,but by a different route than taken by the "Zvezda" Design Bureau. While "Zvezda"started from light air-to-air missiles, "Raduga" scaled down heavy air-to-ground missilesfor strategic aircraft into light tactical ones.The Kh-28 (Article 93, alias D8) was built by applying to it Kh-22 and KSR-5 features.Its structure is a conventional aerodynamic one, with small delta wings. Its propulsionsystem is a two-stage liquid-fuel rocket engine. It was produced as early as the nineteensixties, especially as an antiradar missile for Yak-28 bomber aircraft (the first Sovietmissile of this type). It was, however, never actually put on Yak-28 aircraft but insteadused as weapon of Su-7B/17/24 and Tu-22M aircraft. Series production of the Kh-28began in 1971. The warhead is programmed prior to the missile launch, either by a"Filin" [Eagle Owl] set on board the aircraft (Su-24) or a "Metel" [Blizzard] setsuspended from the aircraft (Su-7B/17, Tu-22M), to track the frequency of detectedenemy ground radar. On the Su-17 aircraft this missile is suspended under the center lineof the fuselage and the "Metel" set on the right underwing pylon. The missile is no longerused.

SpecificationsContractor

Entered Service

Total length 5.97 m

Diameter 0.43 m

Wingspan 1.93 m

Weight 720 kg

Warhead Weight 160 kg

Propulsion

Maximum Speed 3500 km/h

Maximum effectiverange 120 km

Guidance mode

Single-shot hitprobability

Zvezda Kh-25 (AS-10 Karen)The Kh-23 missile was very difficult to operate. After having been fired, it requiredcontinuous control by the pilot so that the pilot had to view the target image and themissile image as well as the sight screen. The necessity of continuously watching threeimages diverted the pilot from other tasks was very dangerous during combat. Thedistance to the target was, moreover, logged by the pilot manually on the basis of rough"eyesight" estimates and thus with significant errors.Other methods of guidance were sought, therefore, and the use of a laser for targetindication to a guided missile became the choice. Work on this project was carried out bythe "Zvezda" OKB jointly with Sukhoy's engineering group, the system developed bythem being designated as the Su-17MKG (initial plans also included missiles with laserguidance as weapons for Su-7BM aircraft, but the autopilot of these aircraft was weakerand not able to ensure adequate damping of vibrations and thus sufficiently accurateaiming).While the Kh-23 was still being tested, its Kh-25 version (Article 71) was being preparedwith a 24N1 semiactive laser homing head, using light rays reflected by the target upontheir incidence from the first Soviet aircraft laser station ''Prozhektor-1'' (or possibly froma laser station on the ground). The missile was also equipped with an SUR-71 autopilot.Inasmuch as the Kh-25 version did not need a Delta system, instead an additionalwarhead weighing 24 kg to supplement the 113 kg warhead in the front, was placed in itstail section. The "Prozhektor" laser station had been built by the "Geofizika"[Geophysics] SKB (D. Khorol chief engineer). Flight tests of the Kh-25 missile on an Su-17M aircraft, also carrying a "Prozhektor" laser, began toward the end of 1973, afterwhich followed in autumn 1974 Government Qualification tests of the Su-17KMGcomplex. Both Kh-23 and Kh-25 missiles were also tested on Ka-25 and Ka-27helicopters.The experience acquired during work on radio command-guided Kh-23, laser- guidedKh-25, and Kh-25 antiradar missiles was all applied to a new design: of the "Modulnaya"[Modular] Kh-25M missile (Article 71). This one became ultimately the most popularSoviet missile of its class and replaced earlier types. In 1975-76 it was approved forordnance, especially as weapon of the MiG-27, then later also as weapon of almost allother aircraft and also of some helicopters such as Ka-50.The Kh-25M missile is series produced in three versions, all using the same engine,autopilot, warhead, power supply, body with wings, and other components. Only theguidance heads are different. The Kh-25MP antiradar missile (Article 711, NATO's AS-12 Kegler) is similar to the Kh-27PS with an almost identical outer appearance. The Kh-25ML (Article 713, NATO's AS-10 Karen) has a 24N1 laser guidance head and thus thesame one which the Kh-25 has. The Kh-25MR (Article 714, NATO's AS-10 Karen) hasthe guidance head in the nose section replaced by a deflector and a Delta radio command-guidance system in the tail section, just as in the earlier Kh-23M missile. The latestversion of the Kh-25 missile is the Kh-25MTP with a thermal-imaging guidance head.

SpecificationsVersion Kh-25 Kh-25ML

Contractor

Entered Service

Total length 3.57 m

Diameter 0.275 m 0.275 m;

Wingspan

Weight 320 kg 300 kg (Kh-25MP 320kg)

Warhead Weight 136 kg 89.6 kg

Propulsion

Maximum Speed

Maximum effectiverange

range 10 km (Kh-25MP40 km)

Guidance mode

Single-shot hitprobability

Raduga Kh-58 (AS-11 Kilter)The Kh-58U missile (Article 112, alias D7) was built to replace the Kh-28, first of all forSu-24M aircraft, and was then used as basic weapon of MiG-25BM and other aircraft.Target indication and guidance head programming prior to the launch are done by eitheran on-board (Su-24M) "Fantazmagoria" [Phantasmagoria] set or a "Vyyuga"[Snowstorm] set suspended in a container. The probability of hit within a 20 m radiusaround an operating radar station is 80 percent. The Kh-58 version was equipped with anactive radar head.

SpecificationsContractor

Entered Service

Total length 4.80 m

Diameter 0.38m

Wingspan 1.17 m

Weight 640 kg

Warhead Weight 149 kg

Propulsion

Maximum Speed Mach 3.6

Maximum effectiverange 120 km

Guidance mode

Single-shot hitprobability 80%

Zvezda Kh-25MP / Kh-27PS (AS-12Kegler)One of the most important tasks of a tactical air-to-ground missile is breaking through theenemy air defense system by destroying its radar stations. No wonder then that in 1972,immediately after completing both Kh-23 and Kh-25 missiles, the "Zvezda" OKB beganworking on the Kh-27PS (Article 72) missile of the same family with a passive-radarhead. An antiradar missile must have a long range so as to be able to reach radar stationsfrom beyond the range of the air defense artillery. The Kh-27PS was therefore equippedwith a two-range engine so its range could be extended to 60 km by reducing its speedduring the initial flight stage.The passive-radar head of this missile was equipped with two antennas tuned to the radarfrequencies of two most popular Western air defense systems: Hawk and Nike Herculesrespectively. The missile was also equipped with an autopilot enabling it to perform the"hump" maneuver during the final flight stage so as to hit the target at a 20-30[DEG]angle and thus improve the effectiveness of warhead. The Kh-27PS missile worked withthe airborne "Vyyuga" [Snowstorm] set programming the warhead prior to the launch.The missile was arming Su-17 and MiG-27 aircraft. Government Qualification tests on anMiG-27 aircraft were conducted during the 1975-77 period.

Raduga Kh-59 (AS-13 Kingbolt) andKh-59M (AS-18 Kazoo)The Kh-59 missile (Article D9) was for the first time publicly displayed in November1991, in Dubai (United Arab Emirates). This missile is guided by television andpropelled by a powder-fuel engine, with a powder- fuel accelerator in the tail. Its foldingstabilizers are located at the front, while its cantilever wings with rudders are located inthe rear.The Kh-59M missile differs from the original model by having a twice as large warheadand by another propulsion system. Under the missile body has been suspended a smallturbojet engine, the RDK-300 designed by the "Soyuz" [Union] OKB. The missile isbrought up to speed by a powder-fuel accelerator located in the tail section and thencontinues flying propelled by that turbojet engine. Equipped with such a propulsionsystem, the missile has a three times longer range than the Kh-59.Because television guidance has the drawback that the target must be "seen" by themissile, which limits the missile's range of action, the Kh-59M has a dual guidancesystem. After having been fired, the missile is guided by an inertial navigation systeminto the vicinity of the target and then the television camera is turned on for transmissionof images to the receiver on board the missile's carrier aircraft. The transmitter of flight-correcting radio commands (APK-8 for MiG-27K aircraft or APK-9 for Su-24M/30Mand newer aircraft) is mounted in a container which hangs under the aircraft. Thearmament consisting of a Kh-59M missile with such guidance is called Owad [Insect]-M.

SpecificationsContractor

Entered Service 1982

Total length 5.695 m (Kh-59 5,368 m)

Diameter 0.38 m

Wingspan 1.26 m

Weight 930 kg (Kh-59 760 kg)

Warhead Weight315 kg with penetrating ammunition or280 kg with fragmenting ammunition(Kh-59 147 kg)

Propulsion

Maximum Speed 285 m/s

Maximum effectiverange 115 km (Kh-59 40 km)

Altitude 7 m above water or100, 600, 1000 m above ground

Guidance mode TV-guide

Carried by Su-24M, Su-34

Molniya (AS-14 Kedge)This is the only missile of the air-to-ground class which has been designed by MatusBisnovat's "Molniya" [Lightning] Design Bureau, which specializes in air-to-air missiles.It was developed in the middle nineteen seventies for MiG-27, Su-17, and Su-24 (Fencer)aircraft. It was later also installed on other aircraft. It is used chiefly against heavilyreinforced targets (almost half its weight is the warhead). It is supported on AKU-58launcher pylons, from which it is dropped down before its engine starts. The Kh-29L(Article 63) is an improved version of the Kh-29, with semiactive laser guidance. A targetcan be illuminated from the delivery aircraft or from another aircraft or from the ground.The Kh-29T (Article 64) has a television head with automatic optical homing to adistinguishable object indicated by the pilot in the cockpit. The Kh-29D version with athermal- imaging head is also on the list of Russian export items.

SpecificationsContractor

Entered Service 1980

Total length 3.875 m

Diameter 0.38 m

Wingspan 0.78 m

Weight 657 kg (Kh-29T 680 kg)

Warhead Weight 317 kg

Propulsion

Maximum Speed 600 m/s

Maximum effectiverange 8-10 km

Guidance modeKh-29L (Article 63)semiactive laserKh-29T (Article 64) televisionKh-29D thermal-imaging

Platform Su-17M3, Su-25T, MiG-27M, Su-24M, Su-34, MiG-33, Su-35

Kh-55 GranatAS-15 KentSS-N-21 SampsonSSC-4 SlingshotThe Kh-55 strategic cruise missile is used for destroying targets whose coordinates areknown. Its guidance system combines inertial-Doppler navigation and position correctionbased on comparison of terrain in the assigned regions with images stored in the memoryof an on-board computer. The propulsion system is a dual-flow engine locatedunderneath the missile's tail. The missile carries a 200 kt nuclear warhead.

The first tests of this missile were conducted in 1978 and a few units were installed onTu-95MS aircraft in 1984. Three aircraft versions of this missile are known: Kh-55(Article 120, alias RKV-500, NATO's AS-15a), Kh-55-OK (article 124), Kh-55SM(Article 125, alias RKV-500B, NATO's AS-15b). In addition the land version RK-55(SSC-X-4) was destroyed in compliance with INF disarmament negotiations. The seaversion SS-N-21 Sampson is reportedly deployed on the Akula, Victor III, YankeeNotch, and Sierra class SSN submarines. However, since the SSC-4 coastal defensevariant is carried in a 25.6-in (650-mm) diameter canister, some analysts have suggestedthat the sub- launched variant is probably for launch only from 650-mm diameter torpedotubes.

Russian President Boris Yeltsin announced in January 1992 that he would end themanufacture of all sea- and air- launched cruise missiles. In March 2000 it was reportedthat the Russian Air Force had tested a new cruise missile with a conventional warhead. Itwas said to be a Kh-555 missile, which was developed from the Kh-55, with a range of2000 - 3000 km.

Raduga Kh-65The Kh-65 missile is a tactical modification of the strategic Kh-55. According to the firstavailable information (on data sheets at the 1992 Moscow Air Show), its range was to be500-600 km. The reason for shortening its range was that, according to terms of theSALT-2 Treaty, any aircraft carrying missiles with a range longer than 600 km will beregarded as a strategic one and the number of such aircraft is strictly limited. A full-sizedversio of the Kh-65SE was displayed for the first time in 1993 (February in Abu Dabi,then September 1993 in Zhukovskiy and Nizhniy Novgorod). The missiles shown at theexhibitions did not differ from the earlier versions except for their range, quoted as 250km when launched from low altitude and 280 km when launched from high altitude. TheKh-65 was intended for use against large targets with a larger than 300 m2 effectivereflecting surface area, particularly warships, under conditions of strong electronicinterference. It approaches the target guided by an inertial navigation system while flying

at a low altitude. Having reached the region where the target is located, it rises to a higheraltitude and its active-radar target seeking system turns on.

SpecificationsVersion Kh-55SM Kh-65SE

ContractorRaduga OKBM. I. Kalinin MachineBuilding Plant

Entered Service

Total length 8.09 m 6.04 m / 19 ft, 6 in

Diameter 0.77 m; (Kh-55 0.514 m) 0.514 m

Wingspan 3.10 m 3.10 m / 10 ft, 1 in

Weight 1700 kg 1250 kg

Warhead 200-kt nuclear 410 kg HE

Propulsion

Speed Mach 0.48-0.77 Mach 0.48-0.77

Maximum effectiverange

3000 km (Kh-55 2500km) 250-280 km

Flight Altitude 40-110 m

Guidance mode

AS 15 Mod ARKV-500A

ALCM

AS 15 Mod BRKV-500B

ALCM

Raduga Kh-15 (AS-16 Kickback)The Kh-15 short-range attack missile is analogous to the the American AGM-69 SRAM.Its basic version is the Kh-15P (Article 115) antiradiation missile used for breakingthrough air defenses. Its Kh-15A anti-ship version (exhibited in Abu Dabi 1993 as theKh-15S) has an inertial navigation system for the initial flight stage and a millimetric-wave active-radar self-homing system for the final flight stage. During its initial flightstage the Kh-15 missile, using a solid-fuel, rises to an altitude of about 40,000 m,whereupon the target seeking radar turns on. Having been zeroed in on the target, themissile dives while accelerating to a speed of Mach 5.

SpecificationsContractor

Entered Service

Total length 4.78 m

Diameter 0.455 m

Wingspan 0.92 m

Weight 1200 kg

Warhead Weight 150 kg

Propulsion

Maximum Speed Mach 5

Maximum effectiverange 150 km

flight altitude 40 km

Guidance mode

Single-shot hitprobability

Zvezda Kh-31 (AS-17 Krypton)New air defense weapon systems of the American Patriot kind have raised therequirements which antiradar missiles must meet. These include first of all higher speedand longer range, then also high interference immunity and radar turn-off when attacked.For the special purpose of meeting these requirements, the "Zvezda" group under thedirection of V. Bugayskiy began in 1977 working on the Kh-31 missile (Article) 77P).The first launchings of this missile took place in 1982.The most interesting component of the Kh-31P is its dual propulsion system designed bythe "Soyuz" Design Bureau in Turayevo near Moscow (note: there are several "Soyuz"engineering groups in Russia). First the missile is accelerated by its solid-fuel rocketengine to a speed of Mach 1.8, then the engine is discarded and the interior of the missileis converted into the combustion chamber of the missile's jet engine. The latteraccelerates the missile to a speed of almost Mach 4.5, while four air intake holes on thesides of the missile body open up. On the basis of the Kh-31P antiradar missile weredeveloped the Kh-31A missile (Article 77A) with an active-radar guidance head and alsoan M-31 flying target for air defense training exercises. The Kh-31 was for the first timepublicly displayed in November 1991, in Dubai (United Arab Emirates).The State Scientific Production Center Zvezda-Strela has upgraded the air-to-surfacesupersonic ASM Kh-31A NATO: AS-17 Krypton). Recently a variant of the air-to-airclass based on the Kh-31 was made available, equipped with a hybrid active-passiveguidance head for use against nonmaneuvering airborne targets such as AWACS (passiveguidance) from far distances. The range of this missile is 200 km. The unofficialdesignation of this missile is 'mini-Moskit'. The Kh-31A missile has been developed fromthe technologies of the 1970-80s.

SpecificationsContractor

Entered Service

Total length 5.232 m

Diameter 0.36 m

Wingspan 0.779 m

Weight 600 kg

Warhead Weight 90 kg

Propulsion

Maximum Speed 1000 m/s

Maximum effectiverange 70 km (Kh-31P 110 km)

Guidance mode Active Radarhoming

Carried by

P-750 GromBL-10AS-19 KOALASS-N-24 SCORPIONSSC-5The P-750 Grom supersonic winged cruise missile with a range of 3000-4000 km wasdeveloped for replacing the Kh-55 [AS-15 KENT]. The AS-X-19 Koala was an air-launched land-attack version derived from the SS-NX-24 Scorpion submarine-launchedmissile. A pair of AS-19 missiles was expected to arm the Tu-142 Bear-H bomber. Themissile carried two warheads independently guided to hit two targets 100 km apart. Theletters BL in its American designation refer to the firing range in Barnaul, where it wastested; its Russian industrial index designation is not known. Work on the program wassuspended in 1992.

SpecificationsContractor Chelomey

Entered Service cancelled

Total length 7 meters

Diameter

Wingspan

Weight 2,000 kg

Warhead 2 x 200 kt nuclear

Propulsion turbojet or rocket/ramjet

Maximum Speed supersonic

Maximum effectiverange

Guidance mode 3000-4000 km

Zvezda Kh-35AS-20 KayakSS-N-25 SwitchbladeSSC-6 SwitchbladeIn 1972 the Zvezda-Strela State Scientific-Industrial Center (GNPTs) group beganworking on the Uran (Western SS-N-25) anti-ship missile system - also commonly calledKharpunskiy because of its similarity to the American Harpoon - for ships of variousclasses. The Kh-35 antiship cruise missile can be used by surface ships and motor boats,coastal reconnaissance/strike systems, naval helicopters and also by Air Force planes.The Uran missile systems comprise 16 Kh-35 missiles - 4x4 launchers with pressurisedtransport-launching containers. The Uran system now serves as armament of Project1149.8 missile equipped gun boats and other vessels. A coastal defense variant and, morerecently, an antiaircraft variant were later developed on the basis of this missile.The Kh-35 missile has a normal aerodynamic design and an aluminium-alloy airframe.The missile's power plant consists of a solid-fuel booster and a turbojet powerplant. Themissile's take-off weight is 750 kilograms, the warhead weighs 150 kilograms with arange of up to 130 kilometres. The Kh-35U anti-ship aircraft missile (Article 78U),propelled by a turbojet engine, flies toward its target at a speed of about the 300 m/s at anextremely low altitude. Owing to its high-precision radio-altimeter, the missile can skimthe sea waves at an altitude of 3-5 metres at the terminal phase of trajectory. Its guidancesystem combines inertial guidance for during the initial flight stage and active-radarguidance during the remaining flight stage. The missile has a folding wing and a foldingtail fin.For use by coastal or shipborne launchers the missile is equipped with a rocket starter-accelerator, a container-type launcher having room for four missiles.The air-launched AS-20 Kayak version was scheduled to become part of ordnance in1994. The Kh-35U is intended to serve as weapon of practically all tactical naval aircraft,also of ZOP on the Tu-142 long-range aircraft (eight missiles on two positions, four perposition, under the wings) and carrier-based Ka-27 helicopters (four missiles).Also available is an IC-35 flying target simulator for training a ship's air defense team indestroying missiles of this class. The "Zvezda" product line includes a variant of the Kh-35 missile which operates with thermal-imaging rather than radar guidance during thefinal flight stage.

SpecificationsContractor

Entered Service 1983

Total length 3.75 m

Diameter 0.42 m

Wingspan 0.93 m

Weight 480 kg [630 kg with booster]

Warhead Weight 145 kg

Propulsion

Maximum Speed 300 m/s

Maximum effectiverange 130 km

Guidance mode Active Radarhoming

Platforms Ka-28, MiG-33, Yak-141

AFM-L Alfa3M-51 Alfa P-900The P-900 Alfa [industrial code 3M-51 ] is a version of the Granat [SS-N-19SHIPWRECK] carrying a supersonic [Mach 2.5] final attack stage. There is someconfusion as to whether the SS-N-27 designation applies to this missile, or to the Klub[industrial code 3M-54, also known as Alfa] , although the best evidence suggests that the3M-54 Alfa is the SS-N-27, rather than the 3M-51 Alfa.

The first information about the Alfa or officially AFM-L air-to-water missile built by theScientific-Industrial Association "Mashinostroyeniye" [Machine Construction] (formerlyV. Chelomey's Special Design Bureau since 1984 directed by G. Yefremov) was given atthe Abu Dabi exhibition in February 1993, and in August 1993 a full-size model of thisnew missile was displayed in Zhukovskiy. It has a folding wing and four stabilizers aft.During the first flight stage, covering about 200 km, the missile is propelled by a turbojetengine and flies at a subsonic speed of 220-240 m/s approaching the target, whereupon arocket engine kicks in which accelerates it to 700 m/s.

NPO Mashinostroenie continues the development of the Alfa universal supersonic cruisemissile that can be adopted for service in five to six years. The missile is being developedin submarine, ship, air and coastal-launched variants. As an airborne variant, Alfa willfirst join the armament options for the Su-34 or Su-32FN (NATO: Flanker) attackaircraft. The ship, submarine and coastal-launched variants of the Alfa have take-offweight of 2,600 kg (5,730 lb.) and warhead weight of 300 kg. (661 lb.). The Alfa air-launched variant has take-off weight of 1,600 kg. (3,527 lb.). With the exception of theairborne variant, the missile is fired from a standard transport-launching container (TLC).

SpecificationsContractor NPO Mashinostroyeniye

Entered Service Under Development

Total length 8.0 m

Diameter

Wingspan

Weight2,600 kg (5,730 lb.) ship, submarine and coastal-launched variants1,600 kg. (3,527 lb.) air-launched variant

Warhead Weight 300 kg. (661 lb.)

Propulsion Turbojet + Rocket

Maximum Speed Cruise Subsonic,

Attack Mach 2.5 - 700 m/s

Maximum effectiverange 250 km

Guidance mode Active Radar

Single-shot hitprobability

MoskitSS-N-22 SunburnMoskit is the aircraft variant of the naval missile 3M80 (SS-N-22 Sunburn, thedesignation 3M80 apparently referring to the Mach 3 speed of 1980 weapons) used on"Sovremennyy" destroyers (eight missiles on each) and on "Tarantul [Tarantula] IIIpatrol ships (four missiles on each). The 3M82 "Mosquito" missiles have the fastestflying speed among all antiship missiles in today's world. It reaches Mach 3 at a highaltitude and its maximum low-altitude speed is M2.2, triple the speed of the AmericanHarpoon. When slower missiles, like the French Exocet are used, the maximumtheoretical response time for the defending ship is 150-120 seconds. This provides time tolaunch countermeasures and employ jamming before deploying "hard" defense tacticssuch as launching missiles and using quick-firing artillery. But the 3M82 "Mosquito"missiles are extremely fast and give the defending side a maximum theoretical responsetime of merely 25-30 seconds, rendering it extremely difficult employ jamming andcountermeasures, let alone fire missiles and quick-firing artillery.

The aircraft version, officially called ASM-MMS and apparently also Kh-4, is intendedspecially for Su-27K (Su-33) carrier-based fighter aircraft. It was for the first time shownto the CIS leaders in February 1992 in Machulishche and then to the public in August1992 at the Moscow Air Show in Zhukovskiy.

The missile is propelled by a dual (rocket-jet) engine operating by the same principle asthe Kh-31 engine. The missile, suspended under the aircraft, has a folding wing. Themissile is guided by an autopilot during the initial fight stage, with possible correction bythe aircraft pilot, and by active radar during the final flight stage.

SpecificationsContractor

Entered Service

Total length 9.745 m

Diameter

Wingspan 2.10 m

Weight 4500 kg

Warhead Weight 320 kg

Propulsion

Maximum Speed Mach 3

Maximum effectiverange 250 km

Flight Altitude 20 meters above sea level

Guidance mode active radar

Single-shot hitprobability

3M55 OniksP-800 YakhontP-800 BolidSSN-X-26The supersonic P-800 Yakhont (Gem) is a ramjet version of P-80 Zubr [SS-N-7Starbright]. The ship, submarine and coastal-launched Yakhont is launched from theunified ampoule-shaped transport-launching container (TLC). The container is 9 m long,is 0.71 m in diameter. The firing range reaches 300 km (162 nmi.) when flying along acombined trajectory and 120 kg (265 lb.) when following only a low-altitude trajectory.Flight speed varying over the range from M=2.0 to M=2.5 is provided by the kerosene-fueled multi-mode liquid-fuel ramjet. The P-800 Bolid is the encapsulated, submarinelaunched version of Yakhont. An air-launched version of the missile with the take-offweight of 2,500 kg (5,507 lb.) is also being developed. The closest Americancounterparts, the Tomahawk and Harpoon missiles, are subsonic; the best French antishipmissile, the Exocet, has a range of only 45 miles.

SpecificationsCountry of Origin Russia

Builder Beriev

Role Amphibious anti-submarine patrol aircraft

Range 300 km mixed trajectory120 km low trajectory

Speed Mach 2 to 2.5

Flight altitude 5 to 15 meters, final phase

Weight of warhead 200 kg [about]

Guidance active-passive, radar seeker head

Minimum targetdetection range 50 km in active mode

Maximum seekerhead search angle

45 degrees

Propulsion solid propellant booster stageliquid-propellant ramjet sustainre motor

Launcher type underwater, surface ship, land

Launch method from closed bottom launch-container

Launch angle range 15 to 90 degrees

Weight 3,000 kg launch3,900 kg in launch-container

Launch-containerdimensions

8.9 meters length0.7 meters diameter

FROG-1 3R-1, FilinThe Russian The FROG-1 [ Free Rocket Over Ground] and FROG-2 were the earliest ofthe Soviet large free rockets. FROG-1 can be distinguished by its large, bulbous nose andby the large transporter-launch vehicle based on the JS heavy tank chassis. FROG-2 is asmaller rocket, also with a bulbous nose, but transported by and launched from a light-tracked vehicle derived from the PT-76 tank chassis. Both FROG-1 and FROG-2 areconsidered obsolete today and are no longer in first line units.

FROG-2 3R-2, MarsThe Russian The FROG-1 [ Free Rocket Over Ground] and FROG-2 were the earliest ofthe Soviet large free rockets. FROG-1 can be distinguished by its large, bulbous nose andby the large transporter-launch vehicle based on the JS heavy tank chassis. FROG-2 is asmaller rocket, also with a bulbous nose, but transported by and launched from a light-tracked vehicle derived from the PT-76 tank chassis. Both FROG-1 and FROG-2 areconsidered obsolete today and are no longer in first line units.

FROG-3 R-9, LunaFROG-4 LunaFROG-5 3R-10, Luna-1The Russian FROG-3 [Free Rocket Over Ground], FROG-4, and FROG-5 are threevariants of a single unguided, spin stabilized, solid fuel rocket. The system requires about30-40 minutes to prepare missile for firing and about 60-70 minutes to reload. Therockets are transported on and launched from the same basic light-tracked chassis derivedfrom the PT-76 tank. This chassis can be distinguished from that of the FROG-2transport-launch vehicle by the presence of track support rollers. The rockets areidentical, differing only in the size and shape of the warheads. Although still encounteredin some armies, this series of FROG'S was replaced by FROG-7 which is carried on andlaunched from a wheeled vehicle.

SpecificationsContractor

Entered Service

Total length

Diameter

Wingspan

Weight

Warhead Weight Up to 800lbs

Propulsion

Maximum Speed

Maximum effectiverange 10,000 to 61,000 m

Guidance mode unguided, spin stabilized

FROG-3

FROG-4

FROG-5

FROG-6The Russian FROG-6 [Free Rocket Over Ground] is a dummy rocket used for trainingpurposes. It is transported on a specialty modified ZIL-157 (6?6) truck chassis.

FROG-7A (3R-11, 9K21, 9M21, R-65)FROG-7B (9K52, 9M52, R-70), Luna-MThe FROG-7 is the latest addition to the "Free Rocket Over Ground" family of unguided,spin-stabilized, short-range (battlefield support) artillery rockets. The rocket is ofconventional single-stage design, with a cylindrical warhead of the same diameter as therocket body, giving it a cleaner, more modern appearance than its predecessors. TheFROG-7 has a range of 70 km and a 550 kg warhead, and an impact area ofapproximately 2.8 km long by 1.8 km wide. The FROG-7 is capable of delivering HE,nuclear, or chemical warheads. The FROG-7 gave the Soviet division commander a deepinterdiction/penetration nuclear threat.

The FROG-7A was first introduced in 1965 as a replacement for earlier FROG variants,some of which had been in service since the mid-1950s. The FROG-1 and -2 areobsolete. The FROG-3, -4, and -5 variants, mounted on a non-amphibious version of thePT-76 light tank chassis, are obsolete in the USSR, but were still found in other WarsawPact armies at the end of the Cold War. The FROG-5 is still used as a training rocket, andthe FROG-6 is a dummy rocket used for training purposes only. The FROG-7B,introduced in 1968, is essentially the same rocket as the FROG-7A but with a longerwarhead section.

The FROG-7 was replaced by the SS-21 tactical ballistic missile which has greater range(120 km) as well as probable improvements in reaction time, missile reliability, accuracy,and handling characteristics. Since the SS-21 is mounted on a six-wheeled TEL similar tothe SA-8/GECKO SAM system, it has improved cross-country capability and is probablyamphibious. Like the SA-8, it probably has an air filtration and overpressure system for-collective chemical and biological protection. The SS-21 was first deployed in 1976 inthe USSR and was reported in GSFG in 1981.

During the Cold War the most prominent short-range nuclear force [SNF] system at at thedivision level was the unguided free-rocket-over-ground (FROG), which in the SovietArmy was deployed in a battalion of four launchers. As of 1987 the Soviets werereplacing FROGs with the more accurate, longer range SS-21s in some divisions oppositeNATO. About 500 FROG and SS-21 launchers were opposite NATO. Another 215FROG launchers were opposite China and in the Far East; some 100 were oppositeSouthwest Asia and eastern Turkey; and about 75 were in strategic reserve. Non-nuclearversions of the FROG-7 have been exported to both Warsaw Pact and some non-WarsawPact nations. The FROG-7 is deployed by Cuba, Egypt, Iraq, Kuwait, Libya, NorthKorea, Syria, and Yemen. Laith, an Iraqi improved version of the FROG-7, has a 90 kmrange.

The FROG-7 (9K52 Luna), the final version of the FROG family, is an unguided, spin-stabilized, short-range, battlefield support artillery rocket. The range of the FROG-7Arocket is 70 km with a CEP of 500 to 700 meters. It is fitted with either a 450 kg HE, 450

kg nuclear, or 36 kg chemical warheads. The improved FROG-7B carries a cargowarhead for delivering bomblets or mines.

In addition to improvements in the rocket which give it greater range, a new transport-launch vehicle using a wheeled chassis has been developed based on the ZIL-135 [BAZ-135] 8x8 truck. This wheeled transporter erector launcher (TEL) carries one rocket and acrane. It incorporates a number of improvements in rocket handling such as the on-boardcrane. Reload missiles are placed on the TEL by that vehicle’s own hydraulicallyoperated crane on the right side of the launcher rail. A very similar vehicle is also usedwith the FROG-7 system to transport the reserve rockets. The earlier FROG'S usedsemitrailers towed by ZIL-157V tractor trucks, and needed crane trucks for reloading ofthe transport-launch vehicles. Preparation for firing can take 15 to 30 minutes dependingon the situation. A typical FROG-7 battalion is equipped with two firing batteries eachwith two TELs and a D-band RMS (END TRAY) long-range meteorological radar. Thecruising range of the transporter-erector-launcher vehicle is 400 km. The FROG-7 TELvehicle provides no NBC protection for the crew. The single-rail launcher has limitedtraverse.

SpecificationsContractor

Entered Service

Total length

Diameter

Wingspan

Weight

Warhead Weight 550 kg

Propulsion

Maximum Speed

Maximum effectiverange

70 km

Guidance mode ballistic

Accuracy 145 It has an impact area of approximately 2.8 kmlong by 1.8 km wide

Users CIS, Cuba, Egypt, Iraq, Kuwait, Libya, North Korea,Syria, Yemen

SS-21 SCARAB (9K79 Tochka)The SS-21 SCARAB (9K79 Tochka) single-stage, short-range, tactical-ballistic missile istransported and fired from the 9P129 6x6 wheeled transporter erector launcher. It issupported by a tactical transloader (9T218) and a 9T238 missile transporter trailer towedby a ZIL-131 truck. The 9P129 TEL crew compartment is in the forward section and themissile compartment behind. During transport the missile is enclosed with the warhead ina temperature-controlled casing.

The SS-21 SCARAB missile (9M79) has a maximum range of 70 km and a CEP of 160meters, while the improved composite propellant 9M79-1 (Tochka-U) has a maximumrange of 120 km. The basic warhead is the 9N123F HE-Frag warhead which has 120 kgof high explosives. The 9N123K submunition warhead can probably carry eitherbomblets or mines. The SS-21 can also carry the AA60 tactical nuclear warhead. Otherwarheads are believed to include chemical, terminally guided warhead, and a smart-munition bomblet warhead. In 1981, the SS-21, a guided missile (providing improvementin both range and accuracy), began replacing the FROG in forward-deployed divisions,and 140 are were deployed as of 1988. Division-level SS-21 battalions were beingconsolidated into brigades in Soviet armies in East Germany.

On 21 October 1999 US satellites [reportedly the Defense Support Program] tracked twoRussian short-range ballistic missile launched from the Russian city of Mozdok some 60miles northeast of Grozny. The missiles slammed into a crowded Grozny marketplaceand a maternity ward, killing at least 143 persons, according to reports from the region.The missiles are believed by intelligence analysts to have been SS-21s.

SpecificationsUSA Code Name SS-21

Nato Code Name: Scarab

Russian Designation: 9K79

Range: 120 Km

Stages: 1

Fuel: Solid

Inservice: Current System

Notes: Replacement for FROG -7 System. Very Mobile

Contractor

Entered Service

Total length

Diameter

Wingspan

Weight

Warhead Weight

Propulsion

Maximum Speed

Guidance mode

Single-shot hitprobability

SS-N-2 StyxHY-1 / SY-1CSS-C-2 SILKWORMFL-1 Flying DragonCSS-N-1 SCRUBBRUSHChina acquired the Russian SS-N-2 Styx missile technology in 1959, and productionbegan in 1974. The Russian SS-N-2 was used in 1967 against Israel by Egypt, in 1971 byIndia against Pakistan, and by Iran during its 1980-88 war with Iraq. Chinese copies ofthe Styx design (CSS-C-2 Silkworm and CSS-C-3 Seersucker) coastal defence missilesand the ship launched CSS-N-1 and CSS-N-2 were used by both sides in the Iraq-IranWar

Technological improvements to the C-801/SARDINE and the C-802/ SACCADE areproviding a gradual upgrade to China's current force of antiquated first generation CSS-N-1 SCRUBBRUSH ASCMs. It was reported in 1996 that Iran had begun indigenousproduction of a medium-range antiship missile, the FL-10, based on the Chinese FL-2 orFL7 and developed with Chinese technical assistance.

SpecificationsContractor

Entered Service

Total length 5.8 meters

Diameter o.76 meters

Wingspan 2.4 meters

Weight 2,300 kg

Warhead Weight 454kg HE hollow charge

Propulsion

Maximum Speed

Maximum effectiverange

80 km

Guidance mode Auto pilot, Active radar

Single-shot hitprobability

P-350 Bazalt 4K-77P-500 Bazalt 4K-80SS-N-12 SandboxSS-N-12 Sandbox is a Russian supersonic speed cruise missile with a range of 550 kmcarrying a payload of 1,000 kg. The P-350 Bazalt [industrial code 4K-77] was thesuccessor to the P-35 Bazalt, which was started in 1963 and subsequently cancelled. Itevolved into the P-500 Bazalt [industrial code 4K-80] which was the production versionof the original P-350 Bazalt. Developed to replace the SS-N-3 Shaddock anti- shipmissile, it was initially deployed on Kiev-class aircraft carriers in the mid-1970s. TheSlava-class cruisers carry an advanced version with an improved sophisticated guidancesystem, an autopilot that can be programmed for mid-course maneuvers, and an enhancedengine. The P-700 Granat [SSN-19 Shipwreck] was developed as a more successfulturbojet alternative to the SSN-12 Sandbox, from which it was derived.

SpecificationsContractor Chelomey

Entered Service 1973

Total length 11.70 meters

Diameter 0.90 meters

Wingspan 2.60 meters

Weight 5,000 kg

Warhead 1,000 kg high-explosive or350 kiloton nuclear

Propulsion liquid-fueled rocket[turbojet according to some sources]

Maximum Speed Mach 2.5

Maximum effectiverange 550 km

Guidance modemid-course missile guidance radar on lamuchplatformactive or passive terminal homing

Circular ErrorProbable (CEP) 300-700 m

SS-N-14 SilexRPK-3 Metel / RPK-4 MussonSS-N-14 Silex is a Russian anti-submarine weapon. It was initially and incorrectly giventhe SS-N-10 designation. There is also an ASuW(SSM) version where a homing head ismounted on the nose of the carrier and the torpedo is replaced by a warhead- the wholemissile is then guided onto the target. it uses UPRK-3, UPRK-4 or UPK-5 missiles.

SpecificationsUSA Code Name SS-N-14

Nato Code Name Silex

Russian Designation RPK-3 Metel / RPK-4 Musson

Range 55 Km

Propulsion Solid Rocket

Speed Subsonic

In-service: Yes

Guidance Command

SS-N-15 StarfishRPK-2 ViyogaThe SS-N-15 (Starfish) is a Russian 533 mm calibre anti-ship missile capable of beingfitted with a 10-20 kT warhead or a Type 40 torpedo, and has a range of 37-45kilometers. The SS-N-15 Starfish ASW has a range of 45-50 kilometers. This nonstrategic weapon was deployed in 1973. It uses the 82R torpedo or 90R nuclear depthcharge missile.

SpecificationsUSA Code Name SS-N-15

Nato Code Name Starfish

Russian Designation Tsakra / RPK-2 Viyoga

Range 45 Km

Design Bureau Novator

Propulsion Solid Rocket

Speed Subsonic

In-service: Yes

SS-N-16 StallionThe SS-N-16 (Stallion) is a Russian 650mm calibre anti-ship missile capable of beingfitted with a 10-20 kT warhead or a Type 40 torpedo. The SS-N-16 Stallion ASW systemwas deployed in 1979-1981. This non strategic weapon has a range variously estimated atbetween 50 kilometers and 100-120 kilometers. The SS-N-16 concept is a unique antishipcruise missile that can carry alternatively a high-explosive charge to destroy surface shipsor a torpedo for use against submarines. This type of weapon can be used by surfaceships or submarines, as with the American AGM-84 Harpoon, although they are notequivalent. The diameter of this type of missiles is so large that it must be launched from650 mm tubes, and cannot be carried in the standard 533 mm torpedo tubes. The RPK-6Vodopod is the surface ship system, firing the 83R torpedo carrying or 86R nuclear depthcharge, while the RPK-7 Vodopei is the submarine system.

SpecificationsUSA Code Name SS-N-16A - Torpedo Warhead

SS-N-16B - Nuclear Depth Charge

Nato Code Name Stallion

Russian DesignationRU-100 Veter ( Torpedo Warhead - Type 40)RU-100 Vodopod ( Nuclear Depth Charge -200kT)

Design Bureau Novator

Range 100 Km

Propulsion Solid Rocket

Speed N/A

In-service: Yes

P-700 3M-45 GranatSS-N-19 SHIPWRECKThe P-700 Granat [SSN-19 Shipwreck] was developed as a more successful turbojetalternative to the SSN-12 Sandbox, from which it was derived. Developed in the 1970's,the Shipwreck's initial employment was on the battle cruiser Kirov (later renamedAdmiral Ushakov). The Shipwreck was subsequently deployed on the nuclear poweredcruiser Peter the Great. It is also deployed on submarines, which can launch the missilewhile submerged.

SpecificationsContractor Chelomey

Entered Service

Total length 10 meters

Diameter 0.85 meters

Wingspan

Weight 7,000 kg

Warhead 750 kg conventional high explosive or500 kiloton nuclear warhead

Propulsion 2 solid-fuel boosters1 turbojet sustainer engine

Maximum Speed supersonic

Maximum effectiverange 625 km

Guidance mode inertial with command update, active radar/IR andanti-radar homing

Single-shot hitprobability

3M-54 KlubSS-N-27The Novator Design Bureau developed the Club anti-sub/ship cruise missile system[sometimes referred to as the Klub, Biryuza and Alpha/Alfa]. There is some confusion asto whether the SS-N-27 designation applies to this missile, or to the P-900 Alfa[industrial code 3M-51 ] , although the best evidence suggests that the 3M-54 Alfa is theSS-N-27, rather than the 3M-51 Alfa.

The Club missile system is designed to destroy submarine and surface vessels and alsoengage static/slow-moving targets, whose co-ordinates are known in advance, even ifthese targets are protected by active defences and electronic countermeasures.

There are two 'known' modifications of the system; Club-S (for submarines) and Club-N(for surface vessels). The Club-N can be installed in vertical launch cells or in angledmissile boxes. Both systems are based on common hardware, the only difference beingthe design of the missile launchers and missile transport-launching containers.

Five types of missiles - 3M-54E, 3M-54E1, 3M-14E, 91RE1 and 91RE2 - have beendeveloped for the Club ASCM. The Club-S can be armed with a 3M-54E or 3M-54E1anti-ship missile, 3M-14E submarine-to-coast missile or a 91RE1 anti-submarinetorpedo. The Club-N can be armed with a 3M-54E or 3M-54E1 anti-ship missile, 3M-14E submarine-to-coast missile or a 91RE2 anti-submarine torpedo.

The missile is 6.2 meters long, which is the same as the length of the standard torpedotubes used by Western navies. It is designed according to the double-stage cruise scheme.The first solid-fuel stage ensures the missile's launch from a universal vertical launcher ofa surface craft or from a submarine torpedo tube with a diameter of 0.533 meters.

The 3M-54E missile has a range of 300 km. For the majority of its trajectory it flies at ahigh subsonic speed. The first stage drops off when the missile reaches the prescribedaltitude and its second stage sustainer engine goes into action. This is the time when themissile's wing and tail assembly unfold. The altitude of its flight goes down to 10-15metres above the sea surface and the missile heads towards the target in accordance withthe target designations, fed before the start into the memory of its board guidance system.The targeting on the cruise sector of the trajectory is effected by an inertia navigationsystem. The end sector of the missile's flight with the homing head active proceeds onlyfive metres above the water surface. At 60 km from its target the third, solid-fuel stageseparates from the missile, accelerates to supersonic speed and overcomes the defencezone of the target vessel

In spite of its relatively small launch weight of 1,570 kilograms, the missile has a rangeof 300 kilometres and a powerful 450-kilogram warhead, which can blow up very large

surface craft. The missile's moderate weight allows even warships with a smalldisplacement to take aboard quite a few of such deadly weapons.

India is making substantial purchases of the Novator 3M-54 Alfa missile to equip Kiloclass submarines and its new frigates. The first two Indian 877YeKM submarines (Kiloclass, according to NATO classification) will be armed with the latest Russian 3M-54Eantiship cruise missiles. These missiles will also be fitted onto three frigates which arebeing built to order for the Indian navy at the Baltic shipyard in St Petersburg. Each ofthe frigates will carry eight antiship missiles which will be launched from vertical launchcontainers on the bow of the ship.

It is believed that an air-launched variant will be purchased to arm the Tu-142s currentlyin service and the six to eight additional aircraft being sought by the Navy. If an air-launched version of the Alfa is procured, it is anticipated that India's Tu-22M3s willeventually be equipped to fire them.

Specifications- 3M-54E 3M-54E1 3M-14E 91RE1 91RE2

Length [m] 8.22 6.2 6.2 8.0 6.5

Diameter [m] 0.533 0.533 0.533 0.533 0.533

LaunchWeight [kg]

2,300 1,780 1,780 2,050 1,300

MaximumRange [km]

220 300 300 50 40

Speed [Mach] Dependson flightmodeSubsonicMode:Mach 0.6 -0.8,SupersonicMode:Mach 2.9

0.6 - 0.8TerminalStageSpeed forthe 3M-54E1

0.6 - 0.8TerminalStageSpeed forthe 3M-14E

2.5BallisticStageSpeed forthe 91RE1

2.0BallisticStageSpeed forthe 91RE2

WarheadWeight [kg]

200 400 400 76 76

ControlSystem

Inertial +ActiveRadarHoming

Inertial +ActiveRadarHoming

Inertial Inertial Inertial

Flight Path Low-Flying

Low-Flying

Ballistic Ballistic Ballistic

RPK-9 MedvedkaSS-N-29The RPK-9 Medvedka [SS-N-29] is similar to the American ASROC-like torpedocarrying rocket for small ships. The MEDVEDKA Missile System is intended to engagehostile submarines and can be installed at surface ships. It has no analogies in terms ofpotential installation on small ships. The system can be used in shallow water. Thesystem comprises missiles each with the small torpedo as the warhead, launchers*intended for single and ripple missile launches, the fire control system to provide targetmovement parameters, data for single and ripple firing, output and transmission of launchand flight data, and ground support facilities to store and maintain the system at depots,bases, arsenals, and mobile basing posts. The system can be modified and suited forinstallation on customer's operational ships to provide inclined or vertical launch onrequest. The basic variant of the system comprises two four-tube launcher modules.Modular design makes it possible to install one/two/four launcher modules to configurecustomised system variants comprising from one to eight launchers at customer's request.

Specifications

Nato Code Name

Russian Designation

Range 0- 20,000 meter15-500 meters Target engagement depth

Design Bureau

Propulsion Solid Rocket

Speed Subsonic

In-service: Yes

Total weight12,000 kg shipboard system with four missiles19,400 kg Total weight of system with eightmissiles

Missile weight 800 kg

length 5.5 meters

calibre 400 mm

http://www.fas.org/man/dod-101/sys/missile/row/Medved.jpg

VA-111 Shkval underwater rocketIn 1995 it was revealed that Russia had developed an exceptionally high-speed unguidedunderwater missile which has no equivalent in the West. Code-named the Shkval(Squall), the new weapon travels at a velocity that would give a targeted vessel very littlechance to perform evasive action. The missile has been characterized as a "revenge"weapon, which would be fired along the bearing of an incoming enemy torpedo. TheShkval may be considered a follow-on to the Russian BGT class of evasion torpedoes,which are fired in the direction of an incoming torpedo to try to force an attacking toevade (and hopefully snap the torpedo's guidance wires). The weapon was deployed inthe early 1990s, and had been in service for years when the fact of its existence wasdisclosed.Development begain in the 1960s, when the Research Institute NII-24 (Chief DesignerMikhail Merkulov) involved in the artillery ammunition research was instructed to launchthe development of underwater high-speed missile to fight nuclear-powered submarines.On 14 May 1969, pursuant to a government resolution, NII-24 and GSKB-47 merged intothe Research Institute of Applied Hydromechanics (NII PGM), which formed the basis ofthe present day 'Region' Scientific Production Association. Advances in the developmentof jet engines and fuel technologies, as well as outstanding results in the research of bodymotion under cavitation made it possible to design a unique missile with a dived speedmuch greater than that of conventional torpedoes.

When the suction on the low-pressure side of the propeller blade dips below ambientpressure [atmospheric plus hydrostatic head] the propeller blade cavitates -- a vacuumcavity forms. There is water vapor in the cavity, and the pressure is not a true vacuum,but equal to the vapor pressure of the water. High-speed propellers are often designed tooperate in a fully-cavitating (supercavitating) mode. A high speed supercavitatingprojectile, while moving in the forward direction, rotates inside the cavity. This rotationleads to a series of impacts between the projectile tail and the cavity wall. The impactsaffect the trajectory as well as the stability of motion of the projectile. The present paperdiscusses the in-flight dynamics of such a projectile. Despite the impacts with the cavitywall, the projectile nearly follows a straight line path. The frequency of the impactsbetween the projectile tail and cavity boundary increases initially, reaches a maximum,and then decreases gradually. The frequency of impacts decreases with the projectile'smoment of inertia.

Apparently fired from standard 533mm torpedo tubes, Shkval has a range of about 7,500yards. The weapon clears the tube at fifty knots, upon which its rocket fires, propellingthe missile through the water at 360 kph [about 100 m/sec / 230 mph / 200-knots], threeor four times as fast as conventional torpedoes. The solid-rocket propelled "torpedo"achieves high speeds by producing a high-pressure stream of bubbles from its nose andskin, which coats the torpedo in a thin layer of gas and forms a local "envelope" ofsupercavitating bubbles. Carrying a tactical nuclear warhead initiated by a timer, it woulddestroy the hostile submarine and the torpedo it fired. The Shkval high-speed underwatermissile is guided by an auto-pilot rather than by a homing head as on most torpedoes.

There are no evident countermeasures to such a weapon, its employment could putadversary naval forces as a considerable disadvantage. One such scenario is a rapid attacksituation wherein a sudden detection of a threat submarine is made, perhaps at relativelyshort range, requiring an immediate response to achieve weapon on target and to ensuresurvival. Apparently guidance is a problem, and the initial version of the Shkval wasunguided However, the Russians have been advertising a homing version, which runs outat very high speed, then slows to search.A prototype of the modernised "Shkval", which was exhibited at the 1995 internationalarmaments show in Abu Dhabi, was discarded. An improved model was designed with aconventional (non-nuclear) warhead and a guided targeting system, which substantiallyenhances its combat effectiveness. The first tests of the modernised Shkval torpedo wereheld by the Russian Pacific Fleet in the spring of 1998.The 'Region' Scientific Production Association has developed developed an exportmodification of the missile, 'Shkval-E'. Russia began marketing this conventionallyarmed version of the Shkval high-speed underwater rocket at the IDEX 99 exhibition inAbu Dhabi in early 1999. The concept of operations for this missile requires the crew of asubmarine, ship or the coast guard define the target's parameters -- speed, distance andvector -- and feeds the data to the missile's automatic pilot. The missile is fired, achievesits optimum depth and switches on its engines. The missile does not have a homingwarhead and follows a computer-generated program.On 05 April 2000 the Russian Federal Security Service [FSB] in Moscow arrested anAmerican businessman, Edmond Pope, and a Russian accomplice, on charges of stealingscientific secrets. A FSB statement said it confiscated "technical drawings of variousequipment, recordings of his conversations with Russian citizens relating to their work inthe Russian defense industry, and receipts for American dollars received by them." Pope,a retired US Navy captain who spent much of his career working in naval intelligence,was at the time of his arrest the head of a private security firm. On 20 April 2000 the FSBrevealed that Pope had been seeking plans the Shkval underwater missile. Pope wasdetained during an informal contact with a Russian scientist who had participated in theShkval's creation.The arrest of Daniel Howard Kiely, deputy head of the Applied Research Laboratory atPennsylvania State University, came almost simultaneously. The laboratory led by Mr.Kiely has for many years been developing torpedoes for US warships and submarines.Professor Kiely had joined Pope in Moscow to offer technical advice and determine thetasks for Pope's further activity. Kiely was interrogated as a witness. His testimony andobjects confiscated during the search proved his involvement in Pope's activities. Laterthe 68-year-old professor was released and allowed to return to the United States.

The objective of the High-Speed Undersea Weaponry project at the US Office of NavalResearch is to develop the vehicle guidance, control and maneuvering capabilities for thequick reaction weapons. High-speed weapons could offer an advantage for AntiSubmarine Warfare (ASW) "close encounter" scenarios. The overall system response of ahigh-speed weapon for breaking off engagements with enemy submarines would bemeasured in seconds, rather than minutes. The High-Speed Undersea Weapons projecthas three tasks; Vehicle Guidance, Vehicle Control, and Test Bed Development. VehicleGuidance deals with homing sensors, signal processing, waveform design, and autopilot

commands that are used to guide (either autonomously or with external interaction) theweapon to its target. Vehicle control deals with control and maneuvering of the high-speed weapon with emphasis on stabilizing the supercavitating bubble cavity, andoptimizing the flow for low drag. Technical issues include instability due to vehicleplaning and tail slap, interaction between cavity with propulsion exhaust, and propulsionsystem transients, including startup. Test Bed Development is an ongoing effort thatdevelops a test platform to test and evaluate S&T candidate systems such as homingsystems, vehicle control, and propulsion systems.

AT-1 SNAPPERThe first antitank guided missile to be used in the Warsaw Pact forces was the AT-1"SNAPPER" which was launched from a UAZ-69 jeep. Although by the mid-1970s thislauncher was rarely encountered with Soviet troops, it was still used in other countries ofthe Pact and has been exported to Yugoslavia and the Middle East.

The AT-1 "SNAPPER" is a wire guided missile with a HEAT warhead. Officially it isknown to the Soviets as the 3M6, with a nickname of "Shmet", meaning bumblebee. TheAT-1 has a warhead capable of penetrating 380mm of armor and a range of 2,000 meters.The AT-1 is easily recognized by its wide wing span and pointed nose.

The UAZ-69 launch vehicle has a very distinctive appearance since the quadruplelauncher with the missiles is rotated to the vertical position during travel. Both themissiles and launcher are covered with a canvas top which give the vehicle theappearance of a baby carriage. For firing the canvas ton is towered to the rear and thelauncher is rotated downward to the rear of the vehicle. Since the UAZ-69 is a smallvehicle no reserve rounds are carried. The two-man crew of the launcher is located in theforward compartment of the vehicle where the on-board fire control equipment is located.Off-vehicle remote control is also provided for.

The "SNAPPER" is also launched from a modified BRDM amohibious scout car. Thislaunch vehicle carries a triple launcher which is raised for firing, with the armor platesmoving to the side. As in the case of the UAZ-69 off-vehicle remote control is providedfor, although the two-man crew normally operates from the forward compartment of thevehicle. This BRDM launch vehicle wass still used in a number of Warsaw Pact armies inthe 1970s.

SpecificationsUSA Code AT-1

Nato Name Snapper

Fuel Solid

Guidance Wire MCLOS

Range 2 Km

Launcher Rail

Inservice OOS = Out Of Service

Notes Used from Tank Destroyers

AT - 2 SWATTER Anti-Tank GuidedMissileThe SWATTER is a radio-guided antitank guided missile with a HEAT (High Explosive,Anti Tank) warhead. The SWATTERs with manual command to line of sight (MCLOS)guidance have the disadvantage that the operator must track target and missilesimultaneously and manually guide the missile to the target. The slow flight speed makesevasive action an effective countermeasure, especially at long ranges.

The SWATTER was introduced into service in 1960 specifically for use with the BRDMreconnaissance vehicles. The SWATTER is mounted on BRDM/BRDM-2 scout vehicleswith four launch rails on a traversable mount. When the launcher is raised for firing,armor plates on the BRDM move to the sides, while the launcher on the BRDM-2 isattached to the underside of a flat, retractable, armored cover. The Mi-8/HIP E can mountfour SWATTERs above its outboard weapons racks, and the Mi-24/HIND A and Dmount four SWATTERs on wingtip launch rails. BRDM/BRDM-2 SWATTERs aresometimes found in the antitank battery of motorized rifle regiments although this role ismore likely filled by the AT-3 or AT-5. The BRDM-mounted SWATTERs with MCLOSguidance were replaced by the new AT-5/SPANDREL.

The Mi-24 helicopter was equipped with the heavy 9M17 Skorpion (AT-2 Swatter)missile of the Falanga [Phalanx] family (Vertoletnaya Falanga-V helicopter version). Itsolder version, the 9M17M, was guided manually by commands from the pilot tracking itsflight. Its 9M17P version is guided semiautomatically by an on-board Raduga-F set, theoperator's sole task being to keep the target within field of view of the sight eyepiece.Signals are transmitted to the missile over radio. The appearance of the helicopter-mounted SWATTER C, retrofitted with a semiautomatic IR/radio guidance system andIR terminal homing, was apparently an interim measure pending the full deployment ofthe longer-range, second-generation missile AT-6/SPIRAL. SWATTERs are currentlyseeing limited use, however the AT-2c uprated version, are still in wide use as helicopter-mounted missiles.

The SWATTER-A has a maximum range of 2500 meters and a minimum range of 500meters. It has manual command to line of sight (MCLOS) guidance. This means that themissile operator literally flies the missile onto the target using a small joystick. Themissile has a flare in its tail that helps the operator fly the missile down his line of sight tothe target. Unlike later ATGM's which use a wire to transmit commands from theoperator to the missile, the SWATTER uses radio. The SWATTER B also has MCLOSguidance but the maximum range was extended to 3500 m. The SWATTER C wasdesigned as an interim between the SWATTER B and the AT-6 SPIRAL for use byhelicopters. The C version uses semi-automatic command line of sight (SACLOS)guidance instead of MCLOS guidance. The difference is that instead of manually flyingthe missile with a joystick, the operator simply keeps the cross hairs of his sight on the

target and the missile flies itself there. In addition the missile has terminal IR guidanceand a maximum range of 4000 m.

The 9M17P SWATTER missile's length is 1160 mm, its body diameter is 132 mm, andits launch weight is 31.5 kg. The SWATTER's HEAT warhead weighs 5.4 kg, and canpierce 500 mm thick steel armor. The SWATTER A can engage targets at rangesbetween 500 and 2,500 meters. SWATTER B and C have maximum ranges of 3,500meters and 4,000 meters respectively. All versions have a flight speed of 150-170 metersper second, resulting in a flight time of 17 seconds to 2,500 meters (SWATTER A), 23seconds to 3,500 meters (SWATTER B) or 26 to 27 seconds to 4,000 meters (SWATTERC). Armor penetration is over 500 mm, and the probability of first-round hit is 67 percentfor SWATTER A and B and over 90 percent for the SWATTER C.

VariantsThe initial version of the missile was the SWATTER-A, but two upgrades wereintroduced in the 1970s, designated SWATTER-B and SWATTER-C. The SWATTER Awas introduced in the early 1960s, and the SWATTER B was in service before 1973when it was first displayed in the Red Square parade. All versions are 1,1 60 mm longand 148 mm in diameter. The SWATTER A and B, both with manual command-to-line-of-sight (MCLOS) guidance, differ in weight (27 kg and 29 kg respectively). However,the AT-2c/SWATTER C has semiautomatic command-to-line-of-sight (SACLOS)guidance with IR terminal homing.

SpecificationsWeight 27.0 kg (A)

29.0 kg (B,C)

Length 1.2 meters

Range500 - 2500 m (A)500-3500 m (B)4000 (C)

Warhead High Explosive Anti-tank

Warhead weight 5.4 kg

Armor Penetration 500+ mm

Launching PlatformsBRDM/BRDM-2Mi-8 HipMi-24 Hind

Using Nations:Former Soviet Republics, Afghanistan, Bulgaria, Cuba,Czechoslovakia, Egypt, Hungary, Libya, Poland,Romania, Syria, Vietnam, Yemen.

AT-3 SAGGER Anti-Tank Guided MissileHongjian (Red Arrow)-73The wire-guided 9M14M Malutka [Tiny or Little Baby] SAGGER, also known by the USdesignation AT-3, was first seen in 1961. The SAGGER is a wire-guided antitank guidedmissile with a shaped-charge HEAT warhead. It is more compact than the earlier AT-1/SNAPPER and AT-2/SWATTER ATGMs, but carries an equally powerful warhead.Antiarmor missiles are used, above all, as helicopter weapons on Mi-2 and Mi-8helicopters and thus are modifications of army missiles. Introduced in 1961, theSAGGER was smaller but just as effective as its predecessors the AT- 2 SWATTER andAT-1 SNAPPER. It has now been withdrawn from ordnance.

The SAGGER may be employed as a man-packed missile, on vehicles, and from rotary-wing aircraft. AT-3 is classed by weight as portable (21-40 kg), rather than manportable(<21 kg). The launcher is also a missile carry case.

The manpack version is carried in a fiberglass "suitcase", is launched from a railattached to the lid of the case on a hinged support, and is fired and guided by acontrol box with firm button, periscope sight, and control stick.

On BRDM/BRDM-2 scout vehicles launch rails are mounted on the underside ofthe retractable armored cover, with eight additional missiles carried inside thevehicle. The BMP and BMD combat vehicles both have a single launch railmounted above the 73-mm main gun and carry a total of four and three missilesrespectively. The retractable launcher on the BRDM-2 vehicle has the ability totraverse 70 degrees to the left or right with elevation varying from 3.5 to 17degrees.

The Mi-2/HOPLITE helicopter can carry four SAGGERs on the sides of its cabin.The Mi-8/HIP F carries six SAGGERs, and some export models of the Mi-24/HIND carry four SAGGERs on wingtip launchers.

The 9M14M missile weighs 10.9 kg, is 860 mm long, has a body diameter of 125 mmand a wing span of 393 mm. Its maximum range is 3000 m and its minimum firingdistance is 500 mm. With an average speed being 120 m/s, the missile is slow, taking 25seconds to reach its maximum range of 3000 meters.

The SAGGER is capable of engaging targets at ranges of 500 to 3,000 meters and canpenetrate over 400 mm of armor. As with the SWATTER, the SAGGER uses manualcommand to line of sight (MCLOS) guidance system in which the operator must observeboth missile and target and guide the one towards the other. The improved SAGGER-Cwas fitted with semi-automatic command line of sight (SACLOS) guidance to serve as aninterim until the AT-5 SPANDREL and AT-6 SPIRAL entered service. The guidancepanel can be located up to 15 meters from the launcher, and can control up to four

launchers. If a target is <1,000 meters from launcher, the operator can joystick the missileto target without using optics. The guidance elevation (°) is -5/ +10. Because the moduleis small and can be shifted, elevation and field of view are operationally unlimited.Improved versions can be used on older launchers, but in the MCLOS mode.

The SAGGER A or B gunner must visually track target and missile simultaneously,which requires extensive training and constant practice. Although the missile leaves thelauncher armed and can detonate and kill at very short range, it can be captured by thegunner only at ranges of 500 to 800 meters. Under combat conditions, however, mostgunners probably will be able to engage targets successfully only between 1,000 and3,000 meters. The missile has a very long flight time to the target (12.5 seconds to 1,500meters; 25 seconds to 3,000 meters), and evasive action is effective against it, especiallyat long ranges. Although a SAGGER launching gives off a cloud of gray smoke and aloud roar, this signature is difficult to detect on the battlefield. The wire-guided missile isinvulnerable to electronic countermeasures and has a very small percentage ofmalfunctions.

The antitank platoon of a BTR-equipped motorized rifle battalion (MRB) has two ATGMsquads with two manpack SAGGER firing teams (two missiles each). In each three-manteam, the gunner carries a suitcase containing the control box, and two assistant gunnerseach carry one missile in a suitcase. One of the assistant gunners is also an RPG-7gunner. One missile can be set up, checked out, and fired in five minutes (1 2 to 1 5minutes for all four missiles). Using a tour-position selector switch on the control box,each gunner can fire up to four missiles consecutively. Both gunners can remotely firemissiles from positions up to 15 meters from the launchers. For targets at less than 1,000meters, the missile can be guided by eye; for longer ranges, the 8x magnifying periscopicsight must be used. The RPG-7 gunner usually is deployed 1 50 to 200 meters in front ofthe SAGGER position to cover targets inside the minimum SAGGER range of 500meters. The antitank platoon also has two SPG-9s which may be employed with themanpack SAGGERs.

BRDM/BRDM-2 SAGGERs are found in the antitank battery of motorized rifleregiments, in the antitank battalion of motorized rifle and tank divisions, and in theantitank regiment of artillery divisions. The BRDM/BRDM-2 vehicles have a reactiontime of one minute to fire from a completely buttoned-up mode. Six missiles can be firedwithout reloading, and eight additional missiles are carried inside the vehicle. Successivemissiles can be fired and tracked within five seconds of the previous missile's impact.The gunner can operate either from within the vehicle or from a remote position up to 80meters away. The two-man crew (commander/gunner and driver) also has assault riflesand an RPG-7 antitank grenade launcher.

SAGGERs are also found in airborne units. The manpack version is found in the antitankplatoon of a non-BMD-equipped parachute company and also in the antitank battery of anon-BMD-equipped airborne battalion. BRDM/BRDM-2 SAGGERs are found in theATGM battery of the BMD-equipped airborne regiment.

VARIANTSSome SAGGER systems, designated AT-3c, were retrofitted with semiautomatic IR/wireguidance systems. Only the vehicle-and helicopter-mounted missiles were so retrofitted,obviously an interim measure pending the full deployment of longer-range, second-generation AT-5/SPANDREL and AT-6/SPIRAL missiles. Manpack SAGGERs werereplaced by the AT-4/SPIGOT, as were the SAGGERs. The AT-3c/SAGGER C variantemploys semiautomatic command-to-line-of-sight (SACLOS) guidance. It is primarilymounted on the BRDM-2, but may also be mounted on the HIP F and HOPLITEhelicopters. These hellebore systems provide greater flexibility to the ground commandbut at a greater vulnerability cost to the launch platform.

Copies include North Korean Susong-Po, Taiwanese Kun Wu, and the Chinese copy, RedArrow-73/HJ-73, with indigenous guidance. The "Hongjian (Red Arrow)-73," China'sfirst-generation anti-tank missile developed in the mid-1980s, had an estimated hitprobability of 70 percent. POLK is a Slovenian Portable Anti-armor Launching Set thatincludes a new launcher, guidance panel with binocular sight, and 3 ATGMs similar toAT-3C Improved (nose probes and lower smoke signature). With a nose probe andimproved propellant, the MCLOS-guided ATGM can reach maximum range in 25 secand penetrate 580 mm. A Russian AT-3c/Improved (SACLOS) has similar capabilities.

Iran makes a copy of the Russian AT-3 9M14M (Sagger or Ra’ad) anti-tank guidedmissile. An improved version of RAAD missile, RAAD-T missile, incorporates a tandemwarhead armament system and due to new airframe, its maneuverability increasedconsiderably. Irrespective of the year and place of production, all versions of RAADmissiles can be upgraded to the new version. The RAAD-T weapon system is a portableanti-tank guided missile, which is used to attack any armored fighting vehicle includingthose with Explosive Reactive Armor (ERA). In field operations, only by one groundguidance equipment, up to four missiles on their launchers can be shot, each in every 30seconds. The system Safety and Arming Device (SAD) provides a high level of safetyduring the transportation and handling besides a reliable arming in operation. It istransported in new packing and tested with new equipment. By impacting the target, evenat high angles of attack, explosion of the front charge, will remove the ExplosiveReactive Armor (ERA) and after a delay time, the main charge will be exploded and thetank distrusted.

The Slovenian Iskra TS-M thermal sight is available, with detection at 3,000 meters andrecognition at 1,800 meters. Any AT-3 can be modernized to Malyutka-2 withreplacement of warhead and or replacement of specific warhead and motor components.

SpecificationsAlternativeDesignations

Malyutka Complex

Launching Platforms ManpackBMD

BMPBRDM/BRDM-2Mi-8 HipMi-24 Hind

Date of Introduction 1963

Proliferation

At least 45 countries, including: Former SovietRepublics, Afghanistan, Algeria, Angola, Bulgaria,Czechoslovakia, Cuba, Egypt, Ethiopia, Hungary, Iraq,India, North Korea, Libya, Mozambique, Poland,Romania, Syria, Uganda, Vietnam, Yugoslavia,Zambia.

Description

Crew 3

Primary Mount Ground mount on "suitcase" launcher

Alternate Mounts Rail on BMP-1, BMD-1, BRDM, BRDM-2 etc.

Weight Overall,Excluding Missile(kg)

30.5 launcher + guidance

Length Overall inFiring Position (m)

0.86 with AT-3/a/b/c1.02 with Malyutka-2

Height Overall InFiring Position (m) INA

Width Overall InFiring Position (m) INA

ARMAMENT

Launcher Name 9P111 Case launcher

Launch Method Rail on case

Elevation (°) Fixed for launcher

Rate of Launch(missiles/min)

2

Reaction Time (sec) INA

Emplacement Time(min) 1.7 POLK set

Displacement Time(min)

INA

Ready/StowedMissiles 4/0, 3/0 POLK set

FIRE CONTROL

FCS Name 9S415/9S415M/9S415M1 guidance panel

Guidance MCLOS (9S415/-M panel), SACLOS

Command Link Wire

Beacon Type Incandescent infrared bulb (SACLOS)

Tracker Type N/A for MCLOS, flare tracker for SACLOS

Susceptible ToCountermeasures

EO jammers, smoke, counterfire

Counter-countermeasures Offset guidance panel, laser filters

Rangefinder INA

Frequency INA

Counter-countermeasures INA

Sightsw/Magnification

Gunner

Day 9Sh16, 8x

Field of View (°) 22.5

Acquisition Range(m) 4000

Night Available

Field of View (°) N/A

Acquisition Range(m)

N/A

AMMUNITION

Antitank GuidedMissiles

Name AT-3, -3a, -3b/SAGGER

AlternativeDesignations Malyutka, Malyutka-M

Missile Weight (kg) 10.9

Warhead Type Shaped Charge (HEAT)

Armor Penetration 400

(mm)

Minimum/MaximumRange (m) 500/3,000

Probability of Hit(%)

70 against moving tanks

Average Velocity(m/s) 115

Time of Flight toMax Range (sec) 26

Name AT-3c/SAGGER

AlternativeDesignations Malyutka-P

Missile Weight (kg) 11.4

Warhead Type Shaped Charge (HEAT)

Armor Penetration(mm) 520

Minimum/MaximumRange (m) 500/3,000

Probability of Hit(%) 90 (SACLOS)

Average Velocity(m/s) 115

Time of Flight toMax Range (sec) 26

Name Malyutka-2

AlternativeDesignations Malyutka (Modernized)

Missile Weight (kg) 12.5

Warhead Type Tandem Shaped Charge (HEAT)

Armor Penetration(mm) 800

Minimum/MaximumRange (m) 500/3,00

Probability of Hit(%) 90 (SACLOS)

Average Velocity 130

(m/s)

Time of Flight toMax Range (sec) 23

Other Missiles Malyutka (Modernized) HE, AT-3c Imp, POLK

AT-4 SPIGOT Anti-Tank Guided MissileThe first concrete evidence of the existence of second-generation Soviet ATGMs was a1975 report in a Yugoslav military periodical that an ATGM called FAGOT had recentlyappeared in the Warsaw Pact forces. Subsequently, it was reported that the FAGOT firstentered service in 1972. The man-portable FAGOT system has now been given theNATO nickname SPIGOT and the US designation AT-4. The BRDM-mounted AT-5/SPANDREL was at one time misidentified as the FAGOT, and the missiles are indeedquite similar.

Introduced in the mid-1970s, the SPIGOT was designed primarily to replace AT- 3SAGGER man-packed missiles. The SPIGOT has a number of improvements over theSAGGER including a smaller but more lethal warhead, SACLOS guidance that gives a90 percent probability of a first round hit, a speed of 183 meters per second that propelsthe missile to its maximum range in just 11 seconds, and minimum range of only 70meters. While meant to be a primarily a man-pack missile, the SPIGOT may be mountedon the BMP and BMD in place of the SAGGER.

Because of its weight, the Russians categorize the AT-4/4B system as portable (21-40 kg)rather than manportable. For dismounted carry load is divided among three packs. Due tothe greater weight, AT-5/-5B fits into the "heavy" class (40+ kg), and should only becarried short distances from vehicles (<500 meters). For crews using both ATGM classesand operating near vehicles, combat load is 8 (4 stowed in the vehicle).

The AT-4/SPIGOT is a tube-launched, semiautomatic command-to-line-of-sight(SACLOS), antitank guided missile system with a HEAT warhead. The SPIGOT launchtube, in which the missile is stored and carried, is 1,200 mm long, 134 mm in diameter,and weighs 5 kg. The missile itself is estimated to have slightly smaller dimensions and aweight of 7 kg. This tripod-mounted, wire-guided ATGM, similar in many respects to theUS TOW system, was deployed as a direct replacement for the man-portable SAGGER,and to replace SAGGERs on the BMP and BMD as well.

The SPIGOT has a minimum range of only 70 meters and a maximum range of 2,000meters. Missile speed is estimated at 185 meters per second, with a maximum flight timeof 11 seconds. The warhead, which is probably smaller than that of the SAGGER, has anarmor penetration capability of 500 to 600 mm. Probability of first-round hit should be atleast the same as for the AT-3c semiautomatic SAGGER (90 percent).

The SACLOS guidance system increases accuracy and reduces operator trainingrequirements, since it is no longer necessary for the operator to track target and missilesimultaneously. The operator keeps his sight trained on the target while the missile istracked automatically. The deviation between the missile's path and the operator's line-of-sight is measured by an IR tracking apparatus, the IR source being in the tail of themissile. An apparatus at the control site then generates guidance commands which aretransmitted to the missile by wire, causing the missile to eliminate the deviation.

The requirement that the missile launcher of a SACLOS system be collocated with theaiming and tracking assembly (i.e., the operator) eliminates the possibility of moving theoperator to a remote position for safety.

The antitank platoon of a BTR-equipped motorized rifle battalion has two ATGM squads.Each squad has two SPIGOT firing teams. In each three-man team, the gunner carries thelauncher and tripod as a backpack, and the two bearers each carry two launch tubes asbackpacks. All three men carry an assault rifle, but no RPG-16, since the SPIGOT doesnot have the 500-meter deadspace of the SAGGER.

The AT-4B/Factoria is an upgrade ATGM with a 2,500 meter range, 550-mmpenetration, and a velocity of 180 m/s (13.2 - 14.0 sec TOF). Russian firms havedeveloped counter-countermeasures, such as encoded-pulse beacons for ATGMs andcounter-dazzler adjustments to the 9S451M1 guidance box. Filters can be mounted infront of reticles. TPVP/1PN65 thermal sight is available, with the range approximately2,500 meters. Weight is 13 kg. Slovenian TS-F sight and Russian 1PN86-1/1PN86/Mulathave a 3,600 meter detection range.

Currently, the Russian Army employs the BRDM-2/AT-5 ATGM variant carrying eitherSPIGOT (normally for the AT-4 system) or longer-ranged SPANDREL missiles. Thissystem is antiquated by modern standards, and lacks the mobility, armor protection, andeffectiveness needed on the modern battlefield. The Russian Army is faced with theoption of purchasing the BMP-3 mounted AT-14 Kornet system, which is a follow-on tothe AT-5, or the more expensive AT-15 Khrizantema, a more powerful system capable ofengaging more targets at greater ranges.

SpecificationsAlternativeDesignations 9P135M Firing Post, Fagot/Fagot-M

Date of Introduction 1973

Proliferation At least 25 countries, including : former SovietRepublics, Czechoslovakia, Poland, Syria.

Description

Crew 3

Primary Mount Ground mount on folding tripod

Alternate Mounts Pintel (post) on BMP-1P, BTR-D, UAZ-469, etc.

Weight Overall,Excluding Missile(kg)

22.5

Length Overall inFiring Position (m) 1.1/1.3 AT-4/5 tube

Height Overall InFiring Position (m)

INA

Width Overall InFiring Position (m) INA

ARMAMENT

Launcher Name 9P135 (AT-4 only), 9P135M (AT-4/AT-5), -M1, -M2, -M3

Launch Method Tube-launched

Elevation (°) (-/+) INA

Rate of Launch(missiles/min) 2-3, depending on range

Reaction Time (sec) INA

Emplacement Time(min) INA

Displacement Time(min) INA

Ready/StowedMissiles 4/0 full dismount, 4/4 on or near vehicle

FIRE CONTROL

FCS Name 9S451M1 Guidance control box

Guidance SACLOS

Command Link Wire

Beacon Type Incandescent infrared bulb

Tracker Type IR, 9S451M1

Susceptible ToCountermeasures EO jammers, smoke, counterfire

Counter-countermeasures EO jamming alarm

Rangefinder INA

Sightsw/Magnification

Gunner

Day 9Sh119M1, 4x

Field of View (°) 4.5

Acquisition Range(m)

INA

Night Available

AMMUNITION

Antitank GuidedMissiles

Name AT-4/SPIGOT

AlternativeDesignations Fagot

Missile Weight (kg) 13.0 (in tube)

Warhead Type Shaped Charge (HEAT)

Armor Penetration(mm)

480

Minimum/MaximumRange (m) 70/2,000

Probability of Hit(%) 90

Average Velocity(m/s) 186

Time of Flight toMax Range (sec) 11

Other Missiles AT-4B/Factoria

AT-5 SPANDREL Anti-Tank GuidedMissileIntroduced in 1977, the SPANDREL is equivalent to the American TOW missile. Thefirst of the second-generation Soviet ATGMs to be seen in public was the BRDM-mounted model displayed in the Red Square parade of November 1977. This model, atone time misidentified as the FAGOT (AT-4/SPIGOT) eventually was designated theAT-5/SPANDREL. The SPANDREL is similar to the SPIGOT in most respects. TheSPANDREL has a maximum range of 4,000 meters and a minimum range of 100 meters.Other capabilities are essentially the same as for the AT-4/SPIGOT, except for weight,and maximum range and the time of flight which are twice that of the SPIGOT.

The AT-5/SPANDREL is a wire-guided, SACLOS antitank guided missile systemmounted on the BRDM-2 scout vehicle. The dimensions and shape of the launch tube aresimilar to those of the AT-4/SPIGOT, but the SPANDREL missile is considerablyheavier. The SPANDREL launch tube has a blow-out cap at the front and is flared at therear. Five SPANDREL missiles are carried on a traversable mount just behind the twofront cupolas of the BRDM-2. A bowed hatch in the vehicle roof immediately behind thelauncher is possibly used to allow the mount to be folded backwards into the hull forreloading under armor protection. An additional 10 reload missiles are estimated to becarried inside the vehicle. A rotatable optical sighting/tracking periscope, similar inappearance to the periscope on the AT-4/SPIGOT launch apparatus, is mounted atop thegunner's hatch on the right front of the vehicle roof.

Unlike the SPIGOT the SPANDREL is intended for use on vehicles only. TheSPANDREL was supposed to replace all vehicle-mounted SWATTER and SAGGERmissiles, but with the collapse of the USSR this did not become a reality. It has also beenmounted atop the turret of the BMP M1981 variant. Currently, the Russian Armyemploys the BRDM-2/AT-5 ATGM variant carrying either SPIGOT (normally for theAT-4 system) or longer-ranged SPANDREL missiles. This system is antiquated bymodern standards, and lacks the mobility, armor protection, and effectiveness needed onthe modern battlefield. The Russian Army is faced with the option of purchasing theBMP-3 mounted AT-14 Kornet system, which is a follow-on to the AT-5, or the moreexpensive AT-15 Khrizantema, a more powerful system capable of engaging more targetsat greater ranges.

VARIANTS

9 P135M3 -- Konkurs-M Complex. Launcher with 1PN65 thermal sight and AT-5B/Konkurs-M missiles. Night range is 2,500m.

SpecificationsAlternativeDesignations 9P135M Firing Post, Fagot/Fagot-M

Date of Introduction 1973

Proliferation At least 25 countries, including : Former SovietRepublics, Czechoslovakia, Poland.

Launching Platforms BRDMBMP-2

Description

Crew 3

Primary Mount Ground mount on folding tripod

Alternate Mounts Pintel (post) on BMP-1P, BTR-D, UAZ-469, etc.

Weight Overall,Excluding Missile(kg)

22.5

Length Overall inFiring Position (m) 1.1/1.3 AT-4/5 tube

Height Overall InFiring Position (m) INA

Width Overall InFiring Position (m) INA

ARMAMENT

Launcher Name 9P135M (AT-4/AT-5), -M1, -M2, -M3

Launch Method Tube-launched

Elevation (°) (-/+) INA

Rate of Launch(missiles/min) 2-3, depending on range

Reaction Time (sec) INA

Emplacement Time(min) INA

Displacement Time(min) INA

Ready/StowedMissiles 4/0 full dismount, 4/4 on or near vehicle

FIRE CONTROL

FCS Name 9S451M1 Guidance control box

Guidance SACLOS

Command Link Wire

Beacon Type Incandescent infrared bulb

Tracker Type IR, 9S451M1

Susceptible ToCountermeasures

EO jammers, smoke, counterfire

Counter-countermeasures EO jamming alarm

Rangefinder INA

Sightsw/Magnification

Gunner

Day 9Sh119M1, 4x

Field of View (°) 4.5

Acquisition Range(m)

INA

Night Available

AMMUNITION

Antitank GuidedMissiles

Name AT-5B/SPANDREL-B

AlternativeDesignations

Konkurs-M

Missile Weight (kg) 26.5 (in tube)

Warhead Type Tandem Shaped Charge (HEAT)

Armor Penetration(mm) 925

Minimum/MaximumRange (m) 75/4,000

Probability of Hit(%)

90

Average Velocity 208

(m/s)

Time of Flight toMax Range (sec) 19

Name AT-5/SPANDREL

AlternativeDesignations Konkurs

Missile Weight (kg) 25.2 (in tube)

Warhead Type Shaped Charge (HEAT)

Armor Penetration(mm) 650

Minimum/MaximumRange (m)

75/4,000

Probability of Hit(%) 90

Average Velocity(m/s) 200

Time of Flight toMax Range (sec) 20

AT - 6 SPIRAL Anti-Tank Guided MissileThe SPIRAL is much larger than previous Soviet ATGMs. The AT-6/SPIRAL is a tube-launched, SACLOS antitank guided missile mounted on the Mi-24/HIND E helicopter asa replacement for the heliborne AT-2/SWATTER variant found on previous HINDmodels. There are attachment points for two SPIRAL launch tubes on each wing tip ofthe HIND E. The 9M1114 Kokon [Cocoon] missile of the Shturm [Assault]-V (AT-6Spiral system was adapted for the Mi-24V helicopter, later also used on Mi-28 and Ka-29helicopters. The weight of the Kokon missile is 31.8 kg, which includes a warheadweighing 6 kg, its length is 1840 mm and its caliber is 130 mm. The missile is fired froma horn launcher.

Introduced in 1978 as a long-range stand-off weapon for the Hind attack helicopter, theSPIRAL is often incorrectly said to be a laser-guided weapon similar to the AmericanHellfire. The SPIRAL has often been erroneously assessed as a laser-guided weapon, andcredited with an unrealistic range of 7,000 to 10,000 meters.

Unlike the AT-4/SPIGOT and AT-5/SPANDREL, this new missile is not wire-guided.The SACLOS system with IR missile tracking and radio guidance (similar to the AT-2cuprated SWATTER) operates the same as the SPIGOT and SPANDREL, except for thefact that the SPIRAL is not wire-guided. The SPIRAL uses radio instead of wire totransmit commands from the operator to the missile. Probability of first-round hit shouldbe a least the same as for the AT-2c (90 percent).

The missile's speed (estimated at 450 meters per second) pushes the missile out to 5000meters, during which time the helicopter must maintain the target in its sight. During theflight time of the SPIRAL to the target (estimated at approx. 11 seconds at maximumrange), the target has an opportunity to take evasive action, but the helicopter launchplatform has limited ability to take evasive action itself since the SPIRAL operator mustkeep the target in his sight. The warhead is believed to contain two tandem HEATcharges that will punch through 600-700 mm of rolled homogenous steel armor.

SpecificationsWeight 30 kg

warhead weight up to 10 kg

Length 1.8 meters

Range 5000 m

Warhead High Explosive Anti-tank

Armor Penetration 600-700 mm

Launching Platforms Mi-8

Mi-24

Users Using Nations Former Soviet Republics,Czechoslovakia, Poland.

AT-7 Metis SaxhornAT-13 Metis-MThe Russians characterize the AT-7 ATGM complex as light or manportable (5-20 kg),permitting long-distance carry by dismounted infantry. Although the AT-13 complexslightly exceeds 20 kg, it is close enough to fit into the category. Guidance elevation hasa 15° span. Because the module is small and can be quickly corrected by shifting,elevation and field of view are operationally unlimited, and permit use against hoveringor stationary helicopters. The Russian 1PN86V/Mulat-115 thermal sight is available foruse on the launcher, with detection at 3,200 meters and recognition beyond the missile's1,500 meter range. Field of view is 4.6°.

SpecificationsName AT-7/Saxhorn AT-13

AlternativeDesignations Metis Metis-M (often mislabeled

Metis-2)

Date of Introduction 1978 1992

Proliferation At least 5 countries

Missile Weight (kg) 6.3 (in tube) 13.8 (in tube)

Warhead Type Shaped Charge(HEAT)

Tandem Shaped Charge(HEAT)

Armor Penetration(mm) 460 1,000/900 behind ERA

Minimum/MaximumRange (m) 40/1,000 80/1500

Probability of Hit(%) 90 90

Average Velocity(m/s) 180 287

Time of Flight toMax Range (sec)

6.2 8

LauncherDesignations 9P151 Firing Post

Crew 2

Primary mount Ground mount on tripod

Alternate mounts Shoulder for launch, UAZ-469 pintel mount

Weight Overall,Excluding Missile(kg)

10.2

Length Overall inFiring Position (m) 0.78 with AT-7/Metis 0.98 with AT-13/Metis-M

Height Overall InFiring Position (m) 0.72 with AT-7/Metis

Width Overall InFiring Position (m) INA

Launcher Name 9P151 Firing Post

Launch Method Tube

Elevation (°) -5/+10

Rate of Launch(missiles/min) 3-5, depending on range

Reaction Time (sec) INA

Emplacement Time(min) 0.20

Displacement Time(min) 0.33

Ready/StowedMissiles

4/0 (1 on launcher )

FIRE CONTROLName 9S816 Guidance system

Guidance SACLOS

Command Link Wire

Beacon Type INA

Tracker Type IR

Susceptible ToCountermeasures EO jammers, smoke, counterfire

Counter-countermeasures INA

RangefinderFrequency INA

Counter-countermeasures INA

Gunner Field of View INA

(°)

Acquisition Range(m) INA

Night Sights Available

AT-8 (Songster) Anti-Tank Guided MissileThe AT-8 (Songster) is a Russian ATGM. It was designed to be fired from the 125 mmsmooth-bore gun. It uses radio for guidance from the gunner. The AT-8 has a flight speedof 250m/s and a range of 4000m. It can penetrate 550 mm of flat steel and 445 mm ofsloped steel armour.

Specifications

Weight 30 kg

Length meters

Range 4000 m

Warhead High Explosive Anti-tank

Warhead weight Not available

Armor Penetration 445-550 mm

Launching Platforms Mi-24

Vikhr (AT-9)The latest aircraft antiarmor missile is the 9A4172 of the Vikhr (AT-9) family for Ka-50helicopters and Su-25T aircraft. It was built in Tula by A. Shipunov's group(Priborostroyeniye Design Bureau), builder of aircraft guns. The missile is fired fromlaunchers containing a 6-8 pack. Its guidance system combines radio-command guidanceduring the initial flight stage followed by laser-beam guidance afterwards. The missile isa supersonic one with a 8-10 km range, its caliber is 125 mm, and its weight togetherwith the launcher is 60 kg. The two-stage shaped-charge warhead is capable of piercingarmor of equivalent to 900 mm thickness. With the switch set in the appropriate positionon the pilot's panel in the cockpit, the Vikhr operates as an air-to-air missile with a radarturn-on for approach navigation. It is effective against airborne targets flying at speeds upto 800 km/h (600 km/h during rendezvous tacks).

AT-10 STABBERThe 9K116 Bastion (AT-10 STABBER) is a laser-beam riding, antitank missile launchedfrom the main gun of a T-55AM2B main battle tank, BMP-3 Infantry Fighting Vehicle,and the MT-12 antitank gun. The 9K116 system uses beam-riding laser guidance for the9M117 missile.

AT-11 SNIPERThe AT-11 SNIPER laser-guided ATGM, which can penetrate 700-mm of RHAe out to4000 meters, gives the T-90 the ability to engage other MBTs, vehicle ATGMs, and evenmost helicopters before they can engage the T-90.

AT-12 SWINGERThe 9K118 Sheksna (AT-12 SWINGER) is a laser-beam riding, antitank missilelaunched from the main gun of a an improved T-62 main battle tank. The 9K118 systemis essentially a 9K116 system modified to be fired through the 115-mm gun of the T-62instead of the 100-mm of the T-55.

Kornet (AT-14)In October 1994, the KPB Instrument Design Bureau introduced the Kornet (AT-14)ATGM system. The Kornet was developed introducing a laser beam-riding missile withautomatic command-to-line of sight (SACLOS) guidance. The operator simply has tokeep the sight on the target to ensure a hit. The laser beam-riding system is also lessvulnerable to countermeasures. The Kornet was specifically designed to replace theKonkurs, which has been in service with the former Soviet and Russian armies for overtwenty years.

The Kornet, which has a claimed ability to penetrate 1100 to 1200 millimeters of steelarmor protected by explosive armor, provided a formidable antitank weapon system.However, even with the improved capabilities the Kornet has over earlier systems, anATGM with all-weather, day or night, immunity to countermeasures, and fire and forgetcapabilities was still highly desired.

AT-15 KhrizantemaThe development of the Khrizantema missile system provides the Russian Army with aweapon system that will significantly upgrade its antitank capability. Even with theimproved capabilities the AT-14 Kornet has over earlier systems, an ATGM with all-weather, day or night, immunity to countermeasures, and fire and forget capabilities wasstill highly desired. In July 1996, Russia's KBM Engineering Design Bureau revealed adual-guidance missile system with the desired capabilities. A new long-range ATGM, theKhrizantema (9M123), capable of firing six-kilometer-range supersonic missiles,incorporating both radar and laser command guidance receivers, is in its last stage oftesting. KBM expects production to begin in 1998. The key role of the Khrizantema(Russian for "chrysanthemum") is to destroy armored vehicles at long range. In addition,it could be used to destroy bunkers, and to engage slow- or low-flying helicopters. TheKhrizantema missile system is mounted on a modified BMP-3 infantry combat vehiclechassis. The chassis is designated the 9M157-2, and has the amphibious capability of theBMP-3.Two models of the 9M123 missile have been developed. One has a tandem high-explosive antitank (HEAT) warhead; designated the 9M123-2, it apparently can penetrateover 1000 millimeters of steel armor protected by explosive reactive armor (ERA). Thesecond model, the 9M123-F-2, has a high explosive warhead. The maximum range of themissile is 6000 meters with a maximum speed of 400 meters per second; thus it issupersonic. The missile has two movable control surfaces at its rear, with four wrap-around wings about three-quarters of the way down its body toward the rear.For the first time in the world, an automatic radar target detection and tracking system,with simultaneous missile control during its guidance to the target, was developed for theKhrizantema ATGM. The unique feature of the missile is that it has two modes ofguidance: automatic, where it is guided by a roof-mounted radar; and by a semi-automatic laser beam rider, using the sight mounted in the front of the hull on the rightside. There is no known comparable missile in the West under development or in servicewith a similar guidance system.

The Russian Army is now faced with the option of purchasing the less expensive BMP-3mounted Kornet system, which is a follow-on to the AT-5, or the more expensiveKhrizantema, a more powerful system capable of engaging more targets at greater ranges,possibly employing the Kornet at regimental level and the Khrizantema at division level.Regardless of its placement in the Russian Army, many nations may find it desirable andallocate a portion of their budgets to purchase the extremely capable Khrizantema missilesystem.

Ataka-V VIKhR 9M120 (AT-16)A modification of the Shturm-V family is the Ataka-V family of missiles used on Mi-28helicopters and on the latest Ka-50 helicopter. The Vikhr antitank missile is also the mainweapon of the Su-39. The aircraft is armed with 16 such missiles The Ataka-V familyincludes several versions, the basic one being the 9M120 with a shaped-charge warheadagainst armored targets and its improved version being the 9M220. Addition of a secondwarhead, a demolition warhead, has created the Fugasnaya [High-Explosive] 9M120F.Another version used against airborne targets is the 9A2200 with a rod warhead. Allthese missiles of the Ataka-V family have semiautomatic radio command guidance and a6000 m range, the producer quoting a 0.95 probability of a hit. Missiles of the Malutka-Falanga-Shturm-Ataka families were built by the "Mashinostroyenie" Design Bureau inIzhevsk, which had been established by Boris Shavyrin and is now directed by SergeyNiepobiedimyy.

SpecificationsContractor NPO Mashinostroyenie

Entered Service

Total length

Diameter

Wingspan

Weight

Warhead Weight HEAT

Propulsion

Maximum Speed

Maximum effectiverange

10,000 mEffective against ground & air targets at convergingspeeds to 800 km/h.

Penetration 900 mm

Guidance mode Laser Beam Rider SACLOS

Single-shot hitprobability 0.95 probability claimed