Sukhoi Su-25

.

"Sukhoi Su-25 'Frogfoot'

The Su-25 was built to survive heavy punishment over the battlefield when flying in support of ground forces. It has armor protection for critical components and the pilot, the cockpit being protected by 24mm (0.3in) welded titanium. The two R-135 turbojets are housed in widely

separated bays, and the internal fuel tanks are filled with reticulated foam for added protection against explosion. Low- speed handling is aided by wing-tip pods that split at the rear to form airbrakes. A flat-glass nose window covers a laser rangefinder/target designator, while at the back a Sirena-3 radar warning system antenna is located above the tailcone. The two-seat combat-capable derivative of the single-seat Su-25 (Su-25K for export) was developed as the Su-25UB (UBK for export), which in turn led to the unarmed Su-25UT two-seater (also known as the Su-28), A navalised version of the Su-25UT was known as the Su-25UTG. However, it was combat experience over Afghanistan that led to the most potent development, namely the Su-33, Based on the Su-25UB two-seater, the Su-39 had a new nav/attack system with automatic weapons selection and release, wing-tip ECM pods, and a large cylindrical fairing at the base of the fin housing chaff/flare dispensers and an IR jammer."

(source: Collins/Jane's Combat Aircraft, by Bob Munro and Christopher Chant, Harper Collins Publishers, 1995)

Model: Sukhoi Su-25 Country of origin: Russia Type: Close support/ground attack aircraft Powerplants: Two 44.2kN (99201b) Soyuz/Tumansky R-195 turbojets. Performance: Su-25TM - Max speed at sea level 950km/h (512kt), max cruising speed at 650ft 700km/h (378kt), economical cruising speed 650km/h (350kt). Max initial rate of climb 11,415ft/min. Service ceiling 32,800ft. Combat radius with a 2000kg (44101b) weapon load at altitude 630km (340nm), at low level 400km (215nm). Ferry range 2250km (1215nm). Weights: Su-25TM - Max takeoff 20,500kg (45,1951b). Dimensions: Su-25TM - Wing span 14.52m (47ft Sin), length overall 15.35m (50ft 5in), height 5.20m (17ft 1 in). Wing area 31.1 m2 (324.0sq ft). Accommodation: Pilot only, or two in tandem in Su-25UB. Armament Su-25T - One NNPU-8M 30mm gun. Ten underwing hardpoints for laser guided rockets, bombs, Vikhr M anti armour tube launched missiles, laser guided Kh-25ML (AS-10 'Karen') and Kh-29L (AS-14 'Kedge') ASMs, KAB-500 laser guided bombs and Kh-58 (AS-11 'Kilter') anti radiation missiles, and R-27, R-77 and R-73 AAMs. Operators: Afghanistan, Angola, Bulgaria, Czech Republic, Iraq, North Korea, Slovakia, Russia, Ukraine. History: The Su-25 ('Frogfoot' to NATO) was designed specifically for close air support missions in support of ground forces. Su-25 development began in 1968, although it wasn't until February 22 1975 that a prototype, designated T-8-1, first flew. This prototype was powered by twin Tumansky RD-913s, (non afterburning developments of the MiG-19's engines). Between then and 1984 when the first Soviet Su-25 units were declared operational, the Su-25 underwent a number of detail modifications and engine changes. A unit of Su-25s, initially pre production aircraft, saw combat in Afghanistan where experience resulted in a number of modifications including bolt on chaff/flare dispensers, engine exhaust IR signature suppressors and titanium shielding between the engines. The Su-25 features titanium cockpit armouring and wingtip pod airbrakes. The Su-25's engines can run on kerosene, diesel or petrol if necessary while the aircraft can self deploy its own ground support and maintenance equipment in four underwing pods. The basic Su-25 and export Su-25K (both 'Frogfoot-A') account for most Su-25 production. The Su-25UB and export Su-25UBK (both 'Frogfoot-B') are two seat conversion trainers with a ground attack capability. The Su-25UT later Su-28 (both also 'Frogfoot-B'), was offered as a dedicated advanced trainer. Ten carrier capable two seat Su-25UTGs (with arrester hook and strengthened undercarriage) were built for carrier trials while 10 similar Su-25UBPs were ordered, but may have been cancelled. Su-25BMs are single seater target tugs.

(source: International Directory of Military Aircraft, 1998-1999)

GOSUDARSTVENNOYE UNITARNOYE PREDPRIYATIE AVIATSIONNYI VOYENNO-PROMYSHLENNYI KOMPLEKS/AK SUKHOI (State Unitary Enterprise, Aviation Military-Industrial Complex/Concern Sukhoi)

SUKHOI Su-25 and Su-28

NATO reporting name: Frogfoot

Type

Attack fighter.

Programme

Development began 1968; Novosibirsk-built prototype, known as T8-1, flew 22 February 1975, with two 25.5 kN (5,732 lb st) non-afterburning versions of Tumansky RD-9 turbojet and underbelly twin-barrel depressable GSh-23 23 mm gun in fairing; in eventual developed form, second prototype and rebuilt first aircraft, T8-2D and T8-1D, had more powerful non-afterburning versions of Soyuz/Gavrilov R-13, designated R-95Sh, increased wing span, wingtip avionics/speed brake pods, underwing weapon pylons, and internal AO-17 30 mm gun necessitating offset nosewheel. Also Klen-PS laser range-finder replacing Fone, and new DISS-7 Doppler, new gunsight and new navigation computer; observed by satellite at Zhukovsky flight test centre 1977, given provisional US designation `Ram-J'; production, with R-95Sh turbojets, began 1978. T8-1D and preseries T8-3 sent to Afghanistan April 1980, as Rhombus team, for trials and combat testing; followed in mid-1981 by 200th Independent Shturmovik Squadron, Soviet Air Force, flying 12 production Su-25s for co-ordinated low-level close support of Soviet ground forces in mountain terrain, with Mi-24 helicopter gunships; fully operational 1984; 200th OShAE and later Su-25 squadrons flew 60,000 sorties during the eight-year war in Afghanistan, losing 23 aircraft and eight pilots killed; all but two of 139 laser-guided ASMs launched in combat achieved direct hits. Attack versions built initially at Factory No 31, Tbilisi, Georgia; production at Tbilisi ended 1989 (approximately 875 built, according to company statement); may subsequently have restarted for small batches, and factory reports sufficient parts ``in stock'' to assemble up to 75 aircraft; production at Ulan-Ude completed 1991-92; see separate entry on Su-25T.

Current Versions

Su-25 (`Frogfoot-A'): Single-seat close support aircraft. Cannon muzzle redesigned from ninth production series; aileron control rod fully faired and trim tab deleted from 10th series. Revised airbrakes with double fold on late production aircraft, and by retrofit. Export version Su-25K (kommercheskiy; commercial). Detailed description applies basically to late production Su-25K.

Su-25SM: Russian Air Forces decided to upgrade about 40 per cent of surviving Su-25s (about 80 aircraft) in March 1999. Single-seaters will be modified to Su-25SM standards; two-seaters to Su-25UBM configuration; new variant uses some equipment and systems developed for Su-25TM (Su-39). Su-25SM features Panther fire-control system with Kopyo-25 radar in a rebuilt nose (not pod-mounted, as on Su-25TM), giving compatibility with a wider range of air-to-air and air-to-ground weapons; Klen PS laser range-finder is relocated below fuselage. Revised cockpit with a new HUD and two large colour LCD MFDs, but retains standard analogue flight instruments. Irtysh EW system, with new RWR, MAWS and automatic control of chaff and flares. Structural changes limited to life-extension modifications and provision for nose-mounted radar. Sukhoi Shturmovik Consortium promises improved maintainability and a service life extended to 2,500 flying hours. Conversion of Russian Su-25s to be undertaken by Air Forces' own Aircraft Repair Works No. 121, at Kubinka; programme management by Sukhoi Stormovik Concern, which agreed in mid-2000 to fund initial two aircraft as means of launching programme. Belarusian aircraft to be upgraded at Baranovichi; Ukrainians also being converted locally. Current timescales call for acceptance tests to be completed during the third quarter of 2000. Czech Su-25s are undergoing a more modest SLEP to allow them to remain productive until replaced by Aero L 159s during 2001-2002. Su-25UB (`Frogfoot-B'): Tandem two-seat operational conversion and weapons trainer; prototype T8U-1 first flew 10 August 1985; entered production (only at Ulan-Ude) 1987; first photographs early 1989; rear seat raised considerably, giving humpback appearance; separate hinged portion of continuous framed canopy over each cockpit; taller tailfin, increasing overall height to 5.20 m (17 ft 0Ѕ in); new IFF blade antenna forward of windscreen instead of SRO-2 (`Odd

Rods'); weapons pylons and gun retained. Optional periscope over rear cockpit. Export version Su-25UBK. Su-25UBM: Two-seat Su-25s are to be modernised in the same way as the Su-25SM and, in fact, accorded higher priority to allow pilot training for those destined to fly the new single-seat version. First aircraft to be upgraded in the OKB's own Moscow workshops by Sukhoi Stormovik Concern will be a new Su-25UTG which, in April 2000, remained at Ulan-Ude factory, awaiting payment. Cost estimated as US$1 million per aircraft for UBM or US$500,000 for single-seat Su-25SM. Su-25UT (`Frogfoot-B'): As Su-25UB, but without weapons; intended as L-29/L-39 replacement for air forces and DOSAAF; prototype (converted from T8U-1) first flew 6 August 1985; demonstrated 1989 Paris Air Show as Su-28; overall length 15.36 m (50 ft 4Ѕ in); one or two only. Discontinued. Su-25UTG (G for gak: hook) (`Frogfoot-B'): As Su-25UT, with added arrester hook under tail; first flew September 1988; used initially for deck landing training on dummy flight deck marked on runway at Saki naval airfield, Ukraine; on 1 November 1989 was third aircraft to land for trials on carrier Admiral of the Fleet Kuznetsov, after Su-27K and MiG-29K; 10 built in 1989-90; five in Ukrainian use at Saki; one lost; four at Severomorsk, Kola Peninsula, for service individually on Kuznetsov. Two on board when ship deployed to Adriatic December 1995. Russian Navy received 11th aircraft in September 1997, while 12th was due in late 1998. These reportedly being given combat role: No. 11 said to be with millimetre-wave SLAR, Pastel-K RWR and TKS coded datalink for reconnaissance and target acquisition; No. 12 reportedly with anti-ship missiles and target acquisition systems also earmarked for Kamov Ka-29 upgrade. Discussions reported in early 1998 on possible further 12 for Russian Navy, but Ulan-Ude foresaw no prospect of further production after 2000. Su-25UBP: Further aircraft to similar (UTG) standard, produced by conversion of Su-25UBs, to compensate for losses to Ukraine and attrition. Su-25T/TM (Su-39): See separate entry. Su-25BM (BM for buksir misheney: target towing aircraft) (`Frogfoot-A'). Standard late-series, R-195-engined Su-25 attack aircraft, with added underwing pylons for a winch, and Planyer-M miss-distance detection system and datalink, TL-70 Kometa towed target or PM-6 rocket-propelled targets released for missile training by fighter pilots; prototype (converted T8-9) first flew 1989; 50 built at Tbilisi.

Customers

Russian tactical air forces and Naval Aviation have 225, plus 25 for traininng; pre-1985 aircraft now withdrawn. Exports to Angola (12, plus two two-seat), Azerbaijan, Belarus (currently 80), Bulgaria (36 plus four two-seat), Congo (10 ex-Georgian aircraft), Czech Republic (24, plus one two-seat), Georgia (five), Iran (seven), Iraq (45), North Korea (36, plus four two-seat), Peru (10 Su-25 and 8 Su-25UB from Belarus), Slovak Republic (11, plus one two-seat), Turkmenistan (46 currently in storage) and Ukraine (currently 64). Croatia also reported to have received a `squadron' (never uncrated, according to some reports), but denied by Croatian Air Force. Some sources suggest that Afghanistan received 12, all now out of service. Tbilisi plant quotes total of 875 single-seat Su-25s built (including 50 Su-25BMs), plus Su-25UBs. Combined production stated by Sukhoi to exceed 1,000, of which more than 200 were exported and almost 300 are two-seat.

Su-25 CURRENT OPERATORS

Unit Base Equipment

Russia (Air Force)

16th OShAP Taganrog Su-25

18th GvOShAP Galenki Su-25

237th GvTsPAT Kubinka Su-25

368th OShAP Budyennovsk Su-25

461st OShAP Krasnodar Su-25

899th OShAP Buturlinovka Su-25

968th IISAP Lipetsk Su-25

Unident OShAP Olovyannaya Su-25

Unident OShAP Chernigovka Su-25

Krasnodar Higher Military Aviation School

Krasnodar Su-25

Russia (Naval Aviation)

279th KIAP Severomorsk Su-25UTG, UBP

Angola

Unident unit Saurimo Su-25, UB

Armenia

121st ShAE Kumayari Su-25

Azerbaijan

Unident unit Kyurdamir Su-25

Belarus

206th ShAB Lida Su-25

Bulgaria

22nd Shturmova Aviobasa Bezmer/Yambol Su-25K, UBK

Czech Republic

322 Taktica Letka Namest Su-25K, UBK

Georgia (Republic)

Unident unit Kopitnari Su-25

Georgia (Abkhazia)

Unident unit unknown base Su-25

Iraq

Unident unit1 unknown base Su-25

Kazakhstan

Unident unit unknown base Su-25

Korea (North)

Unident unit unknown base Su-25

Peru

Grupo 11 Vitor Su-25UB

Slovak Republic

33/2 Letka Malacky-Kuchyna Su-25K, UBK

Turkmenistan

56 BRS Kizyl-Arvat Su-252

Ukraine

299th OShAP Saki Su-25, UTG

452nd OShAP Chortkov Su-25

Uzbekistan

59th APIB Chirchik Su-25

Notes: OshAP is Otdel'nyi Shturmovoy Aviatsion'nyi Polk (Independent Stormovik Aviation Regiment); KIAP is Korabel'nyi Istrebitel'nyi Aviatsion'nyi Polk (Shipborne Fighter Aviation Regiment); APIB is Aviatsion'nyi Polk Istrebetelei-Bombardirovchikov (Aviation Fighter-Bomber Regiment); ShAB is Shturmovoy Aviatsion'nyi Baza (Stormovik Aviation Base); BRS is Basis Reserv Samolety (Base for Reserve Aircraft). Gv prefix indicates Gvardiya (Guards) 1 Probably not in service. Seven survivors fled to Iran in 1991

2 In storage

Costs

Tbilisi factory quoting US$6 million per aircraft during 2000.

Design Features

Robust structure and systems redundancy increase resistance to small arms fire. Emphasis on survivability led to features accounting for 7.5 per cent of normal T-O weight, including armoured cockpit; pushrods instead of cables to actuate flying control surfaces (duplicated for elevators); damage-resistant main load-bearing members; widely separated engines in stainless steel bays; fuel tanks filled with reticulated foam for protection against explosion. Maintenance system packaged into four pods for carriage on underwing pylons; covers onboard systems checks, environmental protection, ground electrical power supply for engine starting and other needs, and pressure refuelling from all likely sources of supply in front-line areas; engines can operate on any fuel likely to be found in combat area, including MT petrol and diesel oil. Shoulder-mounted wings; approximately 20є sweepback; 2є 30' anhedral from roots; thickness/chord ratio 10.5 per cent; extended chord leading-edge dogtooth on outer 50 per cent each wing; wingtip pods each split at rear to form airbrakes that project above and below pod when extended; retractable PRF-4M landing light in base of each pod, outboard of small glareshield and aft of dielectric nosecap for ECM; semi-monocoque fuselage, with 24 mm (0.94 in) welded titanium armoured cockpit; pitot on port side of nose, transducer to provide data for fire-control computer on starboard side; conventional tail unit; variable incidence tailplane, with slight dihedral.

Flying Controls

Conventional and partly assisted. Hydraulically actuated ailerons, with manual back-up; multiple tabs in each aileron; double-slotted two-section wing trailing-edge flaps; full-span leading-edge slats, two segments per wing; manually operated elevators and two-section inset rudder; upper rudder section operated through sensor vanes and transducers on nose probe and automatic electromechanical yaw damping system; tabs in lower rudder segment and each elevator.

Structure

All-metal (60 per cent duralumin, 13.5 per cent titanium alloys, 19 per cent steel, 2 per cent magnesium); three-spar wings; semi-monocoque slab-sided fuselage.

Landing Gear

Hydraulically retractable tricycle type; mainwheels retract to lie horizontally in bottom of engine air intake trunks. Single wheel with low-pressure tyre on each levered suspension unit, with oleo-pneumatic shock-absorber; mudguard on forward-retracting steerable nosewheel, which is offset to port; mainwheel tyres size 840Ч360, pressure 9.30 bars (135 lb/sq in); nosewheel tyre size 660Ч200, pressure 7.35 bars (106 lb/sq in); brakes on mainwheels. Twin 25 m

2 PTK-25 cruciform

brake-chutes housed in tailcone.

Power Plant

Two Soyuz/Gavrilov R-95Sh turbojets in long nacelles at wingroots, each 40.21 kN (9,039 lb st), superseded in about 50 late production aircraft (from 1989) by R-195s, each 44.18 kN (9,921 lb st); these first trialled by T8-14 and T8-15; 5 mm thick armour firewall between engines; R-195 turbojets have pipe-like fitment (believed not initially cleared for export, thus not fitted to Su-25K) at end of tailcone, from which air is expelled to lower exhaust temperature and so reduces IR signature; non-waisted undersurface to rear cowlings, which have additional small airscoops (as three-view); self-sealing fuel tanks filled with reticulated foam. Nos. 1 and 2 tanks in fuselage between cockpit and wing front spar, and between rear spar and fin leading-edge (latter acting as collector tank) contain 2,386 litres (630 US gallons; 525 Imp gallons); and in wing centre-section, capacity 1,274 litres (337 US gallons; 280 Imp gallons); total capacity 3,660 litres (967 US gallons; 805 Imp gallons); provision for four PTB-1500 external fuel tanks on underwing pylons.

Accommodation

Single Severin (Zvezda) K-36L ejection seat with zero altitude/54 kt (100 km/h; 62 mph) envelope; sideways-hinged (to starboard) canopy, with small rearview mirror on top; flat bulletproof windscreen. Folding ladder for access to cockpit built into port side of fuselage.

Systems

28 V DC electrical system, supplied by two engine-driven generators. Dual independent hydraulic systems, pressure 206 bars (2,987 lb/sq in).

Avionics

Comms: SRO-1P (`Odd Rods') or (later) SRO-2 IFF transponder, with antennas forward of windscreen and under tail. SO-69 ATC transponder. R-862 V/UHF transceiver, R-855 emergency radio, R-828 air-to-ground radio. Flight: RSBN Tacan, MRP-56P marker beacon receiver, RV-1S radio altimeter, ARK-15M radio compass SVS-1-72-18 air data system UUAP-72 AoA and acceleration indicator. Instrumentation: ASP-17 BC-8 weapons sight incorporating AKS-750s camera gun. Mission: Klyon PS laser range-finder and target designator under flat sloping window in nose; strike camera in top of nosecone. Self-defence: SPO-15 (L-006LE) Sirena-3 radar warning system antenna above fuselage tailcone; ASO-2V chaff/flare dispensers (total of 256 flares) can be carried above root of tailplane and above rear of engine ducts. Some later aircraft fitted with Gardeniya active jammer.

Armament

One twin-barrel AO-17A 30 mm gun with rate of fire of 3,000 rds/min in bottom of front fuselage on port side, with 250 rounds (sufficient for a 1 second burst during each of five attacks). Eight large pylons under wings for 4,400 kg (9,700 lb) of air-to-ground weapons (though 1,400 kg; 3,086 lb regarded as normal maximum), including UB-32A rocket pods (each 32 Ч 57 mm S-5), B-8M1 rocket pods (each 20 Ч 80 mm S-8), 240 mm S-24 and 330 mm S-25 guided rockets, Kh-23 (AS-7 `Kerry'), Kh-25ML (AS-10 `Karen') and Kh-29L (AS-14 `Kedge') ASMs, laser-guided rocket-boosted 350 kg, 490 kg and 670 kg bombs, conventional bombs, 500 kg incendiary, anti-personnel and other cluster bombs, and SPPU-22 pods each containing a 23 mm GSh-23 gun with twin barrels that can pivot downward for attacking ground targets, and 260 rounds. Some late-production R-195-engined Russian Su-25BMs may have been wired for the carriage of Kh-58U/E (AS-11) ARMs and the associated Vynga datalink pod. Some Soviet aircraft configured to carry RN-61 nuclear weapon or associated IAB-500 `shape' for role training. Two small outboard pylons for R-3S (K-13T; NATO AA-2D `Atoll') or R-60 (AA-8 `Aphid') self-defence AAMs. SU-25BM carries TL-70 winch and Kometa towed target below port wing, with inert FAB-250 or FAB-500 to starboard.

Dimensions, External (A, Su-25K; B, Su-25UTG)

Wing span: A, B 14.36 m (47 ft 1Ѕ in)

Wing aspect ratio: A, B 6.1

Length overall: A 15.53 m (50 ft 11Ѕ in)

B 15.36 m (50 ft 4Ѕ in)

Height overall: A 4.80 m (15 ft 9 in)

B 5.20 m (17 ft 0Ѕ in)

Areas

Wings, gross: A, B 33.7 m2 (362.75 sq ft)

Weights and Loadings

Weight empty: A 9,500 kg (20,950 lb)

T-O weight: normal:

A 14,600 kg (32,187 lb)

B 13,005 kg (28,671 lb)

max: A 17,600 kg (38,800 lb)

B 16,245 kg (35,814 lb)

Max landing weight: A 13,300 kg (29,320 lb)

Max wing loading: A 522.2 kg/m2 (106.97 lb/sq ft)

B 482.0 kg/m2 (98.73 lb/sq ft)

Max power loading: A 199 kg/kN (1.95 lb/lb st)

B 184 kg/kN (1.80 lb/lb st)

Performance

Max level speed at S/L:

A M0.8 (526 kt; 975 km/h; 606 mph)

B M0.775 (512 kt; 950 km/h; 590 mph)

Max attack speed, airbrakes open:

A 372 kt (690 km/h; 428 mph)

Landing speed (typical): A 108 kt (200 km/h; 124 mph)

Service ceiling: clean: A, B 7,000 m (22,960 ft)

with max weapons: A 5,000 m (16,400 ft)

T-O run: typical: A 600 m (1,970 ft)

A, with max weapon load from unpaved surface under 1,200 m (3,935 ft)

B, on concrete 750 m (2,460 ft)

B, on carrier ramp 175 m (575 ft)

Landing run: normal: A 600 m (1,970 ft)

A, with brake-chutes 400 m (1,315 ft)

B, arrested 90 m (295 ft)

B, on concrete 1,000 m (3,280 ft)

Range with 4,400 kg (9,700 lb) weapon load and two external tanks:

at S/L: A 405 n miles (750 km; 466 miles)

at height: A 675 n miles (1,250 km; 776 miles)

g limits: with 1,500 kg (3,307 lb) of weapons: A +6.5

with 4,400 kg (9,700 lb) of weapons: A +5.2

(source: Jane's All the World's Aircraft 2001-2002)

UUAP - ULAN-UDENSKY AVIATSIONNYI ZAVOD OAO (Ulan-Ude Aviation Plant JSC)

MANUFACTURER DETAILS

ulitsa Khorinskaya 1, 670009 Ulan-Ude Tel: (+7 3012) 25 33 86, 25 74 75 and 25 35 55 Fax: (+7 3012) 25 21 47 e-mail: uuaz@buriatia.ru or uuaz@chat.ru

General Director: Leonid Ya Belykh Technical Director: Sergey V Solomin Deputy Director-General, Sales and Marketing: Ts Ts Galdanov

Founded on 1 January 1939 as GAZ 99, the Ulan-Ude Aviation Plant formed on 26 October 2000, having previously been known as Ulan-Ude Aviation Industrial Association. It manufactures a wide range of items, from helicopters and aeroplanes to spares and domestic equipment. Is only Russian plant currently producing both fixed- and rotary-wing aircraft.

Employees in 2000 totalled 5,056. The factory has built An-24 transports, Yak-25RV reconnaissance aircraft and MiG-27 fighter-bombers. Helicopter production began in 1956, progressing through Ka-15, Ka-18 and Ka-25 to the 1970 launch of Mi-8 manufacture; total of 3,700 Mi-8 series built. Current products include modern developments of the Mil Mi-8/Mi-17 series of helicopters (including ten Mi-171s delivered to China in 1999); and the Sukhoi Su-25UBK combat trainer and its related Su-39 attack aircraft. Will build Kamov Ka-62 and Ka-64. Also undertakes overhaul and upgrades, including five refurbished Mi-8AMTs supplied to Iranian Navy in 1999. Government shareholding is 38 per cent. Employees total more than 8,000. Joint venture with SME Aviation of Malaysia, 1999, for promotion of Mi-8/Mi-17 and Su-25.

SUKHOI (AVPK SUKHOI) - OPYTNYI KONSTRUKTORSKOYE BURO SUKHOGO AOOT (Sukhoi Experimental Design Bureau JSC)

MANUFACTURER DETAILS

ulitsa Polikarpova 23A, 125284 Moskva Tel: (+7 095) 945 65 25 Fax: (+7 095) 200 42 43

General Director: Mikhail A Pogosyan General Designer: Mikhail Petrovich Simonov First Deputy General Designer: Aleksandr F Barkovsky Executive Director, Manufacture: V V Golovkin Deputy General Designers: V S Konokhov (First Test Base) Boris V Rakitin (Sport Aviation Projects) Vladimir M Korchagin (Avionics) Aleksandr I Blinov (Strength Problems) O G Kalibabchuk (Aerodynamics) J I Shenfinkel (Control Systems)

OKB, which is 57 per cent owned by AVPK Sukhoi, named for Pavel Osipovich Sukhoi, who headed it from 1939 until his death in September 1975. It remains one of two primary Russian centres for development of fighter and attack aircraft, and it is notable that 60 per cent of frontline Russian Air Forces aircraft are of Sukhoi design. Bureau has widened its activities to include civilian aircraft, under konversiya programme. This offsets the drastic reduction in combat aircraft production and competition in the upgrade and overhaul market. Known deliveries in 2000 included four Su-27s for Kazakhstan and eight for China, and 10 Su-30s for latter. Sukhoi also active in design of large ground-effect vehicles, including 100/150-passenger A.90.150 Ekranoplan; see Jane's High-Speed Marine Transportation; has proposed an 860-seat airliner.

Sukhoi Advanced Technologies

General Director: Boris V Rakitin

This division is responsible for promotion and sales of Sukhoi light aircraft, such as the Su-29, Su-31, Su-38L and Su-49; and in 2000 was planning to provide funds to enable Su-29 and Su-31 production to be relocated to KAPO at Kazan from 2002. Related activities include conversion of Su-26s and Su-29s with SKS-94 extraction systems.

Nauchno-Proizvodstvennoe Kontsern Shturmoviki Sukhogo (Sukhoi Stormovik Scientific-Production Concern)

General Director: Vladimir Babak

Offers of upgrades of Su-25 `Frogfoot' to Russian and export customers. In 2000, Ukraine, Belarus, Georgia and Turkmenistan foreseen as potential purchasers.

Sukhoi Civil Aircraft

General Director: Andrey Il'in

Subdivision formed May 2000; on 5 June 2000 signed agreement with Alliance Aircraft Corporation (which see in US section) for joint development and production of StarLiner regional airliner. However, Sukhoi unilaterally cancelled agreement on 2 November 2000.

SUKHOI (AVPK SUKHOI) - GOSUDARSTVENNOYE UNITARNOYE PREDPRIYATIE AVIATSIONNYI VOYENNO-PROMYSHLENNYI KOMPLEKS SUKHOI (State Unitary Enterprise, Aviation Military-Industrial Complex Sukhoi)

MANUFACTURER DETAILS

alleya 604, ulitsa Polikarpova 23A, 125284 Moskva Tel: (+7 095) 941 76 87 Fax: (+7 095) 945 68 06

General Director: Mikhail A Pogosyan Press Officer: Yury Chervakov

AVPK Sukhoi was created, under presidential decree, in August 1996, to bring together the Sukhoi and Beriev design bureaux, the production plants at Irkutsk (IAPO), Komsomolsk-on-Amur (KnAAPO) and Novosibirsk (NAPO), and two banks, Oneximbank and Inkombank. The grouping was formally inaugurated on 30 December 1996. As originally constituted, the group comprises the wholly state-owned KnAAPO and NAPO, plus the partial state shareholdings in Sukhoi OKB (see following entry), IAPO and Taganrog. The replacement of original director Alexei Fyodorov by Pogosyan marked the conclusion of a power struggle between the OKB and the large manufacturing plants, and a move away from total central control of AVPK Sukhoi's disparate elements. Steps are under way which may lead to the merger of Sukhoi, Yakovlev and RSK `MiG', these including the appointment of Nikolov Nikitin (Pogosyan's deputy) as RSK `MiG's' General Director. Sukhoi's political acumen continues to be displayed, the company having flown Prime Minister Vladimir Putin in both the Su-25 and Su-27 before he assumed the presidency. Full privatisation remains unlikely, though AVPK Sukhoi is likely to become a Joint Stock Company.

Length 15.53m

Wingspan 14.36m

Height 4.8m

Weight Empty 9500kg

Max T/O 17 600kg

Max Speed 975km/h

Range 1250km - 750km (at low level)

Ceiling 5 000m (full weapons)

Powerplant two Soyuz/Tumansky R-195 turbojets

Thrust 88.36kN

Customers CIS 250+, Czech and Slovak Rpublics 50+, Hungary 50+, Iraq 25+, North Korea 20+, Syria 60+

Su-25 Tech. Specs.

Crew: 1

Length, m: 15,53

Height, m: 4,8

Wing span, m: 14,36

Wing area, mІ: 33,7

Weight empty, kg: 9500

Weight normal, kg: 14600

Weight max, kg: 17600

Max fuel, kg: 3840

Service ceiling, m: 7000

Take-off speed, km/h: 230

Landing speed, km/h: 200

Max mach at sea level: 0,8

Max mach at height: 0,8

G limit: 5,2

Max wing loading, kg/mІ: 522,2

Max power loading, kg/kN: 218,9

Max rate of climb at sea level, m/s: 40

Range with max internal fuel, km: 1250

Armament: GSh-23 gun, 4400 kg on 10 external pylons

GOSUDARSTVENNOYE UNITARNOYE PREDPRIYATIE AVIATSIONNYI VOYENNO-PROMYSHLENNYI KOMPLEKS/AK SUKHOI (State Unitary Enterprise, Aviation Military-Industrial Complex/Concern Sukhoi)

SUKHOI Su-25TM (Su-39)

Type

Attack fighter.

Programme

Developed as an ATM-armed derivative of the standard Su-25, with a two-crew concept similar to that used in the Mi-24 `Hind'. Plans to put the WSO in the front cockpit were abandoned at an early stage. Airframe is based on that of the Su-25UB, with which it shares about 85 per cent commonality. Three Su-25T development aircraft (Sukhoi T8M; numbered 08, 09 and 10) were converted Su-25UB airframes, with humped rear cockpit faired over and internal space used to house new avionics and extra tonne of fuel; conversions began 1976; first flight by converted first prototype Su-25UB 17 August 1984; construction at GAZ 31 Tbilisi, Georgia, of initial batch of 20 preseries aircraft for air force acceptance testing began 1979; first one flew July 1990 and deliveries to development unit at Akhtubinsk began 1991, although 12 reported in long-term storage at Tbilisi in early 1997, when Georgia reportedly issued a requirement for 50. Passed State Acceptance Tests in 1993. Production transferred to Ulan-Ude (Su-25UB/UTG production plant where two were assembled in 1999, with six more to follow in 2000 and 12 in 2001). Redesignated Su-25TM after provision for 3-CM waveband Kopyo-25 radar, Schkval-M OEPS, Kinzhal MMW radar and Khod IIR pods and other equipment changes; T8M-3 first exhibited at Dubai '91 Air Show as export Su-25TK; version (aircraft 20) with Kopyo-25 radar pack, for improved night/bad weather attack capability, shown at Moscow Air Show '95; at that time, one Su-25TM had been completed at Ulan-Ude plant and first two preseries Su-25T aircraft had been updated to same standard. Two further Su-25TMs built at Ulan-Ude in 1997 and 1998, and will be followed by first batch of four production Su-25TMs. Remaining 20 production Su-25Ts to be similarly upgraded. Known to Sukhoi, but not Russian Air Forces, as Su-39 `Strike Shield'; aircraft 21 at Moscow Air Show, 1997, carried only this designation and was also exhibited in 1999, as Su-25TM; RLPK-25 radar, derived from Kopyo-25, fully installed in pack 1996; development continues, although originally scheduled for completion 1997. Licence for production offered to PZL Mielec of Poland, late 1997, as debt resettlement but not taken up.

Customers

Russian Air Forces have eight Su-25Ts, delivered to Akhtubinsk test centre (two) and Lipetsk training base (six) in 1990-91; further 12 remain uncompleted at Tbilisi, but all planned to be upgraded at Ulan-Ude to Su-25TM. Four Lipetsk aircraft took part in bombing of Chechnya during 2000. Two of Tbilisi stock delivered to Ethiopia (with two UB trainers) in early 2000. Initial batch of seven Su-25 TMs built at Ulan-Ude; third aircraft was first delivered to Russian Air Forces in early 1998. Initial Russian requirement for 24 Su-25TMs to serve in six regional rapid-deployment groups, each of four Su-25TMs and 12 Su-25s, plus helicopters. Two TMs (Nos. 4 and 5) ordered by Russia in 1999 and due for delivery in 2001; further three planned for funding in 2001. Georgia has requirement for 50 TMs, and reportedly ordered three in 1996 and more in 1998.

Costs

Rb50 million (US$8.3 million) flyaway (1998).

Design Features

Basically as Su-25 (which see), but embodies lessons learned during war in Afghanistan, particularly survival in intense anti-aircraft defence environment and night/bad weather capability. All sub-variants use increased-thrust R-195 engines. Welded cockpit `bathtub' of lighter ABVT-20 titanium alloy armour, weight of polyurethane foam fuel tank filling and protective coatings increased. Centre-fuselage fuel pipes and control rods strengthened; gap between fuel tanks and air ducts filled with elastic porous material to avoid spillage into ducts following combat damage; additional armour for fuel system and avionics compartment. Reported to use special radar absorbent paint, previously tested on at least one Su-25. New nav system makes possible flights to and from combat areas under largely automatic control; equipment in widened nose includes TV activated some 5 n miles (10 km; 6 miles) from target; subsequent target tracking to an accuracy of 0.6 m (2 ft), weapon selection and release automatic; wingtip countermeasures pods introduced; gun transferred to underbelly position, on starboard side of farther-offset nosewheel. New, depressible 45 mm cannon originally planned. IR signature reduced by factor of three to four. Wing leading-edge sweepback 19є 54', dihedral 2є 30', incidence 0є 43'.

Flying Controls

Basically as Su-25. Trim only on rudder; artificial feel in lateral and longitudinal channels. Hydraulically actuated elevator. SAU-8 automatic control system linked to WDNS.

Landing Gear

KT-163D mainwheels, with tyre size 840Ч360, pressure 9.30 bars (135 lb/sq in); KH-27A nosewheel further offset to port, with tyre size 680Ч260, pressure 7.35 bars (106 lb/sq in); metal and ceramic disc brakes, with anti-skid units. Two PTK-25 cruciform brake-chutes, each 13.0 m

2 (140 sq ft).

Power Plant

Improved Soyuz/Gavrilov R-195Sh turbojets. Ten internal fuel tanks, with new Nos. 3 and 4 tanks in fuselage; total capacity 4,890 litres (1,292 US gallons; 1,076 Imp gallons). Provision for four 800 litre (211 US gallon; 176 Imp gallon) or two 1,150 litre (304 US gallon; 253 Imp gallon) underwing tanks. Single-point pressure fuelling in starboard engine air intake duct; optional gravity fuelling. Additional air intakes on upper surface of engine nacelles to further cool jet exhaust.

Accommodation

As Su-25 but probably with zero/zero ejection seat.

Systems

Pressurised cockpit, maximum differential 0.25 bar (3.55 lb/sq in). Hydraulic system using AMG-10 fluid; flow rate 76 litres (20.0 US gallons; 17.7 Imp gallons)/min; pressure 207 bars (3,000 lb/sq in). AC and DC electrical systems. Gaseous oxygen system.

Avionics

Radar: Kinzhal (dagger) 8 mm MMW radar abandoned and replaced by podded Kopyo-25 pending provision of a new Kinzhal using Russian rather than Ukrainian parts. Flight: Nav system includes air data system, twin INS, A-312 RSBN radio-nav system combining Tacan and ILS, A-723 long-range Loran/Omega radio-nav, ShO-13A Doppler, RV-21 radar altimeter and GPS. Instrumentation: HUD; SUV-25T Voskhod nav/attack system on stabilised platform, with two Orbita computers, and Krasnogorsk Schkval I-251 nose-mounted electro-optical system for precision attacks on armour. Mission: SUV-39 I-251 weapons control system. Larger window in nose for TV, laser range-finder and target designator of Krasnogorsk OMZ I-251 Schkval daylight system, all using same stabilised mirror, Ч23 magnification lens and cockpit CRT; Khod (motion) night attack IIR pack, with Merkur LLTV and Prichal laser designator, and Phazotron Kopyo-25 radar pod on centreline pylon. Kopyo-25 detection range 13.5 n miles (25 km; 15.5 miles) for tanks, 40 n miles (75 km; 47 miles)

for small ships, 13.5 to 31 n miles (25 to 57 km; 15.5 to 35 miles) air-to-air; able to track eight targets and engage two simultaneously. Self-defence: Irtysh DASS, with Pastel radar warning/emitter location system; UV-26 chaff/flare dispensers (192 cartridges) in top of fuselage tailcone and in large cylindrical housing at base of rudder that also contains L-166SI Sukhogruz 6,000 W Caesium lamp active IR jammer. Optional MSP-410 Omul or Gardeniya underwing active radar jamming pods on outboard underwing pylons.

Armament

One NNPU-8M twin-barrel 30 mm gun (same AO-17A as Su-25, but in new external VPU-17A mounting) with 200 rounds; 10 external stores attachments; two eight-round underwing clusters of Vikhr M (AT-X-16) tube-launched primary attack missiles able to penetrate 900 mm of reactive armour; other weapons include laser-guided Kh-25ML (AS-10 `Karen') and Kh-29L (AS-14 `Kedge'), TV-guided Kh-29T (AS-14 `Kedge'), anti-ship Kh-35 (AS-20 `Kayak') and anti-radiation Kh-58U (AS-11 `Kilter') or Kh-31P (AS-17 `Krypton') ASMs, KAB-500KR laser-guided bombs, S-25L laser-guided rockets, conventional bombs from 50 to 500 kg each, RBK-250 and RBK-500 cluster bombs, KMGU-2 submunition dispensers, SPPU-687 gun pods (containing a GSh-1-30 with 150 rounds) S-8, S-13 and S-25 rockets, and R-27R/RE (AA-10 `Alamo-A/C'), RVV-AE (R-77; AA-12 `Adder') and R-73 (AA-11 `Archer') AAMs.

Dimensions, External

Wing span 14.52 m (47 ft 7Ѕ in)

Wing chord: at root 3.00 m (9 ft 10ј in)

at tip 1.025 m (3 ft 4ј in)

Wing aspect ratio 7.0

Length overall 15.35 m (50 ft 4Ѕ in)

Height overall 5.20 m (17 ft 0Ѕ in)

Tailplane span 4.58 m (15 ft 0Ѕ in)

Wheel track 2.505 m (8 ft 2Ѕ in)

Wheelbase 3.58 m (11 ft 9 in)

Areas

Wings, gross 30.10 m2 (324.0 sq ft)

Ailerons (total) 1.51 m2 (16.25 sq ft)

Trailing-edge flaps (total) 4.44 m2 (47.79 sq ft)

Leading-edge slats (total) 3.16 m2 (34.02 sq ft)

Fin 5.28 m2 (56.84 sq ft)

Rudder 0.75 m2 (8.07 sq ft)

Tailplane 5.61 m2 (60.39 sq ft)

Elevators (total) 1.88 m2 (20.24 sq ft)

Weights and Loadings

Max combat load 5,000 kg (11,023 lb)

Max fuel: internal 3,840 kg (8,465 lb)

external 3,070 kg (6,768 lb)

Max T-O weight 20,500 kg (45,194 lb)

Max landing weight 13,200 kg (29,100 lb)

Max wing loading 681.1 kg/m2 (139.49 lb/sq ft)

Max power loading 232 kg/kN (2.28 lb/lb st)

Performance

Never-exceed speed (VNE) M0.82

Max level speed at S/L M0.77 (512 kt; 950 km/h; 590 mph)

Max cruising speed at 200 m (650 ft) 378 kt (700 km/h; 435 mph)

Econ cruising speed 350 kt (650 km/h; 404 mph)

Landing speed 130 kt (240 km/h; 150 mph)

Max rate of climb at S/L 3,480 m (11,415 ft)/min

Rate of climb at S/L, OEI 1,020 m (3,345 ft)/min

Service ceiling 10,000 m (32,800 ft)

Service ceiling, OEI 9,000 m (29,520 ft)

T-O run 650 m (2,135 ft)

Landing run 750 m (2,465 ft)

Combat radius with 2,000 kg (4,410 lb) weapons:

at low altitude 216 n miles (400 km; 248 miles)

at height 340 n miles (630 km; 391 miles)

Ferry range 1,214 n miles (2,250 km; 1,398 miles)

g limit +6.5

(source: Jane's)