NASA History - V2 - A4 Rocket Technical Development Data 1965

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    P R ~ P A R E D YHI S T O RI CAL O F F I C E

    MANAGEMENT SERVICES OFFICEGEORGE C. M A R S H A L L S P A C E FLIGHT CENTER

    N A T W AERONAUTKS AN@ SPACI ADMINISTRATI

    /'- F E f l i l U A R Y 25 . 1965

    B YH.A. SCHULZE

    CHNICAL DATAON THE DEVELOPMENT OF T H E

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    This report deals with the development of the A 4 (V-2).

    It i s restricted to technical data referring todimensions, test data and test objectives, and is directedt o be used a8 a guide line.

    F & D 876-1126February 1965

    Advice and assistance, rendered by some members of the teaq areaoknowledged and appreoiated.

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    TABLE OF CONTENTS

    Foreword . . . . . . . . . . . . . . . . . . . . . . . . iii. . . . . . . . . . . . . . . . . .able of Contents i v. . . . . . . . . . . . . . . . . . .ntroduction V

    ChapterI A-1 e e . 0A-2 0 e e e . 0A -3 a 0 e e .A-5 e eI1

    I11A-4 . . . . . . . . . . . . . . . . . . .Technical Data for(1 ) Sa t e l l i t e Mis s il e s( 2 ) Space Vehicles(Outgrowth and further development of the A - 4 ) . . . . .

    1251322

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    INTRODUCTION

    T h is r e p o r t was compiled from docum entatio n on Peenemuende whi chwas b ro ug h t t o t h e U. S. and s t or ed fo r approximate ly 12 yea rs a tRedstone Arsenal . Before o f f i c i a l re t urn of these documents i n t h es m e r of 1958 t o West Germany, th e au th or scr eene d th e mater ial andmade dup l i ca t e copi es of the most important da ta .c o n t a i n s t h e s i g n i f i c a n t items i n t h i s s e l e c t i on pe r t a i n ing t o " Tec hn ic alData on the Development of the A-4(V-2);"

    The p r e s e n t r e p o r t

    The mater ial i s a r ra nge d i n t h r e e s e c t i ong . The f i r s t s e c t i on be ginsw i th r e a l ea r ly , p r im i t iv e sounding rock e ts (A-1 th ru A-3) and c loseswi th the fore run ner of the V-2(A-5). The middle and ba si c po rt io n oft h i s book d ea ls on ly wi th th e A-4(V-2) by showing the development ofcomponents, diagrams, t e s t and launch f a c i l i t i e s as w e l l as some picturesof A-4 la unc hin gs.A-4, th e A-4b, which had wings atta ch ed t o th e body. The t h i r d and l a s tpor t i on o f t he book emphasizes avai lable informat ion on technica l capa-b i l i t i e s and t re n ds of fu rt h er developments a f t e r th e A-4, from th e A-6through the A-10 .was ever pursued beyond the drawing board stage.

    Section two closes with some data on an improved

    None of the d a ta i n t h i s f i n a l sec t ion beyond the A-4

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    PEENEMUENDEuI*u* -n lcIIsLl sannm mown -

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    A - 1-1932 - 33:

    Weight : 150 kg (330 lbs)KOElMWSDORPrnear Berlin

    Length:Dimeater: 30.4 c10 (1 ft)Fuel: Lox - Alcohol (75%)

    1.40 m (4 it 6 in)

    Thrust: 300 kg (660 lbs)T W : 16 sec0 & C Platform: 3 phase electric motors with gyroscope (90 lbs)

    Test8;-1. Model exploded at static firing test on 21 December 1932.2. Model never launched.

    T o t a l vehicle was nose-heavy a8 subsequent studies revealed.Delayed ignition detonated an explosive laixture which had

    accumulated In the combu8tion chamber within h second.Test Objectives:

    Propulsion dr Control Test8

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    193b:-Weight:Length:Diameter:Fuel:Thrust:Time:G & C Platform: located in the center of the rocketLaunching Place: Island o f Borkum, Baltic Sea.

    KUMMERSDORFnear Berlin

    Same as A l l , only change relocationof stabilired platform.

    Both successfUI, altitude approximately 1% miles.

    Test Objectives:Propulsion 6 Control Tests

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    GERMAN A-2 ROCKET3

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    /GYRO

    SOME IMO F THE\ D IAMETERLENGTHI WE I G H TTHRUSTIPORTANA - 2 R T DAOC KE

    5-4006 5 0

    T AT

    German A-2 Rocket4

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    A - 3-1936:- PEENEMWNDEBaitic Sea

    750 kg (1650 lbs)6.74 m (22 ft)67.3 cm (2.2 ft)LOX - Alcohol (75%)1.5 to (3300 lbs)45 sec3 dimensional gyro control system, jet ruddersand rudder actuatorsIsland of Greifswalder Oie, Baltic Sea

    Weight:Length:Diameter:Fuel:Thrust:Time:0 & C Platform:

    Launching Place:

    For the first time, liquid nitrogen pressurization systemwas used.Launchings:

    A 3/1: 4 December 1937Take-off perfect.x + 3 8ec parachute ejects (uncontrolled) pull; the rocket

    to one ,side.x + 6.5 sec cut-off.Rocket hits ground 300 m (984 ft) from launch place and

    explodes.5

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    A - 3 (Cont)A - 3/2: 6 December 1937

    Take-off perfect.x + 3 sec again parachute ejects.Again rocket destroyed by explosion.

    A - 3/3: 8 December 1937Parachute taken outTake-off perfect.Rocket again turns sideways, causing cut-off.Rocket hits Baltic Sea and is destroyed by explosion.

    A - 3/k: 11 December 1937Same results as on 8 December.

    Test Objectives:Steering Control Tests

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    GERMAN A- 3 ROCKET I N TEST STAND

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    GERMAN A - 3 ROCKET DTJRING AND AFTER ERE CTI ON I N S ER VIC E TOWER

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    GERMAN A-3 ROCWT AFTER L AUNCH

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    ,

    ,- - 0 3-.

    GERMAN A - 3 ROCKET

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    m

    F

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    JUWa

    5

    ff

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    1937:Weight :Length:Diameter:Fuel :Thrust :Time:Range:Launching Place:

    PEENEMUENGEBaltic Sea800 kg (1760 l b s )7.4 m (24 .2 f t )75.8 cm (2.5 f t )LOX - Alcohol (75%)1.5 t o (31d lbs)45 sec16 km (11.2 mi)Island of Greif'swalder Oie, Baltic Sea

    After fai lures on the A-3 series, new design only retained theexperienced power-plant and added a completely new guidance andstabilization system.

    1. Test of Scale Models:a.b,

    Dropped from airplanes (summer 1938).Launched without guidance (March 1939).

    2. Parachute Tests.3 . Graphite Jet Steering Vanes,

    Launching8:

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    Fully equipped A - 5 with new guidance system andparachute.

    No attempt to go into trajectory.Heights more than 8 km (5.0 mi)Recovery on parachutes successful..

    A - 5/3: October 1939Same as A - s / l and A - 5/2; full success.- First time

    gui-ce system fully lured ( 4 9 traJectory).After this break-through, approximately 70 to 80 launch-ings took place until late 1942.after previous launchings.

    A - 5 was used as "test vehicle" for all different kindsSome vehicles were refurbished

    of modifications.

    Test Objectives?--.I1, Guidance & Control Tests (LEV - 3).2, Jet Vane Tests (Carbon)3 Parachute Tests (Recovery)

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    CONTROL ACTUATOf?BATTERY

    STABIUZU) PUTFORM.RADIO =AGE

    NITROGEN TANK

    OXYGN TANK

    -PARACHUTE

    SOME IMPORTANT DATAO F THE A - 5 ROCKET

    D IAMETERLENGTHWE I G HT (EMPTY)LAUNCH rNQ WE I OH TTHRUST DEVELOPEDPROPULS I ON T IM EALTITUDE REACHEDRANGE

    28 '22 '1,200 LBO1,800 LB.3 , 00 LBOt 5 SEC.13,000 M E T E R S18,000 METERS

    German A-5 Rockef15

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    ~~H V P1940

    Aggregat 5

    T A I T BGERMAN A - 5 ROCKET

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    c -

    GERMAN A - 5 ROCKET DROP-TESTS FROM HE-111

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    iGERMAN A-5 ROCKET OPERATION-DIAGRAM

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    GERMAN A - 5 ROCKET FUEL-VALVES

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    'vc

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    GERMAN A-5 ROCKET COMBUSTION-CHAMBER

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    GERMAN A - 5 ROCKET INSTRUMENT-COMPAR'NT

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    - 1945:weight:Length:M a t e r :Fuel:Thrust:Time:Range:Launching Place:

    P E E " D EBaltic Sea12.52 t o (27,500 lbs)U.3 (43.6 f t )1.65 IQ (5.h ft)LOX - Alcohol (75%)25 t o (56,000 l b s )65 sec200 km ( 1 2 5 mi)Peenemende, Test Stand V I 1

    For the f irs t time a turbo-pump was incorporated, powered byan 80% hydrogen-peroxide steam generator.

    For the f i r s t time a new guidance system (LEV-3) with 3-axisstabilized platform was used.

    Launchings:A - h/l: 18 March 1942Destroyed during power plant test.

    A - &/2: 13 June 1942H i r s l l e atrrrkd rotating early a f t e r take-off.Correction through guidance icst successful, but la ter full

    -360 rotations.

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    x + 54 (approx) cut-off.x + 96 (approx) missile hits Baltic Sea approximately

    1.3 km from Test Stand VII.

    A - 4 / 3 : 16 A w S t 1942x + 4 electrical power system failure.x + 20 missile leaves trajectory.x + 25 Hach 1x + 45 cut-off (11,720m height, velocity 651.4 m/sec)Due to early cut-off, fuel residues destroy tank-heads,

    explodes, missile burns, tumbles, top section and tail fins breakoff.

    x + 196 missile hit8 Baltic Sea approximately 8.7 kpl fromTest Stand VSI.

    A - !& ' , I : 3 Ockober 1942First full success.

    ...- .-..*,_.._."

    Missile stays completely withla calculated trajectory.x + 57.8 cut-off (velocity 1500 m/sec, 90 kn height).x + 296 d e s i l e hits target 190 km away (Baltic Sea)

    A us: 1 October 1942Partial B U C C ~ ~ S ,47 km,

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    A - 4 /6 : 9 November 1942Guidance trouble, missile does not go into trajectory,

    straight up 67 km,A - 4/7: 28 November 1942

    Missile tumbles, looses sheet metal exhawt and v m tcovers, thrust l a s t s only f o r 37 seconds.

    A - w9: 12 December 1942-+ 4 exploaion during programing into trajectory.A - 4 h O : 7 January 19b3Ekplosion on launcher during ignition.

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    A S

    AntemeJ itm~c.-jw Loftrude-

    COMPARISON OF GERMAN ROCKETS A - 3 , A - 5 , A - 4

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    A 3

    A

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    GERMAN A - 4 ROCKET

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    A M . 1 Fernraketc Im Schpitt . Abb.2 Fernrakete A /au f der Startplattfofm .

    GERMAN A- 4 ROCKET CUT-AWAY AND ON LAUNCH PLATFORM

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    8

    R

    GERMAN A-4 RO C U T OPERATION-DIAGRAM

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    GERMAN A - 4 ROCKET COMBUSTION CHAMBER (R&D)

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    GERMAN A - 4 ROCKET COMBUSTION CHAMBER PARTS

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    GERMAN A - 4 ROCKET COMBUSTION CHAMBER (CUT-AWAY)

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    GERMAN A - 4 ROCKET COMBUSTION CHAMBER (PRODUCTION)

    3 2

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    V - 2 Propulsion Cut-off Device, System I

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    A -4 (V-2 ) Stabilized

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    Platform

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    w##a

    V - 2 Propulsion Cut -o f f Device, System I I35

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    cnX- 2xc3

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    XVz3..

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    PE~ENEMUENDE: LAUNCH PREPARATION CAR (ON RAIL TRACKS)

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    . .,' ;. , I*:, n .

    GERMAN A - 4 ROCKET AFTER LAUNCH

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    G e r m a n V - 2 Rocket42

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    1944-Same dimensions a s A - b .A - 4b was ca ll ed the ltGlider.Wings were added for use of some of the unused stored-up ~ i ~ t i . :

    energies t o reach a target approximately 450 km ( 2 8 1 m i ) .

    A - 4b: 24 January 1945First successful launch.-

    Mission not completed due to failure in one wing.

    Test Obdective:~

    Increase in target distance.

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    z0H

    U0d

    E

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    TECHNICAL DATA

    FOR

    (1) Satellite fissiles( 2 ) Space Vehicles

    (Outgrowth and furtherdevelopment of the A - 4.)

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    Blueprint only; never left the drawing board and the pre-liminary analysis stage.

    Design Objective:Subsonic missile.

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    1940 - 43:Dimensions:

    Replica of A - 5 only with wings as forerunner for A - 9 ,with shape of A - 9 (no payload capability)

    Design Objectives:i11. Model of A - 9 for new st ee rin g cont rol device

    tes t ing ( rocket-glider )2. Two models:

    a. Dropg l ider for b a l l i s t i c tests, without pro-pulsion unit (Range: dropped from approximately 8000 ft a l t i tude =45 w .

    b. With propulsion unit for normal rocket l a un chkg(approximately 1800 lbs th rus t - 25 km) .

    Tests:Two drop-glider tests were performed, both unsuccessful,No model of type b. was ever buil t .

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    1940 - 43:Blueprint stage only.Dimensions: Same as A - 4 (without w i n g s )Design Objective:

    1. Increased thrust 66,000 lbs.a, N ew fuel: Nitric acid & kerosene.b. Increased burning the: 90 sec.

    Forerunner for A - 9 (as second stage for A - 10).Tests: Only thrust-chamber tests were run, no vehicle was-

    ever bui l t .

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    1940 - 43:Size of A - 4 equipped with wings.Approximately 5 to more thrust (tot 30 to) to cope with added

    weight of wings.Range: 800 km (500mi)Payload: 1 to (2200 lba)Steering: Air vanes (to be operable over entire flight)

    Design Objective:1.2.3. Payload: same as A - 4.

    Second stage for A - 10 (Roclcct; G l i d e r ) .Without booster (A - 4) approximate range 500 mi.

    4. Booster: new development & fuel see A - 8.

    so

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    A - 10-1940 - u:

    Weight :Length:Diameter: 4.15 m (12.9 ft)

    101,580 kg ( 223,&76 lbs)26.0 m (80 ft)

    Fuel : LOX - Alcohol (75%)Thrust: 20@ to (~0 ,OOOlbs)Th0: 50 secRange: 5500 km (3438 mi)

    Blueprint stage only, never left the drawing board.

    Design Objectives:1. Proof of staging principle.2.3.

    First step for satellite missile.First step for space flight.

    5 1

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    GERMAN A - 1 0 ROCKET

    C Q

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    ARRANGEMENT FOR 6 ENGINE BOOSTER (SKETCH)

    5 3

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    I

    Lalcal.-

    nCLalcE0Y--C.-

    Cal

    0Is)3L L

    n

    -...a,c3

    HMF

    ..

    54

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    CONCLUSION

    The reason for the compilation of this report w as the desire topreserve significant historical information before it became lost ormisplaced with time.an inside view of the tremendous amount of work in development, research,and technology which had to be performed within the last 25 to 30 yearsto make our today's "Space Effort" possible.

    It is hoped that this book has given the reader

    This report shows the very early, but real simple or crude startof our rocket, missile, and space development and gives an appreciationof the amount of research performed to come from the "Grand-Daddy"( A - 4 / V - 2 ) to our present "Space Vehicles" (Saturn IB and Saturn V).