MISSILE DEVELOPMENT AT KB-3, KRASNOARMEYSK, AND PRELIMINARY WORK IN GERMANY

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP80-00810A003900600005-8
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 25
• Document Creation Date: December 22, 2016
• Document Release Date: January 19, 2010
• Sequence Number: 5
• Publication Date: June 10, 1954
• Content Type: REPORT

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INFORMATION REPORT
This Document contains infoneasou airsotleg the No-
tional Defense of the 'United States. within the mean-
ing of Title 19, Sections 7933 and M. of the U.S. Cede. as
amended. Its transmission or revelation of Itsecaten s
to or receipt by an unauthorized person Is prohibited
by law. The reproduction of this torte Is prohibited.
SECRET/CONniOL.U.S0 OFFICIALS ONLY
income=
COUNTRY USSR (Moscow Oblast )/Germany
SUBJECT Missile Development at XB-3.,
IErasnaar*$$k and PreL3minary
Work in Germany
DATE OF INFO.
PLACE ACQUIRED
REPORT
,PATE DISTR. 10 dune 1954
NO. OF PAGES 22
REQUIREMENT NO. RD
THE SOURCE EVALUATIONS IN THIS REPORT ARE DEFINITIVE.
THE APPRAISAL OF CONTENT IS TENTATIVE.
(FOR KEY SEE REVERSE)
1.. The German .engineers. at Putilovo were divided into three labor groups, each .of
which .had its special task to fulfill.
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2. The villages of Putilovo,r Fabrika. Kraft, and 1 rasnyy, Poselok,, the firing
range, and K0rr3 are .included wider the collective name Nrasnoarmeysk. (See
sketch on page 24.. Krasnaarmeysk (N 54-06,. E :38-07) is Icacarted approximately
70 kilommetera northeast. of Moscow and is.reached by a small branch line, which
leads a'oximately 15 kilometers eastward from the Moscow-Yaroslavl (N 57.35,
E .39.50) railroad. between the ,stations, of Pushkin o (N $6-0I,, E 37.51) and
Zagorsk (N 56-].9, E-36-03) at the .station. of Sofrino (N,56.68.. F.37-54). The
terrain around Krasnoarmeysk is -wooded but the woods ..iri-tlie western section
near the tiny Vorya,River,. which floes in a general north-south direction
ire been cut. Distinguishing features of the area are the 30: meter-high
water -tower-, the practice ranges., the churches in the villages of ` 'lutilovo and
Murmanskoyey and the old factory building in the village of Farbr-ika,Kraft.
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STATE I Y I ARMY Ev[ xlNAW Eb !g- AIR -` : M,...'
(Note; Wmhleglen DI*IhSiisa h.dk sad, Iy' 'X'?i Fi.W OiNrlbutbs Ry
ATIC is Lw,
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3.
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The total installations gave the impression that they had all existed even
before the war. In 1946,the installations were under brisk construction.
In recent years no further expansion work had been undertaken. Essentially
Kral' .oarmeysk was divided into the Design 'Bureau and the firing range. Both
divisions. were cappletely independent organically and had nothing to do with
one another.
Organization of KB-3
The Design Bureau bears the designation m3? It is subordinate to the
Ministry of Agricultural Machine Building. this. is.
obviously a screen. No clue as to the actual directing office or ministry
waa,,ever established, however.
Ministry of A ricultur :l Building
Chief., KB-3
Ge "man Labor,lGroups -- dministration
I (Tromme8orf) II (S chaadt /Boehm) l.r ~!uiee ) IV (Frank)
Local Soviet control was exercised by the So,;riet Da;vyshev (fnu)
His assistant was J'l'miov kfnu), an engineer, civilian,
7. The German labor groups comprised, in all., 16 engineers,, who had been
deported to the USSR at the same time and Fleo released together on 16 May
1952. After fttno more German personnel remained in KB-3. Until June 1947,
they worked essentially without Soviet co-workers except for auxiliary
personnel. Sometime in June 1947, 50 Soviet engineers were attached to them.
Each labor group in that period comp:r?ised., in, all, about 30 engineers,
draftsmen) and helpers.
8. At first,the work was performed Jointly between the Soviet and German
engineers. From 19489 on,the previously homogeneous work was gradually
divided and in 1950 a complete separation of the group? into Germans and
Soviets took place. It could no longer be observed-what the counterpart
Soviet'groups were doing. German knowledge was progressively taken over by
the Soviets, while the latter, for their part offered no insight into
further development and were very mistrustful. The total number of employees
of KB-3 amounted to approximately 400 men., 200 to 250 of whom worked in the
laboratory.
9.
The German Labor Groups consisted of the fo 1owings
Labor Group ,I Supersonic ram-jet missiles
Labor Group II - Panzet?fa,euste
Labor Group III - Powder rockets
Labor Group IV - Powder group
~Aahqxr)
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10. Labor Group IV was soon dissolved =;.nd the personnel were rotated among
the other - groups. In this group were the following
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D? Eugen Saigger, rhhector - former chemist at 'the W.AZAG
Arthur Frank,, engineer a detonator construction expert from 'Soemmerda.
Dr. Hans Rakett a former chemist at -t'te WMAG.
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Hugo Peukert, :engineer,.
H.. Heide (fnu), engineer - later &1.ile,r,
Soviet co-workers with Labor Group 1. were the following
Lieutenant Colonel Sudakov;
Engineer Metrikhas,
Engineers Rotshteyn and F:r?idma,:n., M3D fuac+::i.oasries assigned as observers.
Got`man Labor Group was directed b Engineer Franz Schaadt,
fos;eAerl3r of HASAG in Dresden, specia.lf - is in the cons-t-'ruction of the
Panzerfaust. Oiher members of this group were the following-
Fritz Boehm, engineer from Berlirr,,, who lacer took over le+ dership of the
group
Ti=ler (fnu), engineer from Leip.ig.
Dr. Rudolf Oswald, e'ng:ineer, formerly of (! 50-25, E 11+-09) .
7the Soviet co-worker,
group developed Pan7e:rJie + ' J:t' 1 fts,ks were t art of
manufacture a,nd increase of range. 'Tkt ^ ";'F gas of development exceeded
15 30, 50, 1000 and p to 150 m.e te,rs
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results of this work as follows: up to a, range of
150 meters the target was reacher], with an. accurwrs,cy of 1.5 x 1.5 meters.
te, deman,ded: rsngee of ;x,00, 4000 500, and 600 metere.with
an accuracy of 4.5 times 4.5 metexrr 'llese requirements could not be
fulfilled, causing the group a good. ma,ziy -roubles.
13. German Labor Group. III (Auler) coxasiated of the following:
Herbert Karl Auler, sk i er, former, .;y pl.am~tt magi gcr of the Marienfelde
factory, expert. in the field of powder rockets of every type.
Belonging to the Auler group were trh following :
Hugo Paul Taubert, mathematician .
Dr. Karl Rauch, phys i c ist .
Hans Bac1 ,nn,, graduate mathematician., baa,11?Ystica expert.
Heinz Bauecke, graduate engineer,, rocket chsxiber designer.
Wilhelm Eieenkrdmer, engineer.
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The group was engaged.in the development of powder rockets for the following:
Air-g oond' tank combat.
b,. Tank ebanbat by means of mother rockets which eject five daughter rockets.
c.-: - Air-.ground. combat.
d. `kitiatroraftartillery.
individual projectiles 25X1
haA,,been tested with success. in disputes with the Sovietp
the operation of the missiles. was under . controversy but 25X1
less-because of poor performance than because the Soviets
wished to cause annoyance. they were reasonable 25X1
designs and reuced good results. The operations of the group were suspended
in 1950. In addition, the group 25X1
was engaged in the development of a. two -cent imeter rcennon:'which was:. to
attain a cyclic rate of 30,000 rounds per minute. Through special
techniques'a very high cyclic rate of 16-24 rounds at a.time was actually
reached, which by mathematical .:::ektxcolation would amount to 30,000 rounds,
were it not.necessary to reload after the 24th round.
ThheFirinngRan e
15. The firing range was a separate unit and had its. own commanding officer,
who was always an air force colonel. In 1946, the commanding officer
was Colonel Ivanoy. In 1950 he was; succeeded'by,.another air force colonel,
puxTbses:
16. L
The firing.range served the folowing 25X1
a. The firing of light antiaircraft weapons, antitank and field guns, and
howitzers with calibers . up to 150 mm.
daily .from Moscow at the firing range.
b. Discharging of light and medium caliber powder rockets up to 28 cm.
c. Occaaional.dropping of bombs, flash bombs, and flares.
d. Bombings in fall 1951, by a modern bomber with two TL:,(Turbinenluftstrahlmotor
i; ?7, tkirbojet, engiipe4 , Occasionally ,noibes floom the firing range lasting up to 60 seconds,could be
heard, which suggested the"operation of a V-1 prqpupulsi'on`unit, Present
at the practice ranges w re the simplest V, (sic)measuri$ instruments,
captured German apparat~, and gas measuxtthg 4evices.,'?Theee_were in general,
0$#*1ete; and: ialpxaeticable. Officers of all branches of the services; arrived
The And DWI
direct access 25X1
The existence of a,larger wind tunnel was kept secret by the Soviets
to the 10 by 10 centimeter high-pressure wind tunnel
wind tunnel was'built on the basis of
started in the' middle of 1950. At the time
brickwork construction was completed.
e 25-cm,
This construction
the bare
17. The nearest airfield is located 1000 meters west of the Moscow-Yaroslovl
railroad line,'"between Moscow and the railroad station of Post Al Km.
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AQQtiv~.ti,,, .e_;KB
2$. The second period of work eganin the KB-3 at Ktaer9m meyik. Twice
in November 1946 and once in March 1947 the Minister paid a personal visit.
In March 1947 he declared,, "We consider the work on the ram-jet engirt an
especially important and promising develoiment. N The tanks in the second
period of work consisted in the following:
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a.
Completion of the report on "the theory and operation of the ram-jet
power plant at high Mach numbers", with the following sub-headings,
1)
The auxiliary thrust superso?:d c diffusor.
2)
The auxiliary thrust supersonic diffusor with variable collector.
3)
The fuels of the. ram-jet e:rig:i.ner .
1)
Technical problems in the of ram-jet engines for high
Mach numbers.
The possibilities of bringt:og engines to the required high
initial velocities. The ra7-iou:s -.ypes of ram-jet engines for high
Mach: numbers.
b. Demonstration of the principle of the ,gym-.jet engine at high Mach
numbers with projectiles of the E-SF tes;, including the E-5, E-6,
and E-7 experimental missiles of .1. em caliber and without explosive
charge.
c. Comi3tion. of the C-3, a 28 cm she:.: for the German K-5 railroad
gun.
d. Design, construction, and operation-,. of 10 by 10 cm high-pressure
supersonic wind tunnel for ram-je*.. erg.nes.
Added later to these tasks were the
e. Development of the A-4 (to be caps.ble of carrying 250 kilogx!ams. of
explosive for 150 kilometers).
f. Design and construction of a 28 by 28 cm high-pressure supersonic
wind tunnel.
29. On the basis of the development and fulfillment of the above tasks through
the instructions, work directives, a_ridful.iil..lment wisheh of the Soviets,
conclusions could
be drawn concerning the concepts under the management of the
Soviets, despite the fact that the latter exerted every effort to disguise
their own ideas and their real intentions. 17 he following impressions were
gained or facts established:
a. At no time was the center of development located in Putilovo.
Evidence was clear that an agency
was repeating a! t operations an$ designs tb the
minutest detail and conducting all tes~s all over again under controlled
conditions. Through exhaustive and. er ::W?~--recurring,-inquiries, possible
only on the basis of carefully conch cttea parallel work, it became evident
that the Soviets with large resources rn-.d skilled manpower were checking
every train of thought and every proposal by means of actual testing.
b. The development of ram jet-engines is being taken very seriously in the
Soviet Union and is considered p:r rrrwz.. ;.; . n
C. The discovery of principles was gi,tle.,z hroad attention. Some 1l0 different
individuals in all, for the most part wit-1h a good education in gas
dynamics, thermodynamics, and engineering in general
Among them were detached
officers of all three branches of the armed services, dressed in
civilian attire, and members of the No cow and Leningrad Universities.
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1) ?'ghat shells 'bf this type,of 21 cm caliber and up, will be able to provide
-,surprisingly long-range fire from the sea to coastal area,.targets,
2) That'in ship-to-ship combat, shells of this-.type, from 21 cm caliber
and t p; tfill' be ;able, as a result of their striking velocity of
1500 to 1800 meters per second, to develop great armor piercing
capacity and, as a result of the flat trajectory (average flight speed,
1500 meters per seeond).,'to ;cover a greater zone in depth.
3) That the shorter flying time will make possible faster trial fire.
301. The other more significant point of developinent. .ies ; in the very '41 p znaatt.
production of rata,-,het powered missiles w:ith powder rocket launching ;siich as
A-4s , which can effectively convey explosive charges of 250 kilograms and heavier
very revealing observations of the engineer Metrikhasy.it is :possible that...
d. In 1949, at the latest, the thermodynamics and gas dynamics .concepts
had:been~recorded in the appropriate textbooks
atomic explosives are even.being?cor_templated.
31. ,,.The' 10 by 10 cm high-pressure supersonic wind' tunnel in Putiliov y;;hi
ce
lit
f
-
i~-;.,moo .,....
y, v~.n
aci
1:11
a,a1lalDle as a res Ci7,.L
of up to 34 are attainable, ' while magni,t,udes within.the tunnel mess ~,
?
C during a` blast.period,o.
range amount to one kilogram.-per emaa.nd 18
12 seconds, At lesser magnitudes the Mach number is eight.
32. In spring 1953, at the latest, the 26' by 28 cm tunnel in Putilovo will be
available. The Mach numbers and magnitudes are the same as with the 10
by 10 cm tunnel,
33.
successfully fired:.at the ruT51Lovo ' I LJ.7-1.11e~ 106LLe=
d" nd initial velocities of up to 1460 meters per second
TT~ .. , rilrri r:,;ar,.r.imatal v .7 (]'"rrti'ss3les of '.the experimental series were
meters- per, sewn
maximum'at an engine efficiency of up to 40 percent were recorded, F
The firing 6f?the:-C=3. projectile to distances of up to 350 kilometers turned
out successfully in the. winter of` 1949,/50, . The further development
and application of this projectile is concentrated'in"the Navy. The
following are expected:
further' details in regard to '.the C-3 projectile, as fo7atae
The C-3 was already finished by the end of 1949.
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the A-l+, a powder rocket fired from
rocket launching rail, and the C-3,fired from 28-cm railroad gunshave
been, or will be, rendered capable of effective use by the Soviets at
ranges of 150 and 350 kilometers. The K-5 railroad gun has a normal
range of 53 kilometers.
Prospects and grogram for the Ffature Development of Pan-Jet ,Engines
34. The future development of the ram-jet powered missile must be based upon
the present situation. That may be described briefly. The principle
of jet powered missiles may be presumed to be common knowle.dge~_ -
35.
36.
Missiles in the A-series
Large shell bodies with auxiliary thrust diffusor, large central combustion
chamber, and stabilizing surfaces (flying without spinning), remote controlled
on.ocassion, ' ? by means of a powder rocket., attain the necessary initial
velocity of approximately Mach 1.5. In the first stage of.flight the combination
shell-powder-rocket is guided along a firing track. This firing track sets
the initial direction of the flight path. After the powder rocket or
powder rocket composition has burned out, the-rocket is expelled and the
ram-jet-power action begins. This -functions until the fuel is exhau$ted,
at an altitude of approximately 25 kilometers, and then the missile travels.
freely along a ballistic curve.
Present ',projects in the A-series are as follows.
Project
Kilograms
Kilometers
A-1
50
50
Drafting project only.
A-2
50
150
Drafting. project only.
A-3
250
50
Drafting project only,
A-4
250
150
Executed and attained.
A-5
250
300
Drafting project only.
A-6
=_1000
300
Drafting. project only.
Of these designs the A-l+ is test-proven. A distance of 150 kilometers and
a.pay load-'of 250 kilograms have been realized, Additional types of the
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37%
38r
39.
AAseries, A-5 and A-6Apromised a stepwise increase of range and payload up
to 300 kilometers and 1000 kilograms.
The powered missiles of the A-series are produced as simply and cheaply
as possible. The primary part of the 4tsile (see E1losure 1, sketch.of A-h) is a
standard thin walled tube. The central body is welded together from simple
sheets. Fine mechanical treatment is reduced to a minimum. The-fuel
required amounts to between six .percent and ten -,.percent of the missile
by weight. The A-series missiles can carry a pay load up to 20 percent:,-
of the total weight. A caliber between 30 and. 80 cm and a.missile length of
between 2.50 meters and 10 meters seem most practicable. The firing from
a ,rail., whibh is mounted as a.revolving unit on a truck or a full-track
vehicle, allows a firing position at a, good.vantage point,.well. camouflaged,
and independent of roads and railroads. Tiq take-off by powder rocket
_ oduces great sources of error in.the fliVht path. The.'deviationthrough
installation of a remote-control mechanism (radar-control) would rob this
model of its most important advantage, its.low cost.of production.
Future developments would have to be alor* the following lines:.
a. Maintaining the over-land mobility ate. inconspicuousness of the firing unit.
b.' Maintaining the simple,. cheap construction of the missile body.
c. Careful examination of the possibilities of improving the deviation.
The most serious disadvantage of the entire type is the necessity for
powder take-off. The total Weight ..of the powder take-off rocket is
approximately equal to the weight of the ram-jet missile. Emphasis in
the further development must be put on increasing the range of velocity in
.which the ram-Jet motor can operate,-thus increasing the initial velocity
required by the ram-jet motor, and consequently permitting the mass and
weight off' the powder take-off rocket to be lowered. For this purpose
there arr~ arrangements which promise success. Careful study has shown
the possibility of developing ,combinations of Schmidt-tubes and ram-jet
engines in such a way that these combinations,operate as Scbmidt-tube in
the lowet' velocities; the frequency of the individual combustions.of the
Schmidt-tube increases as the velocity increases until about-Mach number
1.5, when the combustion goes over into the .continuous type of the -ram--jet
engine.
The initial velocity which would be effective in'such.a
combination is estimated at about 80 meters per second, a.velocity which
can be delivered by.a etanclard.catapult or.a very small powder rocket. The
first experimental results on such combinations of Schmidt-tube and ram jet
motors.might occur early in 1954.
Mgssil+sa in the B,-S-rie
In the case of missiles and launching units of the B-series the guiding
principle was as,follows: The increase of initial velocities of prorjectile.s,
in standard guns-reacheis a limit!, according'to caliber., in the neighborhood
of 900-1000 meters per second. If higher velocities are to be obtained,,. there
is a necessary disproportionate expenditure on the gun (gun weight, 4reight
of powder charge, erosion within the rifle,, shortening of the life span),
which make,;; the increase of projectile velocity beyond the limit stated
ecorlomically impracticable or, indeed, impossible. If greater initial
velocities and longer ranges are necessary, it is obvious that a basic
velocity (600-900 meters per second) should be fixed for the gun itself,
and then the projectile should be developed as a. ram-jet eagine,which
increases it a.own velocityafter-leaving the gun. The fact that this
mechanism h4,4-become possible in both principle and in practice by.means
of the yet-to-be-discussed C and E-kseries is shown by the following. If
one intends to fire a. missile Wt of as ordinary,,- gun, such requirements will
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42.
the designing of a missile with the following characteristics
for testing the principles of the B-series:
Pay.load-250 kilograms.
Range-150 kilometers.
Diameter of bore-57 cm.
Length of the launching tube-36 meters (capable of being dismounted into six
equal sections,: each six riteter5 lor7,g).
Launching tube attached to launching base plate without recoil mechanism.
Initial. velocity-800 meters per second.
Highest gas..pressure-500 kilograms/cm?.
Weight of launching tube-30 tons.
Weight of base plate -8 tons.
Such a.missile (to be designated B-3 in the development series) might
combine optimal mobility with good range,: low deflections and the Lbweat.'u-
production cost. The use of a propellant other than chemical explosives
is easily possib e. For the explosive, whatever type it might be, :.space
of 0.16 to 0.2 m is provided.
C-Series
projectiles which are fired from standard guns. During
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the firing process with the guna cartridge-case base covers the hollow
chamber running through the entire projectile, in which the propelling
forces.of the ram-jet are later released. This cartridge-case base falls
off after the projectile has left the muzzle of the gun. The projectile is
!Stabilized through rifling. The ram--jet begins to operate immediately
after the projectile leaves the gun muzzle. The initial velocity is
.set for more than 900 meters per second. At this velocity and with
suitable fuels,self-ignition of the fuel is guaranteed. The fuel is
driven partly by rotation and partly.by.means of special aids (pressure
gas,. burning powder cartridge) through jets into the combustion chamber.
The most-important results of the development projects were:
a. The design of the diffuser at the nose of the missile in such a
way that the projectile operates under almost optimal conditions
in a.rather great velocity interval (Mach . 2.6 to 6).
b. Design of the projectile so simple as to place the cost of pro-
duction no higher essentially than that of the standard projectile
for the same gun. This goal was.reached.to the extent that the
production-material costs for missiles of the C-series were only
2.0 to 2.2 times as high as the costs for a regular projectile.
c. Development of a simple control devices for limiting the dispersion
of range on a horizontal target:
1) The introduction of a simple acceleration regulator (in testing
stage).
2) The introduction of a means of limiting the combustion period
(not yet being tested).
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Limitations. Exhaustive investigations have shown that projectiles
of the,C-series.are not to be built under.21 cm caliber. Twenty-
one cent.meters is the limit below. which.an..explosive pay load can
not be borne. The larger the caliber, the larger the borne
explosive pay load can be in proportion to the normal fuel load.
In 38-cm caliber missiles already 65 percent of the explosive
pay load of the standard projectile can be carried. The initial
velocity cannot be reduced essentially below.900 meters per second.
The maximum velocity is about 1900 meters per second. The heating
up at this velocity causes serious difficulties.
e. Ranges up to 360 kilometers can be realized. Within these limitations
the powered missile of the C-series is, for all calibers above 28
cm,,an effective and promising improvement on existing missile types.
These missiles can be used at very low cost. The gun tube is not
subject to the stresses, occasioned by ordinary projectiles. The
gas pressure is always around two-thirds of normal gas pressure.
Only through the use of the cheap powered missile of the C-series
can ranges up to 350 kilometers be reached with any gun, from 28 cm
caliber on up.
In the D-series, missiles. are planned which no longer fly on a',ballistic
curve but by remote control in horizontal flight at great altitudes over
maximum distances. The take-off here)tootaffords difficulties which
have not yet been ironed out. A _take-off by. means of powder rocket
requires enormous velocity for such a missile. The total take-off unit
of powder rockets would weigh two to three times as much As the missile
itself. Another launching method seems more promising.. A heavy mother
aircraft tows the missile, to 12,000 -15,000 meters' altitude. The missile
is then released in a dive and brought up to Mach numbeii l.5 by meansi
of a.small powder rocket. Mach 4 has been determined as the most
favorable operations. Mach number for missiles of the D-series. From
Mach.l.5 up to Mach 4 the missile propels, itself by using its own
fuel supply, which likewise produces the energy necessary to lift the
missile tote moat favorable operational altitude (24.kilometers). A
.ton ton miss
ile flying 1200 meters,per second at.24 kilometers'altitude
uses i.5 kilograms of fuel per second. With its fuel supply of 6000
kilograms it can fly 4000 seconds and can cover a,powered-flight
distance of 4800 kilometers . It can cover an additional distance of
about ?+00 kilometers in glide flight; thus,distances of over 5000
kilometers can be attained with such missiles. Operational velocities
greater than.Mach 4 appear to be unfavorable for the fhlowing reasons;
a. The efficiency of the ram-jet engine does not increase-essentially
with increased Mach number.
b. The fuel requirement for each kilometer of distance increases.
c. The heating-sup. of the entire missile at higher Mach numbers would
require the use of expensive special alloys in this construction.
A. The thermal stress of the combustion chamber cannot be endured.
over extended.flight periods by alloys known at this time. In the
case of the above-mentioned example, all parts of the missile are
exposed to temperatures of about 620?C. The..combustion temperature
will amount to about 1100?C.
k cperi;nenta1 E-Series
In the E-series (E-1 to E..7 produced and tested) were. powered missiles
which were shot from guns of 10.5 cm (E-1), 12.2.cm.(E-2), and 15 cm.
(E-3 to E-7) at a'small quadrant angle of departure (six.degr..ees). These
missiles carried no pay load au.. ,rere used merely to.test the propulsion
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-i5-
process in free flight.
This E-series produced cheaply and con-
clusively a large fund of knowledge. A missile of the E-series cost
about 200 to 250 RM and produced data for the construction of larger
missiles.
45 F-1 and F-2 in the F-series are antiaircraft missiles which have been
designed and constructed in detail (19)+5). Present-day flight velocities
and altitudes make it inadvisable to pursue these types further.
Summary
46.. According to the preceding discussion the following projects offer promise
of success:
a. A reconstruction of A-4 and, on the basis of the knowledge to be
gained through this reconstruction, the continued development of
missiles and powder rockets for distances of '100 to 350 kilometers
and pay loads of 250 to 1000 kilograms. The chief emphasis in the
development program will be'-placed on the effort to reduce the initial
velocity of the ram-jet engine through combination with the Schmidt-
tube.
b. Construction of the B-3. A carefully prepared drawing model of B-3
can be produced within four months after assignment of contract.
Experiences with a B-3 unit could help in producing data for the
further development of types in this series, which could be developed
as long-range artillery and mounted on ships for use in naval warfare.
c. A reconstruction of the C-3 or similar missiles of the C-series for
guns of 28 cm caliber and up. Most promising utilization of this
type is on shipboard for naval warfare. A carefully worked out con-
struction of this type can be prepared within six months after assign-
ment of contract.
d. Missiles of the D-series for maximum distances of 5000.,6000 kilometers.
Pay loads of 1000 kilograms can be established as standard'. The
scarcely promising powder-rocket launching of the missiles of the
D-series is not recommended. A missile of the D-series can be designed
and constructed when the data for a launching from a heavy mother air-
craft has been clarified. Than the construction of a D-series missile
will meet with no significant difficulties as far as the problem of
propulsion is concerned. The question remains unanswered, whether an
effective control by means of radio control units can be realized
over such great distances, The construction and careful completion
of the driving mechanism of the D-missile might require four months.
e. If the further development of ran-jet engines for high Mach numbers
is seriously considered, the continuation of the experiments with
the simple E-types promises good results. The most suitable caliber
seems to be 15 em, The com- 25X1
pletion of a missile design for the E-series requires about three
months.
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.16-
4T. Characteristics of the powered missile, C-3:
a..
Launching unit: German railroad gun. K-5 (230 tons).
Initial velocity: 1225 m/s.
0.
Gas pressure: 1680 kg/6m2.
d.
Missile'%reight at take-offs
about 175 kilograms.
e.
Maximum velocity: 1860 meters per second (at an altitude of 29
kilometers).
f.
Missile weight after burning:
155 kilograms.
Efficiency of combustion: 47 percent.
h.
Fuel: 16.3 kilograms of,a mixture of flame-thrower fuel and
carbon disulphide.
i.
Range:' 350 kilometers.
J.
Range dispersion on horizontal target:
5 to 8 kilometers.
113~. Description of the powered C-3,.missilP and its function (see Enclosure 41
ntnnerals. 'ift the text below refer to corTesponding points on the-4kItch) s
a. Preparation for firing:
The missile, less diffusor spike (1) nose (5), striker (6), detonator
(8), and cartridge-case base (34, 435, is taken from the packing case
and installed in a rack (Laboriervorrichtu ) in such a way that it
can easily be rotated aroun its gravitational axis,so that now the
nose and then the tail of the missile can point vertically upward.
The nose of the missile-is swu upward. The igniting charge (9,10)
is inserted the detonator is threaded on (8), the striker ) and
the nose (55 are inserted. (The very sensitive:nose piece and diffusor
spike are protected in transport by cotton-wadding packing The tail
of the missile is.'swung upward. In a filling can the flame-thrower fuel
and carbon disulphide are weighed off and mi=d. The mixture is then
poured into the fuel container (31); the packing ring (42) is carefully
threaded in. This causes a drop of excess fuel to run out at the
opening (40). Then the venting screw (40) is inserted and screwed
tight. Finally the cartridge-case base (4+3, 44) is inserted. This
must sit loosely and slide'easily. If a cartridge-case base sticks,
it should be discarded, The seat and sliding :surfaces of the cartridge-
case base are to be cautiously cleaned and slightly greased before
being inserted. After the cartridge-case base has been inserted, liquid
paraffin (1.5 kilograms) is poured in at the funnel of the jet (3). The
paraffin, when cooled, holds the cartridge-case base firmly in position
and is pressed, at firing, by the powder gas pressure into the fine
crevice between the missile and the cartridge-case base, thus preventing
the cartridge-case base from seizing or sticking or being blocked by the
residue of combustion, The so-prepared missile is placed into the gun-
barrel combustion chamber in the usual way, during which operation special
care is taken to see that the sensitive diffusor spike is neither bent
nor otherwise damaged nor the missile nose damaged.
It
b. Firing (launching)
barrel, length of the K-5-i 20'_ meters
I
Maximal gas pressure in-firing-the. heavy (174:,kijograms,),)powered missile C-3
rovided with-paraffins' 1666 kg/cm2..
y'J
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25X1
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-17-
Terminal twist: 5 degrees 42 minutes.
Initial velocity: 1225 m/s (Mach .3.6).
In launching,rotation and initial velocity are imparted to the
missile in the extended portion of the gun barrel by the pressure
of the powder gases. The cartridge-case base prevents powder gases
from entering the combustion chamber of the missile between the
casing and fuel container (23).
The rotation flaps (15) cause the liquid fuel to rotate along with
the missile before the latter has left the gun barrel. That portion
of rotating liquid between the rotation flaps is driven outward by
centrifugal force and leaves the area between the rotation flaps at
the outer wall of the fuel container. There is still no rotational
flow of liquid along the axis. After, a few turns of the missile the -.. !.
entire contents of the fuel container are driven by the rotation flu 8
and are involved in the rotation of the missile. The propellant (32.)
is likewise ignited within the gun barrel. Under the effect of the
discharge acceleration of 6000 g (sic) the firing pin (36), as a
result of its inertia, breaks the shear pin (37) and strikes against
the ignition cap (30). Through the pointed flame of the exploding
ignition cap (30) the primer charge (35) is ignited. After a very
small pause,the primer charge (35) conveys the flash on to the
powerful ignition charge (33), which in turn ignites the (carefully
cleaned and roughened) surface of the propellant (32). The rising
powder gas pressure in the chamber of the fuse cap (38) bursts and
opens the weakened central part of the fuse cap in such a way as
to permit the powder gases to enter the fuel container (23) and exert
a pressure on the fuel. The cylindrical propellant (32) is wrapped
by a chemical-mechanical procesa, with a propellant cover (alternating
layers of asphalt and elastic crepe paper applied under pressure) in
such a way as to allow only the frontal. area to burn A safety pressure
valve, not drawn in sketch,,,allows the escape of excess gases so that
the powder gas pressure will not rise over a desired maximal level.
c. After firing (launching)
After the discharge, air pressure has-been built up in the com+
bustion space between the outer shell (2) and the fuel container.
This pressure ejects the cartridge-case base from the missile. Through
the compressed hot air the collodion layer (45) is likewise destroyed
and the spray nozzles (24) are cleared. The fuel, under a powder-gas
pressure of approximately 180 atmospheres and under an additional
centrifugal force of about 38'atmospheres in the pert heral area of
the fuel container, is led through,the fuel lines (16) to the accelera-
tion regulator (19, 20, 21, 22, 46, 47, 48, 49, 50). The acceleration-
regulating weight (20),with interval rings (47, 48),slides freely over
the light elastic split tube (21) made of plastic. The acceleration-
regulating weight is held between two leaf springs (19). If the driving
thrust makes the longitudinal acceleration too high, the acceleration-
regulating weight, under the influence of the acceleration, slides to
the rear, covering over the passage slit and throttling the fuel supply.
If the acceleration is too low, the acceleration-regulating weight
opens up'.a greater portion of the slit in the split tube and the fuel
supply increases. Through the fuel lines (17) the fuel is led out
of the split tube into a circular distributor space before the spray
nozzles. A'1Iorough preparation; of the fuel-air mixture is provided by the
14;8O ' spray. nozzles (24),whose inside diameter is 0.25 mm. ..The, spray nozzles
are inserted in deep cavities, the ignition cavities,.in such a way
that the ignition cavity supports the ignition process as a type of
Aflame holder". At the same time the vortex area at the edge of separation
of flow at the end of the explosive container (il) has a stabilizing effect
on the formation of the flame.
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-18-
Upon contact with the injected fuel droplets the air has a temperature
of about 760 degrees centigrade. A spontaneous combustion process is
introduced especially by the admixtuve of carbon disulphide. As a con-
sequence of the multiplicity of injection points, of high injection
pressure and the resultant good atomization of'the fuel droplets, of
the high temperature (760 degrees c,enti.grade), and of the high pressure
(68 kg/mn2) of the combustion air, the combustion is quite complete-
in spite of the high air velocity in the combustion chamber (70 m/si
and in spite of the very short combustion duration period (2.5 thousandths
of a second). At the end of 'combustion the gases in the missile have
reached a temperature of 1670 degrees centigrade. The combustion. gases
leave the nozzles at 1700 m/s and develop a thrust of 2280 kilograms.
After 20 seconds the combustion is completed; the missile has reached
its maximum velocity of 1880 m/s at an altitude of 24+ kilometers.
The protection of 'the interior walls of the combustion chamber against
high temperatures is done in the following manner: The wall of "the
fuel container is greatly cooled by the fuel, which adheres to the
wall as a result of centrifugal forces. The flame is directed by the
manner-of injection in such a way that it does not touch the outer shell(O un-
til it reaches the end of the combustion chamber. The air streaming
past outside removes heat from the outer shell. The great mass of the
nozzle (3) is able to absorb heat during the short burning period.
Nevertheless, there were instances of 'bore erosions observed in the
nozzle (3); these erosions were of no significance in the function'-.'of
the missile, however. The most difficult part of the cooling was the
effective cooling of the posterior flanges (Stege) (26). This was done
by means of borings connected with the fuel container'and filled with
circulating fuel. All parts exposed to the flame are provided with
ceramic insulation.
Rotation gain: During flight the gases drive,the diagonal posterior
flanges in such a way as to increase rotation so that even at terminal
velocity the rotation values necessary for a stable and continuous
trajectory have been maintained.
Missile at impact: The missile of this type is provided with a stir--
sensitive impact detonator. The missile nose, fixed at three places,
and the rigidly bound striker give enough impetus, even when the missile
lands at an angle slightly less than vertical, to the detonator to ex-
plode the charge above ground (impact velocity at about 480 m/s)
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Putilovo
30 June 1945 16 June 1952
Project 1947 1948 1949 // 1950 1951 1952
A-4
Theoretical and construction work on A-4
(
Beginning of 1950: A-4
and C-..running parallel
construction finished
Theoretical and construction work on A-4
To end of 1950: Improvements
and C-3 running parallel
)
in construction, experimental'
firings (possibly of C-3 and I
C-3
End of 1949: C-3
A-4) `A
EDnstruCtiOII
I
completed
Development in the Experimental firings
I
E-5
test nu.ssile Improvements in
I
construction
Tunnel built and used
Calculations and studies
I ! -
10 x 10 an
1
in experiments; Mach 8
wind tunnel
2.5 z 25 cm
'Calculations and Corking(
Building of structures
Wird tunnel
(drawings until. November
observed
i I
Theoretical projects and ( I February:
Radial-
calculations; 29 September I construction+
compressor
lecture Moscow completed
L
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)* jJ
0 F. k L ~.. i
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-21-
Legend to Sketch of Krasnoarmeysk
A. Design Bureau KB-3.
1. One-story building with all rooms used by. the Design Bureau.
2. Laboratory. The laboratory was equipped with brand new German
machine tools and had excellent vertical drill presses,
a. One planing table, 1 x 2metere.
b. 30-4+0 standard lathes, height of'centers 300-500 meters /S_iC'Z
length of material to be lathed may be up to five meters.
c, Shaping and ripping machines, cold.saws.
d. Foundry for small bronze castings.
e. Forges. Cabinet making.
f. Precision workshop for the rbpair of ballistics measuring in-
struments.
D.
A 400 square meter storage area with captured German instruments.
3. A 10 cm wind tunnel.
4. A 25 cm wind tunnel, in early construction stage, 120 meters long and
15 meters high.
5. Two sheds.
Electricity was supplied by Moscow via a 200-kilowatt private transformer.
Another private transformer was installed to power the wind tunnel.
In the laboratory, rockets and projectiles up to 1000 kilograms in
weight are being produced.
Firing range with shops.
6. Powder charging installation.
7. Munitions production.
8 and 9. Outbuildings with shops.
10. Firing range, 32 kilometers long.
11. 94x gun emplacements.
Rocket practice range
12. Practice range, 19 kilometers long.
13. Four rocket launching emplacements.
Firing Mange (olp igon)
14. Headquarters.
15. Barracks for range personnel, 3 stories.
16. Automobile garage and workshops surrounded by a board fence;
individual buildings are not marked.
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A22w
17. Water tower, 30 meters high, a conspicuous landmark.
p18. Bath house.
19. Central heating plant.
20. Sawmill.
21. "Athletic field.
The remaining structures indicated but not enumerated in,the diagram
are-residence, administration, and service buildingsbelonging to the
firing range.
E. Colony of German experts, This colony consisted of small plywood houses.
F. Sheds and barns west of the large practice range in the forest.
22. Large factory buildings for the manufacture of small consumer
articles.
The scale of the sketch is valid for approximate distances but may not be
cited for estimating the dimensions of the individual buildings.
Enclosures:
1.
Sketch of Tr. Geschoss A-1+, (Tr. Missile A-4).
Sketch of the c15 cm Tr. Geschoas; (15 cm Tr. Missile) .
3.
Sketch of the 15 cm Tr. Versuchsgeschoss (15 cm Tr. Experimental
Missile).
4.
Sketch of the 28 cm. Tr. Geschoss (28- cm Tr. Missile, C-3).
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Sclanitt A-B
Tr Geschos. Ay
5crrze ohne Masstab
12
D?ten des Geschasts
S~rengstoff
250 kg
Anfanss9cxhw
T40 ,r?,''
Mantel
2yC
NochstgescAw. ~?SO Mi'
StnbiliSator
20
Richweitc 754 koi
Srrrngsloffbe%:120
Brtnrtst'off 54
Biennstcfftark 6
GexAoss 750 *9
A bschussraktte.
Pulver 37Skg Xnmmtr 335l
Abschusila~luna :w:73Sdy
4'
ZuKder
2 t " d/Qdun
S rcn ladun
3
94 D' uiorschncidr
S Ver taWZ9srin
s 9
6 to hrun9S warts.
8 Pttotrohr,
rJ-crr Steye
l Vo
9 Br~nnstoJFdu;cm.
!Q Br~nn to
s
r~
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c r
13 Ni4tcrt 5te9t.
14 2 n t l4nfc
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46 o~laclun9.
4t 1-? n /
a
8 I k
1 t n t`rx Cr,acr
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-19 kc t
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21 1rcrrnAetrnd 5.
12 Pu1rcrrakdch fabil;c
s
s
23 tabrlfsierun9 I.
!Z ~Khr1sto r 24 L a YafcIii5
s.~ Ce.- r
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 Sanitized Copy Approved for Release 2010/01/19: CIA-RDP80-00810A003900600005-8
Sclanitt A-B
Tr Geschos. Ay
5crrze ohne Masstab
12
D?ten des Geschasts
S~rengstoff
250 kg
Anfanss9cxhw
T40 ,r?,''
Mantel
2yC
NochstgescAw. ~?SO Mi'
StnbiliSator
20
Richweitc 754 koi
Srrrngsloffbe%:120
Brtnrtst'off 54
Biennstcfftark 6
GexAoss 750 *9
A bschussraktte.
Pulver 37Skg Xnmmtr 335l
Abschusila~luna :w:73Sdy
4'
ZuKder
2 t " d/Qdun
S rcn ladun
3
94 D' uiorschncidr
S Ver taWZ9srin
s 9
6 to hrun9S warts.
8 Pttotrohr,
rJ-crr Steye
l Vo
9 Br~nnstoJFdu;cm.
!Q Br~nn to
s
r~
! ~alr,h
c r
13 Ni4tcrt 5te9t.
14 2 n t l4nfc
IS Iii ndtr fe r A t sfasS
46 o~laclun9.
4t 1-? n /
a
8 I k
1 t n t`rx Cr,acr
.
-19 kc t
Pi 1tetra cnk
20 Reketcn utrer
21 1rcrrnAetrnd 5.
12 Pu1rcrrakdch fabil;c
s
s
23 tabrlfsierun9 I.
!Z ~Khr1sto r 24 L a YafcIii5
s.~ Ce.- r
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 Sanitized Copy Approved for Release 2010/01/19: CIA-RDP80-00810A003900600005-8
Sclanitt A-B
Tr Geschos. Ay
5crrze ohne Masstab
12
D?ten des Geschasts
S~rengstoff
250 kg
Anfanss9cxhw
T40 ,r?,''
Mantel
2yC
NochstgescAw. ~?SO Mi'
StnbiliSator
20
Richweitc 754 koi
Srrrngsloffbe%:120
Brtnrtst'off 54
Biennstcfftark 6
GexAoss 750 *9
A bschussraktte.
Pulver 37Skg Xnmmtr 335l
Abschusila~luna :w:73Sdy
4'
ZuKder
2 t " d/Qdun
S rcn ladun
3
94 D' uiorschncidr
S Ver taWZ9srin
s 9
6 to hrun9S warts.
8 Pttotrohr,
rJ-crr Steye
l Vo
9 Br~nnstoJFdu;cm.
!Q Br~nn to
s
r~
! ~alr,h
c r
13 Ni4tcrt 5te9t.
14 2 n t l4nfc
IS Iii ndtr fe r A t sfasS
46 o~laclun9.
4t 1-? n /
a
8 I k
1 t n t`rx Cr,acr
.
-19 kc t
Pi 1tetra cnk
20 Reketcn utrer
21 1rcrrnAetrnd 5.
12 Pu1rcrrakdch fabil;c
s
s
23 tabrlfsierun9 I.
!Z ~Khr1sto r 24 L a YafcIii5
s.~ Ce.- r
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 Sanitized Copy Approved for Release 2010/01/19: CIA-RDP80-00810A003900600005-8
Sclanitt A-B
Tr Geschos. Ay
5crrze ohne Masstab
12
D?ten des Geschasts
S~rengstoff
250 kg
Anfanss9cxhw
T40 ,r?,''
Mantel
2yC
NochstgescAw. ~?SO Mi'
StnbiliSator
20
Richweitc 754 koi
Srrrngsloffbe%:120
Brtnrtst'off 54
Biennstcfftark 6
GexAoss 750 *9
A bschussraktte.
Pulver 37Skg Xnmmtr 335l
Abschusila~luna :w:73Sdy
4'
ZuKder
2 t " d/Qdun
S rcn ladun
3
94 D' uiorschncidr
S Ver taWZ9srin
s 9
6 to hrun9S warts.
8 Pttotrohr,
rJ-crr Steye
l Vo
9 Br~nnstoJFdu;cm.
!Q Br~nn to
s
r~
! ~alr,h
c r
13 Ni4tcrt 5te9t.
14 2 n t l4nfc
IS Iii ndtr fe r A t sfasS
46 o~laclun9.
4t 1-? n /
a
8 I k
1 t n t`rx Cr,acr
.
-19 kc t
Pi 1tetra cnk
20 Reketcn utrer
21 1rcrrnAetrnd 5.
12 Pu1rcrrakdch fabil;c
s
s
23 tabrlfsierun9 I.
!Z ~Khr1sto r 24 L a YafcIii5
s.~ Ce.- r
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