STUDENT HANDOUT TITLE: AH-64D AERIAL ROCKET SYSTEM (LOT 11...
Transcript of STUDENT HANDOUT TITLE: AH-64D AERIAL ROCKET SYSTEM (LOT 11...
UNITED STATES ARMY AVIATION CENTER OF EXCELLENCE
FORT RUCKER, ALABAMA
April 2009
STUDENT HANDOUT
TITLE: AH-64D AERIAL ROCKET SYSTEM
(LOT 11)
FILE NUMBER: 011-0922-3.5
Proponent For This Student Handout Is:
COMMANDER, 110TH
AVIATION BRIGADE
ATTN: ATZQ-ATB-AD
Fort Rucker, Alabama 36362-5000
FOREIGN DISCLOSURE STATEMENT: (FD6) This product/publication has been reviewed by the product developers in coordination with the USAACE Foreign Disclosure Authority. This product is releasable to students from foreign countries who have purchased the AH-64D model, but the IETM is not releasable.
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TERMINAL LEARNING OBJECTIVE:
NOTE: Inform students of the following Terminal Learning Objective requirements.
At the completion of this lesson, you (the student) will:
ACTION: Identify components, controls, procedures, inhibits, and ballistics factors of
the AH-64D Aerial Rocket System (ARS).
CONDITIONS: In a classroom environment, given an AH-64D Operator's Manual (TM 1-
1520-251-10),Aircrew Training Manual (TC 1-251), and Helicopter Gunnery
(FM 3-04.140 (FM 1-140))..
STANDARD: Identify the components, controls, procedures, inhibits, and ballistics factors
of the AH-64D Aerial Rocket System (ARS) and receive a ―Go‖ by answering
7 of 10 questions on scoreable unit 2 of criterion referenced test 011-1081
IAW the SEP.
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A. ENABLING LEARNING OBJECTIVE 1
After this lesson, you will:
ACTION: Identify the components of the ARS.
CONDITIONS: Given a written test without the use of student notes or references.
STANDARD: In accordance with TM 1-1520-251-10 and TC 1-251.
1. Learning Step/Activity 1
Identify the components of the ARS.
Figure 1. Aerial Rocket System (ARS).
a. M140 ARS
(1) The M140 ARS provides AH-64D pilots with the capability to remotely
select:
(a) Rocket type
(b) Warhead
(c) Fuze
(d) Quantity desired
(2) The ARS can fire the 2.75-inch/70mm Folding Fin Aerial Rockets
(FFAR) in two firing modes:
(a) Independently Pilot (PLT) or Copilot/Gunner (CPG) controlled
(b) Cooperative (simultaneously PLT/CPG controlled)
D-4
Figure 2. Pylons.
b. ARS components
(1) Pylons. The pylons are mounted on the underside of the wings and
provide mounting for the following:
(a) The ejector rack contains attaching lugs for securing the store
to the pylon and the explosive ejector for stores jettison.
(b) The Pylon Interface Unit (PIU) provides interface between the
Weapons Processor (WP) and the pylon discrete signals.
(c) The pylon actuator articulates the pylon in elevation by
applying hydraulic power in response to pointing commands
from the WP.
1) Ground stow
a) The Ground Stow mode commands the pylons
to the stow position (–5°) so that the wing
stores are parallel to the ground (level terrain).
b) The Ground Stow mode is automatically
commanded when the Squat switch indicates
GROUND when a rocket launcher or a hellfire
launcher is present. The pylons can be
manually ground stowed while in flight via the
Weapon Utility (WPN UTIL) page.
2) Flight stow
a) The Flight mode commands the pylons to a
single fixed position (+4°).
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b) The Flight mode is automatically commanded
on at takeoff when the squat switch indicates
airborne for more than 5 seconds.
3) In flight, the pylons remain in the Flight mode until
missiles or rockets are actioned. Pylons are
independently articulated through a range from
+4.9° to –15° in elevation.
(d) The pylons are equipped with hydraulic and electrical quick-
disconnect provisions and contain electrical aircraft interfaces
for the 2.75-inch ARS, auxiliary fuel tanks, Hellfire Modular
Missile System, and servo control of rack positions.
Figure 3. Pylon Interface Unit (PIU).
(2) PIU
(a) The PIU is a remote processor that communicates with the WP
and provides interface to the M261 rocket launchers and pylon
actuators.
(b) The PIUs perform rocket fuzing and squib ignition.
(c) PIUs are solid state Remote Terminal (RT) Line Replaceable
Units (LRUs).
(d) Each PIU provides the necessary Input/Output (I/O) and
processing capability to control up to nineteen 2.75-inch FFAR.
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Figure 4. M261 Rocker Launcher.
(3) M261 rocket launchers
(a) The M261 rocket launcher carries and launches the 2.75-inch
(70mm) FFAR within the operating environment of the AH-64D
helicopter.
(b) The rocket pod weighs approximately 86.8 pounds.
(c) The pods are 65 inches long.
(d) The pods have a diameter of 16 inches.
(e) Each rocket launcher has 19 individual rocket tubes.
(f) Up to four rocket launchers (one per pylon), for a total of 76
rockets can be loaded on the AH-64D helicopter.
(g) Two top mounted suspension lugs allow attachment to the
wing pylon.
(h) Two electrical connectors on the top of the launcher provide
fuzing and firing interface.
1) The forward connector provides the fuzing.
2) The aft connector provides the firing circuit.
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(i) Rocket pods can be jettisoned individually or all at once from
either crewstation.
Figure 5. STORES JETTISON (JETT) Panel.
(4) STORES JETTISON (JETT) panel
(a) The STORES JETTISON panel is located on the left console
in the pilot and CPG crewstations. The STORES JETTISON
panel provides the pilot or CPG with the capability to jettison
individual wing stores.
(b) Pressing one or more of the pushbuttons on the STORES
JETTISON panel will illuminate the selected pushbutton(s) in
both crewstations to indicate that the Stores Jettison function
at the selected station is now in the ARM mode.
(c) Pressing an illuminated pushbutton a second time will cause
that pushbutton light to be extinguished, indicating that stores
jettison at that station is no longer in the ARM mode.
(d) Pressing the recessed JETT pushbutton will cause stores to
be jettisoned from all stations in the ARM mode.
(e) Only that crewstation arming the STORES JETTISON panel
can de-arm it. Once armed, either crewstation can activate the
Stores Jettison function.
D-8
Figure 6. Emergency Stores Jettison (JETT) Switch.
(5) Emergency Stores Jettison switch
(a) Located on the flight section of the collective grip.
(b) Provides the pilot or CPG with the capability to jettison all
external wing stores at the same time.
(c) Pressing the guarded JETT switch will cause all external
stores to be jettisoned from the aircraft at the same time.
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Figure 7. LOAD / MAINTENANCE PANEL (LMP).
(6) LOAD / MAINTENANCE PANEL (LMP)
(a) Located in the right aft avionics bay.
(b) Provides the ground crew with the capability to manually enter
and display rocket weapon data and position pylons for loading
wing stores.
1) Display and specify rocket type associated with
each rocket zone.
2) Position the pylons (PYLON POS) for Maintenance
Operational Checks (MOCs) with a range of UP +4°
to DOWN –5°.
3) Override the Squat switch (AIR/GND mode) setting
to simulate airborne conditions for troubleshooting
and testing on the ground.
CAUTION
There is no indication in the cockpit when the SQUAT ORIDE switch is in the AIR position.
The possibility exists that the Area Weapon System (AWS) could inadvertently be driven
into the ground.
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(c) The LMP provides the capability to check/verify rocket type
within each of the rocket zones on pre-flight.
(d) The WPN UTIL LOAD page is provided on the Multipurpose
Display (MPD) to permit aircrews to modify (override) the LMP
zone inventory in the event an entry error is made by the load
crew during munition loading or an LMP failure occurs.
NOTE: At aircraft power-up, the WP will read the rocket zone inventory from the LMP.
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CHECK ON LEARNING
1. Pylons are independently controlled through a range of ________ in elevation.
ANSWER: __________________________________________________________________
__________________________________________________________________
2. The ________ provides the interface between the weapons processor and the pylon
discrete signals.
ANSWER: __________________________________________________________________
__________________________________________________________________
3. The flight mode is automatically commanded on takeoff when the squat switch indicates
airborne for more than _____ seconds.
ANSWER: __________________________________________________________________
__________________________________________________________________
4. The STORES JETTISON panel allows for ________ jettison of wing stores while the
emergency JETT pushbutton will jettison all stores.
ANSWER: __________________________________________________________________
__________________________________________________________________
5. The pylons are positioned to ground stow (WPN UTIL Page) which commands the
pylons to ______degrees.
ANSWER: __________________________________________________________________
__________________________________________________________________
D-12
ENABLING LEARNING OBJECTIVE 2
ACTION: Identify the controls and displays of the ARS.
CONDITIONS: Given a written test without the use of student notes or references.
STANDARD: In accordance with TM 1-1520-251-10, TC 1-251, and FM 3-04.140(FM 1-
140).
2. Learning Step/Activity 1
Identify the controls and displays of the ARS.
Figure 8. ARMAMENT Panel.
a. ARS controls and displays
(1) ARMAMENT panels
(a) The crewstation ARMAMENT panels provide pushbuttons
used for arming and safing the aircraft armament as well as
overriding the aircraft Squat switch when the aircraft is on the
ground.
(b) The ARMAMENT panel is located on the Instrument panel in
each crewstation. It provides two pushbuttons to activate
switches.
1) The ARM/SAFE indicator is a momentary-action,
illuminated pushbutton. This is an aircraft common
switch. The aircraft is either armed or safe in both
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crewstations, regardless of who activated the
switch.
a) The ARM legend is illuminated Night Vision
Imaging System (NVIS) yellow.
b) The SAFE legend is illuminated NVIS green.
2) The GND ORIDE (ground override) indicator is a
momentary-action, illuminated pushbutton
illuminated NVIS green ON.
3) Upon application of aircraft power, the System
Processor (SP) establishes the aircraft state as
SAFE.
Figure 9. Weapon Page Rocket Format.
(2) Weapon (WPN) page Rocket (RKT) format. Rocket moding is
controlled from the Weapons page, with the rocket format displayed.
(a) Selecting the RKT button on the WPN page or actioning the
rockets with the Weapons Action Switch (WAS), will cause the
rocket icons to become inverse video and rocket moding
controls to be displayed.
(b) If the RKT selections are not initialized with preloaded data,
the firing quantity, penetration distances, and warhead/fuze
options are initialized with default values.
(c) Rocket icons and indicators
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1) Rocket icons will be displayed respective to their
location on the wing stations.
2) Rocket type will be displayed within the rocket icon,
when a rocket type selection has been made from
the inventory grouped option.
3) The rocket type will be selected automatically if
only one type of rocket is inventoried.
Figure 10. Weapon Page Rocket Format—DEGR Icon.
(d) RKT launcher Degraded (DEGR) or FAIL icons. The ARS can
detect Degraded or Failed modes through Built-In-Test (BIT)
processing.
1) DEGR
a) A degraded rocket launcher is considered to
be one where the PIU can select certain
rockets for firing, but cannot select all the
rockets in that launcher for firing; that is, one
or more rocket launcher tubes is not available
for firing, or warhead fuzing capability is lost.
b) When a station is in DEGR mode, a yellow
DEGR icon is displayed around the rocket
launcher icon.
D-15
Figure 11. Weapon Page Rocket Format—FAIL Icon.
2) FAIL
a) A failed rocket launcher indicates that no
rockets can be fired from a particular station
for one reason or another, such as a failed
PIU.
b) When a system failure renders a station
unavailable, a yellow FAIL icon is displayed
around the rocket launcher icon.
c) Additional indications of system failure are
provided by the Data Management System
(DMS).
D-16
Figure 12. Weapon Page Rocket Format—Rocket Inventory.
(e) Rocket inventory
1) Rocket INVENTORY buttons are used to select the
desired rocket warhead and type.
2) The Option buttons include a warhead/rocket
motor-type label and the total number of rounds
available. These values are loaded at the LMP but
can be updated on the LOAD page.
3) The number of rounds shown in the Option buttons
will decrease in real time to reflect the number of
rounds remaining as the rockets are fired. When all
rockets of the selected type have been fired, the
selected Rocket Warhead Option button will blank
and the label will be removed from the icon.
4) Another Rocket Warhead Option button (if
available) must be selected to resume rocket firing,
unless it is the last type/warhead remaining.
5) Rocket inventory selections are independent in
each crewstation.
D-17
Figure 13. Weapon Rocket Quantity Format.
(f) Rocket quantity
1) The Rocket Quantity (QTY) button, on the WPN
RKT (Weapon Rocket) page, is used to select the
number of rockets to be fired: 1, 2, 4, 8, 12, 24, and
ALL; the default quantity is 2.
2) Selecting one of the QTY selections will set that as
the quantity and return to the Weapons page rocket
format. The selection will be displayed under the
QTY button label.
3) Rocket quantity selections are independent in each
crewstation, except in the Cooperative mode where
the QTY and TYPE will default to the CPG, (then,
the last-select logic applies).
4) Quantities greater than one will be fired in pairs,
one-half of each quantity setting from the left wing
store and one-half from the right wing store.
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Figure 14. Weapon Rocket Penetration Format.
(g) The Rocket Penetration (PEN) button on the WPN RKT page
is used to select the desired warhead fuze penetration setting.
These selections are independent in each crewstation.
1) The PEN button is displayed only when warheads
requiring a penetration selection, such as those
with M433 Fuze, are loaded.
2) Selecting the PEN button calls up the following
options:
a) 10—Detonate 10 meters after jungle canopy
contact.
b) 15—Detonate 15 meters after jungle canopy
contact.
c) 20—Detonate 20 meters after jungle canopy
contact.
d) 25—Detonate 25 meters after jungle canopy
contact.
e) 30—Detonate 30 meters after jungle canopy
contact.
f) 35—Detonate 35 meters after jungle canopy
contact.
g) 40—Detonate 40 meters after jungle canopy
contact.
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h) 45—Detonate 45 meters after jungle canopy
contact.
i) BNK—Set to defeat bunkers up to 3 meters
(9.84 feet) thick.
j) SPQ—Set to detonate when fuze makes
contact with any object.
Figure 15. TOTAL ROCKETS Status Window.
(h) TOTAL ROCKETS status window
1) The TOTAL ROCKETS status window is displayed
when there is a difference between the number of
rockets available for firing and the number of
rockets actually of the selected type. The status
window and messages are displayed in white.
2) An example for displaying this status window would
be if rocket fuzing failed and the rockets did not fire.
In this case, the SP would inventory the total
rockets at each trigger pull but decrement the failed
rockets from the displayed INVENTORY. When a
rocket misfire occurs, the misfired rocket is no
longer available for firing.
3) The total rockets available for firing (of the selected
type) will be displayed in the INVENTORY Grouped
Option buttons.
4) The total of all rockets (including failed or misfired)
will be displayed in the TOTAL ROCKETS status
window.
D-20
5) Due to safety considerations, the ARS cannot be
cycled off and on to reinventory the rockets while in
the air. This prevents a double fuzing pulse to
remote set-type-rockets, which may result in
unreliable fuze settings. Once on the ground, the
RKT system can be cycled on the WPN UTIL page
to reinventory the rockets.
Figure 16. UTIL LOAD Page.
(i) Rocket Inventory (INV) options
1) The RKT INV bracket on the WPN LOAD page will
display the five ZONE buttons possible for selecting
the desired rocket type loaded into that particular
tube location.
2) A zone selection will be highlighted in white with a
question mark when rocket inventory data is not
valid.
3) Selecting one of these multi-state buttons within the
RKT INV group will call up the rocket ZONE status
window and inventory options.
D-21
Figure 17. Rocket Launcher Inventory.
(j) The rocket launcher zone selection is based on the number of
launchers available.
1) Zone E is available if any rocket pods are installed
on any wing store.
2) Zones C and D are available if inboard pods are
installed.
3) Zones A and B are available if outboard pods are
installed.
4) The RKT INV zone (A, B, C, D, and E) selections
located on the LOAD page are used to select the
desired rocket type and warhead for a particular
zone.
5) When a ZONE selection is made, the LOAD page
will display that selected zone with the rocket type
selections available.
CAUTION: Due to the possibility of surging the engines, do not fire rockets from the inboard stations.
Fire no more than pairs with two outboard launchers every three seconds, or fire with only one
outboard launcher installed without restrictions (ripples permitted). These are the only conditions
permitted.
NOTE: The cautions and notes in Chapter 4 of the -10 covers several parameters for rocket operation
and configuration that must be addressed before firing.
D-22
Figure 18. Rocket Inventory and Zone Options.
Figure 19. Common Rocket Types.
D-23
6) The inventory selections may include the following
rocket types:
a) MK-66 Rocket Motor/Warheads
1 6PD—Point detonation, high
explosive
(a)M151 Warhead HE is anti-
personnel, anti-material and
referred to as the ―10 pounder‖.
The body is olive drab with a
yellow band and yellow or black
markings. This warhead contains
2.3 pounds of composition B with
a bursting radius of 10 meters and
a lethality radius of more than 50
meters. The compatible fuze for
this warhead setting (6PD) is the
M423, which will arm in flight
approximately 52 to 110 meters.
(b)M229 Warhead is HE anti-
personnel, anti-material and
referred to as the ―17 pounder‖.
This warhead is an elongated
version of the M151. The body is
olive drab with yellow markings.
This warhead contains 4.8 pounds
of composition B with a bursting
radius of +14 meters and a
lethality radius of more than 75
meters. The compatible fuze for
this warhead setting (6PD) is the
M423, which will arm in flight
approximately 52 to 110 meters.
There is no ballistic solution for
the M229 warhead.
(c)M274 Warhead is the smoke
signature training rocket, which
will match the ballistic settings of
the M151 warhead. The body of
the warhead is blue with a brown
band. Contains 2 ounces of
potassium perchlorate with
aluminum powder, this will
produce a flash bang smoke
signature. The compatible fuze for
this warhead setting (6PD) is a
modified M423.
D-24
2 6RC—Penetration, high explosive
The M151 and M229 warheads
will accept the M433 fuze (6RC),
which uses the PEN settings for
penetration. The M433 arms at
approximately 143 meters
downrange. There is an
increased risk of premature fuze
function.
3 6MP—Time, multi-purpose
submunition (MPSM)
(a)M261 Warhead provides improved
lethality against light armor,
wheeled vehicles, material, and
personnel. The body of the
warhead is olive drab with yellow
markings and band. This warhead
contains 9 M73 SM’s with the
M230 omnidirectional fuze with a
M55 detonator is used on each
SM and functions regardless of
impact. Each SM contains 3.2
ounces of composition B,
internally scored steel body to
optimize fragments against
personnel and material. The SM
arms when the ram air decelerator
(RAD) deploys. The RAD stops
forward velocity and stabilizes the
descent. Upon detonation the SM
body explodes into high-velocity
fragments (about 195 at 10 grains
each up to 5,000 feet per second
that can penetrate more than 4
inches of armor) to defeat soft
targets. A SM will land 5 degrees
off center 66% of the time, which
has a 90% probability of
producing casualties against
prone exposed personnel within a
20 meter radius. A SM will land
30 degrees off center 33% of the
time, which has a 90% probability
of producing casualties against
prone exposed personnel within a
5 meter radius. The compatible
fuze for this warhead setting
(6MP) is the M439, which will arm
in flight approximately 96 to 126
meters.
D-25
(b)M267 Smoke signature Training
rocket, which will match the
ballistic settings of the M261
(MPSM). The body of the
warhead is blue with a brown
band and while markings. This
warhead contains 3 M75 practice
(1 ounce of pyrotechnic powder)
and six inert SM to replicate the
M261. The compatible fuze for
this warhead setting (6MP) is
M439.
4 6IL—Time, illumination
(a)M257 was designed for battlefield
illumination. The body of the
warhead is olive drab with white
markings. M257 contains 5.4
pounds of magnesium sodium
nitrate. The candle descends 15
feet per second and provides one
million candlepower for 100-120
seconds. Preset to deploy
approximately 3500 meters down
range. It can illuminate
approximately one square
kilometer. The compatible fuze
(6IL) is the M442 (9 second fuze),
which will arm 150 meters from
the launcher.
(b)M278 Infrared Illumination
Warhead is designed for target
illumination using NVG’s. The
body of the warhead is black with
white markings. The M278 puts
out an equivalent of million
candlepower of IR illumination.
Preset to deploy approximately
3500 meters down range. The IR
flare will provide IR light for
approximately 180 seconds. The
compatible fuze is the M442 (6IL).
5 6SK—Time, smoke. M264 red
phosphorus (RP) is a smoke-screen
warhead. The body of the warhead is
light green with a brown band and
black markings. The warhead contains
72 RP wedges that are air-burst
D-26
ejected over the intended target area.
The smoke generated by 14 rockets
will obscure a 300 to 400 meter front,
in less than 60 seconds for 5 minutes.
The smoke generated by the RP will
block the entire visual spectrum as
well as much of the IR spectrum. The
effective range is 1000 to 6000
meters. The compatible fuze is the
M439 (6SK).
6 6FL—Flechette. M255 rocket is
equivalent to the tanker’s canister
round. The warhead body is olive drab
cylinder with white diamonds and
white markings. This rocket contains
1,179 60 grain steel flechettes. They
are packed in a red pigment powder
that can alert the crew to the point of
payload deployment. The flechette
warhead detonates 150 meters before
the range set at launch. The flechette
cloud is a cylinder of about 49.7 feet
in diameter. The compatible fuze is
the M439 (6FL).
b) CRV7 Rocket Motor/Warheads (Not currently
used)
1 PD7—Point detonation, high
explosive
2 RA7—Armor piercing, high explosive
3 IL7—Time, illumination
4 SK7—Time, smoke
5 MP7—Time, multi-purpose
submunition
6 FL7—Flechette
7) The available rocket inventory options are
presented on both sides of the display. CRV7
warhead types are shown in the L1–L6 Multi-State
Option buttons. Similarly, the MK-66 warhead
types are shown in the R1–R6 Multi-State buttons.
Selecting an inventory option will change the
inventory for that zone and return to the LOAD
page. The type selections will be displayed on the
left side of the WPN page when the rocket system
is selected.
(k) The M433 (PEN) allows the pilot to set the fuse for bunker
penetration and M439 resistance capacitance fuze allows for
the pilot to remotely set the fuze for airburst.
D-27
1) The fuze has no internal battery; the required
voltage is supplied to the capacitor by the aircraft
through an umbilical assembly.
2) If a selected rocket fails to launch, the WP will not
allow the operator to fire the selected rocket again
until the rocket system is re-inventoried (on the
Squat switch).
3) This procedure precludes the possibility of
overcharging the delay circuit and premature
explosion.
4) In the AH-64D, the voltage sent to the capacitor is
measured for the proper amount before allowing
the rocket to fire. This will ensure a far more
accurate fuze detonation at the set range.
Figure 20. Weapons Action Switch (WAS).
(3) Weapons Action Switch (WAS)
(a) The WAS is a five-position, momentary contact switch that
actions the selected weapon. The actioned weapon may be
deselected by re-actioning the same weapon or by actioning
another weapon.
(b) The WAS is mounted on the PLT/CPG cyclic and on the
TEDAC Left Handgrip (LHG). Weapons selection (action) is as
follows:
(c) G (12 o’clock position on the WAS): Actions the M230 30mm
automatic gun.
(d) R (9 o’clock position on the WAS): Actions the ARS.
D-28
(e) M (3 o’clock position on the WAS): Actions the Hellfire missile
system.
(f) A (6 o’clock position on the WAS): Is a growth function for Air-
To-Air (ATA) missiles.
Figure 21. Trigger Switches.
(4) Trigger switches
(a) The Trigger switch is a three-position, guarded switch used to
fire the selected weapon.
(b) It is mounted on the forward portion of the pilot and CPG
cyclics and on the forward portion of the TEDAC LHG.
1) Pressing the trigger to the first detent will fire a
weapon if no inhibits exist.
2) Pressing the trigger to the second detent will
override the weapons performance inhibits and fire
the weapon. Safety constraints can never be
overridden.
D-29
Figure 22. Rocket Steering Cursors.
(5) Rocket steering cursors
(a) The rocket steering cursor is a dynamic I-beam symbol that
indicates the delivery mode and how to point the aircraft for
rocket delivery. The I-beam represents the articulation range
of the pylons.
1) If the pilot or CPG actions the rockets from the
cyclic, then the ARS will be fired in the independent
mode and the rocket steering cursor is only
displayed on the crewmember that WAS the
rockets.
2) When the CPG actions rockets from the TEDAC,
the rocket steering cursor is presented in both pilot
and CPG formats for cooperative engagements.
3) When the rocket fixed mode is selected, the rocket
system is actioned, pylons containing available
rockets of the selected type are positioned to +3.48
degrees, and a unique continuously computed
impact point (CCIP) constraint symbol is presented.
The CCIP symbol reflects the point in space in
which the rockets will pass and the operator simply
maneuvers the aircraft to align the symbol over the
intended target prior to initiating launch. The pylon
elevation angle for fixed rocket mode will permit
firing of the rockets in the event of an invalid
IHADSS LOS.
D-30
(b) The cursor moves about the format to indicate the azimuth and
elevation position of the aircraft in relation to the selected Line
Of Sight (LOS) to provide a steering cue to the crewmember.
(c) The rocket steering cursor is displayed six ways:
1) Stowed rocket performance/safety inhibited
steering cursor
2) Stowed in-constraints rocket steering cursor
3) Normal rocket performance/safety inhibited steering
cursor
4) Normal in-constraints rocket steering
5) Inhibited cursor training
6) Articulated cursor training
7) Inhibit fixed cursor
8) Fixed cursor
D-31
CHECK ON LEARNING
1. The ________ processor establishes the aircraft state as SAFE upon aircraft power-up.
ANSWER: __________________________________________________________________
_________________________________________________________________
2. The M151 warhead has a bursting radius of ______ meters and a lethality radius of
_______ meters.
ANSWER: __________________________________________________________________
_________________________________________________________________
3. The TOTAL ROCKETS status window is displayed when there is a difference between
the number of rockets available for firing and ________.
ANSWER: __________________________________________________________________
_________________________________________________________________
4. The PEN button will display when the _____ fuze is loaded which can defeat bunkers up
to _______ meters thick.
ANSWER: __________________________________________________________________
_________________________________________________________________
5. The M261 (MPSM) warhead contains _____ M73 submunitions that will produce 195 (10
grain) high velocity fragments that travel up to 5000 feet per second and can penetrate
more than _____ inches of armor.
ANSWER: __________________________________________________________________
_________________________________________________________________
6. Due to the possibility of surging engines, do not fire rockets from the ______________
stations. Fire no more than ________ with two outboard launchers every _______
seconds, or fire with only one outboard launcher installed without restrictions.
ANSWER: __________________________________________________________________
_________________________________________________________________
D-32
Enabling Learning Objective 3
ACTION: Identify the ARS Safety and Performance Inhibits.
CONDITIONS: Given a written test without the use of student notes or references.
STANDARD: In accordance with TM 1-1520-251-10 and TC 1-251.
3. Learning Step/Activity 1
Identify the ARS Safety and Performance Inhibits.
a. Rocket constraints are organized into safety and performance inhibits.
SAFETY PERFORMANCE GENERIC
ACCEL LIMIT PYLON LIMIT (AIR) SAFE
ALT LAUNCH TXX
GUN OBSTRUCT TRAINING
LOS INVALID
PYLON ERROR
PYLON LIMIT (GROUND)
TYPE SELECT
Figure 23. Rocket Inhibits.
(1) Rocket system safety inhibits. The WP will abort the remainder of the
rocket launch event if a safety inhibit is detected during the launch
event.
(a) ACCEL LIMIT: Indicates that the vertical acceleration is less
than 0.5 G’s and may cause the main rotor blades to obstruct
the trajectory of the rockets..
(b) ALT LAUNCH: Indicates that a Hellfire launch is in progress
(c) GUN OBSTRUCT: Indicates that rockets resident on inboard
launchers are inhibited from launch because the gun is out of
coincidence and may obstruct the trajectory of the rockets.
(d) LOS INVALID: Indicates that the selected LOS is either failed
or invalid, also no valid FCR Next –To-Shoot (NTS) target will
cause this safety inhibit
D-33
(e) PYLON ERROR: Indicates that the pylon elevation position is
not equal to the commanded position. The WP will inhibit
rocket firing for pylon position errors as follows:
1) If the selected sight is Target Acquisition
Designation Sight (TADS) or FCR, and the pylon
position error is greater than 0.5.
2) Integrated Helmet And Display Sight System
(IHADSS) is the selected sight, and the pylon
position error is greater than 1.5
(f) PYLON LIMIT: Indicates that the commanded pylon position
exceed the pylon articulation limits of +4 to -5 on the ground
(g) TYPE SELECT: Indicates that no rocket type is selected.(
multiple rocket types are available)
(h) If the Sight mode has changed since trigger pull was initiated,
the WP will inhibit launch from all pylons until the trigger is
released.
(2) Rocket Performance inhibits: If a performance criteria is not met, the
2nd
detent of the weapons trigger switch may be used to override the
performance inhibit.
PYLON LIMIT: Indicates that the commanded pylon position exceed
the pylon articulation limits of +4 to -15 in the air.
(a) The WP will inhibit rocket firing for pylon position errors as
follows:
(3) GENERIC inhibits
(a) SAFE: Indicates the weapon system is not been armed
through the Armament Control Panel.
(b) TXX: Displayed for 4 seconds to indicate the file address in
which the coordinate data has been stored. (TADS/FCR target
store switch on LHG)
(c) TRAINING: Indicates the weapon training mode is active, or
the TESS is enabled, and the armament control is in the ARM
state and a weapon is actioned in either crew station.
(4) The selected range source is beyond the rocket type maximum range
(MK-66 = 7500 m, CRV-7 greater than 9000 m). There are no ballistic
calculations for the MK40 rockets.
D-34
CHECK ON LEARNING
1. The two types of rocket inhibits are _______________ and ___________________.
ANSWER: __________________________________________________________________
_________________________________________________________________
2. What does an ALT LAUNCH message indicate?
ANSWER: __________________________________________________________________
_________________________________________________________________
3. What message will display when the actioning crewmember’s selected sight is Fire
ControlRadar (FCR), and there is no Next-To-Shoot (NTS) target?
ANSWER: __________________________________________________________________
_________________________________________________________________
4. What is the maximum range for MK-66 and CRV-7?
ANSWER: __________________________________________________________________
_________________________________________________________________
D-35
B. ENABLING LEARNING OBJECTIVE 4
ACTION: Identify the procedures for operation of the ARS.
CONDITIONS: Given a written test without the use of student notes or references.
STANDARD: In accordance with TM 1-1520-251-10 and TC 1-251.
1. Learning Step/Activity 1
Identify the procedures for operation of the ARS.
a. Procedures for ARS operation. The ARS can be operated by either
crewmember independently or collectively in the Cooperative mode.
(1) Independent mode
(a) When Independent moding is used, only the actioning
crewmember trigger is active and the ballistics calculation is
based on their LOS and range source.
(b) The WP calculates a ballistic solution based on the selected
LOS and associated range source data, aircraft inertial data
from the Embedded Global Positioning Inertial Navigation
System (EGI) units, air data from the Helicopter Air Data
System (HADS), and the selected warhead type.
(2) Cooperative mode
(a) The Cooperative mode is active whenever the rocket system is
actioned via the TEDAC left handgrip and pilot cyclic WAS.
(b) When the Cooperative mode is in use, the CPG acquires and
tracks the target and the pilot aligns the aircraft for launch
using the rocket steering cursor.
(c) In the Cooperative mode, both weapon triggers are active and
the CPG LOS and range source are used for the ballistics
calculations.
(d) When this mode is used, the rocket inventory and quantity will
default to the CPG selection but can be changed based on the
crewmember’s last choice.
(3) Training mode
(a) The Weapons Training mode is an emulation of weapons
system operation. All controls and displays will appear to
function as they would during normal operation.
(b) The TRAIN button is used to activate and deactivate the
Training mode.
1) The TRAIN button is not displayed when the
Tactical Engagement Simulation System (TESS) is
enabled.
2) When the Armament control is in the ARM mode, or
when a Weapon system is actioned, the TRAIN
button is displayed with a barrier.
D-36
(c) HMD and TEDAC displays show different symbology in the
Training mode.
1) The rocket steering cursor is displayed with a
boxed T.
2) TRAINING is displayed on the High Action Display
(HAD) while in the weapon inhibit field unless a
valid weapon inhibit is displayed.
(d) Sound effects indicate each firing event, and the simulated
RKT INV (19 rockets per M260 launcher installed) is
decreased accordingly.
1) There are six sound effects that represent 1, 2, 4,
8, 12, 24, or 38 rockets fired.
2) Rocket sound effects will cease after 120
milliseconds for each pair of rockets.
3) All sound effects cease when the trigger is
released, or all of the rockets have been fired.
(e) TESS is an interactive simulation system that allows aircrew
training for all of the AH-64D Sight and Weapons systems.
NOTE: A data entry change to the gun rounds count or the use of rocket "spoofing" devices will
adversely impact gross vehicle weight.
(4) Targeting data. The ARS accommodates use of the FCR NTS, TADS,
Integrated Data Modem (IDM) handover, and IHADSS LOS inputs.
D-37
CHECK ON LEARNING
1. When the Independent mode is used, only the ________ crewmember’s trigger is active.
ANSWER: __________________________________________________________________
_________________________________________________________________
2. In the Cooperative mode, the ________acquires and tracks the target, and the
________aligns the aircraft for launch using the rocket steering cursor.
ANSWER: __________________________________________________________________
_________________________________________________________________
3. The rocket INVENTORY and QTY selection defaults to the ________ selections during
cooperative engagements.
ANSWER: __________________________________________________________________
_________________________________________________________________
4. The Cooperative mode is active whenever the rocket system is actioned via the:
ANSWER: __________________________________________________________________
_________________________________________________________________
5. In the Cooperative mode, both weapon triggers are active and the ________ Line Of
Sight (LOS) and range source are used for the ballistics calculations.
ANSWER: __________________________________________________________________
___________________________________________________________________
D-38
C. ENABLING LEARNING OBJECTIVE 5
ACTION: Identify the ballistic factors that affect rocket firing.
CONDITIONS: Given a written test without the use of student notes or references.
STANDARD: In accordance with TM 1-1520-251-10, TC 1-251, and FM 3-04.140(FM1-
140).
1. Learning Step/Activity 1
Identify the ballistic factors that affect rocket firing.
a. Ballistics
(1) Ballistics is the science of the motion of projectiles and the conditions
that influence that motion.
(2) The four types of ballistics influencing helicopter-fired weapons are:
(a) Interior
(b) Exterior
(c) Aerial
(d) Terminal
(3) Each type produces dispersion, which is the degree that projectiles
vary in range and deflection about a target.
(4) Interior ballistics. Interior ballistics deals with characteristics that affect
projectile motion inside the gun barrel or rocket tube. It includes
effects of propellant charges and rocket motor combustion. Aircrews
cannot compensate for these characteristics when firing free-flight
projectiles.
(a) Propellant charges
1) Production variances can cause differences in
muzzle velocity and projectile trajectory.
2) Temperature and moisture in the storage
environment can also affect the way propellants
burn.
3) Propellant burn variations, as a function of ambient
temperature, are also a significant contributor to
muzzle velocity variations and are addressed in the
aforementioned muzzle velocity temperature
compensation.
(b) Launch tube alignment
1) The AH-64D aircraft employs a PIU in each pylon
assembly for launch positioning of the pylons based
on its independent error sources as measured with
the Captive Boresight Harmonization Kit (CBHK).
2) A further consideration associated with alignment
accuracy is related to the M261 rocket launcher.
Specifically, the launcher deflects appreciably when
rocket motors initially ignite and the launcher
D-39
holdback mechanism is not yet overcome. This
phenomenon is most pronounced when rockets are
launched from the periphery tubes of the launcher
(outer ring).
3) Finally, the mechanical misalignment of the
launcher tubes pales in comparison to the inherent
round-to-round dispersion of the MK66 rocket,
which approaches 10 milliradians (mr).
4) As such, any attempt to precisely align the rocket
launcher beyond current guidelines represents
diminishing returns.
(c) Thrust misalignment
1) A perfectly thrust-aligned, free-flight rocket has
thrust control that passes directly through its center
of gravity during motor burn. In reality, free-flight
rockets have an inherent thrust misalignment,
which is the greatest cause of error in free flight.
Spinning the rocket during motor burn reduces the
effect of thrust misalignment.
2) Firing rockets at a forward airspeed above Effective
Transitional Lift (ETL) provides a favorable relative
wind, which helps to counteract thrust
misalignment. When a rocket is fired from a
hovering helicopter, the favorable relative wind is
replaced by an unfavorable and turbulent wind
caused by rotor downwash. This unfavorable
relative wind results in a maximum thrust
misalignment and a larger dispersion of rockets.
(5) Exterior ballistics. Exterior ballistics deals with characteristics that
influence the motion of the projectile as it moves along its trajectory.
The trajectory is the path of the projectile as it flies from the muzzle of
the weapon to the point of impact. Aerial-fired weapons have all the
exterior ballistic characteristics associated with ground-fired weapons.
They also have other characteristics unique to helicopters.
(a) Air resistance
1) Air resistance, or drag, is caused by friction
between the air and the projectile.
2) Drag is proportional to the cross-section area of the
projectile and its velocity.
3) The bigger and faster a projectile is, the more drag
it produces.
4) The AH-64D ballistics calculation factors air density
ratio, based on the data from the High Integrated
Air Data Computer (HIADC), in the gun and rocket
time-of-flight calculations, which ultimately impacts
the aimpoint.
D-40
5) Projectile time-of-flight increases in denser air
masses. The opposite is true in thin air.
6) Any increase in the munitions time of flight equates
to a larger ballistic correction due to the effects of
gravitational ―drop.‖
Figure 24. Gravity.
(b) Gravity
1) The projectile loss of altitude because of gravity is
directly related to range. As range increases, the
amount of gravity drop increases.
2) This drop is proportional to time-of-flight (distance)
and inversely proportional to the velocity of the
projectile.
3) The appreciable decay in projectile velocity is the
root cause of increased time-of-flight and
associated gravitational drop.
4) The MK66 rocket achieves maximum velocity at
approximately 400 meters from launch and, like the
30mm round, decays rapidly thereafter.
5) The AH-64D algorithms, and associated rocket and
gun coefficients, automatically address gravitational
drop as a function of time of flight.
(c) Yaw
1) Yaw is the angle between the centerline of the
projectile and the trajectory.
D-41
2) Yaw causes the projectile trajectory to change and
drag to increase.
3) The direction of the yaw constantly changes in a
spinning projectile.
4) Yaw maximizes near the muzzle and gradually
subsides as the projectile stabilizes.
5) Unlike other exterior ballistics, yaw cannot be
quantified or compensated for.
6) Spin-stabilized projectiles help minimize yaw error.
7) Yaw error is largest at muzzle exit due to tip-off, not
because of lack of spin stabilization.
8) In the case with the rockets, the MK66 motor flutes
impart a high spin rate (in excess of
30 revolutions/second) during the boost phase of
motor burn (approximately 1 second).
9) Thereafter, the folding fins reverse the roll and
sustain the spin stabilization for the remainder of
the munitions free-flight profile.
(d) Projectile drift
1) When viewed from the rear, most projectiles spin in
a clockwise direction.
2) Spinning projectiles act like a gyroscope and exhibit
gyroscopic precession. This effect causes the
projectile to move to the right, which is called the
horizontal plane gyroscopic effect.
3) As the range to the target increases, projectile drift
increases. The amount of projectile drift is
proportional to the spin rate of the projectile, which
varies throughout the flight profile.
4) The AH-64D ballistic algorithms compensate for
this phenomenon and no adjustments are required.
(e) Wind drift
1) The effect of wind on a projectile in flight is called
wind drift.
2) The amount of drift depends on the projectile time
of flight and the wind speed acting on the cross-
sectional area of the projectile.
3) Time of flight depends on the range to the target
and the average velocity of the projectile.
4) When firing into a crosswind, the gunner must aim
upwind so that the wind drifts the projectile back to
the target.
5) Firing into the wind or downwind requires no
compensation in azimuth but will require range
adjustment.
D-42
6) In the AH-64D, wind drift is compensated
automatically by the WP. Important wind
compensation considerations:
a) Munition sensitivity
1 Rockets ―weathervane‖ into the wind
vector during the motor boost phase
and drift with the air mass during the
motor coast phase.
2 The 30mm round drifts with the air
mass throughout its free-flight
trajectory.
3 The amount of projectile drift
attributed to wind effects is directly
proportional to munitions time-of-flight,
which accounts for air density ratio,
wind vector (angle), and wind
magnitude.
b) Wind compensation characteristics
1 Longitudinal and lateral wind data
received from the aircraft Air Data
System is translated by the WP to the
predicted LOS (where the target will
be at termination of munitions free
flight).
2 Since the air mass characteristics are
measured locally, the ballistics applies
wind sensitivity adjustments to the
aimpoint as if the munition flies
directly to the target, and the
measured winds are constant from
ownship to target.
3 However, as a function of increased
range and gravitational effects dictate
that the munitions be aimed well
above the target to achieve intercept,
and the wind characteristics at these
altitudes or target ranges do not
reflect those measured locally by the
aircraft, appreciable error can occur.
4 For example, MPSM (6MP) and
illumination (6IL) rockets the
submunition payloads are deployed
between 600 and 1900 feet above the
target and exhibit high wind drift
sensitivity due to their slow descent
rates. Clearly, the potential for large
wind variations exists under certain
conditions.
D-43
(6) Aerial ballistics. Common characteristics of aerial-fired weapons
depend on whether the projectiles are spin-stabilized and whether they
are fired from the Fixed mode or the Flexible mode.
Figure 25. Rotor Downwash Error
(a) Rotor downwash error
1) Rotor downwash acts on the projectile as it leaves
the barrel or launcher. This downwash causes the
projectile's trajectory to change.
2) Although rotor downwash influences the accuracy
of all weapon systems, it most affects the rockets.
3) Delivery error is largest while hovering In Ground
Effect (IGE), because it is harder to characterize
and compensate for due to blade impulses and the
random nature of induced flow pattern. In essence,
IGE launch yields greater dispersion, because the
aircraft cannot apply appropriate downwash
compensation. Note that the real reason rockets
pitch up in hover, whether IGE or OGE apply, is
weathervaning.
4) As stated previously, rockets turn into the relative
wind source during boost. The rotor downwash
magnitude of the Longbow Apache (LBA) varies
appreciably as a function of aircraft gross weight.
At 18,000 pounds, the downwash magnitude is
nominally 21 meters/second or 40 Kts in stabilized
hover. This wind source imparts a significant
angular error (pitch axis) dependent upon exposure
D-44
time. At approximately 33 Kts forward airspeed
(indicated), the rotor disk is pitched forward such
that the influence vector is moved just aft of the
rocket launcher front bulkhead, thus reducing
downwash to zero.
5) When transitioning to rearward flight, downwash
magnitude initially increases since the rotor disk is
pitched aft and the rockets spend more time in the
influence vector.
6) Note that the LBA ballistics algorithms
automatically compute rotor downwash
compensation for rockets based on aircraft dynamic
gross weight, air density ratio, and longitudinal true
airspeed. However, this compensation assumes
rocket launch is initiated at OGE altitudes.
Downwash compensation is not applied for the gun
due to the position of the muzzle with regard to the
rotor disk and the short exposure time of the 30mm
projectiles.
7) When initiating rocket launch in crosswinds, the
aircraft should be temporarily leveled for munitions
release, presuming that terrain permits doing so.
Automatic roll compensation of the rocket aimpoint
(and pylon position angle) will not be implemented
with any degree of effectiveness.
Figure 26. Angular Rate Error.
(b) Angular rate error
1) The motion of the helicopter causes angular rate
error as the projectile leaves the weapon.
2) For example, a pilot using the running-fire delivery
technique to engage a target with rockets at 4500
D-45
meters may have to pitch the nose of the helicopter
up to place the reticle on the target. When the
weapon is fired, the movement of the helicopter
imparts an upward motion to the rocket. The
amount of error induced depends on the range to
the target, the rate of motion, and the airspeed of
the helicopter when the weapon is fired. Most of
this motion is compensated for by the pylons by
articulating up to 10 per second.
3) Angular rate error also occurs when aircrews fire
rockets from a hover using the pitch-up delivery
technique. Anytime a pitch-down motion is
required to achieve the desired sight picture, the
effect of angular rate error causes the projectile to
land short of the target.
(c) Fin-stabilized projectiles
1) The exterior ballistic characteristics affecting fin-
stabilized projectiles are very important. The AH-
64D ballistics algorithms automatically compensate
for weathervaning during the boost phase of rocket
motor burn.
2) Relative wind effect
a) When a helicopter is flown out of trim, either
horizontally, vertically, or both, the change in
the crosswind component deflects the rocket
as it leaves the launcher.
b) Because the rocket is accelerating as it leaves
the launcher, the force acting upon the fins
causes the nose to turn into the wind.
(7) Terminal ballistics. Terminal ballistics describes the characteristics
and effects of the projectiles at the target. These include projectile
functioning, including blast, heat, and fragmentation.
(a) Penetration fuzes (impact fuzes)
1) Penetration fuzes (6RC M433) activate surface and
subsurface bursts of the warhead.
2) The type of target engaged and its protective cover
determine the best fuze for the engagement.
3) Engage targets on open terrain with a superquick
fuze that causes the warhead to detonate upon
contact.
D-46
Figure 27. Fuze.
4) Engage targets with overhead protection, such as
fortified positions or heavy vegetation, with either a
delay or forest penetration fuze. These fuzes
detonate the warhead after it penetrates the
protective cover.
(b) Fixed time-base fuzes and airburst fuzes. Fixed time-base
fuzes detonate and release their payloads at a fixed time after
rocket launch.
1) Fixed time-base fuzes are employed in the 6IL and
IL7 (CRV7) illumination rockets with the associated
function time of 9.0 seconds after motor burnout.
2) Fixed timed fuzes produce airbursts and are most
effective against targets with no overhead
protection.
3) Optimum release range is established as 3.5 km for
the 6IL and approximately 4.0 km for the IL7 (due
to increased motor velocity).
4) Airburst fuzes (M439) permit the host aircraft to
establish a variable time of function from 0.95 to
25.575 seconds.
5) The ballistic algorithms define the optimum fuze
time-of-function value based on conventional
ballistics compensation, use of prescribed range
and height offset associated with the payload, and
submunition free-flight characteristics.
6) M439 fuzes are employed in the following rockets:
a) 6FL—MK66 motor, flechette warhead
b) 6SK—MK66 motor, smoke warhead
c) 6MP—MK66 motor, Multi-Purpose
Submunition (MPSM) warhead
D-47
d) MP7—CRV7 motor, MPSM warhead
e) SK7—CRV7 motor, smoke warhead
Figure 28. Wall-In-Space Concept.
(c) Wall-in-space concept
1) The MPSM (M439 fuze with M261/M267 warheads)
provides a large increase in target effectiveness
over standard unitary warheads.
2) The MPSM warhead helps to eliminate range-to-
target errors because of variations in
launcher/helicopter pitch angles during launch.
3) The timing cycle begins immediately after
termination of the fuze charging cycle. The
warhead Safe/Arm device simply isolates the
charging line and connects the firing capacitor to
the detonator at the first instance of motion.
4) At the computer-determined time (a point slightly
before and above the target area), the M439 fuze
initiates the expulsion charge.
5) The submunitions eject, and each Ram Air
Decelerator (RAD) inflates. Inflation of the RAD
separates the submunitions, starts the arming
sequence, and causes each submunition to enter a
near-vertical descent into the target area.
D-48
Figure 29. Dispersion Pattern.
(d) Dispersion
1) Dispersion and accuracy are functions of slant
range.
2) This is directly attributed to high projectile velocity
(flat trajectory) wherein a small miss distance
above the target yields a significant downrange
error.
3) As range increases dispersion decreases.
4) Longer engagement ranges do not necessarily
equate to improved accuracy for aerial rockets.
5) Firing at extended ranges reduces linear (range)
dispersion but increases cross-range dispersion.
This specific problem is best addressed by using
airburst (M439 fuze) rockets whenever possible.
D-49
CHECK ON LEARNING
1. What are the four types of ballistics influencing helicopter-fired weapons?
ANSWER: __________________________________________________________________
_________________________________________________________________
2. Which type of ballistics best describes the characteristics and effects of the projectiles at
the target?
ANSWER: __________________________________________________________________
_________________________________________________________________
3. Thrust misalignment is a characteristic of ________ ballistics.
ANSWER: __________________________________________________________________
_________________________________________________________________
4. Interior ballistics deals with characteristics that affect projectile motion inside the:
ANSWER: __________________________________________________________________
_________________________________________________________________
5. The pilot may have to pitch the nose of the aircraft up when firing rockets beyond
________ meters. The pylons will articulate up to _________ degrees per second to
compensate for this motion.
ANSWER: __________________________________________________________________
_________________________________________________________________
D-50