I 2 -] I 0ao - Defense Technical Information Center M1A3 Remover is a three-tube, telescoping ejection device containing an explosive cartridge, designed to forcibly jettison the canopy

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AD NUMBER

AD481006

NEW LIMITATION CHANGE

TOApproved for public release, distributionunlimited

FROMDistribution authorized to U.S. Gov't.agencies and their contractors;Administrative/Operational Use; 1 Apr1965. Other requests shall be referred toU.S. Army, Frankford Arsenal,Philadelphia, PA 19137.

AUTHORITY

USAEA ltr, 22 Jun 1971

I 2 -] I 0ao /

THIS PAGE IS UNCLASSIFIED

Best Available Copy

g IEP-65-6370-8

- C?CD

PROPELLANT ACTUATED DEVICES

ENGINEERING MANUAL

I0

LU

APRIL 1965

IA

ENGINEERING MANUAL/

FOR

PROPELLANT ACTUATED DEVICES.

/-1 APRPW65

--- I- -- -

|a

1l

I+ 4

-

INTRODUCTION

The major purpose of this Eit4ft•a4ig Manual is to provide technical personnel of in-

dustries involved in design and provisions for emergency escape from extra-tcrrestrial vehicles. '

a convenient reference of basic design and performance characteristics of Propellant ActuatedOevices.-,ince the advent of high-speed jet aircraft generated the need for an automated meansof escape cem aircraft, Frankford Arsenal has pioneered the design and development of Pro-pellant a tuated Devices; such as Catapults, Initiators, Thrusters, Removers and RocketCaiap (ts.

SThe major consideration in the design, development and production o, the devicesdescribed :n this Manual was to attain an optimum Reliability Design Goal. Fin,.amental to thetheory of reliabiliiv is the relationship between total and component reliabilities. Otn thisbasis, total reliability can be no greater than the least re!iable componem. To at:ain this goal,the de, ices listed in this Manual undergo stringent quality ontrol tests ard avav'ysis for the

propellant, pyrotechnic and hardware component!., aii •,•yh the complete loaded and as-

Si t ¢ • . . "

ii

Propellant Actuoted Devices

Removers

SECTION I

REMOVERS

Propellant Actuated Devices

Removers

INTRODUCTION

Description:

The remoer is a two or three tube tele;.coping device, containing an explosive compo-nent, de-igned to ietrison ;he canopy from high-speed aircraft pdior to the ejection of crewmenfrom disabled aircraft.

The Removers are of two basic types, i.e., mechanical and gas actuated. A third typeis the electric-mechanical ballistic types which pcrmits normal opening and closing of thecanopy as well as emergency jettisoning of the canopy.

1.11.2

i 44


j Removers

REMOVER, AIRCRAFT CANOPY, 14A3

The M1A3 Remover is a three-tube, telescoping ejection device containing an explosivecartridge, designed to forcibly jettison the canopy from high-speed aircraft to provide a safepath for the ejection of the crewman from disabled aircraft.

The remover is approximately 16 inches long and 1.93 inches in diameter. The removerhas the MIAI Firing Pin Release attached. The firing pin release, which when functioned by theM3AW Initiator, releases a spring loaded firing pin in the remover. The spring propels the firingpin which strikes and detonates the primer, thereby igniting the black powder and propellant inthe M29A2 Cartridge. The remover thrust which is developed from the expanding gases of thef burning propellant, forces the inside and telescoping tubes to move sirtnlIteously until theshoulder of the telescoping tube comes in contact with the telescoping tu!he stop, thus restrict-

I.j ing its movement. The continuous moving head assembly and inside tube_ are jettisoned with theSaircraft canopy. The base, outside and telescoping tubes, and telescoping tube stop remain with

the aircraft.

PRINCIPAL CHARACTERISTICS

Stroke 23.3 inchesWeight (total assy) 2.1 poundsPropelled Weight 300 poundsTemperature Limits -65 0 F to + 160'FVelocity, min (at 70'F) 20.0 fpsThrust, min (at 70cF) 2800 poundsStroke Time (at 70'F) 0.135 secondsFiring Method Gas Actuation of the MIAl

Firing Pin Release, whichreleases MlA3 RemoverFiring Pin

S~1-3


qemovr.: Aircraft Conopy, M1A3

e 0

CROSS-SECTION DRAWING

Component Component

A Spring, Firing Pin G Base

B Pin, Safety H Tube, Outside and Pellet .\sscmblv

C Wire, Locking, .062" x 8" 1 Tube. Telescoping

D Cartridge, Aircraft Canopy j Tube, Inside and Pellet Assem:,lvRemover. M29A2

K Stop, "'elescoping TubeE Seal, Inside

L Ilead. FiringF Seal, Telescoping

MI Pin, Firing

A- J . .. . 16.00 MAX.16 - 8. 1.945 L S

S 8 .27 DIA 4 HOLES 1.9 ,, 2.450

-.l " i ,I - - -- -....

• I I1.93. .01 DIA

V -- --. 2.20 -01 :TALii

2.50013 H c 00f~

EN.VELOPE DRAWING

1.4

Propellant Actuated Devicer

Remover, Aircraft Cae'opy, MIA3

PRSSURE -RIVE- Itt-ATIONS-ttP STANDA&D PROPELL.ED WE!G647 300 LS

200

ALV~ tCo4E

RfLTsSfl SIFR 0LD~EN

-m

soo

i Hf0 6 . 20 2

TRAVEýýN2HE

VE-OITYTRAEL RLATQNSIP TANORD ROPLLEO*EIHT OOL


Remover, Aircraft Canopy, MIA3

-. PRESSURE-TIME RELATIONSHIP STANDARD PROPELLED WEIGHT 300 LB-* di 1TC0F41

20)0

.2 1

.4

0 10 so 30 40 50 do 70 go 90 *0 "0 '20 130

VELOITY-IME ELATONSIP SANAR PRLIEOPELD EGTSOL

Propellant Acttned Devices

Reaovers

REMOVER, AIRCRAFT CANOPY M2A1

The M2AI Remover is a two-tube, telescoping ejeczion device containing an explosivecartridge, designed to forcibly jettison the canopy from high-speed aircraft to provide a safepath for the ejection of the crewman from disabled aircraft.

The remover is approximately 31 inches long and 2.19 inches in diameter. The removeris actuated by removal of the safety locking pin first and the manual rotation of the searthrough a pulley system connected to a lever on the pilot's seat. Rotation of the sear releasesa spring loaded firing pin and unlocks the inside tube. The firing pin is propelled forward andI detonates the primer, thereby igniting the black powder and propellant in the M3IAI Cartridge.The remover thrust which is developed from the expanding gases of the burning propellant,forces the inside tube outward. The block assembly and inside tube are jettisoned with aircraft

canopy. The cap and outside tube remain with the aircraft.


Stroke 26.0 inchesWeight 4.4 poundsPropelled Weight 300 poundsTemperature Limits -65 0 to + 160'FVelocity, min (at 70QF) 20.5 fps

Thrust, min (at 701F) 2600 poundsStroke Time (at 70'F) 0.150 secondsFiring Method Mechanical Actuation

1.7


Remover Aircraft Canopy, M2A1

f ® 0 09 0 0 ® ®

"- ... ' -" ............ .. .. .. .. .


Compcnurit C(omponenr

A Pin. L.ocking I (artridpe. Aircraft (armpyb Tube, Becaring ,emoxer. M31A-I

( spring. I:mnL Pin Frin, lFtriiqI) SY.c'\C K Seat1: IL. be. inner L SpringF T"ub,. Outside M Safcty Pin AssemblyG (ap N Iflock Assembly

II Ring. Retaining

S- - -I A --- ---- ,,.

ENVELOPE DRAWING1-8-

___,*


Remover, Aircraft Canopy, M2AI

THRUST-TIME RELATIONSHIP

STANDARD PROPELLED WEIGHT 300 LB

4I

'°° ! ii !! ,----. --~-- "t •, i - - ------,-... .. 4- -•-

- -ME- MILL|E-ON-

U) --",-- --,VL- IYTME-LT *N•I -- ...

0 ,

O)80 -0 40 - 0 80 - 0 t2----------

1000

0 2 40 60 so t00 120 140 n60

-- ~VELOCITY-TIME RELATION5HIP -

-. STANDARD PROPELLED WEIGHT: 300 LB

U) -TIME- MILLISECONDS-

11~-9

Propellent Actuated Devices

Remover, Aircraft Conopy, M2AI

THRUST-TRAVEL RELATIONSHIP

STANDARD PROPELLED WEIGHT 30O LB

Ix

1000

~IsEPARATIONj0 12 16 20 24 28 32

TRAVIFL- INCHES

- -- VELOCITY-TRAVEL RELATIONSHIP

-. STANDARD PROPELLED WEIGHT' 300 LB

- -- - , '-

U

w ,0

L-NTUBE- SEPARATION

0

-- - - STNDR POELEIWIHT-.OLC - - = - - -1--i---I - -•H ----. -.

:•L. - -- -- "I-.. .' 1 - "------

0 4 8 12 16 20 24 28 32

TRAVEL- INCHES

1.10


Rofemvers

MREOVER, AIRCRAFT CANOPY, M3AI

The M,3AI Remover is a two-tube ejection device containing an explosive cartridge, de-signed to forcibly jettison the canopy from high-speed aircraft to provide a safe path for theejection of the crewman from disabled aircraft.

The remover is approximately 31 inches long and 2.19 inches in diameter. The removerhas an initiator attached by a length of flexible hose. When the initiator is functioned, the gasdeveloped flows through the flexible hose exerting force against the remover firing pin. Thetiring pin is propelled forward and strikes and detonates the primer, thereby igniting the blackpowder and propellant in the M3IAI Cartridge. The remover is unlocked by cam action as thefiring pin moves toward the primer, unlocking the block assembly and inside tube. The removerthrust which is developed from the expanding gases of the burning propellant, forces the insidetube outward. The block assembly and inside tube are jettisoned with the aircraft canopy. Thecap and outside tube remain with the aircraft.


Stroke 26.0 inchesWeight (total assy) 4-4 poundsPropelled Weight 300 poundsTemperature Limits -65' to + 160 0FVelocity, min (at 700F) 20.5 fpsThrust, min (at 70'F) 2600 poundsStroke Time (at 7 0 F) 0. 150 secondsFiiibt Method Gas Actuation

1.11

Propellant Actuted Devices

Remover Aircroft Conopy, M3A1

r+

-T-

•+•-• ..., ,+ • .- - i ,]". ,. =

i i

! I i i -

CROSS.SECTION DRAWING

(CompLoent Componenrt

A Cap if Tube. Outside and Pellet AssemblyLt Plug I Tube, Inside arid Pellet Assembly

C Screw, Cap. Socket Head, Seli Locicinr ; Tube, Bearing and Pellet Asscmblh(Shown 90WOut of Position ) K Sea). !-ximd

1) Pin. Shear L Rin. Stop and Pellet Asst-mblyE Latcl. M Pin, Firin-g

Pip, Plug .oor shipping onhy N EklockF Seal Tamper Proof 0 Cartridge, Aircraft CanopyG " .ring Remover. N.MIAI

30.033 MAX

.99.98 MIN1.815 MAX

'1.83 !'I .959 MIAX

.35 !.AX,. - .:03 -M-A N"X -917 M*tIN

.33 '!IN. . I

R WIDTH.3801 PR-

1WIIII. IFT.

.75 0 ,1 - -•.,i .

- -380 I.003 DIA2.187- 005 DIA 2.328-.010 DIA "1.2[-.01

2.38 -. 01 DIA.1< " . "-.

.• \. t-~--'" . "---

ENVELOPE DRAWING

1.12

II Il illII•


Remover, A;rcroft Conopy. M3A1

.. THRUST-TIME RELATIONSHIP

STANDARD PROPELLED WEIGHT:300 L8 - -.

100101

TIME- MILLISECONDS

•--- --- STANDARD PROPELLED WEIGHT: 300 LB ...-

I- • i i , .I

L2~ -I - -1-.,• K :;, i-i" ,--"-- F- -- .. ' I - - -- =-" " " *... . -

0 20 40 60 80 0 20 140 '60

LI

T!*ME-MILLISECONDS


Remover, Aircraft Canopy, M3A1

- THRUST-TRAVEL RELATIONSHIP

-STANDARD PROPELLED WEIGHT: 300 LS

400 1 ~ T T~LiF~

STANDARD PRPLE EGH:30L

'I J..SPAA RAT O

-- 4

o 4 8 12 16 20 24 28 32TRAVEL- INCHEIS

u.1

PropelIont Actuated Devicts

Removers

REMOVER, AIRCRAFT CANOPY, M4

The ,lt4 Remover is a three-tube, telescoping ejection device containing an explosivecartridge, designed to forcibly jettison the canopy from high-speed aircraft to -rovide a safe

path for the ejection of the crewman from disabled aircraft.

The remover is approximately 14.67 inches long and 1.93 inches in diameter. The re-

ma-;cr has an initiator attached by a length of flexible hose. When the initiator is functioned.

the gas developed flows through the flexible h,,,e exerting force against the remover firing pin.

The firing pin is propelled forward and strike. and detonates the primer, thereby igniting the

black powder and propellant in the .M29A2 Cartridge. During the forwaAd motion of the firing pin,

the locking keys slide inward, thus unlocking the remover. The remover thrust which is develop-

ed from the expanding gases of the burning propellant, forces the outside tube to travel forward

until the washer engages the shoulder on the telescoping tube. The telescoping tube is then

pulled forward by the outer tube until it is free of the inside tube, and is jettisoned with thecanopy. The inside tube and firing head assembly remain with the aircraft.


Stroke 19.0 inchesWeight (t..,:a assy.) 3.84 pounds

Propelled ;cight 300 pounds

Temperature Limits - 6 5*to -1 60cFVelocity, min (at 70Fe? 20 fps

Thrust. min at Q0CF) 2800 pounds

Stroke Time (at 0c'Fl 0.114 secondsFiring Methou Gas Actuation

1-15

Propellent Actuaited Devite&

Remover, Airciraf Canopy, M4

CROSS-SEZIHON DRAWING

:Componenr Component

A Pin, Shear (Shown W0 out of positior' L Stop. Firiegi~ PinB Ring.. Retaining !Il asherC Ring, Sealing Y ey Lock'ng (2)

E Tube. Telesco'ping P -0'- RingF Tube, Inside Q Pin, FiinG Ring, Sealing R Head. Firini,I Gasket crS Screw, Set QSiio,.n 9()lývut of positionl

J Ring, Scaling i Shipping PlugK Cartridge. Aircraft Canopy

Remover, M120

14.659 MIAX

1. 146 ----- 2.2u 44 .3

DI.

5 .,/ HOLES

ENVELOPE DRAWING

1.16

Piopollont A,.tuot*d Dtvic~s

Reniovtr, Aircraft Canopy, M4

THRUST-TIh4E RELATIONSHIPSTAN4DARD PROPELLED WEIGHT 300 LO

;7-6 F

VELOCITY-TlIdr RELATIONSHIPSTANOAAC PROPELLED *EIGT SOO LB

0 5 to 11 20 253 0 35, 40 45 50 ft 10 m3 70 13 SO v3 1 3 0I ~T'E-MI LLISECONM"


Removers


The M3 Remover is a three-tube, telescoping ejection de"vice containing an explosivecartridge, designed to forcibly jettison the canopy from high speed aircrait to provide a safepath for the ejection of the crewman from disabled aircraft.

The remover is approximately 14.67 inches long and 1.93 inches in diameter. The re-mover has an initiator attached by a length of flexible hose. When the initiator is functioned,the gas developed flows through the flexible hose exerting force against the remover firing pin.The firing pin is propelled forward, strikes and detonates the primer, thereby igniting the blackpowder and propellant in the M120 Cartridge. During the forward motion of the firing pin, thelocking keys slide inward, thus unlocking the remover. The remover thrust which is developedfrom the expanding gases of the burning propellant, forces the outside tube to travel forwarduntil the washer engages the shoulder on the telescoping tube. The telescoping tube is thenpulled forward by the outer tube until it is free of the inside tube and is jettisoned with thecanopy. The inside tube and firing head assembly remain with the aircraft.


Stroke 19.0 inchesWeight (total assy) , 3.84 poundsPropelled Weight 1000 poundsTemperature Limits -65' to + 160°FVelocity, min (at 70'F) 10 fpsThrust, min (at 70°F) 4500 poundsFiring Method Gas Actuation

1. 10

Propellanit Actuated Devices

Remover, Aircraft Canopy, M5


C omponent Comporncti

A P in, -%car t~bewn 0o~ut of position L Stotr. Fifint: Pin11 King, Retainini; %I WasherC Rmg Staliny Kct' t~Locnj Q;L) Tube. ()urtidc so t-vE Tube. Telescopin 1 -0- RingI- Tube. Inside.QG Ring .(4 scln Q Pin~. Firing

I Gaskct Scrcu,-',e 'r Shown 90f oui t ofposion)j RnSaigT Shipping PlugK Cartridge. Airc raft t anory

37S 01A il 1 2 J7

IVIA

ENVELOPE DRAWING


Removers


The M8 Remover is an electro-machanical-ballistic, two tube telescoping device designedto raise and lower the FI06A aircraft canopy under normal conditions during ground operation andto jettision the canopy prior to ejection of the pilot from the aircraft during emergency escape inflight or on the ground.

The electro-mechanical portion of the remover consists of a reversible, intermittent duty26 volt direct current motor, a gear transmission with an indexing mechanism and torque limitswitch, a solenoid-operated clutch with an integral ratchet mechanism, and a ball-bearing screwassembly which is coaxial with the remover ballistic chamber. Raising and lowering the aircraftcanopy is accomplished by electrically energizing the remover motor which transmits rotarymotion through the gear system to the clutch. As the clutch' rotates the ball-bearing screw turnswithin a non-rotating ball nut, which is attached to the inside tube of the remover. Rotatioh of

the ball-bearing screw drives the remover inside tube outward, raising the canopy; or inward,lowering the canopy, when the motor is electrically reversed. As the inside tube extends 9.38inches, power to the motor is shut off automatically by an extension limit switch which is camactuated. Upon retracting the remover inside tube and canopy, a torque limit switch de-energizesthe motor when the canopy is restrained by the fuselage and a tension load of 1000 to 1450pounds is imposed on the ball-bearing screw assembly. This cinch-down load insures that thecanopy is properly seated on the fuselage for locking by the pilot. A safety feature is incorpor-ated in the clutch mechanism which prevents the canopy dropping to the closed position shouldthe clutch inadvertently disengage during any position of remover stroke. The remover in theretracted position is approximately 20.25 inches long between mounting points.

The ballistic portion of the remover is used to jettison the canopy prior to ejection of thepilot from the disabled aircraft. The remover has an initiator attached by a length of flexible hose.When the initiator is functioned, the gas developed flows through the hose, exerting forceagainst the remover firing pin. The firing pin is propelled forward and strikes and detonates thecartridge primer, thereby igniting the black powder and propellant in the .M1150 Cartridge. Pro-pellant gas from the cartridge expands through the opening in the adapter housing where it actsagainst the ballistic lock components and the inside tube. With the increase in pressure theballistic lock unlocks the inside tube and the gas pressure forces the inside tube outward. Theinside tube which is pin-mounted to the canopy, clears the outside tube and jettisons the can-opy,clear of the aircraft. The outward movement also triggers an M3AI Initiator for a relatedballistic operation.


Weight (Total Assy) 22.5 poundsTemperature Limits -65'F to 2001F

1-21

00

0.

r -I


Removers

PRINCIPAL CHARACTERISTICS (MB Cont'd)

Electro-Mechanical

Electr'c Pow er 28 Volt D.C. System

Ope-tatin/e Voltage Limit 18 to 29 VoltsOperating Loads

Overload 250 pounds (tensionl to680 pounds (comrressionI

Normal load 380 pounds (compressionrlOverload 4,0 pounds itensioni to

940• pounds ftensioniExtension or Retraction Time 1$ sec max, 5 sec. nin.

Clutch Engage Time, max. 0.500 sec.Clutch Disengage Time, max. 0.500 sec.Cinch-Down Load 1000 to 1450 pour.dsStroke 8.38 to 9.8 inches

Ballistic

Stroke 12.0 inchesPropelled Weight 350 poundsVelocitv (at "00 F) 24.0 fpsPeak Thrust tat -0*Fl 5400 poundsFiring Method Gas ActuatianStroke Time (at 7e0F) 0.150 sec.

1.22



-SEE SFZCTION A-A (-

0N

"- ._ - I• I ,-•-. - -. .

-4 -,-----_1 ,. .-- _ . ..P

-J M15 0-.


Component Component

A •iring Arrangement II Cartridge. Aircraft CanopyB Ballistic Assembly Removr-r. %1150

C Bracket, Shipprng I MotorD Gear Box Assembly J SolenoidE Pin, Firing K Pin. ShearF Housing L AdapterG Plug, Shipping %I Head

,•- .-.. a ,

IIn

-.. ,, \ .-. a, . . . , *.

-~ A---------------- -

~~j c.~ ~ 17 ItLL TC.k&. E[MbWS40U STROKIL.----

ENVELOPE DRAWING

1.23

rm

Prpellant Actuated Devices

Re~mver, Aifcroit Canopy, Mg

THRuST-TIME RELATIGOSHIPSTANDARD PROPELLED WEIGHT 350 LB

- ~ ~ ~ ~ ~ _5 F

0 K ,4C w0 so 2^9 40 160O 180 200TME-M6SEOD

I,F" ..... VELOCITY-TIME RELATIONSHIP

z~. STANDARD PROPELLED WEIGHT 350 LB

5- 4 0

'."' .. _. 1....'"

. . . . . . . . . . .

0 20 4- 60 s 0 I!4 2 0 :60 160 2n_ 2C:"ME -y.-tSECONtS

1.24


Removers

REMOVER, AIRCRAFT CANOPY M9

The M9 Remover is an electro-mechanical ballistic, three tube telescoping device design-ed to raise and lower the F106B aircraft canopy under normal conditions during ground operationand to jettison the canopy prior to ejection of the pilot from the aircraft during emergency escapein flight or an the ground,

The electro-mechanical portion of the remover consists of a -eversible, intermittent duty,26 volt direct current motor, an electronic speed control box, a gear transmission, a clutch mech-anism with an integral ratchet mechanism, mechanical clutch disengage mechanism, and a doubleball-bearing screw assembly which is coaxial with the remover ballistic chamber. Raising andlowering the aircraft canopy is accomplished by electrically energizing the remover motor whichtransmit rotary motion through the gcar system to the mechanically operated clutch. As the clutchrotates the ball-bearing screw turns within a non-rotating ball nut, which is attached to the insidetube of the remover through a bearing. Rotation of the ball-bearing screw drives the remover insidetubes outward, raising the canopy; or inward, lowering the canopy, when the motor is electricallyreversed. As the inside tubes extend approximately 45.86 inches, power to the motor is shut offautomatically by an extension limit switch which is cam actuated. Upon retracting the removerinside tubes and canopy, a torque limit switch de-energizes the motor when the canopy is restrainedby the fuselage and a tension load of 400 to 500 pounds is imposed on the ball-bearing screw assem-bly. This cinch-down load insures that the canopy is properly seated on the fuselage for lockingby the pilot. The electronic speed control box which is attached to the adapter housing is used toreduce the motor speed on the retraction stroke. A safety feature is incorporated in the clutchmechanism which prevents the canopy dropping to the closed position should the clutch inadvert-ently disengage during any position of remover stroke. The remover in the retracted position isapproximately 23.51 inches long between mounting points.

The ballistic portion of the remover is used to jettison the canopy prior to e~ection of thepilot from the disabled aircraft. The remover has an initiator attached by a length of flexible hose.When the initiator is functioned, the gas developed flows through the hose, exerting force againstthe remover firing pin. The firing pin is propelled forward and strikes and detonates the cartridgeprimer, thereby igniting the black powder and propellant in the M151 Cartridge. Propellant gas fromthe cartridge expands through the opening in the adapter housing where it acts against the ball-bearing screw assembly and the inside tube. With the increase in pressure the spring pin whichsecures the ball-bearing screw assembly to the bearing housing shears, and the continued produc-tion of gas pressure forces the inside tube and ball-bearing assembly outward simultaneously. Theinside tube and ball-bearing assembly which is pin mounted to the canopy, clear the outside tubeand jettisons the canopy clear of the aircraft.


Weight (Total Assy) 35 poundsTemperature Limits -65OF to 200"F

1.25

Propellont Actuated Devices

Removers

PRINCIPAL CHARACTERISTICS (M9 Cont'd)

Electro-Mechonicol

Electric Power 28 Volt D.C..Sv'uOperating Voltage Limit jS to 29 VoltsOperating Loads

Overload 315 pounds (compreqsior., to398 pounds (compression)

Normal load 288 pounds (compression) to228 pou•ds (compression"

Overload 196 pounds +tension') to142 pounds (tensiont)

Extension or Retraction Time 20 sec. max; 10 sec. rain.Clutch Disengage Load 7 to 1I poundsCinch-Down Load 400 to 500 poundsStroke 45.86 inches

Ballistic

Stroke 2-.0 inchcsPropelled Weight 300 poundsVelocity (at -0'F) 33.0 IpsPeak Thrust (at -0 FI•f 000 proundFiring Method Gas ActuationStroke Time (at N0JF) 0.090 sec.

1.26

L

Propollent Actuated Devices


T _ A QA SECTION A-A

A A

F . • h'• y -- ' r -- -" jCROSS-SECTION DRAWING

Component Component

A Housing, Bearing I Ptug, Shiplpin "

B Housing, Adapter J Pin, Firing

C Pin, Spring K Cap, Ballistic ChmbtrD Speed Control Box Assembly L Tube, 'Trurnion

E Actuator Assembly I MotorF Gear Box Assembly N Cartridge. Aircraft Canop.G Bracket, Clutch Release (able Remover. ,l'l

H Tube, Ballistic

- - t' .[

S. . . . . ..- • • .. . .. -- - ¶.. -- -.

ENVELOPE DRA~WING

1.27

Propel lent Actuioted Devieci

Romovei', Airctaft Canopy, M9

THRUST-TIAME RELATIONSHIP4STANDARD PROPELLED WEIGHT 300 LS

rý 20 30 40 so 6c so 8 90

VELOCITY-TIME RELATIONSI4P ..STANDARD PROPELLED WEIGHT 300 L6

4-I

0 t0 20 30 40 50 Go to s 90 -7 ,TIME-WLLlSECONOS

1.28

Ptopdt'ifnt Actuated Devices

Thrusters

SECTION II

THRUSTERS

4

PropelOlnt Actuated Devicts

Thrust•ers

INTRODUCTION

Description:

A thruster is a component part of an aircraft escape system, which is used to accom-plish a certain task prior to implementing the final phases of escan-e procedure, for cret manfrom a disabled aircraft. The basic parts of a thruster consist of a gas operated firing mechanism.cartridge, chamber and a piston. The main purpose of a thruster is to impart a thrust to a known

load o, oppose a force through a given travel (stroke).

Each thruster is provided with an initial lock mechanism for the piston. This mechanismis released only when the cartridge functions. Thrusters have been developed with piston strokesbetween 1-1 2 and 13 inches. Unlike corresponding parts of catapits and removers, the thrusterpistor does not separate from the thruster at the end c! the piston stroke. Thus the thruster isa closed system.

Buffer or damper mechanisms are used in conjunction with thrusters to restrict thevelocity and acceleration of the propelled load because of limitations on aircraft structure andhumar physiology. The rate of application of thrust and r'axirnum thrust are specified whr: athruster is used to position a crewman.

Operation:

All thrusters are triggered by gas pressure supplied from another cartridge actuateddevice. The firing pin of the thruster is held in position with a "shear pin". When gas p:es~vrcis supplied, the force applied on the firing pin will shear the "shear pin" and propel the firingpin against a cartridge containing a percussion-sensitive primer. The primer ignites the blackpowder and propellant contained in the cartridge. The cartridge ruptures at the unsupportedarca. and propellant gas fills the thruster chamber and exerts a force on the face of the piston.

The initial piston motion unlocks the thruster and a force is applied through the piston to theleai, setting it in motion. In some thrusters, there is a final lock ti hold the piston in theextended position.

2-1 2.2

r


Thtusters

MIA2 THRUSTER

The M'IA2 Thruster was develeped to either jertison a hatch or unlock a tail turret.In• both applications, the thruster is required to complete a 2 inch stroke against a va-i ng force.

The opposing force distance is represented by several shear pins located with respect to initialpistoo position. The diameter of each pin was se!ected so that the shear force at a givendistance is equal to the corresponding maximum opposing force in the above applications.

Thruster performance data using this test system is presented below.

The thruster is cylindrical in shape, approximately 9-1 2 inches long and 1-13 16inches in diameter. The piston is initially locked in the chamber with 4 keys and is capableof withstanding a tensile load of 2000 pounds, without separation or mechanical failure.


Average Peak Thrust 6900 lbs.

Completed Stroke 2 inches (min)

Average Stroke Time 0.009 secondsAssembled Weight 3.2 lbs.Propelled Mass, Horizontal 20 lbs.

Firing Method Propellant GasTemperature Limits -65 "F to 160OFRestraining Force 1000 lbs. .00 in. stroke;

6000 lbs. .25 in. stroke

Force Required to Un.ock Initial Lock 60 lbs.

i

2.3

Proptrllant Actuated Dovicos

Thruster, Cortfidg* Actuated, MIA2


Component Component

A Head K Spring, Piston Locking

B Pin, Firing L Body

C "0" Ring M Plug, Piston

D Cartridge. CAD), M42 N Retainer, Curttidge

E "0" Ring 0 Trunnion

F Piston P -0- Ring

G Key QGuide, Firing Pin

Hi Sleeve. End R Pin, Shear

I Screw, Cap, Socket Head S Washer. Lock

j "0" Ring

In

00

'9 iI0

ENVELOPE DRAWING

2-4

Propellanit Actuated Dev~ices

Thruster, Cartridge Actuated, M1A2

THUTTIME REILSECONOSHP

20 ~ ~ ~ ~ ~ ~ ~ ~ - 26N EGT RPLE HRZNAL


Thrusters

MW2 THRUSTER

The M12A2 Thruster is a comportni: pari of an aircraft escape syctem whose purpo:;c isto position the teat iu an aircraft prior to ejection of the crewman. This device was designed tobe used with a damper supplied by the airframe manufacturer. The thruster is required to corn-

cte a inch stroke against in opposing force. The opposing force reprcs-nts an approvedejection seat that must be moved either upward or downward with a velhxity that does not exceed12 feet per second.

The thruster is cylindrical in shape, approximately 13.- inches long and 1-7 8 inchesin diameter. The piston is initially locked in the chamber with 4 keys and is capable of with-standing a tensile load of 2000 pounds without separation or mechanical failure. The thrusteralso has a final lock which holds the prston in the extended position and is capable of with-standing an 11,000 pound compressive load without unlocking.

The damper used with the M2A2 thruster is to control the acceleration of the pro-pelled weight to limits consistent with human physiology limits and or restrict the finalvejociy 4o d.at :hv ii.,.ysct does not damage the aircraft structure.


Average Peak Thrust w Seat in tlorizontal

Positicn I "3'F 6i-0 lbs.Completed Stroke 5.7 inchesVelocity. Maximum 12 ft secAssembled Weight 4.0 lbs,Propelled Mass, Horizontal 300 lbs.Firing atuethod Propellant GasTemperature Limits -G5:F to a 1si- FAverage Stroke Time w Seat in Horizontal

Position ,; -0, F .410 secondsForce Required to Unlock Initial Lock so lbs

2-7

Prapellant Actuated Devices

Thruster, Cartridge Actuated, M2A2

DVy ~ *J11


Component Component

A Pin, Shear J Screw, Cap, Socket Head

B Trunn ion K Key

C "0" Rinp L Piston And Plug Assembiv

D Body % H ead

E Spring, Piston Locking N Ring. Holding

F Ring, Snap 0 Cartridge, CAD. M43

G "0" Ring P "0" Ring

H Washer Q Pin. Firing

I Sleeve, End

x

an x4 18UN-2Q H.375oi D-lUN-2 1

9.587 MAX - --- *

12.7 71 MAX__________________________________

ENVELOPE DRAWING

2.8

Propellent Actuctted Devicts

Thtustw, Cortri dgit Actuatitd, MWA

THRUST-TIME RELATiONSH~r ..

300PON WEG. IPA

0 40 *0 *10 SS*0040 DA Oý 04 00C 04 400 44A*

- --- -- -

A"'O

too** ----- -- -. ......

a 40 40 .10 ~40 t0o 140 too~ 310 ago 400 *440 *60

...... THRUjST-IM %t E CIOS-P

300 POUO EIR w 40RIZATA 0LCONI 0SS.Q-4 DAMPER OPI0 12 )A

Iwo,

*PO-------7---

-- ~ ~ ~ ~ .--- --------

Propellant Ac.,ated Devices

Thrusters

"M3A3 THRUSTER

The M3A3 Thruster is a component part of an aircraft escape system whose purpose is

to release the control column stowage spring and sqpply sufficient energy to operate the seat

actuator disconnect. The thruster is required to complete a 1-1/2 inch stroke against an opposing

force and supply 600 psi pressure, minimum, at the end of a 4 foot length of hose. The opposing

force is represented by a 550 pound load that must be propelled vertically with sufficient force

so that the load continues to move after the piston reaches the end of its stroke. Thruster per-

formance data using this test system is presented below.

The thruster is cylindrical in shape, approximately 9 inches long and 1-5/64 inches in

diameter. The piston is initially locked in the chamber with 3 keys and is capable of withstanding

a tensile load of 800 pounds, witI~out separation or mechanical failure.


Average Peak Thrust Under Normal Load @ 70'F 1660 lbs.

Completed Stroke 1-1/2 inches, min.

Assembled Weight 1.0 lb.

Propelled Mass, Vertical 550 lbs.

Firing Method Propellant Gas

Temperature Limits -65'F to +165 0 F

By-Pass Pressure ý 70'F Under Normal Load at theEnd of 4 Ft Length of #,V Hose 600 psi, min.

Average Stroke Time .090 seconds

Force Required to Unlock Initial Lock 20 lbs.

2.11


Thrvster, Cattridge Actuated, M3A3

S~CROSS-SECTION DRAWING

C'omp~onent ( .om ptinent

A Tftu.,oon -1 'leevvc, En.d

B -I0-" Ring K "0"" Ring

C" Retainer. Cartridge" L Rodt, Piston

) D th:v At (artritipt, M4-i-ili

LI• "O" Ring 52Pin, Firing

SF Cap. End 0 .•tvrC%4. %mt Socket

t, Ktvx P Pin•. Slw'ar

Iti "0"" Ring Q Breech

I Spring. Piston Locking

[ •:-1}07 -0. VIA

ENVELOPE DRAWING

S2.12

• . || | | | | |

Propellant Actuot*J Devices

Thruster, Cartridge Aciliated, M3A3

PEAK BY-PASS PRESSURE.

VS HOSE LENGTH.............. .... ....

ra C ... ..- TEMPERATURF. -65

v E1TICALLY, 550 LS

1500 -

0..- .. ....

....... ..

............ .~1000 .. . . .. . . .. ...

.. . . .. . . . .. .... .........l --

0-1----------.

5 0 7 7:7 0 0-0-0 0 0 0-0700:. :2.................. T:M ... . .. .. .. ... . .. .. . ..

........---- --- --- 3 -- ----

T


Thtusttrs

MSA3 THRUSTER

Theb \I 5 A! Thruster is a component part of an aircraft escape s-ystem whose purpose 'sto jettison the tail turret or to wc usea in vatious aircraft canopy esv- t s-tems. I'he 'hru'tt

is required to complete a 5 inch strok- against an opposing force. The opposing force is rcptf-

senred !% a 100 pound carriace that must be propelled horizontally. after an iritial restraining

forc'e ot .400K0 poundc :s overcome. The i;itial retraining force ik re-'•,s-tc ! !-y a shear pin

l..ated at zero inches of stroke. Thruster performance data using this test system is presented

below.

The thruster is cylindrical in shape. approximateiy i2.6 inches long and 1.4 inch indiameter. The piston is initially locked in the chamber with 4 keys and is capable of with-

standing a tensile load of 2000 pounds without separation or mechanical failure.


Average Peak Thrust Unaer NormalLoad §_ 70- F 66-0 lbs.

Completed Stroke 5.U inchesAverage Stroke Time Und'er Normal

Load :- -0-hF ý05 seconds

Assembled Weight 3.6 lbs.Propelled Mass, Horizontal 500 lbs.Firing Method Propellant Gas

Temperature Limits -65-F to lt)o5FRestraining Forces 4o0K li.sŽ' iiches ,; -r:.,se

b00 0s. in(hes Li s,::-c

2.15

Prope.tint Actuated Devices

Thruster, Cartridge Actuated, m5A3

tn ....... ..6k...... . ý. - I- __ _

. . . . . . . . . . . . . . .....-


Component Component

.A Head K Scrciv, litifhtr

B "0" Ring L Key

C "0" Ring MI Piston

D Cartridge, M-3 N Trunnior

E "0"' Ring 0 Retainer, Cinrtrid,~c

F Body P Pin, Firing

G Spring. Piston Locking Q Pin. Sixar

fl "0" Ring R cGuitic. Firing. Pin

"1"0" Ring

0i --t

ENVELOPE DRAWING

2;-- _ _1_6_

Prop*!1ont Actuated Devices

Thruster, Cartridq* Actuated, M5A3

THRUST-TIME RELATIONSHIP

510 POUND WEIGHT PROPELLED HORIZONTALLY

2 SHEAR PINS

08,0

0 10 20 30 40 so go TO soTIME, MILLISECONDS

2-17 2-18

Propellant Actuated Deviecs

Thrusters

M6 THRUSTER

The M6 Thruster is a component part of an aircraft escape system whose purpose is topoc .ion the gun si.'hting equipment prior to imolementing the escape procedure from the aircraft.The thruster is required to complete a 1-1 2 inch stroke against an opposing force. The opposingforce is represented by a 60 pound weight that must be propelled horizontally, after an initial

restraining force of 400 pounds is overcome. The initial restraining force is a shear pin locatedat zero inches )f stroke.

The thruster is cylindrical in shape, approximately 11.73 inches long and 1._0 inches

in d;amecer. Tne piston is initially locked in the chamber with 3 balls and is capable of with-standing a tensile load of 25C pounds, without separation or mechanical failure.


Average Peak Thrust Cinder Load -0-F 110) lbs.

Completed Stroke 1.5 in.Assembled Weight 1.0 lbs.Propelled Mass, Horizontal 60 lbs.Firing Method Prc;:. .,.r:. Gas

Temperature Limits 45:F -.1.l65•FRestraining Force 400 lbs.

2.19


Thruster, Cc rtridge Actuated, M6

i~ ~ 4

CROSS-SECTIOH DRAAW1NG

C•omponent fopone rt

A Pin. Shear H Ball

B Screw, Socket. Set I " 0- Ring

C Trunnion JCrrdc h tM

1) Ilody K Pin, Firing

1: Piston L "0" Ring

F Spring. Piston Locking M Breech

; Sleeve, End

i~- It AUXi

'AA

ENVELOPE DRIAWING

2.20


Thru ster, Cartridge Actuated, M6

IJ I I I I I I I

I0 I~o ~I o I0.0I20 ...

A I i 'KL I I I II~w I SEIfIC

GO 0i

0 ~~ ~ 0. 01.j.

_LTqAI I I----

9

A-YWA7ROMAC-IECRE

ki.2 2.221


Thrusters

M7 THRUSTER

The M• Thruster i% a component "art ot an aircraft c-scapt- system whose Furlose is tounlock and or open a hatch. The thruster is requirej to comrFicv a 2-1 2 inch stroke againstan oppsing force. The opposing force is represented by an I1 6 pound weight that mL.t be

rropee.'d horizontal ly against constant 560 pound restraining force, which is sinai !.(vt' -Nitihan air cylinder.

The thruster is cylindrical in shape. approximately 10.2 inches loni and L1I inchesin diameter. The piston is initially locked in the chamber with 2 keys and is capable of .ith-standing a tcnsile load of 500 lbs.. without separation or mechanical failure.


Average Peak Thrust Under Normal Laaa TOF 1600 lbs.Completed Stroke 2.5 inchesAverage Stroke Time .JO- secondsAssembled Weight LOS lbs.Propelled Mass, Horizontal C116 lbs.

Firing Method Propellan't GasTemperature Limits -65 F to , FRentraining Force ii0 lbs.

2-23


Thruster, Cartridge Actuated, M7

A L

Y-..


Component Component

A Pin. Shear Key

, Pin, Firing K Spring. Piston Locking

C Guide L Piston

1) Screw, Set M Carridgc. Thrus'er. %I')-

F Body N "0" Rink.

F Panke,. "0" Ring 0 Head

G Collar P Gasket. "J" Ring

It "0" Ring Q q'

I Sleevr. End

- O )MAN j-zeuNr-33

~c-c'l DEEP

S....., .'-. ,, , ..

' -- ;. - '. . ..... . ,,... .... .I ~ 7 . . .z -r -.'i -•7 |:

". .-'' ""I .. .... .. A- .... ..- .-

t . . . .. . . 1-'

ENVELOPE DRAWING

2.244

i I, -

PrpletActuated De.vicest

Thowiter, Cartridige Actuated, M7

fit

t i-I

7t Lo

0 40 N

Nw

SS1-J.It ji

0-522


Thruster%

M9 THRUSTER

The M9 Thruster is a component part of an aircraft escape system whose 'purpose is tounl-tch the canopy of an aircraft prior to implementing the escape procedures of aircraft ptrsonnelfrom tb.- aircraft. The thruster is required to complete a stroke of 3.6 inches against a constantresist!ve force and supply a 100), psi minimum pressure at the end of a, -*2 inch length of hoseupon completion of its stroke. The force is represented by 50 pounds mass which is propelledagainst a 500 pound resistive force. Thruster performance data using this test system is pre-sented below.

The thruster is cylindrical in shape, approximately 9.1 inches long and I.-' inches indiameter. The piston is initially locked in the chimber with two "shear pins" and will unlockupon the application of a tensile load of 96 ±10 pounds. OP


Average Peak Thrust Under Load "'CF 2600 lbs.Completed Stroke 3.6 inches minimumOperating Time .0,30 secondsAssembled Weight 1.0 lbs.Propelled Mass, Horizontal 50 lbs.

Firing Method Propellant GasTemperature Limits -(6,5F to ;200-FResisting Force 500 lbs.By-Pass Pressure Under Normal LoaA

at the End of 42 Inch Length of--4 Hose V)00 psi

2.27

Propellant Actuated Devaes

Thruster, Cartridge Actuated, M9

a -

CROSS-SECTION, DRAWING

(omprinnnt (Compnntnt

A Collar I scre,.,;. -Ct •2)

11 Pin. 'ihcarý Firinm: Pin I Rind

( King Aiaprtr and Pelct Assembly

1) Trunnion L Pin, Shear. Piston #2)

V -0- |inF Ni 't atrrid e. Thruster. NIl 19

[ tlody N Pin. Firing

t, Pi•ton 0 -0- Rii•gSIt "'0" King 12, 1 lrBevch

!I

- ' . . . . . . . . . ... . . . . .. 4* -C-

L-ii-!I

L_ ......,s,,., ....

ENVELOPE DRAWING

2.28


Thruster, Cortridge Actuated, M9

5000

THRUST-TIME RELATIONSHIPLOAD PROPELLED HORI'O NTALLY

4000 50-POUND WEIGHT500-POUND RESISTIVE FORCE

3000(U)

I

I- -65 F2000 -

.0 10 20 30 40 50TIME (MS)

2-29 2.30


Thrusters

M) THRUSTER

The M11 Thruster is a component part of an aircraft escape system whose purpose iSto jettison the canopy of an aircraft prior -o implementing the escape procedures of aircraft

personnel from the aircraft. The thruster is required to complete a stroke of 5-3 4 inches andproped a simulated canopy through an arc of 90 degrees at a rate of 5 radians per second. The

simulated canopy is represented by a 35 inch beam weighing 45 pounds. Thruster pet formancedata using this test system is presented below.

The thruster is cylindrical in shape, approximately 5.3 inches long and 1-25 inches

in diameter. This thruster differs from the ordinary thrusters because it has three telescoping

tubes in lieu of a moving piston. The tubes are initially locked with a shear screw, which will

unlock upon the application of a tensile load of 160 ± 20 pounds.


Average Peak Thrust Under Normal Load T70OF 22-2 lbs.

Completed Stroke 5.-5 incaes

Assembled Weight .95 lbs.

Propelled Nfass. Ra¢;alh- 45 lbs.Firing Method Propellant Gas

Temperature Limits -W5F t~o -2(13-F

Ve'ocitt a•f Propelled Mass. Min. 5 tad sec

2.31

1.i

Prpopllant Actuated Devices

Thruster, Cortridge Actuated, M11

1

I0 01I


C omponent Component

A Pellet K rube, Outside

H [lead and Pellet Assienbl% L 'rube. Inside

( ''0" :. ing %1 "'0" Ring

V~ C.itrudgtc. Thtu' ret, Mu-ii N Rcuimeir and f'eijei ~eniE Ring. 5egment 0 '.0" RinFg

F -0- Ring P Guije

(1 '"0" Ring QPin.. Firing

Ii 'Icre%. Shear R -0- Ring

I Stop and Pellet Assembly S Pin. SI'ear

J Blod% T AXasher. C~ur~ed

---- 5.255 A--e'

.50+.01.- -- 4.755 MAX----e

---- 4.25 -0

1 015 D; A__-- It

1.250 DIA - _ _-- .9 37 010 DIAl

ENVELOPE DRAWIN4G

2.32


Thruster, Cartridge Actuated, M I I

THRUST-TIME RELATIONSHIPTEMPERATURE 700F

25001- I i iH --

2000

14500-

'1000

i! ~Soo : •

0 2 4 6 a t0 12 14TIME (MS)

2.33/2-34

I!

Propelled Actuated Devices

Thrusters

M13 THRUSTER

The M13 Thruster is a component part of an aircraft escape system whose purpose is tounlock the canopy of an aircraft prior to ejection of the crewman. The thruster is required tocomplete a stroke of 2.76 inches against an opposing force and su2ply 1000 psi pressure, mini-mum, at the end of a 6 foot length of hose. The opposing forces are represented by a 70 poundweight which is propelled vertically after an initial restraining force of 2000 pounds is overcome.The initial restraining force is represented by a shear pin located at zero inches of stroke.Thruster performance data using this test system is presented below.

The thruster is cylindrical in shape, approximately 8.3 inches long and 1.2 inches indiameter. The piston is initially locked in the chamber with 2 shear pins and will unlock uponthe application of a tensile load of 96 pounds.


Thrust Under Load ? 70°F 2700 lbs.Completed Stroke 2.86 inchcs, m,.

Assembled Weight 1.07 lbs.Propelled Mass, Vertical 70 lbs.

Firing Method Propellant GasTemperature Limits -65'F to 4.200°FBy-Pass Pressure Under LoadS6 Foot of s4 Hose 1000 lbs., min.Restraining Force 2000 lbs. - "0" inches of strokeOperating Time .080 seconds, max.

2.35

Prqpelient Actutedl DeOtes

Thruster, Cartridge Actuated, S 13

Flo______! F


Component Component

A :::" Ring I Screw, :et (2)

B Pin. Shear. Firing Pin J Ring, Shear

C -0- Ring K Fastener, Piston and Pellet Assembly

D Cartridge, Thruster, M119 L Pin, Shear, Piston (2)

F "tO" Ring M Breech

F Body N Pin, Firing

G Piston 0 "0" Ring

H "0" Ring (2) P Cap, Base and Pellet Assembly

< Z,4 ýOb SMKIL ' STAý;RT

.375- M02DIA

T 1 .50 -0....

2,--200 -.02

ENVELOPE DRAWING

2-36

It .. . . . - -

Actllt*4[4*v'c l

4000

42O650F

wU

4 0 s o 6 0 7 0o o

0 "A 0 2 30 TiMI (MS

I

/Pnpe0*1taw AZI,,*.* D*ntcit

MIS THRUSTER

The M0I Thrustet is a component part of an aircraft escapt- m whost. purpose k

to position the ctc-wman's, fret and raise the leg guards of the ejection !;at prior to ciection ofthe crewman. The thruster is required to complete a 4.42 inch stroke, with the piston being re-tracced into the cylinder, against an opposing force. The opposing force is represented by an11 pound weight which must be propelled horizontally against a restraining force of 2250 poundsafter an initial restraining force of 3750 pounds is overcome. Silicone oil is employed for internaldamping to keep the acceleration of the propelled weight within limits consistent with humanphysiology, Thruster performance data using this test system is presented below.

The thruster is irregular in shape, approximately 16-7/, inches from the end of theextended piston to opposite mounting end of the body. An external reservoir is attached to thebody for the accumulation of oil as it is metered from the body. The piston is initially lockedin the body with a "shear pin" which will unlock upor the application of a compressive loadof 1150 pounds. The thruster also has a final lock which holds the piston in the retractedposition and is capable of withstanding a tensile load of 15,000 pounds without unlocking.


Approximate Thrust 6700 psiCompleted Stroke 4.42 inchesAssembled Weight 5.0 lbs.Resistive Force (shear pin) 3750 lbs.Resistive Force (air load) 2250 poundsFiring Method Propellant GasTemperature Limits -65 0 F to ý 165 0 FPropelled Mass 11 lbs.Operating Time -65 0 F 500 milliseconds, approximately

2-39

Puwspflea Acffietid Devices

Thrvater, Cumld.p Actwetd, M1S

VIEW A


Component Component

A Spacer M PistonB Body, Reservoir N BodyC Pin, Shear, Firing Pin 0 Cartridge, Thruster, M94D Ring, Back-Up (4) P Pin, FiringE "0" Ring (2) Q "0" RingF Spacer R Housing, Firing Pin

G Ring, Retaining S Screw, Cap, Socket Head (4)H Nut, Ring And T Screw, Hollow Lock

Pellet Assembly Plug, ReservoirI Rod, End GasketJ Rod, Piston U "0" RingK "0" Ring %I Pin, Unlock Shear1. "0" Ring (2) T Fluid, Silicone

.374 4 .005 DIA HOLE

1/276

~ 4 L4.430 ± _0107 TROKE --' 9.125

15.930 ±.010 1° ± O 5 '. .

ENVELOPE DRAWING

2.40

S

i

Pmepull.wt Actwrted Otwic-ce

Thrusters

MZOAJ THRUSTER

ThtL 12(0A I Tllrbinscr is' a vomponent part of an alit raft sx '.tvmn wvh,'t- purpot, 1is to

;etrison, th caholý oi in naicraft prior to imnplenimtning the CScajln procedur, of aircaft per-sonnel from the aircraft. The thruster is required to complete a S inch stroke against a constant

iorte. With the thruster connecwctl to a 50 pound weight, the piston shall move a constant load of4000 pounds, horizontally, throughout its entire 5 inch stroke.

The thruster is cylindrical in shape. approximately 12.6 inches long and 1.4 inches in

diameter. The piston is initially locked by 4 keys in a locking groove and will withstand a

tensile load of 2000 pounds without separation or mechanical failure.


Average Peak Thrust Under Normal Load f 70'F 5877 lbs.

Completed Stroke 5.0 inches

Average Stroke Time .046 sec.

Assembled Weight 3.6 lbs.Propelled Mass, Horizontal 50 lbs.

Firing Method Propellant Gas

Temperature Limits - 65'F to 200"t:

Restraining Force 3000 lbs.

Force Required to Unlock Initial Lock 60 lbs.

2.57

Prtepllo.nt Acivetwd Deviett

Thruster, Cartridge Actvsted. M20A!

I J I_ I


Component Component

A Head J Screw, Buffer and Pellet Assembly

B Pin, Firing K Key (4)

C "O" Ring (2) L Body and Pellet Assembly

D Trunnion M Sleeve hE Piston IN Cartridge, Thruster, \1127 {

F Spring 0 Guide Rctainer Assembly

G "O"Ring P "0" Ring

H Sleeve, End Q Pin, Shear

I "O"Ring

12.57

-6- 1AO8 6-1 UNF-2A

ENVELOPE DRAWING

2-58

Thivuter, Cottdge Acttvfq. M2DAI

0.1

t- g --

Q0 cm4e-sn~

2.5

Ptopellent Actuated Devices

Cetapults

J4

44/i

SECTION III

CATAPULTS

I


Catapults

INTRODUCTION

Dczrrption

The catapult is a two or three tube telescoping device, containing an explosive compo-nent, designed for upward or downward ejection of crewmen and their seat from high-speed aircraft

to provide safe escape from disabled aircraft.

Operation

The catapult must impart to its load (ejection seat with occupant a velocity which willinsure its clearing the aircraft and reach sufficient height to permit full deployment of a parachute,at the same time keeping the acceleration within safe physiological limits.

Two additional types of catapults have been designed to indoctrinate USAF trainees inthe catapult ejection procedures; namely, one type which is used on a fixed veziical training towerand a mobile type which propells the seat and occupant along a guided vertical track.

-11/3-2

iI.t


Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, MIAI

The first catapult developed for USAF was the mechanically actuated M1Al Catapult.

The catapult is a three rube telescoping ejection device, containing an explosive cartridge, de-signed for upward ejection of crewmen and their seat from high speed aircraft to provide safeescape from disabled aircraft.

The catapult is approximately 39 inches long and 2.3 inches in diameter. The catapultis actuated by removal of the safety locking pin first and manual operation of the sear through apulley system connected to a lever on the pilot's seat. Rotation of the sear unlocks the catapulttubes and releases the spring loaded firing pin which strikes and detonates the primer, therby

igniting the black powder and propellant in the M28A1 Cartridge. The catapult thrust which isdeveloped from the expanding gases of the burning propellant, forces the inside and telescopingtubes to move simultaneously until the shoulder on the telescoping tube comes in contact withthe trunnion, thus restricting its movement. The continuous moving block assembly and insidetube are ejected with the seat. The outside and telescoping tubes remain with the aircraft.


Stroke 66.0 inchesWeight (total assembly) 8.2 poundsPropelled Weight 300.0 pounds

Temperature Limits -65°F to + 160'FMax Acceleration (at 701F) 20.0 gVelocity, min (at 70°F) 60.0 fps

Max. Rate of Change of Acceleration

(at 701F) 170.0 g/secFiring method Mechanical ActuationStroke Time (at 70*F) ' :20 sec

3.3


Catapult, Aircraft Ejection Soat, MIAI

00Z~


Componen Component

F Seat N artridge, Aircraft Ejection Seat,G Seal, Fixed Catapult, MUMAH Trunnion 0 Pin, Firing

P Pin, Safety, Assem~bly

47P1J4 4

3.32


Catcpult, Aircraft Ejection Seat, MIAl

PRESSURE-TIME RELATIONSHIP STANDARD PROPELLED WEIGHT: 300 L6

*ý r

'Tii-7O-74I

7N 7-1S~OO

4j~~~~~ELERATION~~ ~ ~ .6 IFgALTOIIPSADR R~LLDWIN OL

- zx-efftiio

;43.5

Propellant Actuated ])*vices

Catapult, Aircraft Ejection Seat, MiAl

1 A AESW -TfttL ELATION"STA iwDARO PftOPELuo WEIGHT 300 L&

-i

17' -- 7

I OOIVELOMY-TW'?EL RELAT1ONSMIF STANWAO PpOpELLEI> WEIGHT: 300LB,

--- ---- 1O

TUBE-Tr SEPARATION

3.7t

0 25 0 3546 s 6:0


Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, TRAINING, M2

The Catapult, Aircraft Ejection Seat, Training, M12 with the Cartridge M3UAI .as designedto be used on a fixed vertical training tower for indoctrinating United States Air Force trainees 'inthe catapult ejection procedure. In this application, the catapult ejects the seat and occupant along

a guided track to About a height of 40 feet with moderate acceleration.

The training catapult is a three-tube, mechanically actuated unit which is constructed ofsteel. This cdtapult is approximately 39 incbes long and 2.2 inches in diameter. Aiter removal ofthe safety locking pin, the catapult is actuated by manual rotation of the sear through a pulley svs-tern connected to the actuating lever on the indoctrinee's seat. Rutat.ion of the sear releases thespring-lo-tded firing pin which strikes and detonates the primer, thereby igniting the black powderand propellant in the M3OAI Cartridge. The Caraauir chrusr which i- ,c•.evpe,., !-Inn -::- expandiniggases of the burning propellant, forces the inside and telescoping tubes to move simultaneouslyuntil the shoulder on the telescoping tube comes in contact with the trunnion, thus restricting itsmovement. The continuous moving block assembly and inside tube are ejected with the seat. The

outside and telescoping tubes remain with the simulated cockpit.

The catapult is designed for repeated use on a fixed tower installation, with a new car-tridge inserted for each firing.


Stroke 60.0 inches

Weight (total assembly) 13.0 poundsPropelled Weight 300.0 poundsTemperature Limits -65'F to - 160LFMax Acceleration (at 7"OF) 12.0 gVelocity', min (at 70 0 F) 38 fps

Max Rate of Change of Accel (at 70F) 150 gisecFiring Method Mechanical ActuationStroke Time (at 70 0 F) 0.210 seconds

P 3.


Catapult, Aircraft Election Seot, Training, M2


Component Component

A Pin, Firing G Tube, OutsideB Sear H Tube, Telescoping

C Sp-ing, Firing Pin I Tube, InsideD Pin, Safety, Assembly j CapE Block K Cartridge, Aircraft Ejection Seat

F Trunnion Catapult, M30AI -(Installed atTraining Base)

30.647 MAX__________________366547 MtN

-22tý01 1A "925 MAXza~ 01 i 4,734 MIWN

ENVELOPE DRAWING

3.o


Catapult, Aircraft Ejection Seat, Training, M2

PRESSURE-TRAVEL RELATIONSHIP STANDOARD PROPELLED WEIGHT: 300 LB.S 41

* r70 F

Ij SEPARATION

0 6 0 is to 25 so0 3 40 45 110 8 0

IVjLELCiry-TRAVEL RELATIONSHIP STANDARD PROPELLED WEIGHT: 3QOLU.

A- -4 - : T4RSEAATO_

- ~ ~ ~ ~ . 70 F- .-- -- ~

SEPARATI-

- EERTON4RAVEL RIELATIONSHIP STANDARD PROPELLED WEIGHT: MOML [1-

700?F

-i-Kr- ~ ~ UB t7 zr -7-~*~-F I 7ý-J S PAR ATIO

o 0 s0 Is 20 25 so .1 so 0 0 0TAE-INCMIS

3.9

Ptopellont Actuoted Deylces

Catapult, Aircraft Ejections Saot, Training, 'M2

PRESSWA-TIME 8"LTIONSHIP STANDARD 0PROPLLED INEW0T:S00L& -

-L-4


Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, M3AW

The M3AW Catapult is a gas actuated :hree-tube telescoping device containing an explo-sive cartridge, designed to propel upward, an ejection seat together with a crewman from high-speed aircraft to provide safe escape from disabled aircraft.

The catapult is approximately 51 inches long and 3.0 inches in diameter. The catapulthas an initiator attached by a length of flexible hose. When the initiator is functioned, the gasdeveloped flows through the flexible hose, exerting force against the catapult firing pin. The

firing pin is propelled forward and strikes and detonates the primer, thereby igniting the blackpowder and propellant in the M36 Cartridge. The catapult is unlocked by cam action as the firingpin moves toward the primer, unlocking the block assembly and inside tube. The catapult thrustwhich is developed from the expanding gases of the burning propellant forces the inside andtelescoping tubes to move simultaneously until the shoulder on the telescoping tube comes incontact with the trunnion, thus restricting its movement. The continuous moving block assemblyand inside tube are ejected with the seat. The outside and telescoping tubes remain with theaircraft.


Stroke 88.0 inches

Weight (total assembly) 24.9 pounds

Propelled Weight 350.0 pounds

Temperature Limits -65"F to + 1601FMax Accel. (at 70'F) 20.0 gVelocity, min. (at 70'F) 77.0 fps

Max Rate of Change of Accel(at 70'F) 180.0 gisec

Firing Method Gas ActuationStroke Timne (at 70"F) 0.240 sec

3.11

Propellant Actuated D*Y~ic~s

Catapult, Aircraft Ejection Seat, MWA'

(D) ®R 09 OOyO

177-7


Component Component

A Cap L Pic. FiringB Seal, Plain 'i BlockC Tube, Outside and Pellet N Plug, Shipping

Assembly 0 "0" RingI) Trurnion P Ring. Stop and Pellet Assembly

E Seal, Fixed R PlugF Seal, Plain S Cartridge, Aircraft Ejection

G Washer, Shock Seat, Catapult. %f36It Screw, Cap, Socket Head, T Tube, Inside and Pellet

Self-Locking (shown out of position) AssemblyI Pin, Shpar U Tube, TelescopingJ Latch (2) N' SpacerK Seal, Tamper Proof

3-12


Catapult, Aircraft Ejection Seat, MWA

PRES..~SURE-TRAVEL. RE LAIONSHIP STANDARDl PROPELLED WtHaIT:35iso IA

70- IF70

I LI

I _-4-- 4EPRTO

$71

VELcCiTRTAT; L MEAMNSP STANDARD PROPELLED WVGT. 5LLJ

O0 I

65O

TUBEI ISEPARArioýN,

71o0 -0) ZO 4C * t a 0 00 0

a ~ ~ ~ ~ ~ ~ hL 10 a110D 0 It 1 4 o 0

ACC LERA104T RAEL IELAION~iP TANARD ROPLLEDWEIHT3 5O3

Pwopollont Actuated Dievicas

Catapult, Aircraft Ejection Seait, MWA

PLOCYRE-d. E RELATIONSMIP STANDARD PWOPILL WEIIGMT.350 LB.

g -4

II fI I.

30 uoIO m0tr Mbi~m.-aO~

3.14T-1, EAINIP TNADPMLC CS 5


Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, M4AI

The M4A1 Catapult is a gas actuated three-tube telescoping device, containing an explo-sive cartridge, designed to propel downward, an ejection seat together with a 'crewman from high-speed aircraft to provide safe escape from disabled aircraft.

The catapult is approximately 31 inches long and 2.6 inches in diameter. The catapulthas an initiator attached by a iength of flexible hose. A hen the initiator is functioned, the gasdeveloped flows through the flexible hose, exerting force against the catapult firing pin. Thefiring pin is propelled forward and strikes and detonates the primer, thereby igniting the blackpowder and propellant in the MY37 Cartridge. The catapult is unlocked by cam action as the firingpin moves toward the primer, unlocking the block assembly and inside tube. The catapult thrustwhich is developed from the expanding gases of the burning propellant, forces the inside andtelescoping tubes to move simultaniously until the shoulder on the telescoping tube comes incontact with the ring tube stop, thus restricting its movement. The continuous moving blockassembly and inside tube are ejected with the seat. The outside and telescoping tubes remainwith the aircraft.


Stroke 45.0 inchesWeight (total assembly) 6.7 pounds

Propelled Weight 325.0 poundsTemperature Limits -65' F to , 160'FMax Accel (at 70'F) 12.ý gVelocity, min. (at 70'F) 36.J fp-Max rate of change of Accel

(at 7/0F) I00.C g s.cFiring Method Gas Actuation

Stroke Time (at ' ") 0.2,0 s-,:

3.15

IPropel lont Actuated Devices

Catapult, Aircraft Ejection Seat, M4AA

I I?


Component Component

A Ring, Compression M "0" Ring

B p.ta-ce N Seal, Tamper Proof

C Tube, Outside 0 Latch (2)D Tube, Telescoping & Pellet Assembly P Plug

1_ Seal, Plain Q Washer, Shock

F Ring, Tube Stop & Pellet Assembly R Seal, Fixed

G Screw, Cap, Socket Head, Self-Locking S Tube, Inside & Pellet Assembly

II Pin, Shear T Seal, Plain

I Ring, Stop & Pellet Assembly U Cap & Pellet Assembly

J Pin, Firing V Cartridge, Aircraft Ejection ScatK Block Catapult, M%3"

L Plug, Shipping

Vy tip

Q to

'?AO

.35

-2.5006 +.01 DA

l 80.6 •N30.14 MAX

ENVELOPE DRAWING

3.16


Catapult, Aircraft Ejection Seat, MJAA

VRELOCITYTIUE RELATIONSHIP STANDARD PROP9ELLE WEIGHT:'325 LB .

IF.

.60 IF ... .. ..

0 sIgo too2o

VELOCITY-TiMERELATIONSHIP STNDR PROPELLED WEIGHT 325 LO.

V __

3.1


Catapult, Aircraft Election Seat, M4A1

-4 23URE-TRAVEL IIELATION" STANDARD PROPELLED WEIGHT* 325 LIS

160 F -- I T4:;;; ý 77 .-J.

-j- 700 F

-4

A4-7

runA --fIONA

-777T , . i 4

- I i . I -1 -7 ! I i-I I I I 1 -1 1 .ý I . 1 4-t0 a 0 0 so a 30 a ýw w

VELO"M-TRAVEL RELATIONSHIP STAMMAD PROPELLED WEIGHT: 325 L9,

1/1 ̀ 4 1:4 t L-111 I ý'I 1 1 ýk

+T

-70OFi L:L;w --4

L FL

-1 TUBE4 b -W4- SEPARATION

14

J;F

zi1 7,

4) 6 ID a 30 w 40 40 so

ACICELEVAtfON'TRAWL, WATIO"W STANDARD MtOMLEO WEIGHT-325 1-9.

-V J, -t

+-j

170'F I:70 FT

.6e tit-"uj

4' tTUBE

SEPARATION

-j

Li 1 1 ITo 4 to 4 0 a 30 Is AD soIUVEL-

3.18


Catapult

CATAPULT, AIRCRAFT EJECTION SEAT, MSA1

The M5Al Catapult is a gas actuated three-tube telescoping device containing an explo-sive cartridge, designed to propel upward an ejection seat together with a crewman from high-

speed aircraft to provide safe escape from disabled aircraft.

The catapult is approximately 39 inches long and 2.3 inches in diameter. The casapulthas an initiator attached by a length of flexible hose. When the initiator is functioned, the gas

developed flows through the flexible hose, exerting force against the catapult firing pin. Thefiring pin is propelled forward and strikes and detonates the primer, thereby igniting the blackpowder and propellant in the M28A1 Cartridge. The catapult is unlocked by cam action as the

firing pin moves toward the primer, unlocking the block assembly and inside tube. The catapultthrust which is developed from the expanding gases of the burning propellant forces the inside

and telescoping tubes to move simultahiously until the shoulder on the telescoping tube comesin contact with the trunnion, thus restricting its movement. The continuous moving block assem-

bly and inside tube are ejected with the seat. The outside and telescoping tubes remain withthe aircraft.


Stroke 66.0 inchesWeight (total assy) 8.2 poundsPropelled Weight 300.0 poundsTemperature limits -65'F to +160*FMax Accel (at 70'F) 20.0 gVelocity, min (at 70*F) 60.0 fpsMax rate of change of accel

(at 70'F) 170.0 g/secFiring Method Gas ActuationStroke Time (at 70 0F) 0.220 sec

3.19


Catapult, Aircraft Ejection Seat, MSA I

CROSS- SECTION DRAWING

Component Component-

A Cap JPin, ShearD Sel Plain K Ring, Step & Pallet AssemblyC, Tube, Outside & Pellet L **0" Ring

Assembly M BlockD Tube, Tlescoping N Pipe Plug, Shipping

Assembly P Seal, Tamper Proof

F Seal, Fixed Q Latch (2)G Trunnion R PlugH Washer, Shock S Cartridge, Aircraft Ejection SeatI Screw, Cap, Socket Head, Catapult, kI28Al

Self-Lockirtg T Seal, Plain

C.~~6 r, a 0

ZA50- ov5 SoCCIA

52 0112

ENELP DRAWING

3-2/


Catapult, Aircraft Ejection Seat, MSAI

1- PRESSMR-TRAVEL RELATI OND4IP STAME0ARO PROPELLED WCi6 HT: SOO L9.

16O

'41r~

-~SEPARATIOrI

7: VOCITY-TRA'EL RELATIONSHIP STANDARD PROPELLED WEIGHT: 300 L8.

-4-VO 160O$

1C - _; . . 3.2.1

Propellent Actuated Devictz

Catapult, Aircraft Electioni Seat, MSAI

P ESURE TOAE RELATIONSH4IP STANDARD PROPELLED WEIGHT: 300 La

n- ~ 70'F -

- -VEOCITY-TtME RELATIONSHIP STANDARD PROPELLED WEIGHT: 300 LB

71 -j w 6 o~'

IACCELERATION -TIME RELATIONSHIP STANDARD PROPELLED WEIGHT 300LS

3.22


Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, TRAINING, M6A1

The M6AI Catapult with the Cartridge, Aircraft Ejection Seat Catapult, Training, M57was designed to be used in the MH-15 Ejection Seat, Indoctrination Trainer (Mobile Type) for

indoctrinating U. S. Air Force trainees in the catapult ejection procedures. In this application,

the catapult ejects the seat and occupant along a guided track to about a height of 12 feet with

moderate acceleration.

The training catapult is a two-tube, mechanically actuated, short stroke unit which

is constructed of steel. The catapult is approximately 50.0 inches long. After actuation of thesafety plate, the catapult is actuated by mechanical operation by the indoctrinee by means of a

grip on the arm rest which is connected to the firing arm by a cable. Squeezing the grip rotatesthe firing arm and releases the spring loaded firing pin which strikes and detonates the primer,

thereby igniting the black powder and propellant in the M57 Cartridge. The catapult thrust

which is developed from the expanding gases of the burning propellant propels the seat andoccupant up the tower. The inside tube and firing head assembly. which are attached to the

sear, separate from the outside tube and are carried with the seat on ascent. The outside tube

and its permanently attached parts remain in the cockpit of the trainer.

There are two safety systems connected to the catapult. The first system consisting

of a plate prevents firing of the catapult inadvertently by the trainee, while the second preventsseat movement in the event of cartridge failure or other malfunctions. The latter safety system

is accomplished by rotating the catapult outside tube through a cable locking system located onthe trainer. This rotation causes the lugs of the bell cap located on top of the outside tube toengage corresponding protrusions inside the trunnion and securely locks both inner and outer

tubes together,

A ballistic safety value assembly, incorprating a pre-bulged rulpture disc, is attachedto the lower end of the catapult outside tube and its purpose is to bleed off excessive gaspressure which might result in an excessive height of travel on tho trainer.


Stroke 21.0 inches

Weight (total Assembly) 31.5 pounds

Propelled weight 300.0 poundsTemperature Limits 40'F to 125-F

Max accel (at 70°F) 8.5 g

Firing Method Mechanical Actuation

Stroke Time (at 70°F) 0.163 sec

3.23


Catapult, Aircraft Ejection Seat, Training, M6Al

-'T~


Component Component

A Valve, Safety Assembly K Spring, Firing Pin(shown out of position) L Ring, Sear

B Plate M Body, Breech

C Ring, Snap N Trunnion and BreechD Cap, Breech Ring Assembly

E Firing Arm Assembly 0 Cap, BellF Ring, Snap, Retaining, P Tube, Inside

Internal, Inverted Lug Q Tube, OutsideG Mount Assembly R Pin, Firing and StopIt Handle AssemblyI Slide S Cartridge, Aircraft Ejqction3 Spring, Sear, Ring Seat, Catapult, M57

(Installed atTraining Base)

ENVELOPE DRAiNx

•z~cs t{ -• DtA

3-24

DI

S49.995

ENVELOPE DRAWING

3.2

Propellant Actuated D~evices

Catapult, Aircraft Ejection Seat, Training, M6A1

ACCELERATION -TIME RELATIONSHIP I. . .'FTEMPERATURE 7Q0 F .......

................................... 11:1S

0 20 40 6O so 100 120 140 160TIME (MILLISECONDS)IACCELERATION -TIME RELATIONSHIP....

300 POUNDS PROPELLED

.........................

10 20 40. GO...0..2..4..E

- ~ .............

................ ....

0 20 40 Go 80 00 120 140' 160TIME (MILLISECOtNS)

.... ........

Praoeliant Actuote~l Devicts

Cotepult, Aircraft Ejection Siet, Ttaining, M6Al

.~AOCELERAT-O -TRAVEL RfiLATi0S~.4 :.

.... TEMPERATURE 70, F

----- ----- .....

..................................... ..

-------_ VA.CfETIN -TRAVEL RELATIOW14P

;:;l;::%::

3.:46

---------------

rl


Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, M8

The M8 Catapult is a rocket-assisted two tube telescoping device developed for use inthe F105 Aircraft to provide "off-the-deck" as well as high speed ejection capability from dis-abiled aircraft. The catapult is a two-stage device; the initial booster phase and final rocketmotor phase.

The catapult is approximately 46.3 inches long and 2.89 inches in diameter. The cata-pult has an initiator attached by a length of flexible hose. When the initiator is functioned, thegas developed flows through the hose, exerting force against the catapult firing pin. The .firingpin is propelled " ,ward and strikes and detonates the primer contained in the primary igniter.This action i "he firing of the booster phase. The primer ignites the pyrotechnic compo-sition contai, -- igniter which flashes down the booster tube igniting the strip propellantbonded co the b-., , wlder. The booster gas pressure moves the can, thereby permitting the tangsof the nozzle retainer to be cammed inward, unlocking the unit. Continued booster gas productionpropels the rocket motor and the seat vertically. At a point prior to motor tube separation, thecable, which is attached to the can, engages the cable guide on the stripholder assembly andforces the piston slider valve downward uncovering the gas by-pass ports on the cylinder boostertube assembly. This allows the hot booster gases to dump into the motor chamber which ignitesthe auxiliary igniter and the rocket propellant grain. The burning propellant grain produces gasat a high rate, pressurizing the motor chamber. This pressure forces out the nozzle cups allow-ing the gas to exhaust through the nozzle ports, thus providing thrust which propels the seat and

occupant upward and forward. The nozzle is canted 37'30, so as to direct the rocket thrust throughthe center of gravity of the seat-man combination.


Weight (total assembly) 27.0 lbs.Propelled Weight 350.0 lbs.Temperature Limits -650 to -, 160OF

Catapult (Booster Section)

Stroke 40 inchesMax Acceleration (at 70*F) 20.0 gVelocity (at 70'F) 40.0 fpsMax Rate of Change of

Acceleration (at 70'F) 300.0 g/secStroke Time (at 70'F) 0.175 secFiring Method Gas Actuation

3-27

Ptopelant Actuated Devices

catapults

PRINCIPAL CHARACTERISTICS (M8 Cont'd)

Rocket (Sustainer Section)

Action Time, max (at 701F) 0.400 sec.Impulse (resultant at 70'F) 1200 lb-sec.Pressure, max 4600 psi.Ignition Delay, max (at 70'F) 0.012 sec.Nozzle Angle 37030'

3.28

Propellant Actuated Dev ices

Catapult, Aircraft Election Sent, M8

A E E I'N~ K D L ESM D

DD0 'S' D' as WkA X. 1-. W D V U iT _ S


Component Component

A Breech, Launcher P Plug, ShippingB Can, bottom Q Sleeve, Firing PinC Holder, Cable Lower R Ring, RetainingD "0" Ring S Wire, LockE Screw, Set T Igniter, Primary AssemblyF Plate, Orifice U Igniter, Auxiliary AssemblyG Tube, Launcher And V Pin, Valve Shear (4)

Pellet Assembly W Screw (2)H Tube, Motor X W~ashe. (2)1 Trunnion Y Cylinder, Slider Valve And

jPiston, Slider N'alve Tube Booster Assembl%K Spring, Grain Z Collar, GrainL Cip, Igniter AA Holder, Strip, Loaded AssemblyNki Head, Motor Tube BB Propellant, Grain InhibitedN Pin, Firing CC Nozzle Assembly0 Pin, Shear DD Spring, Can

EE Screw, Set (4)

W.OTOR r5 i

+ Ik0 -

t--zs ?S -.OO6O01A-

4.. 4. -4ENVELOPE DRAWING

3.29/3-30


Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, M9

The M9 Catapult is a rocket-assisted two tube telescoping device developed for usein the T-38 Aircraft to provide "off-the-deck" as well as high speed ejection capability from

disabled aircraft. The catapult is a two-stage device; the initial booster phase and final rocketmotor phase.

The catapult is approximately 41.9 inches long and 2.89 inches in diameter. The cata-

pult has an initiator attached by a length of flexible hose. When the initiator is functioned, thegas developed flows through the hose, exerting force against the catapult firing pin. The firing

pin is propelled forward and strikes and detonates the primer contained in tile primary igniter.This action initiates the firing of the booster phase. The primer ignites the pyrotechnic compo-

sition contained in the igniter which flashes down the booster tube igniting the strip propellant

bonded to the strip holder. The booster gas pressure moves the can, thereby permitting the tangs

of the nozzle retainer to be cammed inward, unlocking the unit. Continued booster gas production

propels the rocket motor and the seat vertically. At a point prior to motor tube separation, the

cable, which is attached to the can, engages the cable guide on the strip holder assembly andforces the piston slider valve downward uncovering the gas by-pats ports. on thr cylinder booster

tube assembly. This allows the hot booster gases to dump into the motor chatrifer which ignites

Ethe auxiliary igniter and the rocket propellant grain. The b'lting propellant gtain produces gas

at a high rate, pressurizing the motor chamber. This pressure forces out the nozzle cups allow-

ing the gas to exhaust through the nozzle ports, thus providing thrust which 1,upels the seat

and occupant upward and forward. The nozzle is canted 47' 30, so as to direct the rocket thrust

through the center of gravity of the seat-man combination.


Weight (total Assembly) 24.0 lbs.

Propelled Weight 350 lbs.

Temperature Limits -65WE to -1 160Ul'


Stroke 35-3,;4 inches

Max Accel. (at 70'F) 20.0 gVelocity (at 700 F1 40.0 fps

Max. Rate of Change of 300 g secAccel. (at 70SF'

Stroke Time (at 7OtF) 0.160 sec

Firing Method Gas Actuation

3J31


Catapults

PRINCIPAL CHARACTERISTICS WM9 Cont'd)


Action Time, max (at 70 0F) 0.350 secImpulse (resultant at 70 0F) 1100 lb-secPressure, max 4600 psiIgnition Delay, max (at 70 0F) 0.012 secNozzle Angle 47030'

3.32


Catapult, Aircraft Ejection Seat, M9

x, x X

It 0 A I O 0 'I


Component Component

A Breech, Launcher P Plug, ShippingB Can, Bottom Q Sleeve, Firing PinC Holder, Cable Lower R Ping, RetainingD "0" Ring S tire, LockE Screw, Set T Igniter, Primary AssemblyF Plate, Orfice U Igniter, Auxiliary AssemblyG Tube, Launcher And V Pin, Valve Shear (4)

Pellet Assembly W Screw (2)H Tube, Motor X Washer (2)I Trunnion And Pellet Assembly Y Cylinder, Slider Valve AndJ Piston, Slider Valve Tube Booster AssemblyK Spring, Grain Z Holder, Strip, Loaded AssemblyL Cap, Igniter AA Collar, GrainM Head, Motor Tube BB Propellant, Grain InhibitedN Pin, Firing CC Nozzle Assembly0 Pin, Shear DD Spring, Can

EE Screw, Set (4)

.00 + X02 MA,. 3.00-.0o2.728-.oo l,"_ T \ : 132.89. .0 DA. 005 DIA,. 3.00 .J01 .500 DIA: 1'•2 r

4 7C•+>h 75,5L'' -I -o

6.242 0.2 .u-r* 2 L .563- .005

41.536 3i. i EF DI_ .41.342 • '16" 0LNF"3

ENVELOPE DRAWING

3.33

Propellant Actuated Device,

Catapult, Aircraft Ejection $*at, M9

IPRESSURE TI!m.L 1Z.CLATIONSHIPA I~ ' 'STANDARD PX-J)!1rL LED WRIGHT =350 LB~I

4000-

100 5., 100 ISO 2002503003 5 40 04O500 55 0- 650 700 1/so

TIME - MILLISECONDS

I- fVELOCITY TIME RELATIONSHIP- 4NOZZLE ANGLE 47'30'

' ISTAN.'.'.RD PROPELLED WRIGHT =350 LB

TOTAL HEIGHT OF TRAVEL =220 FT

L12VEOIT = 10.3 FTSVELOCITY = 104.33 FT /SEC

1200

605> - CTPL ELCT=42F/E

I -CATAPULT VELOCITY 4440. FT/SEC

L _

0 s0 100 IS0 200 250 300 350 400 450 500 550 600 630 700 750

TIMtE - MILLISECONDS

ACCELERATION4 TIME RELATI'ONSI-UP

STANDARD PROPELLED WRIGHIT =350 L -

z 160OFIENDT . OF CATAPULT STROKE

w 0r70'Fw 20 [ -4 END OFCATAPULT STROKEE - -

U - END 0O' CATAPULT STROKE .

0 so 100 150 200 250 300 350 400 450 300 350 600 650 700 750

TIME - MILLISECONDS

3.34

Propellant Actuate Devices

Catapults

CATAPULT, AIRCRAFT EJECTIF2N SEAT, 14O

The MIO Catapult is a rocket-assisted two tube telesc.ping device developed for usein the F104 Aircraft to provide "off-the-deck" as well as high speed ejection capability fromdisabled aircraft. The catapult is a two stage device; the initial booster phase and final rocket

motor phase.

The catapult is approximately 44.1 inches long and 2.89 inches in diameter. The cata-pult has an initiator attached by a length of flexible hose. Then the initiator is functioned, thegas developed flows through the hose, exerting force against the catapult firing pin. The firing

pin is propelled forward and strikes and detonates the primer contained in the primary igniter.

This action initiates the firing of the booster phase. The primer ignites the pyrotechnic compo-

sition contained in the igniter which flashes down the booster tube igniting the strip propellant

"bonded to the strip holder. The booster gas pressure moves the can, thereby permitting the rangs

of the nozzle retainer to be cammed inward, unlocking the unit. Continued booster gas production

propels the rocket motor and the seat vertically. At a point prior to motor tube separation thecable, which is attached to the can, engages the cable guide on the strip holder assembly and

forces the piston slider valve downward uncovertng the gas by-pass ports on the cylinder booster

tube assembly. This allows the hot booster gases to dump into the motor chamber which ignite

the auxiliary igniter and the rocket propellant grain. The burning propellant grain produces gas

at a high rate, pressurizing the motor chamber. This pressure forces out the nozzle cups allow-

ing the gas to exhaust through the nozzle ports, thus providing thrust which propels the seat andoccupant upward and forward. The nozzle is canted 3 6W 2 0 ', so as to direct the rocket thrustthrough the center of gravity of the seat-man combination.


Weight (Total Assy) 26.0 pounds

Propelled Weight 400.0 poundsTemperature Limits -651F to + 160 0F


Stroke 34.0 inches

Max. Acceleration (at 70 0F) 20.0 gVelocity (at 70"F) 40.0 fps

Max. Rate of Change ofAcceleration (at 70F) 350.0 g/sec

Stroke time (at 701F) 0.155 sec

Firing Method Gas Actuation

3

3-35


Catapults

PRINCIPAL CHARACTERISTICS WMIO Cont'd)


Action Time, mix. (at 70'F) 0.400 secImpulse (resultant, at 70'F) 1100 lb-secPressure, max. 4600 psiIgnition Delay, max. (at 70"F) 0.012 secNozzle Angle 36- 20"

3.36

Pitop.Ilant Actuotod D~vices

Catapult, Aircraft Eitiction Seat,, Mill

CROSS.-SECTIOII DRAWIN4G

Component Component

A Breech, Lau~ncher Trunnion QPin, ShearB Can, Bottom R Head, Motor TubeC Holder, Cable Lower S Plug, 'Shipping

D "C"W Ring T Pin, FiringE Screw, Set U Sleeve, Firing Pin

F Plate, Orifice V Cap, Igniter Retaining

G Propellant Grain, Inhibited X% Wire, Lock

HI Tube, Launcher X Igniter, Auxiliary Assembly

I tube, motor Y Pin, Valve, Shear (4)

J Screw (2) Z Cylinder, Slider Valve AndK W'asher (2) Tube Booster AssernblyL Sleeve, flead AA Holder, Steip Loaded AssemblyNI Spring, Grain BB Collnr, GrainN Piston, Slider Valve CC Nozzle Assembly

o Igniter, Primary Assembly DD Spring, CanP Ring, Retaining EE Screw Set (4)

It*-.62S.003DIA.31nI

.~.?7

Oc .00 DI . 1.250

4193 40.864 REF 2 38DA

ENVELOPE DRAWING

3-37

Propellant Actuated Devicel

Catapolt, Aircraft Ejection Seat, M110Of

PRESUE TIM REILAISONSHI

STNERDPOPELLE WEIGHT 400SE

400CT 13. Y/E

1 300

0 50 100 ISO 200 250 300 35n0 400 450 500 550 600 650 To0

TIME - MILLISECONDS

AVELECATYO TIME RE LATIONSHIPN~OZZLE ANGLE 360 20

, ~ ~ ~ STANDARD PROPELLEI) WRIGHT =400LB -

TNONCTALHIGHT SFTROKE ý 37F

VLCTI Y - 11"_ LISECONS

3.3CT8132 liSC


Initiators

SECTION IV

IINITIATORS

rLPropellant Actuated Devices

Initiators

INTRODUCTION

Description:

An initiator is an actuating energy source for the operation of the firing mechanisms ofother propellant actuated device components of aircrew escape systems. It is a cylindricaldevice consisting of a chamber with a pressure outlet port, a firing mechanism and a cartridge.

Initiator devices are classified in accordance with the following characteristics:(1) Method of Actuation - mechanical or gas pressure; (2) Function Time - nondelay or delay;and (3) Performance - low or high pressure energy.

Operation:

Actuation of the mechanical initiator is accomplished by an axial load application tothe initiator pin. The firing pin, which is locked to the initiator pin with steel balls, compressesthe spring enclosed in the firing pin housing and initiator cap, upon initiator pin withdrawal.

When the firing pin enters the relieved section of the spring enclosure, the balls move outward,disengaging the initiator pin which is withdrawn from the device. The released firing pin isthen propelled against the cartridge percussion primer by the exerted force of the compressedspring.

Actuation of the gas-fired initiator is accomplished when gas pressure. supplied byanother propellant actuated device is introduced into the initiator inlet port, exerting a forceagainst the firing pin which is retained in position by a shear pin. The resultant- force appli-cation, causing shearing of the pin, propels the firing pin against the cartridge percussion primer.

4-1/4.2

4Propellant Actuated Devices

Initiators

INITIATOR, CARTRIDGE ACTUATED, M3AW

The M3AI Initiator consists of a constant volume chamber with a pressure outlet port

incorporating a standard pressure fitting, a mechanically operated firing mechanism and an M73Cartridge. A length of tube or hose connects the initiator to another remotely installed propellantactuated device.

Upon cartridge function, the gas produced by the burning of the propellant and blackpowder charge flows through the tube to the gas pressure actuated firing mechanism of the other

propellant actuated device, exerting a force which propels the firing pin against the cartridgecontained in that device. The length of the connecting tube and/or hose, or the distance thatthe initiator can be mounted from the other device, is limited by the firing pin energy required

for reliable operation of the device.


Actuation Method Mechanical

Actuation Force 40 lbs. min.Temperature Limits -65*F to + 160'F

Assembled Weight 0.9 lb.

TYPICAL PERFORMANCE

Goge Chomber Vol. - .062 in 3

Flexible Hos. MS 28741.4$ 70OF

4M4

0. I2

0 4 a 12 Is 20

Tube length (ft)

4.3

!,


Initiator, Cartridge Actuated, MMA


Component Component

A Pin, Initiator G Cap, ShippingB Pin, Safety H Cartridge, InitiatorC .10" Ring I Pin, FiringD Spring, Initiator J Housing, Firing PinE Ball K Cap, InitiatorF Chamnber, Initiator L Cartridge, Initiator, M73 Asscmblv

-1.6S7 MAX; 4.34() MAX.

23 1.085 MAX.

1815

7 2 DIA-' I 2 A

4 .6

O1rm .29 I00 MIA

ISAFETY PIN-.2908DAINSERT IN EITHER POS. 2 HOLES

ENVELOPE DRAWING

4.4

r


Initiators

INITIATOR CARTRIDGE ACTUATED, DELAY, M4

The M4 Initiator consists of a constant volume chamber with a pressure outlet portincorporating a standard pressure fitting, a mechanically operated firing mechanism and an M46Delay Cartridge. A length of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an M5 Delay Element contained in the cartridge burns for 2seconds, after which the propellant and black powder are ignited. The gas produced by theburning of the propellant and black powder charge flows through the tube to the gas pressureactuated firing mechanism of the other propellant actuated device, exerting a force which pro-pels the firing pin against the cartridge contained in that device. The length of the connectingtube and/or hose, or the distance that the initiator can be mounted from the other device, islimited by the firing pin energy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -65'F to +160'FAssembled Weight 1.0 lb.Delay Time 2.0 seconds

TYPICAL PERFORMANCE

Gage Chamber Vol. = .062 in3

SP Flexible HIose M$28741-4700 F

04

0

I.,

0 2 4 I 8 10

"Tube length (ft.)

4.5


Initiator, Cartridge Actuated, Delay, M4

QE

b F,


Component Component

A Spring, Initiator H Housing, Firing PinBi "0" Ring I CapC Ball J Pin, SafetyD Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator.F Retainer, Cartridge Delay M46 AssemblyG Pin, Firing

Ia-----1.657 MAX 5.03 MAXP ~4.89 MIN011

6 -1.08S MAX.

I S6

4 s56S2 .0 *:D fIA- A'

sag ý 0 '0 I2A 0 13 OJA

3 4U

TRAVEL 20 UN'F. 3A

SAFE TY PIN. .:21MX. 94081A

INSE;RT IN' EITILER POS. A0IIN2 HOLES

ENVELOPE DRAWING


Initiators

INITIATOR, CARTRIDGE ACTUATED, MSA2

The M5A2 Initiator consists of a constant volume chamber with a pressure outlet portincorporating a standard pressure fitting, a gas pressure actuated firing mechansim and an M73Cartridge. A length of tube or hose connects the initiator to another remotely installed propellant

4a¼-,-33t device.

Upon cartridge function, the gas produced by the burning of the propellant and blackpowder charge flows through the tube to the gas pressure actuated firing mechanism of the otherpropellant actuated device, exerting a force which propels the firing pin against the cartridgecontained in that device. The length of connecting tube and/or hose, or the distance that theinitiator can be mounted from the other device, is limited by the firing pin energy required forreliable operation of the device.


Actuation Method Gas PressureActuation Force 750 -ý mrin.Temperature Limits -65 0 F to +160'FAssembled Weight 0.9lb.

TYPICAL PERFORMANCE

Gage Chambee Vol. -. 062 in3

Flexible oas# MS 28741-470OF

,4p I.

0 4 a 12 16 20

Tube length (ft)

4-7


Initiator, Cartridge Actuated, M5A2


Component Component

A Plug, Shipping F Cap, ShippingB Pin, Shear G3 Chamber. InitiatorC Cap H- Retainer, CartridgeD Pin, Firing 1 410" RingE Housing, Firing Pin J Cartridge, Initiator, N173 Assembly

_4A12 NUIMIJM LENGTHI

4.8_ '4

Propellont Actuated Devices

Initiators

INITIATOR, CARTRIDGE ACTUATED, DELAY, M6A1

The NM6A1 Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fitting, a gas pressure actuated firing mechanism and

an M46 Delay Cartridge. A length of tube or hose connects the initiator to another remotelyinstalled propellant actuated device.

Upon cartridge function, an M5 Delay Element contained in the cartridge burns for two

seconds, after which the propellant and black powder are ignited. The gas produced by theburning of the propellant and black powder charge flows through the tube to the gas pressureactuated firing mechanism of the other propellant actuated device, exerting a force which propelsthe firing pin against the cartridge contained in that device. The length of the connecting tubeand/or hose, or the distance that the initiator can be mounted from the other device, is limitedby the firing pin energy required for reliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi min.Temperature Limits -65 0 F to + 160'FAssembled Weight 0.9 lb.

TYPICAL PERFORMANCE


Flexible Hose MS28741.470OF

fi t I I 1 -. 1 1 1

2 4 6 a 10

Tube length (ft.)

4.9


Initiator, Cartridge Actuated, Delay, M6A1


Component Component

A Pin, Shear G Retainer, CartridgeB Cap H Housing, Firing PinC "0" Ring 1 "0"' RingD Pin, Firing ) Plug ShippingE Cap, Shipping K Cartridge, Initiator, Delay,F Chamber, Initiator M46 Assembly

to~~ 505-3 t ~ -- r

i-lT

ENVELOPE DRAWING

4.10

Propelant Actuate Devices

|nitiators

INITIATOR, CARTRIDGE ACTUATED, M8

The M18 Initiator is a cylindrical constant volume device consisting of a mechanicallyoperated firing mechanism, a chamber and end cap with a pressurT outlet port incorporating a

standard pressure fitting and an M68 Cartridge. A length of tube os- hose connects the initiator to

another remotely installed propellant actuated device.

Upon cartridge function- the gas produced by burning of the propellant and black powdercharge flows through the tube to the gas pressure actuated firing mechanism of the other propel-

lant actuated device, exerting a force which propels the firing pin against the cartridge contained

in that device. The length of connecting tube and/or hose, or the distance that the initiator can be

mounted from the other device, is limited by the firing pin energy required for reliable operation of

the device. The Kil Initiator is capable of delivering to an .062 in0 terminal chamber volume at the

end of a 30 foot length of MS28741-4 hose, pressure within the limits of 1000 psi minimum and

3000 psi maximum.



Actuation Force 40 lbs rain

Temperature Limits -65 0 F to + 1600 FAssembled Weight 3.2 lhbs.

4.11


Initiator, Cartridge Actuated, M8

ýpN m

\- ,- /\


Coniponent Component

A Guide, Firing Pin J Cap, End

B Spring, Firing K Cap, ShippingC Ball L Body

D Guide, Firing P.n M StrapE Pin, Firing N Stand

F Screw, Set 0 Wire Lock

G Cartridge, N168 P Pin, Saferv.H -O" Ring Q Cap, Initiator

I Filter

3 --

1o2mAx .29r .09S DIA-- 212i\ i , . .,2,<>,.,,,,,,

___________7.S,9 MX

ENVELOPE DRAWING

4.12

1.$22 IA MAZ2 i I


Initiators


The M9 Initiator is a cylindrical constant volume dev-ice consisting of a gas pressureactuated firing mechanism, a chamber and end cap with a pressure outlet port incorporating astandard pressure fitting and an M69 Cartridge. A length of tube or hose connects the initiatorto another remotely installed propellant actuated device.

Upon cartridge function, the gas produced by burning of the propellant and black powdercharge flows- through the tube to the gas pressure actuated firing mechanism of the other propel-lant actuated device, exerting a force which propels the firing pin against the cartridge containedin that device. The length of connecting tube and/or hose, or the distance that the initiator can be

mounted from the other device, is limited by the firing pin energy required for reliable operation ofthe device. The M9 Initiator is capable of delivering to an .062 in 3 terminal chamber volume at theend of a 30 foot length of MIS28741-4 hose, pressure within the limits of 1000 psi minimum and309)0 psi maximum.


Actuation Method Gas PressureActuation Force 750 I-si MraTemperature Limits --6 5 1F to 160PFAssembled Weight 3.2 lbs.

4-13

[ -1




Component Component

A Cap. Initiator H FilterB Stand I Cap, ShippingC Wire, Lock 3 Cap, EndD Pin, Firing K BodyE Cartridge, Initiator, L Strap

M169 Assembly MI Pin, Shear AndF Screw, Set Screw, SetG "0" Ring

L3_______________ 7.091 MAX

64L 697 H64 16 VF. 3A .565 MIAX

755 10 1SDA, I L3DIA. -

1.82 DIA *

AC P035 FLAtj.20U~ 3 16 j.20UNr. JA

ENVELOPE DRAWING

4.14

fjPropellant Actuated Devices

Initiators

INITIATOR, CARTRIDGE ACTUATED, DELAY, M1O

The MI0 Delay Initiator consists of a constant volume chamber with a pressure outlet

port incorporating a standard pressure fitting, a gas pressure actuated firing mechanism and an

M10 Delay Cartridge. A length of tube or hose connects the initiator to another remotely in-

stalled propellant actuated device.

Upon cartridge function, an M5 Delay Element contained in the cartridee burns for twoseconds, after which the propellant and black powder are ignited. The gas produced by the burn-

ing of the propellant and black powder charge flows through the tube to the gas press.ure actuated

firing mechanism of the other propellant actuated device, exerting a force which propels the firing

pin against the cartridge contained in that device. The length of the connecting tube and or hose,or the distance that the initiator can be mounted from the other device, is limited ky the firing pinenergy for reliable operation of the device.

PRINCIPAL CHARACTERISTICS I

Actuation Method Gas PressureActuation Force 750 psi minTemperature Limits -65cF to - 160 F

Assembled Weight 0.9 lb.Delay Time 2.0 seconds

TYPICAL PERFORMANCE

Gage Chamber Vol. - .062 ins

Flexible Hose MS28741.470 0F

I ta.

Dj.

0 4 0 12 16 20

Tube length (ft)

4. 15

L|

Proptllant Actuated Devices

Initiator, Cartridge Actuated, Delay, MID


Component Component

A Pin, Shear F Cartridge, Initiator,B "0" Ring Delay, %1"10 Assembly

C Pin, Firing G Retainer, CartridgeD Cap, Shipping H Housing, Firing Pin

E Chamber, Initiator I Cap

J Plug, Shipping

5.491 M.AX _____.81 .O S~~5.375 MMII

I ! .20 UN?. 3D- OMO

176

S F _ _41

r_____ 1.5 AXW(

416

-I


Initiators


The N112 Initiator consists of a constant volume chamber with a pressure outlet port

incorporating a standard pressure fitting, a mechanically operated firing mechanism and an S171Delay Cartridge. A length of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an M8 Delay Element contained in the cartridge burns for Isecond, after which the propellant and black powder are ignited. The gas produced by theburning of the propellant and black powder charge flows through the tube to the gas pressureactuated firing mechanism of the other propellant actuated device, exerting a force which propelsthe firing pin against the cartridge contained in that device. The length of the connecting tubeand/or hose, or the distance that the initiator can be mounted from the other device, is limitedby the firing pin energy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -65cF to + 160cFAssembled Weight 1.0 lb.Delay Time 1.0 second

TYPICAL PERFORMANCE

Gage Chamber Vol. -t.062 in3

SFlexible Hose MS28741-470°F

0 2 t o

Tube length (ft.)

4.17



\I

A C

j I FCROSS-SECTION DRAWING

Component Component

A Spring, Iniriaror H Housing, Firing PinB q0" Ring I CapC Ball J Pin, SafetyD Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator,F Retainer, Cartridge Delay, M7I AssemblyG Pin, Firing

1.6S71 MAX -P 45.083 MAX

13 74.89 WNNM10. . , AX.

7Z 2 DIA - .56. 088 3 M - - "- .A× "

-. 005 JDIA-~O

S88 DIA DIA

3 .

""iRAVEL 20UF.3A

k,.261 MAX .259+ . DIA,

SAFETY PIN- 1.160 LUN

INSERT IN EITHER POS. 2 HOLES

ENVELOPE DRAWING4.18


Initiators

INITIATORS, CARTRIDGE ACTUATED, DELAY, Mi4

The M14 Delay Initiator, a miniature version of the M45 Delay Initiator, consists of a

constant volume chamber with a pressure outlet port incorporating a standard pressure fitting, amechanically operated firing mechanism and an M84 Delay Cartridge. A length of tube or hoseconnects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an XM25 Delay Element contained in the cartridge, bums for3 seconds, after which the propellant and black powder are ignited. The gas produced by the burn-

ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or distance that the initiator can be moun:ed from the other device, is limited by the firing pinenergy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs min

Temperature Limits -65'F to + 160'FAssembled Weight 0.39 lb.Delay Time 3.0 secondsMounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chamber Vol. = .062 in 3

Flexible Hose MS28741-470OF

- I I

0 t 6 a I0

Tube length (it.)

4.19




Component Component

A Seal G Pin, Firing

B Spring, Initiator H Balls (3)C Housing, Firing Pin I Cap, InitiatorD Filter J Pin, SafetyE Cap, Shipping K Pin, InitiatorF Chamber, Initiator L Cartridge, Initiator, Delay,

XM84 Assembly

-088---005""-- , ." , MAX - O-

ACAOSS FlArs I

- - ,-20UNF - ALý342-r0o -.

~% TRA~fL- -. N- 2 'OLfs

ENVELOPE DRAWING

1.20

A

Propllant Acuvoted Devicels

Initiators

INITIATOR, CARTRIDGE ACTUATED, DELAY, MIS


constant volume chamber with a pressure outlet incorporating a standard pressure fitting, a gas

pressure actuated firing mechanism and an M84 Delay Cartridge. A length of tube or hoseconnects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an XM125 Delay Element contained in the cartridge burns for 3seconds, after which the propellant end black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exertirg a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,

or the distance that the initiator can be mounted from the other device is limited by the firing pinenergy for reliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi rainTemperature Limits -65 0 F to + 160'FAssembled Weight 0.39 lb.Delay Time 3.0 secondsMounting Integral Lugs

TYPICAL PERFORMANCE

Gag* Chamber Vol. - .062 in3

5 PFixibl* Hose MS2974k.4

0 700Faa4

lf I I I I I I 0I I

If I

tILL]a.J

* 2 4 4 S 10

Tube length (ft.)

Proptilant Actuated Devices



Component Component

A "0" Ring F Cartridge, Initiator,B Pin, Firing Delay, XN184 AssemblyC Chamber, Initiator G Pin, ShearD Cap, Shipping H- Cap, InitiatorE Filter I Plug, Shipping

5. 14350AX

+

ENVELOPE DRAWING

4.22


Initiators

INITIATOR, CARTRIDGE ACTUATED, DELAY, M16


constant vohtme chamber with a pressure outlet port incorporating a standard pressure fitting, a

mechanically operated firing mechanism and an XM85 Delay Cartridge. A length of tube or hose

CoC -rects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an XM25 Delay Element contained in the cartridge, bums for3 seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuated


pin against the cartridge contained in that device. The length of the connecting tube and/or hose;or distance that the initiator can be mounted from the other device, is limited by the firing pin en-

ergy required for reliable operation of the device.


Actuation Method ;kechanicalActuation Force 40 lbs minTemperature Limits -65°F to + 160'FAssembled Weight 0.39 lb.

Delay Time 3.0 secondsMounting Integral Lugs

TYPICAL PERFORMANCE

SGage Chamber Vol. = 062 in3

Flexible Hose MS 28741-4- 8 70OF

. . . . . . . . .

xE

o 4 a 12 Is to

Tube length (ft)

4.23



/CROSS-SECTION DRAWING

Component Component

A Seal G Pin, FiringB Spring, Initiator H Balls (3)C Housing, Firing Pin I Cap, InitiatorD Filter J Pin, SafetyE Cap, Shipping K Pin, InitiatorF Chamber, initiator L Cartridge, Initiator, Delay,

XM85 Assembly

-,5 MAX B~ ~

""-' I " - r "-'- ,-. 3S4f MAX

MUM~C CRWE -~ I DF

ENVELOPE DRAWING

4.24

Pgoptllont Actuated DOvices

Initiators


The M26 Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fitting. a gas pressure actuated firing mechanism and a-iM90 Delay Cartridge. A length of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an M14 Delay Element conained in the cartridge burns for 0.3second, after which the propellant and black powder are ignited. The gas produced by the burningof the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels thefiring pin against the cartridge contained in that device. The length of the connecting tube and-'orhose, or the distance that the initiator can be mounted from the other device, is limited by thefiring pin energy required for reliable operation of the device.


Actuation Method Ga PressureActuation force 750 psi min.Temperature Limits -65'F to +160"FAssembled Weight 0.9 lb.

Delay Time 0.3 second

TYPICAL PERFORMANCE

Gag* Chomber Vol. = .062 in3

Flexible Hoes MS28741.470 0 F

-4

2::

S0 2 4 6 8 tO

Tube length (ft.)

S~4.25 I I'

!-L LL

Piopellant Actvoed Devices

initiator, Cartridge Actuated, Delay, M26


Component Component

A Pi n, Shear G Retainer, CartridgeB Cap H Housing, Firing Pin

C 110" King " 0.' RingD Pi n, Firing J Plug, ShippingE Cap,, Shipping K Cartridge, Initiator, Delay.F Chamber, Initiator M90 Assembly

I 5cUiP6-=

ENVELOPE DRAWING

4.26

Propellont Actuatoi Devices

Initlatots


The M27 Initiator, a miniature version of the %f3Al Initiator, consists of a constant vol-ume chamber with a pressure outlet port incorporating a standard pressure fitting, a mechanicallyoperated firing mechanism and an M91 Cnrrridge. A length of tube or hose connects the initiator to

another remotely installed propellant actuated device.

Upon cartridge fdnctien, the gas produced by the burning of the propellant and black pow-

der charge flows through the tube to the gas pressure actuated firing mechanism of the other pro-pellant actuated device, exerting a force which propels the firing pin against the cartridge con-

tained in that device. The length of the connecting tube and/or hose, or distance that the initiator

can be mounted from the other device, is limited by the firing pin energy required for reliable oper-

ation of the device.


Actuation Method MechanicalActuation Force 40 lbs m:nTemperature Limits -650 to + 160 0FAssembled Weight 0.33 lb.Mounting Integral Lugs

TYPICAL PERFORMANCE

Gae Chamber Vol. - .062 in3

Flexible Hose MS 28741-4706F

wE

0 4 6 12 16 20

Tube length (ft)

4-27




Component Component

A Seal H Pin, FiringD Spring, Initiator I BallC Housing, Firing Pin JCap. InitiatorD Filter K Pin, SafetyE Cap, Shipping L Pin, InitiatorF Chamber, Initiator NI Cartridge, Initiator, N191 Asitinbly

G "0" Ring

f~--4.9161 MA'x

-. 005 l~k0*A

ENVELOPEV DRAIN

4.2

Ptepotlaftt At,.ttd Oewvico

Initiaubrs

INITIATOR, CARTRIDGE ACTUATED, MZ2

The M28 Initiator, a miniature etrsion of the MSA2 Initiator, cunsists of a constant vol-ume chamber with a pressure outlet port incorporating a standard pressure fitting, a gas pressure

actuated firing mechanism and an M91 Cartridge. A length of tube or hose connects the initiator

to another remotely installed propellant device.

1.4 on cartridge function, the gas produced by the burning of the propellant and black pow-der charge flows through the tube to the gas pressure actuated firing mechanism of the other pro-pellant actuated device, exerting a force which propels the firing pin against the cartridge con-tained in that device. The length of connecting tube and/or hose, or the distance that the initiatorcan be mounted from the other device, is limited by the firing pin energy required for reliable oper-ation of the device.


Actuation Method Gas PressureActuation Force 750 psi minTemperature Limits -65°F to + 160OFAssembled Weight 0.3 lb.Mounting Integral Lugs

TYPICAL PERFORMANCE

Gag* Chamber Vol. = .062 in3

Flaxibt. Hose MS 28741.4700 F

I 2S f0.,

0 4 S 12 16 20Tube length (It)

4.29

r _

|a i pivtr e•id19 At |ive tsd, M29


C o m p onie n t C o m p o n e n t

A "0" Ring F Filter

B Pin, Firing G Cartridge, Initiator, %191 Assembly

C "0" Ring H Pin, ShearD Chamber, Initiator I Cap, Initiator

E Cap, Shipping J Plug, Shipping

4.0185 MAX -I

-• •.14

0

|

I~~ ..

r 2() uNF -3A -

--•

.16

-

16O- - .17 MAX DIA " ' L

• ."'oW^

.525 A6 IACROSS 1.125 1.13S MAX DIA

FLATS -20 UNP- 30

ENVELOPE DRAWING

4.30


The M29 Initiator consists of a constant volume chamwer with a l't.'%uft outl-t port

incorporating a standard pressure fiting, a mechanically operated tiring met hanm, ai M-3A

Cartridge, an integral armingt mechanism with a gas intake port and a manual override, and in-tegral mounting lugs. A length of tube or hose connects the initiator to another rcenotely In-stalled propellant actuated device.

Actuation of this initiator is accomplished when gas pressure supplied by another pro-pellant actuated device is introduced into the intake port of the arming mechanism, causing thearming mechanism to disengage with the preloaded initiator pin. The sequence of actuation events

following are the same as those for the conventional mechanical initiator.

Upon cartridge function, the gas produced by the burning of the propellant and black pow-der charge flows through the tube to the gas pressure actuated firing mechanism of the other pro-

pellant actuated device, exerting a force which propels the firing pin against the cartridge contained

in that device. The length of the connecting tube and/or hose, or the distance that the initiator canbe mounted from the other device, is limited by the firing pin energy required for reliable operation

of the device.


Actuation Method Gas Pressure w/manual overrideActuation Force 750 psi min

Initiator Pin Preload 40 lbs minManual Override Force 25 lbs main

Temperature Limits --650 F to 1 160 0FAssembled Weight 1.75 lbs.

TYPICAL PERFORMANCE

Gage Chamber Vol. a.062 idFlexible Hose MS 28741-4

•t6

'CC.., . .. ... . .... .. ..

a---- -- --

o a S$ 20

Tube length (fOl

4-.

I

trellellat Actieiv Ovices

Iiti•~, Cowtidge ActWd, ht"

iA.K ,i. ' .i .c

SEE SECTION &-A

CP a

L~ SECTION A-A tG


Component Component

A Gasket J Pin, Initiator

B Balls (3) K Stop, PistonC Retainer, Cartridge L PistonD Cartridge, Initiator, M73 N1 Gasket

E Pin, Firing N GasketF Spring, Initiator 0 Spring, ExactorG Housing, Firing Pin P Ring. LockingIi Gasket Q Gasket

I Gasket R Gasket

.380 MIN TRAVELi 64 i i : r.400 MAX TrRAVEL

.188D +.002 a .

I00 -42

ýP, I I I IzS9 +.009 2 HOLES

2.23O'0 0 I _.1

21 I-.----TRAVEL 5.295 MAX

ENVELOPE DRAWING

4.32

U

Pu•"ellest Actuate Devices

InitiateTs

INITIATOR,CARTRIDGE ACTUATED, DELAY, M30

The M•O) Initiator consists of a cons•tant volume chamber with a prr•sure outlet portincorporating a standard pressure fitting, a mechanically operatud tfring mchanism and an MTlUDelay Cartridge. A length of tube or hose connects thei initiator to another renmotelv installed

propellant actuated device.

Upon cartridge function, an M5 Delay Element contained in the cartridge bumrs for 2seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firing

pin against the cartridge contained in that device. The length of the connecting tube and/or hose,or the distance that the initiator can be mounted from the other device, is limited by the firing pinenergy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs min

Temperature Limits -65OF to + 1600 F

Assembled Weight 1.0 lb.Delay Time 2.0 seconds

TYPICAL PERFORMANCE


Flexible Hose MS 28741.4

070OF

t,: ( I IIt

Tb legh(t

C4

0 4 S It• 18 20

• Tube length (It)

1 4-33

Inititatr, Cautridg. Actwattil, Dolay. 1430


ýComponent Component

A Spring, Initiator H Housing, Firing PinB "0" Ring I CapC Balls (3) J Pin, SafetyD Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator,F Retainer, Cartridge Delay, M-0 AsscmblyG Pin, Firing

LOP MAX.

-IMAX4~3] 18~DIA *

4 A-50~~3ODS) 1 DI

.18 + 0,DA 3I

3V

SAFETY PIN -INSERT IN FITI]ER POS. 11ol 2 1 OL ES

ENVELOPE DRAWING

4.34 1

Propellant Actuated Dovices

Initiators


The M131 Delay Initiator consists of a constant --olume chamber with a pressure outletport incorporating a standard pressure fitting, a gas p:essure actuated firing mechanism and an

M93 Delay Cartridge. A length of tube or hose connects the initiator to another remotely in-stalled propellant actuated device.

Upon cartridge function, an M8 Delay Element contained in the cartridge bums for 1second, after vuhich the propellant and black pcwder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actu-ated firing mechanism of the other propellant actuated device, exerting a force which propels thefiring pin against the cartridge contained in that device. The length of the connecting tube and/or hose, or the distance that the initiator can be mounted from the other device, is limited bvthe firing pin energy for reliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi minTemperature Limits -65'F to + 160'FAssembled Weight 0.9 lb.Delay Time 1.0 second

TYPICAL PERFORMANCE


Flexible Hoae MS 28741.470OF

07.

4log

0 a 12 is 20Tsibe length (ft)

4-35i|4




Component Component

A Pin, Shear F Cartridge, Initiator,

B "0" Ring Delay, M93 Assembly

C Pin, Fixing G Retainer, Cartridge

D Cap, Shipping H Housing, Firing Pin

E Chamber, Initiator I CapJ Plug, Shipping

5.491 MAX

-2 -!- - - ,

5..36I

f Mat I

~~~~~~s MAN73M~--- ~j.

ENVELOPE DRAWING

4.36


Initiators

IHITIATOR,CARTRIDGE ACTUATED, DELAY, M32

The M132 Initiator consists of a constant volume chamber with a pressure outlet port in-corporaring a standard pressure fitting, a mechanically operated firing mechanism and an N193

Delay Cartridge. A length of tube or hose connects the initiator to another remotely installed pro-pellant actuated device.

Upon cartridge function, an M8 Delay Element contained in the cartridge burns for 1second, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuated

firing mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,

or the distance that the initiator can be mounted from the other device, is limited by the firing pin

energy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 ibs. min.Temperature Limits -65F to + 160'FAssembled Weight 1.0 lb.

Delay Time 1.0 second

TYPICAL PERFORMANCE

Gage Chamber Vol. -. 062 in3

Flexible Hose MS 28741-4a.8 70OF

2

0 4 a 12 16 toTube length (ft)

4.3!! 2a.t' <0




Component Component

A Spring, Initiator H Housing, Firing PinB "0" Ring I CapC Balls (3) J Pin, SafetyD Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator,F Retainer, Cartridge Delay, M93 AssemnblyG Pin, Firing

44

005ET ;'N .259 DI

ENAVELOP DRAWINGF-

4.38


Initiators


The M33 Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fitting, a gas pressure actuated firing mechanism and anM71 Delay Cartridge. A length of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an M8 Delay Element contained in the cartridge burns for Isecond, after which the propellant and black powder are ignited. The gas produced by the burningof the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels thefiring pin against the cartridge contained in that device. The length of the connecting tube and/orhose, or the distance that the initiator can be mounted from the other device, is limited by thefiring pin energy required for reliable operation of the device.


Actuation Method Ga PressureActuation Force 750 psi min.Temperature Limits -65 0 F to + 160'FAssembled Weight 0.9 lb.Delay Time 1.0 second

TYPICAL PERFORMANCE

Gage Chamber Vol. •.062 in3

Flexible Hose M$28741.4700F

C.

S'4 I T- 1-1 T

Tube length (ft.)

4.3

ini

in i I l I




Component Component

A Pin, Shear G Retainer, CartridgeB Cap H Housing, Firing Pin,C "0" Ring 1 "0" RingD Pin, Firing J Plug, ShippingE Cap, Shipping KC Carcridge, Initiator, Delay,F Chamber, Initiator 1.171 Assembly

-20 UPIF -3

ENVELOPE DRAWING

4.40


Initiators


The M42 Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fittine, a gas pressure actuated firing mechanism and anM1 13 Delay Cartridge. A length of tube or ho-e connects the initiator to another remotely in-stalled propellant actuated device.

Upon cartridge function, an M13 Delay Element contained in the cartridge burns for 3seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or the distance that the initiator can be mounted from the other device, is limited by the firing pinenergy for reliable operation of the device.


Actuation Method .-as PressureActuation Force 750 psi min.Temperature Limits -65 0 F to + 160'FAssembled Weight 0.9 lb.Delay Time 3.0 seconds

TYPICAL PERFORMANCE

Goge Chamber Vol. -. 062 idFlexiblt Hose MS 28741-4

-. 8 700FC

160

0 4 6 2 16 20Tube length (ft)

4.41

Prop#llant Actuated Devices



Component Component

A Pin, Shear F Cartridge, Initiator,B "0" Ring Delay, %M113 AssemblyC Pin, Firing G Retainer, CartridgeD3 Cap, Shipping H Housing, Firing PinE Chamber, Iniuiator I Cap

IPlug, Shipping

__________ M 4.M"& ___

I ~-2~J~rI9 Zi~inD

CI~,*a

4.4


Initiators


The M43 Initiator consists of a constant volume chamber with a pressure outlet port in-corporating a standard pressure fitting, a mechanically operated firing mecharnism and an M113Delay Cartridge. A length of tube or hose connects the initiator to another remotely installed pro-pellant actuated device.

Upon cartridge function, an M13 Delay Element contained in the cartridge bums for 3seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas piessure actuatedfiring mechanism of the other propellant actuated device, exerting a fcice -which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or the distance that the initiator can be mounted from the other device, is limited by the firing pinenergy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -651F to -+ 160'FAssembled Weight 1.0 lb.

Delay Time 3.0 seconds

TYPICAL PERFORMANCE

Gag* Chamber Vol. -. 062 in3

Flexible Hose MS 28741.4

76

0 4 S 12 16 20

Tube length (ft)

4.43


Inititor, Cartridge Actuated, Delay, M43

~J

! FI


Component Component

A Spring, Initiatro H Housing, Firing PinB "40" Ring I CapC "aIls(3) j Pin, SafetyD Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator,F Retainer, Cartridge Delay, 113 Assembly

G Pin, Firing

d--1.6S7 MAX. 5.180 MIN13 1.085 MAX.S.S I

6i K ] D. A- 641X56'I IB,+.002 DI~A 1® D~IA 'A

MI

+ -20 tU7NF- 3A

SAFETY PIN- 11-.160 MmN; 29 'D

INSERT IN EITHER POS. 2 HOLES

ENVELOPE DRAWING

4.44


Initiators


The M44 Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fitting, a gas pressure actuated tiring mechanism and anM114 Delay Cartridge. A length of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an M13 Delay Element contained in the cartridge burns for 3I seconds, after which the propellant and black powder are ignited. The gas produced by theburning of the propellant and black powder charge flows through the tube to the gas pressureactuated firing mechanism of the other propellant actuated device, exerting a force which propelsthe firing pin against the cartridge contained in that device. The length of the connecting tubeand/or hose, or the distance that the initiator can be mounted from the other device, is limitedby the firing pin energy requited for reliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi min.Temperature Limits -65 0 F to + 160'FAssembled Weight 0.9 lb.Delay Time 3.0 seconds

TYPICAL PERFORMANCE

SGaeV Chamber Val. . .062 in3

1 Flexible Hose MS28741-4700F

4

•2

0 4 6 a to

Tube length (ft.)

4.45

ii4

Propellant Actuated Device%



Component Component

A Pin, Shear G Retainer, CartridgeB Cap H Housing, Firing PinC "0" Ring 1 "0" RingD Pin, Firing J Plug, ShippingE Cap, Shipping K Cartridge, Initiator, Delay,F Chamber, Initiator Ml14 Assembly

._- M -- 3

ENVELOPE DRNAWING

4.46

, I2 ll O tS


Initiators


The M45 Initiator consists of a constant volume chamber with a pressure outlet portincorporating a standard pressure fitting, a mechanically operated firing mechanism and an M 114Delay Cartridge. A length of tube or hose connects the initiator to another remotely installed

propellant actuated device.

Upon cartridge function, an M13 Delay Element contained in the cartridge burns for 3seconds, after which the propellant and black powder are ignited. The gas produced by theburning of the propellant and black powder charge flows through the tube to the gas pressureactuated firing mechanism of the other propellant actuated device, exerting a force which

propels the firing pin against the cartridge contained in that device. The length of the connectingtube and/or hose, or the distance that the initiator can be mounted from the other device, islimited by the firing pin energy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 Is. nmin.Temperature Limits -65'F to ÷160'FAssembled Weight 1.0 lb.

Delay Time 3.0 seconds

TYPICAL PERFORMANCE

SGage Chamber Vol. •-.062 id3

Flexible Hose M528741-4

707F

I3 fiL [I]

CL

0 2 4 t o

Tube length (ft.)

4-4,

Propellitnt Actuated Devices

Insit'.tar, Cartridge Actuated, Delay, M45


Component Component

A Spring, Initiator H Housing, Firing PinB *.0" Ring I CapC Ball J Pin, SafetyD Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator.

F Retaine:, Cartridge Delay,,%1114 AssemblyG Pin, Firing

-1,657 MAX. 5.03 MAX

13 7 4.89 MIN1-9 1.08S MAX.

1 .565.08ŽI3 .... 16 &IAX

-.005 DA

.188+OO02DIA-1 I

TRAVEL20 UNF 3A

APTV 1. 261 MAX .259 or8DIA.INSERT IN EITHER POS. 2 liOLES

ENVELOPE DRAWING

4.48


Initiators


The M49 Initiator consists of a constant volume chamber with a pressure outlet portincorporating a standard pressure fitting, a mechanically operated firing mechanism and an M490Delay Cartridge. A length of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an M14 Delay Element contained in the cartridge burns for0.3 second, after which the propellant and black powder are ignited. The gas produced by theburning of the propellant and black powder charge flows through the tube to the gas pressureactuated firing mechanism of the other propellant actuated device, exerting a force which propelsthe firing pin against the cartridge contained in that device. The length of the connecting tubeand!or hose, or the distance that the initiator can be mounted from the other device, is limitedby the firing pin energy required ior reliable operation-of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -65 0 F to + 160OFAssembled Weight 1.0 lb.Delay Time 0.3 second

TYPICAL PERFORMANCE

Gage Chamber Vol. .062 id3

Flexible Hose MS28741-470 0 F

0 2 4 6 8 10

Tube length (it.)

4-49

t mm •



S/ /


Component Component

A Spring, Initiator HI Housing, Firing PinB "0" Ring I CapC Ball J Pin, Safety* Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator,F Retainer, Cartridge Delay, M90 Assembly

G Pin, Firing

1.657 MAX.-" 5.03 MAX4.89 MIN

1-6 .q ..-. t - -• 1.085 MAX.08DIA3 A

S .088 3 --- 4 MAX..005 ~ DtA-

I .1884 00 2

0tA -13D)

S--TRAVEL + -a • 20 t:Nv- 3A-

SF TV IN 06,261 MAX .259J -00 .O nIA.

- AIY I -1.6 I

INSERT IN ETITHR POS. 2 IIOL-5

ENVELOPE DRAWING

4.50


Initiataos


The M51 Delay Initiator consists of a constant volume chamber with a pressure outlet in-

corporating a standard pressure fitting, a gas pressure actuated firing mechanism and an M89

Delay Cartridge. A length of tube or hose connects the initiator to another remotely installed pro-

pellant actuated device.

Upon cartridge function, an XM24 Delay Element contained in the cartridge burns for 2

seconds, after which the propellant and black powder are ignited. The gas produced by the burn-

ing of the propellant and black powder charge flows through the tube to the gas pressure actuated


pin against the cartridge contained in that device. The length of the connecting tube and!or hose,

or the distance that the initiator can be mounted from the other device is limited by the firing pin

energy for reliable operation of the device.


Actuation Method Gas Pressure

Actuation Force 750 psi min.

Temperature Limits -65 0 F to + 160'FAssembled Weight 0.39 lb.Delay Time 2.0 seconds

Mounting Integral Threads

TYPICAL PERFORMANCE

Gage Chamber Vol. -. 062 in3

Flexible Hose MS21741-4-. 8 70OF ,

xi

•44

0 4 12i Is 20Tube length (ft)

A-5'




Component Component

A "0" Ring H Cartridge, Initiator, Delay.B Pin, Firing %189 AssemblyC "0" Ring I "0" Ring

D Screw, Set J Cap, InitiatorE Filter K Pin, ShearF Cap, Shipping L Plug, ShippingG Chamber, Initiator

S.1435 MAX

1.752 MAX 1 .546 MAX

.3054+.010 .705 -. 020 7

• • .866 MAX DIAi?. -ZO0iJr-U

II3Acko~ss rLJ,-T 6 1. 13S MAX DIA

ENVELOPE DRAWING

4.52


Initiators


The M52 Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fitting, a mechanically operated firing mechanism and anMX128 Delay Cartridge. A length of tube or hose connects the initiator to another remotely in-

stalled propellant actuated device.

Upon cartridge function, an XM27 Delay Element contained in the cartridge, bums for 5seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firing"pin against the cartridge contained in that device. The length of the connecting tube and/or hose,or distance that the initiator can be mounted from the other device, is limited by the firing pinenergy required for re!iable operation of the device.


Actuation Method MechanicalActuation Force 40 lb. min.Temperature Limits -65 0 F to + 160'FAssembled Weight 0.39 lb.Delay Time 5.0 secondsMounting Integral Threads

TYPICAL PERFORMANCE

Gag*e Chomber Vol. e .062 in3

Flexible Hose MS28741-4S8 700 F

S6

4

a.

4 0 12 16 20

Tube length (ft)

4.53




Component Component

A Seal H Pin, FiringB Spring, Initiator I BallC Housing, Firing Pin J Cap, Initiator

D Filter K Pin, Safety

E Cap, Shipping L Pin, InitiatorF Chamber, Initiator M Cartridge, Initiator,G "0" Ring Delay, XM128

IM' "IMi - 1 *.

,I.I "�/ . -- h�.A.• ------- .-----..

ENVELOPE DRAWING

4.54


Initiators


The M54 Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fitting, a mechanically operated firing mechanism and ai,XMI28 Delay Cartridge. A length of tube or hose connects the initiator to another remotely in-stalled propellant actuated device.

Upon cartridge function, an XM27 Delay Element contained in the cartridge, burns fot5 seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and,:or hose,

or distance that the initiator can be mounted from the other device, is limited b&, the firing pin en-ergy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs minTemperature Limits -65cF to + 1603FAssembled Weight 0.39 lb.Delay Time 5.0 secondsMounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chamber Vo. = .062 in3

Flexihie Hose MS 28741-40700F

i ""£4S --

A.Y

S4 8 12 6 20Tube length kft)

4-55



A


Component Component

A Seal G Pin, FiringB Spring, Initiator H Balls (3)C Housing, Firing Pin I Cap, InitiatorD Filter J Pin, SafetyE Cap, Shipping K Pin, InitiatorF Chamber, Initiator L Cartridge, Initiator, XM128

! ''-, *--- --'• MA/t -4--H - --- .5--

r:; t ; . C L

-A-,

-.-- 2-UGF - .fA

ENVELOPE DRAWING

4-56

Pioptlonlt Actuated Devices

Initiators


The M80 Initiator is a sealed M9 type Initiator which restricts toxic gas leakage to rre-vent atmospheric contamination exceeding concentration limits safe for human occupancy in e.-capsulated environments. It consists of a gas pressure actuated firing mechanism, a chamber and

end cap with a pressure outlet port incorporating a standard pressure fitting and an M69 Cartridge.A length of tube or hose connects the initiator to another remotely installed propellant actuateddevice.

Upon cartridge function, the gas produced by burning of the propellant and black powdercharge flows through the tube to the gas pressure actuated firing mechanism of the other propellant

actuated device, exeruv¼' a force which propels the firing pin against the cartridgc contained in

that device. The length of the connecting tube andior hose, or the distance that the initiator can

be mounted from the other device, is limited by the firing pin energy required for reliable operationof the device. The M80 Initiator is capable of delivering to an .062 in3 terminal chamber volumeat the end of a 30 foot length of MS28741-4 hose, pressure within the limits of 1000 psi minimum

and 3000 psi maximum.

PRINCIPAL CHARACTE"!STICS

Actuation Method Gas PressureActuation Force 750 psi minm.Temperature Limits -6S1cF to lo "FAssembled ieight 3.2 lbs.

4.57

Propellant Actuated .Devices


C F


Component Component

A Cap, Shipping F CapB Pin, Firing G Cap, ShippingC "0" Ring H FilterD Cap, Initiator 1 "0" RingE Body J Cartridge, Initiator, M69 Assembly

?TOe KY')

sr..€ vu.SS' SQSVA

77

ENVELOPE DRAWING

4-58


Initiators

INITIATOR, CARTRIDGE ACTUATED, XM86

The XM86 Initiator consists of a constant volume chamber with a pressure outlet portincorporating a standard pressure fitting, a mechanically operated firing mechanism and an XM169Cartridge. A length of tube or hose connects the initiator to another remotely installed propellant

actuated device.

Upon cartridge function, the gas produced by the burning of the propellant and black pow-der charge, flows through the tube to the gas pressure actuated firing mechanism of the other pro-

pellant actuated device, exerting a force which propels the firing pin against the cartridge con-tained in that device. The length of the connecting tube and/or hose, or distance that the initiatorcan be mounted from the other device, is limited by the firing pin energy required for reliable oper-

ation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -65 0 F to + 160°F

Assembled Weight 0.3 lb.Mounting Integral Thread

TYPICAL PERFORMANCE

Gage Chamber Vol. = .062 in 3

Flexible Hose MS2874AI4700 F

0 a 10

Tube length (ft.)

4-59


Initiator, Cartridge Actuated, XM86

ý\

/ i \ \


Component Component

A St H Pin, FiringB Spring, L.. .iator I BallC Housing, Firing Pin I Cap, InitiatorD Filter K Pin, SafetyE Cap, Shipping L Pin, Initiator

F Chamber, Initiator M Cartridge, Initiator,

G "0" Ring XM169 Assembly

L I.-ý .Al002 . IA. - Z0-UW.!3A" -'

; E~~~ - -4 MAX ;~' __

'rA4. -

ENVELOPE DRAWING

4-60


Initiators


The M87 Initiator is a sealed M27 type Initiator which restricts toxic propellant'gasleakage to prevent atmospheric contamination exceeding concentration limits safe for humanoccupancy in encapsulated environments. It consists of a constant volume chamber with a pres-sure outlet port incorporating a standard pressure fitting, a mechanically operated firing mechan-

ism and an M173 Cartridge. A length of tube or hose connects the initiator to another remotelyinstalled propellant actuated device.

Upon cartridge function, the gas produced by the burning of the propellant and blackpowder charge flows through the tube to the gas pressure actuated firing mechanism of the otherpropellant actuated device, exerting a force which propels the firing pin against the cartridgecontained in that device. The length of the connecting tube and/or hose, or distance that the

initiator can be mounted from the other device is limited by the firing pin energy required for

reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature limits -65 0 F to +160'F

Assembled Weight 0.33 lb.Mounting Integral Lugs

TYPICAL PERFORMANCE

Gag* Chamber Vol. - .062 in3

Flexible Hose MS 28741.4.- 6 700 Fc•1'0.

I I I 12 I6 I 0Tube length fIt)

I I I6 I I



A T


Component Component

A Seal G Pin, FiringB Spring, Initiator H BallC Housing, Firing Pin I Cap, InitiatorD Filter J Pin, SafetyE Cap, Shipping K Pin, InitiatorF Chamber, Initiator L Cartridge, Initiator, M173

- 4.0e3MA -

ta"1 ,•.. O55 MAs -• .•O-- O.... r J,. + ,.4 MAX, !

01

7 .~MM!R t ~ + z '\-,93+005 -2u0'3

ENVELOPE DRAWING

4.62


Initiators


The M88 Initiator is a sealed Ml5 type Initiator which restricts toxic propellant gasleakage to prevent atmospheric contamination exceeding concentration limits safe for human

occupancy in encapsulated environments. It consists of a constant volume chamber with a pres-

sure outlet port incorporating a standard pressure fitting, a gas pressure actuated tiring mechan-

ism and an M174 Delay Cartridge. A length of tube or hose connects the initiator to another re-

motely installed propellant actuated device.

Upon cartridge function, an XM24 Delay Element contained in the cartridge burns for 2

A seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and or hose,

or the distance that the initiator can be mounted from the other device is limited by the firing pinenergy required for reliable operation of the device.


Actuation Method Gas Pressure

Actuation Force 750 psi. min.

Temperature Limits -65 0 F to + 160'FAssembled Weight 0.39 lbs.Delay Time 2.0 seconds

Mounting Integral Threads

TYPICAL PERFORMANCE

Gage Chamber Vol. r .062 in3

Flexible Hose MS28741-470OF

D.

0 a 6 12 16 20

Tube length (ft)

4-63

ii4




Component Component

A "0" Ring G Chamber, InitiatorB Pin, Firing H Cartridge, Initiator, Delay,C Plug, Shipping N1174 AssemblyD Screw, Set 1 "0" RingE Filter ) Cap, InitiatorF Cap, Shipping K Pin, Shear

-- d 1.752 MAX -,• •.546 M.AX

,0 .1 .705S .0o20 7 "

.866 MAX DIA

'B('

" ""-.r.26 -. 010, - 1.IS- A DIA

4 AC oe6AOG. F k-T

ENVELOPE DRAWING

4.64


Initiators


The M89 Initiator is a sealed M54 type Initiator which restricts toxic gas to preventatmospheric contamination exceeding concentration limits safe for human occupancy in enc; p-sulated environments. It consists of a constant volume chamber with a pressure outlet port in-

corporating a standard pressure fitting, a mechanically operated firing mechanism and an M175Delay Cartridge. A length of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an XM27 Delay Element contained in the cartridge burns for5 seconds, after which the propellant and black powder are ignited. The gas produced by the

burning of the propellant and black powder charge flows through the tube to the gas pressureactuated firing mechanism of the other propellant actuated device, exerting a force which pro-pels the firing pin against the cartridge contained in that device. The length of thie connecting

tube and/or hose, or the distance that the initiator can be mounted from the other device is

limited by the firing pin energy required for reliable operation of the device.



Actuation Force 40 lbs. min.Temperature Limits -65 2 F to , 160"'FAssembled Weight 0.39 lb.Delay Time 5.0 seconds

Mounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chamber Vol. =.062 in3

Flexible Hose MS 28741-4070OF

08 12 16 20

Tube length (ft)

4-65




Component Component

A Seal H BallB Spring, Initiator I Cap, Initiator

C Housing, Firing Pin J Pin, SafetyD Filter K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator, Delay,

F Chamber, Initiator M175 AssemblyG Pin, Firing

-.0-0%000 ""1 -- Jr"

.-- CR S ... 946 _A_

.02 1'15 MAX W

V - 1

3 ?lAK W TRA IEL 1. 1A

ENVELOPE DRAWING

4.66


Mi scellaneous

SECTION V

MISCELLANEOUS


Accessory For Pad

RELEASE, FIRING PIN, MIAl

The MIA1 Firing Pin Release is a gas pressure actuated device which performs firingpin release function for such devices as the M1A3 Remover. It is a piston .and cylinder unit, ac-tuated by propellant gas pressure supplied from another propellant actuated device. As gas

pressure is introduced through the intake port, a force is exerted on the unlocking piston result-ing in its displacement and the release of the rod and piston assembly. Upon release, the rodand piston assembly is propelled by gas pressure through the cylinder causing withdrawal ofthe extended rod into the unit.

PRINCIPAi.CH ARACTERISTICS

Aqtuation Method Gas PressureActuation Force 250 psi min.

5.1


Release, Firing Pin, Gas Actuated, MIA1

G C


SComponent Componen.t

A Rod, Piston Assembly E CylinderB Spring, Piston Assembly F Disc

C "O" Ring (2) G Piston Assembly

D Ball H Housing, Piston Assembly

I

I DIA -

5.599 MAX

ENVELOPE DRAWING

5-2


Cutter

CUTTER M8

The N18 Cable Cutter is a component part of an aircraft escape system whose purposeis to sever wires or cables prior to implementing the escape procedure of aircraft personnelfrom the aircraft. Thc cu•:er is capable of severing either a bundle of coaxial cables or abundle of wires. The blade of the cutter is coated to prevent shorting as the blade passes

through the cables or wires.

The cutter is cylindrical in shape, approximately 5.8 inches long and 2.3 inches indiameter. The blade of the cutter is held in position by a "shear pin" which will shear indouble shear when a load of 2160'200 pounds is applied.

The cutter incorporates 4 propellant gas operated firing mechanism. It is actuatedby gas pressure supplied from another propellant actuated device.


Stroke 1.25 inchesAssembled Weight .75 ibs.*Blades aveiage depth of

penetration into anvil whenfired at 70'F .004 inches

Firing Method Propellant GasTemperature Limits -65'F to +200*FMaterial Severed

Cable Assembly .060 inch thick vinyl sheath around9 RG-62 A/N Coax Cables (MIL-C-17/30)

Wire Bundle .060 inch thick vinyl sheath around

27 strands #22 wire (MIL-W-8777)6 strands #18 wire (MIL-W-8777)8 strands #20 wire (MIL-W-12349)

* Depth of penetration of the blade into the anvil is a rough measure of the kinetic energy

remaining in the blade after it has cut the cable. It is also an indication of the margin of

safety insuring that the cable will be severed.

5.3

Propellant Actuated DevFces

Cutter, Cartridge Actuated, M8

U H

A rK)

T


Component Component

A Head 1. AnvilB Plug. Shipping M Swivel AssemblyC' Cartridge, Cutter M122 N "0" Ring1) Body Assembly 0 Pin, Shear Unlock1 Nut, Mounting P "0" RingF Gasket Q "0" Ring

G Blade R Screw, SetI1 Pellet (Shown 22' 30' S Pin, Shear

out of Position) T 'o"t RingI Cap U Pin, FiringJ Clip, Cable Holder V Seal, CarK Pin, Cotter

6 16

2.065 D MAX -

L2.34 MAXJ

ENVELOPE DRAWING

5.4

Documents

I 2 -] I 0ao - Defense Technical Information Center M1A3 Remover is a three-tube, telescoping ejection device containing an explosive cartridge, designed to forcibly jettison the canopy