GUIDED MISSILE ACTIVITY AT BERLIN AND KRANOARMEYSK

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• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP81-01030R000100360005-6
• Release Decision: RIPPUB
• Original Classification: C
• Document Page Count: 36
• Document Creation Date: December 23, 2016
• Document Release Date: August 8, 2013
• Sequence Number: 5
• Publication Date: April 2, 1954
• Content Type: REPORT

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c:F...Pt+TRAL l'itTELLIGENCE AG
INFORMATION REPORT
CONFIDENTIAL
!h'FC".. 44.'`CN
This Document contains information affecting the Na-
tional Defense of the United States. within the mean-
ing of Title 18. Sections 703 and 794, of the U.S. Code, as
amended. Its transmission or revelation of its contents
to or receipt by an unauthorized person is prohibited
by law. The reproduction of this form is prohibited.
COUNTRY USSR (Moscow Oblast)/Germany (Soy Zone)
SUBJECT Guided Missile Activity at Berlin and ?
Krasnoarmeysk..;
DATE OF INFO.
PLACE ACQUIRED
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REPORT
DATE DISTR.
NO. OF PAGES
REQUIREMENT NO.
REFERENCES
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2 April 1954
36
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THE SOURCE EVALUATIONS IN THIS REPORT ARE DEFINITIVE.
THE APPRAISAL OF CONTENT IS TENTATIVE.
(FOR KEY SEE REVERSE)
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CONFIDENTIAL
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STATE
ARMY
NAVY
#x
AIR
#x
FBI
I:
AEC
Note: Woshingjton Distribution Indicated Se "X", Field 171frfrilmtle..
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? COUNTRY s
SUBJECT $
PLACE
ACQUIRED
.DATE ,
ACQUIRED
CONFIDENTIAL
USSR/Germany (SovZone)
Guided Missile Activity at Berlin and
Krasnoarmeyek.
DATE OF INFORMATION 1
THIS IS UNEVALUATED INFORMATION
REPORT
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DATE DISTR./ A PEEL 54
NO. OF PAGES 35
NO. OF ENCLS.
(LISTED BELOW) 50X1-HUM
SUPPLEMENT TO
REPORT NO.
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GENERAL MISSION OF THE GERMAN COLLECTIVE AT KRASNOARMITSKIT
1. rwas.the,laaderof a small group of German engineers located in
grasnoarmeyshiy (Incsmtas Putiloyo before the community of Kras-
noarmeyskiy was incorporated). There were three groups in the
German collective reporting to Design Bureau No.3. This bureau
was headed by a Soviet, DAVISHEV, and reported to the Armament
Section of the All-Union ioultural Machine Build-
ing Repor for information on .
personalities and report snares desoriptionj
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' My,grodi,carriedromt.deeign and development of air-to-air, ground- -
te-eir,',and.air-togrOUnd missiles. (This activityla.described it
:paragraphs 9 to 29 of this reporkg
2. The TROMMEDORF Group carried out research on gas turbine propelled
missiles and supersonic rain-jet power plants. I was isolated from
the activity of the TROMMSDORF Group, and cannot give cogent .,
information On their acti . /For intention On the TROMEROMF
Group activity, see Report
dated October 1953z/
. . 50X11
. :I?? 7,
. The BOEHM Group carried out design and development on ground-to-
ground anti-tank missiles. . I hate WPMe information on this group's
f
activity, it-is only its known to me through hearsay and soci
contacts. ghis information wal-be published in a future report. ?
l'havegivenEuleveluation orthe'contribution of the German
is:: ? ,
Collectiveat Kresnoarmeyskiy:and the potential of the Soviets to
carry out-sueceesful missile development Bee ReportThis 50X1
evaluation is based on my experience and observations during .
World.Wat.IL.: my:ectivity.in Berlin after the war, and m y stay at
Krasnoeimeyskiy..LI have Also prepared a chronological chart Of my
aotiviti at.Berlin.ind'Kresnoarmeyskiy See page 15 J.
TECHNICAL ACTIVITY, BERLIN (GEMA AND RERUN INSTITUTES)
QuestiOningronlormer Rheinmetall-Borsig Development
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5.
AZ this. time I was under. the SKG (Soviet Kommandit Gesellschaft),
Goma. Several former RheinmetallerBorsig employees, headed by me,
forMed a'small group whoseMisition was to gather, and to complete'.
'*her ? nebeseeiliteraturellasociated with former Rheinmetall- .
BOrsig'detelooments. HThis activity was carried out approximately
from July.1945-01ntil4anuary 1946. The projects on which informa-
tion was gathered included the three modelpfrOf Rheintochter; 10- .
second ?Powderpropellant with one-second booster, .30-second powder
propellant with two boosters located on the side of the missile,
and one model, with liquid.beesters. Information was also collected
on the Rheinboote,the.R-100-BS, Fritz "X", various boester rocket
develOpmenie,:"Kurt"., Aon-experimental models. of uncontrolled anti-
aircraft miSellea, Rheinmetalr-Borsig bomb developments, and on.
the operation and construction of firing test stands and field
measuring instruments for missiles. The ostensible purpose of
this questioning was to determine the status of the Rheinmetall-
Bersig development ili.rocket miesiles.-
.
. .
The Design of"Kurt"
In approximately July 1945 my_group was told to 'carry out an
improved disign,baeed on theoretical-considerations,.of-the "Kurt"
development. :This waist. air-to-ground uncontrolled missile
similar to_Fritz,"X".:The modification to the desiga.mould permit
the use of thieleissile fired from a speedboat. This was not ,
completed, and illpeared to me to have been a make-shift project to
occupy-out grouvuntil further work could be organized. This work
was carried Out 'in August 1945.
Design of the "Flues" Missile
7, In the fall of 1945 our group designed a ground-to-air missile with
the following characteristics;
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Maximum Weight
Altitude :
? Range
? Velocity
? Power
Control
Target Information
? In addition to our group, the EITZENBERGER
Hdesigned other portions of "Fluse" such as
'Control my
:airframe.
1000 kilograms
20 kilometers
30-40 kilometers
500 meters/second
Ram-jet
Radio Command
Optical ,
and MUMMERT groups
the guidance and
This project.wae worked on until approximately January 1946.. ?
At, thie time, the design was fairly complete in all its details.
I. refused to work any further because of the lack ofya wind
tunnel to carry out necessary aerodynamic and combustion tests.
a. Aahysioal Characteristics of the"Fluse." The "Fluid"
??missile was supposed to be an annular-wing ram-jet
? supersonic missile. The ieng was actually hexagonal? '
La shape. It was found was high enough to, furnish
the lift. neoessary for coiiTrol. The control surfaces
were located forward of the wing to give a quasi-oanard,
construction to the ' "Fluse." The body of. the missile
housed the control servo equipment, fuel, booster
rocket, etc.
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b. Power Plant. The design of the power plant envisioned
a multiple-shock wave supersonic diffuser. Vaporized
fuel is furnished through a perforated tubular grid.
It was intended to supply also a burning mixture of
nitro-cellulose-nitroglycerine powder and fine aluminum
powder to ensure combustion at supersonic nods.
o. Control System. A cruciform control 'surface was provided
:
to; in the "Fluse" missile. Provisions were also made
. in the body of the missile to house a command radio
system, and a twin-servo system with batteries for power.
...Similar to the Rheintoohter, this missile was not 50X1-HUM
.. controlled in the roll axis. It was planned to' use s...
gyroscopic resolver to feed control signals to the
ApprOPriate axes. )
? MMEMERTis and EITZENBERGERIe groups handled thie prObleni..
:For information on the desigly the oontrolAlystiM'i'syS ?
lepors
. General. Later modifications to the design inoluded;
WrItiduction of weight to 650 lbsi(2):Buoy-launohing:
deviol)(3) Use as an underwater mieeile;(4) Increaser,
of range to 50-60 kilometers for attack against other'? ? '
, ships. Only a short time was spent on these
changes. They were:mot actually ordered; rather they,,,,?
were suggested by the Soviet Shipbuilding Ministry.
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?
Therm was great Soviet interest in this missile design, and many
? oificiale Visited my group during this time. The design activity-
? was terminated in approximately January 1946, when I refused to
? continue without experimental tests both for combustion and
determination aerodyna ic coefficients. ffleferentse is made, to
? pages 3 to 9 of Report This report contains further 50X1
technical detail? on the design o the "Pause" airframe and power .
? Tiant, Drawing? of "Flues" reproduced previously are included
hers onms 16-19 for reference.;
'reparation of Technical Data on Former Nheinmetell-Borsig Projesits
??
8. During the period from April until October 1946, my group mem
' occupied with gathering technical data on the Sohmetterling,
. Rheintoohter and HS-294 missiles. The ostensible ;urban Of this.
?was to furnish enough data to enable the Soviets to fabricate
these missiles; The Rheinmetall-Borsig files were captured by
the Soviets almost intact. my group was also directed to write
technical reports on recommended modification to these misiilep. 50X1
ififerenos'is made to Report ehich contains detailed,
information
information on the projects carried out during this period)
source's groUp and the other groups at the Berlin Instituted
TECHNICAL ACTIVITY AT KRASNOARMEYSKIY:
!he ABR3-220. ?
9. The ABR8-220 is an air-to-air powder rocket missile. The design
of the.ABRS-220 is a modification to the RB-100-S rocket missile
'develOpid in Germany during World War II. The principal differ
ences between the German World War II development :50X1
and the A3RS-220 are the followings ?
?
a. Impulse increased from 4,200 kg./seo, to 4,700 kg./sec.
b. Fuel increased fiom 21 kg. to 24 kg.
c. Operating distance increased from 800-900 meters to
? 1,200-1,600 meters
d. Velocity change increased to 440 meters/sec.
04 addition to the valuable information obtained in learning
about the science of designing and developing an air-t0-air,
pissile, the Soviets apparently used this project to "wring ,
out" grout The later development of the "Ring 50X1-HUM
Magazine" missile see paras.23-20 followed naturally from.
this design.;
?
a. Airframe. The airframe is a bomb-like aerodynamio
shape., with a cruciform tail stabilizer. I have
included a rough drawing of the A8118-220 Lase psi. 20i1.
Am impaOt fits* i.e located in the hollow ogiya4.13ehth?
'the .0414. II large number' of small incendiary. cylinders
irere.paoked., In the center section is located the
explosive charge,. the ele tr cal timer and-the fuss for
'the, rocket. powsr plant.
PC
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b. Power Plant. The fuel consists of sticks of compressed
Diglycol powder,weighing 24 kilograms. The total impulse
produced was 7,400 kg./sec., and the thrust was found to
be 190-195 kilograms. Terminal speed was 440 meters/sec.
plus the speed of the aircraft.
(3. Accuracy. The ABRS-220 is a spin-stabilized, uncontrolled
air-to-air missile. The design requirement put to our
group was one out of two hits on bomber targets. A
considerable portion of the time spent by the group on
this project was in carrying out calculations of disper-
sion. Three different methods of obtaining a rotary
motion were considered as follows: (1) Canted )ocket
thrust (2)Assymetric spoilers on the fin stabilizer
(3) Canted cruciform fin stabilizer.
I rejected the third method, because the Soviets would not have
been able to manufacture the parts with the required accuracy.
d. Tests. Models of the A3RS-220 were ,tested on the ground
firing range at Krasnoarmeyskiy. Not enough tests were
Conducted to determine the accuracy of the missile., /
did not witness any .ait..firinglosts.
10. After-aompletion of the German activity on ABRS-220, it was discovered
that the Soviets were engaged in theoretical and practical aspects of
a similar project. The results of the Soviet tests made in competi-
tion with the German built model's were not made known to me. The
Soviets evidently placed a high priority on this project as .evidenced
from, the following. At the end of the work on.this project,I was
asked to give a lecture on the ABRS-220 design. The lecture took
place at the Soviet institute near the Yaroslavskiy railroad
station and was attended by a great number of guests including
high ranking officers and civilian specialists. This project was
terminated by turning over to the Soviets complete plans,
descriptive literature, and technical instructions.
The Sokol Missile
11. In the spring of 1947 my group was pressed to take up work on a
controlled air-to-air missile based on the "Falke" development.
In Berlin, where a certain amount of preliminary work had taken
place, the term "Super-Moeve" was applied to a supersonic version
of "Falke." 'In the USSR this project was dubbed "Sokol." .
12. I successfully put off working on "Sokol" at this time by pleading
inadequacy of personnel and facilities to carry out a controlled ?
missile development. The Soviets accepted my reasoning that
"Sokol" was not feasible as long as they did not have wind tunnel
results and a control mechanisms laboratory. I was told that.'
would receive the wind tunnel data in due time and in the interim
was assigned another project, the ABRS-240 See paras. 16 -19
belog.
13. However, a considerable amount of pressure was put on my group to
continue our work on the "Sokol" design. In spite of the handioaps,
I was forced to accede to the Soviet desires and started to work on.
it on or about 1 January 1948, without benefit of an appropriate
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laboratory, adequate. personnel, and wind tunnel faoiliiiiiTtFhie
project represents the only missile worked on in the USSR, which.
'involved a control system47 Borrowing heavily rrom Rheintochter,
and with obviously unqualified personnel, we laboriously carried Wi
Out-rOugh designs for the "Sokol."
. Design Characteristics. The "Sokol" is a controlled airs
to-air missile powered by a solid propellant. The design
included the following oharaoteristioss
Maximut Altitude 12 km.
Maximum Transverse 10 g. to 6-8 km. altitude .
Acceleration
Maximum Velocity 800 meters/see. at 6-8 km.altitude
(Missile plus aircraft)
Combustion period up to 10 sec.
Maximum Velocity 1250 km./hr.
of target
. Warhead 6 . Attack method
FUse pursuit curve
7
incendiary explosive
electrical or acoustical proximiti
fuse
Control link VHF pulse command system
(9)
(10) :Range 1200-1800 meters/sec.
Physical Characteristics. The "Sokol" is a canard missile
with swept-back wings, and vertical stabilizers located on
the tips of the wings. Vertical control is achieved by
operating the elevators in unison, Roll is controlled by
differential operation of the elevators. See pages 21
to 24 for Various sketches of the "Sokol:" These
drawings were obtained from material reproduced in Report
Technical design details can be obtained
from Enclosure (A) of this referenaej
Control System. The "Sokol", after being fired from the,:
mother ;plane, was to be controlled through a "Beeper"
:
by, the pilot. Turns could not be accomplished, exoept
1,7 coordination in roll, as in normal aircraft. Consequently,
:the. control 'process was exceptionally diffioult.Oonsidering ?
aAit, O. optical sight was used. Provisions were made for
inclusion of'a proximity fuse to detonate the warhead User-
? -the target. I cannot give any further technical APformatiMi
Ythea t - eviously submitted See Enclosure (A)1A ' ?
BepOrt
" -
At4he'Start of this project, the Soviets placated us with the
promise of anew servo-laboratory and wind tunnel facilities.
Aftera brief Study and rough layout work, the weight and dimen-'
Miens-were given to the Soviets'. After a meeting at the Secret
Section of the, Ministry of Agricultural Machine Building, it which
the casief.engineer of the Ministry was present, it Was decided
to have out group prosecute the "Sokol" design intensively. In
the place of experimental wind-tunnel data, I was told to use my
mathematiaieni for verification of the design. I pointed out that
at iimee seVeral weeks of calculation were necessary to resolve A
problem that could' have been done with a single wind tunnel test:
However, our theoretical work was excellent, and I feel confident
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16.
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that wind tunnel tests would only lead to minor modi . The
lack of verification did not appear to disturb the Soviets. Their
interest seemed to lie in the system design. As a part of "Sokol",
a new servo control system was designed. It was to be driven by
a propeller-driven generator. Where our group was incapable of
carrying out detail design, approximate dimensions and weight
were given to the Soviets, along with broad functional characteristics.
The design was completed about August 1948 and turned over to the
Soviets along with the supporting theoretical caloulations, ballistic
and hit probability calculations. This included a study of the
effect of human error in the control system. The data was tuned
over and discussed at a technical meeting at KB No,), ant the
project was dropped abruptly by our group. All the data and
documents were sealed and sent by courier to another location. No
Permeate ever .came to our group on "Sokol" after this meeting.
The ABRS-240, "Molnya"
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As a substitute to the "Sokol" project, the Soviets asked us whether
we could build an air-to-ground rocket with the following
characteristics;
? a. 1000 - 1200 meters range
b. 50 per cent of missiles in a target area one meter square.
I complained that this accuracy was impossible with an uncontrolled
rocket, but our reply to the fulfilling of these requirements was
the A3RS-240 "Molnya."
17. In April 1947, our group began the design of ABKS-240. The design
itself was based in part on certain intuitive assumptions by me
and the group, i.e., optimum power for the missile, size-of
stabilizer, rpm of main missile, etc. As the detailed design
progressed and calculations were made, the rough design proved to
be optimal in all phases. The Soviets were skeptical about the
reliability of expelling the projectiles without detonating them,
the stability of the projectiles, and the type of explosive pattern
that would be formed; as a result, permission was given to make
:three test Missiles. These were assembled from parts made in the
Soviet experimental workshops at Krasnoarmeyskiy.
ao 'Design Characteristics.
? .The ABRS-240 is an air-to-ground anti-tank missile containing
? seven projectiles in the warhead. This missile was to be
fired from relatively slow aircraft (420 km./hour). The
? terminal speed of the missile was designed to be 114 meters/
sec. plus the aircraft speed. The warhead contained a
cluster of seven powerless projectiles which were ejected
a few hundred meters in front of the target by explosive
charge detonated by the change in pressure in the rocket
motor after burning out. Upon expulsion from the body of
the missile, the projectiles were accelerated tangentially
because of the rotation of the .main missile. The center
projectile remained on the same course as the main missile.
The result was that the projectiles caused a ring-like
pattern in the vicinity of the target. The projectiles
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were detonated by air impact-fuse armed by a
fan-driven
electrical system. gage 25 contains a drawing of the
A3S-2400 showing the design details and a-tabulation
of the design data of the missile. Page 26 contains a
drawing of the hollow-charge projectile used in the
warhead. of the AER2-240. Page 27 contains drawing
of. an.'improved projectile designed by thegroup.
;;;;;;;Iort
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Further teohnical details can be obtained
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? Testa. These missiles were fired on the ground firing
range at Krasnorameyskiy. I. attended these tests; the
missile behaved as designed. After several hundred
yards of flight, the ejection of the projectile took
place and then separated from the missile. airframe.
The folding fins opened and the projectiles stayed on
course., Even the empty airframe, without ?give, stayed
on coUree. After the tests, the project was assigned a
high priority and efforts were concentrated on complet-
ing it in the shortest possible time.
18. After the tests, our group received official requirements for an
improved ABRS-240 to decrease the caliber, decrease the size and
warhead of the projectiles, and increase the penetration capacity
of the projectiles.- These requirements were as follows:
Total. Weight "
Caliber of missile ,
Caliber of projedtiles
Penetration power
Firing
?
Fuse of projectile
Stabilizer
Power Plant'
less than 60 kg.
210 mm.
92 mm.
220 mm, armor plate
by pilot operated button
Z.66 (Redesign of pulse generator fuse)
Folding fins only
No change
In addition, production drawings were required, incorporating
manufacturing?simplifIxations., The only remaining activity on this
project was on hit-probability studies carried out over another ?
six months' period whileour design group worked on the nett Project.
19. After the test firing of the ABRS-240, a Soviet design group in
KB No.5 was given the new requirements and began work on the design
of an improved ABRS-240. I saw, during visits to the experimental
workshops, parts being manufactured that could be definitely
identified with ABRS-240. I noted that several changes had been
made by the Soviets in the manufacture of the missiles. For
example, a leather gasket was changed to cardboard allowing some
of the combustion gases to escape. In order to prevent any further
knowledge of this activity, an order was issued in the:winter of
1948-1949 placing the workshop off limits to German personnel.
The Zenith Missile
20. The Zenith design resulted from the Soviet requirement for a cheap,
uncontrolled mass antiaircraft weapon. The following detailed
requirements were given to our group in the fall of 1948, after the
"Sokol" project was terminated:
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Altitude 18-20 km.
Control Predictor (Optical or radar)
No control after firing
Batteries To be fired in groups.from simple
launching platforms c:
Warhead 500 grams of hexogen ?
21. We developed a design of a two-stage, ground-to-air solid propellant
rocket to meet .the above requirements. The design included all
the important details. However, the theoretical ballistics carried.
out in support of this design were rather sketchy. The design,
once it was decided to use a two-stage missile, was based on old .
? values wii.remembered were used during wartime at Rheinmetall-Borsig.
?This design, with supporting literature, was turned over to the
Soviets at KB No.3. Lit is interesting to note that the data on the
Zenith was not translated until nine months later, and at that time,
sent to the Agricultural Ministry. At this time, several questions
were asked abolt the Zenith, on length of time for development, 'and,
several minor items. The total spent on this project was three
monthsA7
22. I have included drawings showing_ihe general layout of the Zenith
the page 20 ? of this reporyand below I have given, point by
point, a description of the missile, flee pages 3 and 4 of Report
containing a table of design characteristics which
source was unable to elaborate upon during the reinterrogationg
Point a jmnaot Fuse
This impact fuse is spin-armed. The rotation is obtained by the
slanting of stabilizer surfaces. The fuse itself contains in ?
addition to the impact mechanism which operates on the ordinary
centrifugal principle, a self-distribution device which, during
the descent of the projectile, would ensure an explosion of the
second stage if the target were missed.
Point 2 Detonator
? Attached to the fuse. It is possible that the dimensions used hire
. are not the final version since the fuse was to be supplied by the
Soviets,'-It is probable that the diameter of this primer is a
little larger. The Soviets generally use rather flat-detonators.
? ?
p
Point liPfitheallCasing.
COnfiste of deep drawn steel having wall?dimension between 1 mm.
and 1.5owz. In front a threaded nut is provided for attaChment
of the fess. In the rear of the cylindrical part is located a
drawn steel plate of 4 mm. thickness. This plate is connected
with the forward ogiv, by means of a circular welded seam.
"dint 4 panel,
A deep drawn steel cup having a thread that 'serves as't tormidel "
? of the missile's combustion chamber.
Point 5 Esilosive
It was to be a 1-to-1 mixture of Hexogene and Trinitrodonol, with
a slight amount of aluminum aPyrosohliff." .This addition ;wO"
thOughtio achieve maximum penetration effect based on our experi-
ences in Germany.
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? yoint 6 Combustion Chamber
The chamber has a thermal protective lining in order to
prevent the burning-out of, the rocket chambers due to the
hot missile gases. Without this protective coating, we
would not have been able to use 1.5 mm. steel for the
combustion period.
!Cant 7, Powder. Propellant
Outside diameters- approximately 61 mm.
Inside diameters approximately 8.5 mm. (for the channel),
The two interfaces are thermally insulated to prevent com-
bustion in the direction of the axis. Along the circumfer-
? ence, three centering pegs are located.
Point 8
Three Centering Pegs
The three pegs which are located around the circumference
are connected with the powder charge support. The charge
centering support is a cup of drawn steel which has many
holes on its interfaca.
Point 9 Propellant Supporting Panel
This is the propellant charge
the acceleration forces to the
of the support or panel can be
Point 10 .Powder Charge for Igniting the
This charge was stored in a c
the center of this capsule, a
celluloid disk ( or panel) was
:destroyed by the burning gas,
of thicker celluloid and thus
support which must transmit
powder charge. The structure
seen in Detail A and Detail B.
Main Missile
losed celluloid capsule. At
very thin-walled air-tight
located which had to be
The capsule itself was made
was not destroyed by the gas.
Point 11 Nozzle
Made of a thick-walled steel pipe. The required enlarge-
ment of the cross section was made by stamping. The joint
with the rocket combustion chamber was to be accomplished
by a.high-temperature pressing process. The smallest diameter
is approximately 17 mm.
Point 12
Steel Tube
A cylindrical pipe having a wall dimension of approximately
1 mm. It was welded by means of a circular welding seam
to the nozzle panel. On the pipe were affixed the four
stabilizing surfaces.
Point 13 Stabilizing Surfaces
Tke four stabilizing surfaces were canted at an angle of
approximately 3 or 4 degrees to assure the required spin .
during flight. In the rear of the steel tube, some center-
ing.was provided by means of the front panel of the adjoining'
basic stage. This centered onto a peg in the nozzles.
Transverse forces were transmitted at this point.
Point 14 Centering Peg
This conical-shaped peg fits into the nozzle of the second
stage. This is required in order to assure a rigid connec-
tion between the two halves of the missile. A catch
? mechanism located at this point made possible the safe
C ONFIDEN.TIAI
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joint 15
C ONFIDENTIAL
.
- 11 -
tranaport of the two stages on the ground and quick assembly
at the launching site. The catch mechanism was replaced by
a more simple version using a copper shear pin. It was
believed that a quick release catch mechanism would allow
the second stage to be fired alone against low flying
targets. Inside of the peg was a delay powder composition
which was coupled with the pressure-igniter. This pressure-
igniter was activated by the propellant gases of the first
stage. Inside is a cylindrical drill-hole in which a copper- ?
sealed piston is located. The piston is thrown forward by
the gases of the first stage. In its forward position the
piston-hits the firing pin which ignites s percussion cap.
This results in the combustion of the delay powder composition.
The Forward Sealing Panel of the Firstfitage
A Clamped steel part which had a threaded connection on the
frontal interface as will as in the curved position. This
curvature permitted an additional centering of the casing
of the second stage. The sealing panel had an outside thread
which was screwed on to a steel ring. .The steel ring in turn
was connected with the 2.7 mm. pipe by means of a welded /Sam.
The caliber of the steel pipe was approximately 120 atm. On
two diametrically opposed places on the forward sealing
panel, pigs protruded in which the guide pin was screwed.
.Through this guide pin, the igniting voltage was to be fed '
to the missile igniter. For this purpose an electrical
percussion cap was placed in the shaft of the guide peg.
The explosion of charge ignited the centrally located powder
charge.
Point 16 Black Powder Charge
?. The blaok powder charge was contained in a thick-walled
. celluloid capsule which had weak points around its cir-
cumference. These permitted the penetration of the
igniting explosion. The celluloid capsule was centered
' by means of a centering ring.
Point it Centering Ring
This-Wat'pressed of deep drawn steel. It had flanges.which
were bent inwards and served to hold the .celluloid.oapsulas
Three oentpring pegs were attached to the oontering ring. '
Joint li 'OentSrins Pegs
Thee, pegs oentired the main politier propellant charges
of the first stage.
point 19
Point 20
'Frontal Area Insulating Layer
Located on the propellant stick,
. .
Powder Propellant Stick .
Outside diameter of 101 MM.
Inside diameter of 15 mm. (channel diameter)
Total length - 840 mm.
The stiok-was heat insulated at. the point of contact with
,tho:thria-oentering pegs. This prevented'theopabuistAcn.
front from starting at these points of contact.
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CONFIDENTIAL
-12-
yoint 21 pion surmorting Panel
Aeoeleration forces are transmitted by this panel to the
propellant charge of the first stage. It consisted of a
Stall ring approximately 3 mm. thick which was provided
around its circumference with three flat iron strips to
cater the missile's combustion chamber.
Point 22
Sealing Panel
this panel, was also joined to the nozzle. It was a
preesed part constructed .from a thick-walled pipe. The
..thick-walled pipe was turned out in the direction of the
gas jet in order to obtain an enlargement of the cross-
section'. The necessary enlargement for the missile's
Combustion chamber was to be achieved by a high-temperature
process. The connection between the panel and the pipe was
to be effected by means of a circular welded seam.'
Point 23 Conical Steel Casimir
This was designed as a fairing to enclose the nozzle. The
fairing also served as a means for attaching the four 'control
'surfaces.
joint 24
Control Surfaces
'The Ring Magazine Missile
23. During World War II, the Germans had planned to improve the
RB-100-S air-to-air missile by using small ballistic explosive
projectiles in the warhead instead of the incendiary cylinders.
This improvement was called "Miki." After the "Zenith" project,
the Soviets wanted our group to continue along these lines. ,The
Soviets did not approve of the cluster warhead, nor of the
4ength-.of,the missiles designed. They consequently gave new
requirements, in general to shorten the over-all length, and
utilize a. ring magazine construction; these requirements were as
follows:
Range
Speed differential
Warhead
Projectile Fuses
Main Fuse
In'a short time, many diffe
the representative ones are
800-1000 meters
350 meters/sec.
Cluster of explosive ballistic
projectiles
Impact and Time delay for
self-destruction
Time delay ?
rent designs were presented. Only
reported on.
24. The Ring Magazine missile follows generally the design of the
RB-100-S. Ten different designs were carried out over a period
? of two months. They differed from the basic design in methods
of expelling the projectiles and numbers of projectiles. The
airframe of this missile was approximately 1.5 m. long and
Approximately 300 mm. in diameter. The propellant, like all the
? designs carried out at Krasnoarmeyskiy, was solid powder sticks.
Stabilization was to be maintained by a cruciform tail. The
-Projectiles were to be ejected after a time delay and form a cone
9 O'NFIDENTIAL
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25.
26.
CONFIDENTIAL
- 13 -
of fire designed to hit the target at maximum range 50 per cent
of the time. The warhead of the projectiles was to be approxi-
mately 4 kg. of incendiary material detonated by impact, or by
a self-destruction time delay fuSe. The projectiles themselves
were with8ut power,'and stabilized by folded fins which opened
out to 90 as the projectiles were ejected. I have included ?
drawings showing the two principle designs of the projectiles for
the Ring Magazine missile. along'with pertinent data. flee
pages 29 - 31 Also,on pages 32-34 amreproductionsof the
drawinsocontained in Report Further details of the
design.of this missile are contained in this referencej
The design of the Ring Magazine missile and its variation was
carried out from January 1949 to May 1949. In the final reports
on these designs, drawings were included which did not show all
the design details. Kowever,-the -propulsion unit itself was -
fairly complete in order that fabrication could be started
immediately by the Soviets. The hiallistic Calculations were
carried out only far the critical values and not in as great
detail as on the earlier projects. The work was principally
engineering design, and only, 30 per oent of the group's
time was spent on ballistic calculations. Nothing further was
said to us after oup reports were made on this missile. During
the winter. of 1951-1952, I accidentally observed test firings
of., missile which was undoubtedly built along the lines of the
"Ring Magazine" missile. Since the altitude of the aircraft
was approximately 10,000 ft., I could only count the burets and
determined row this that several of the variations in the de040,1
were built. Some showed 24 bursts; others, 50 bursts; and ori9X1 -HUM,
as many as 70-80 bursts.
see page 11 of Report
We were clirected to design a launching device to be housed in
an aircraft of-unspecified dimensions and configuration. This
device was to launch 48 air-to-air missiles in succession. Dur-
ing this time, there was a closer working arrangement between
the Soviet military and the German group. A colonel (Air Force)
came often for briefings and occasionally offered suggestions as
the design progressed, but I do not remember his name. Be was
a permanent representative of the Soviet Air Force at Kras-
noarmeyskiy.
The Automatic Rocket
27. The Automatic Rocket, is a weapon similar to the "Mighty Mouse"
air-to-air missile. An automatic launching device fires 48
air-to-air missiles from the mother aircraft. The missiles of
this weapon are not controlled. The design of the Automatic
Rocket comprised two pods which carried 24 missiles each. The
missiles were mounted on an endless belt which was rotated by
motor. As each missile reached the lowest point in its travel,
it was automatically released by an electrical contact made at
that point. Every other missile was set back a few inches, to
prevent malfunction from contact between adjacent missiles.
The order of firing was such that the front row was fired first,
and then the second. The endless belt thus made two full
CONFIDENTIAL
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CONFIDENT IAL
- 14 -
50X1
. m
ravitlutinnn Aron nagn.35 for drawing of the Automatic Rocket.
?
? 50X1-HUM
28. .Thia.projeet irse initiated in May 1949 and was completed in
Auguit 1949. It represented a fairly quick design solution .
.of the mechanical problem posed by the Automatic Rocket require-
. --Heent:. Design' drewinis for a prototype launcher were turned over
to the Soviets along with a briefing by me, and no more was
heard on this project. Not enough time was given to complete
? this project, and the plans were general. Ballistics Of the
? missile itself were barely touched by our group.
Firing Tests of ABRS-240 Projectiles
29. In the last few weeks of 1949, our group was directed to oirry
out penetration tests of 13115-240 projectiles. I cannot give
much information on this subject, in view of its short period
of duration and my lack of direot contact with it. I do knew,
however, that the warheids involved showed i penetration of
800-800. millimeters. (pee Report for detailed
information on. the firing range at IS No.3. 50X1
CONFIDENTIAL
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- - -
791.LA/Crld/V9)
. ?
,
. . -
BERLIN GERA AND BERLIN I:NSTITUTE)
' - -
. ACTIntf ii-r, 7-
t -
1945
- 1946
1947
! 1948
1949
1950 .
1951
1952
., _., i
Questioning on former aheinmet44?sig
Missile Development -. : ..)!.
Fr?
...
-
i

Counter-Invasion Missile ^tarty
Air to Oround Missile
c
"Moevi"-Design
Air to Ground Missile '
i,.
"Tinge" (Ramjet)
Ground to Air Missile
.
---t.,
Prepared data on "Rheintochter"
"Sohmetterling" RS-293. RS-?94, Fritz "X?
)''
74
PUTILOVO ?13-3
Modification of "BB 1003" to ABRS 220
Air to Air Missile
.
Preliminary Deisign of "Super Moeve"
or "Sokol"
,
,
I
"
"ABRS-240(Nolan)
Anti-tank Missile
1
/
zzza _ _ _
_ . _
_ _
.?13al1istic
Calculation
(Nolan)
'kolV
, .
,.Z :to Air Missile
, .
..
.
"Zenith" 2-Stage . .
Grown4 to Air Missile -
-....,
1
N.
\
'
Design '1 "Ring Isgasint"
Air to Liz 1101$1*

:.
:
AutotiOictrAir to Air Rocket,
i 1 ,
,
? i
i
-
.
1
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Declassified in Part - Sanitized Copy Approved for Release 2013/08/09: CIA-RDP81-01030R000100360005-6
4 Centred RuiKers
1?1140 ? ROAM?' Sera!
WIQi IlanplIfier
Batters
50X1
eikrenbers Type Receiver;
%Starter Racket
Prop e I lank
witght? 60kg.
Impulse= 11000 kip.
not, 041"
Savants
Proximity Fiss? Reducer Valve
Preakeityrusa %Means'
Jet feel Grit
Thsplacement Ggro(Rheintochter) Direct Current Inverter(500?0
FLUSE GROUND TO MR MISSILE
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Recalver knitenna.
Declassified in Part - Sanitized Copy Approved for Release 2013/08/09: CIA-RDP81-01030R000100360005-6
rw.
50X1
-
;
.
_....misper-
injection
?pee...?.
...,....
Velocity ioithoiiA fusel
eft
'qllIllIllIllIllPr
es se
Cho.nye in pressure throu.eli
f u.el injection
PC"
W
' --. Pressure usithou.t
fuel injection
PRESSURE-VELOCITY DIAGRAM OF THE FLUSE
GROUND TO AIR MISSILE
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co
on
DETAILS OF FUEL INJECTION ? FLU SE
G-ROUND TO AIR MISSILE
50X1
tttt tt
ban 4
XclaMINVIIN IINVINVINVZOWNUOVINVINVOIMINVIAVIM
t t tt tt
0
Jet fis.et grid
Thermo.' iostatest ion
Nitrocelissiose. powder plus o.losolVIlLVa peuodar
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Sheet Steel
Annus, lar Wing
Ointermis
Page 19
? FRONT VIEW OF THE FLU SE
GROUND TO AIR MISSILE
fr
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CIRCUIT DIAGRAM OF
TIME DELAY FUN!.
Potexte r sticks
?
Space -For
nrapattLiewse
Time fuse
3
Propellant .igniter
1600 moo yn
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50X1
20mm
,0
SIDE VIEW- SOKOL. AIR TO AIR MISSILE
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rtilsift
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117
FRONT VIEW- SOKOL AIR TO AIR MISSILE
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COMP:1
Page ?ZS
KINEMATIC 'DIAGRAM TVs/IN RUDDER SERVO
SOKOL,- AIR -70-AIR MISSILE
cO.A/ F IOEtVTI4L
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50X1
?s,
\\??:
\\\N
\tr
\\\\??
\ \ \\
?,\
? ?
TOP VIEW SOKOL AIR TO MR MISSILE
0
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In
CONFIDENTIAL
50X1
???11150soin
.3beipectchaiyapriojestile:
Ono.
1300. no of
3 Piece Cap
.3 Screw choichs
Pressare Moo Pose
Ejection Cho/ye
a Piece tjeclote Disc
awing Pond
ignition
cable
Caliber 240 mon
'Total -length fleet 1840 mm
Outside dinowiteo of iiko roared gooey 130 ant
3 spacers Raabe, of hollow charge projectiles 7
* Phu . weipie of one Inflow efterige projestfie .4.r kg. ft,
Total aveighl of coatinte rocked 78 let
ishilgeht of propenent charge (NO R. ) Si A.
Nominal spent increase a lout . Wink
Nominal intpalse. _ sio n.
Penetration neer 'against gonna plates...-200mm
Relative spent of fighter Wen 420 kistik
Operation/ range _ 1100m
AORS-240 AIR TO GROUND MISSILE (MOLNYA)
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Declassified in Part - Sanitized Copy Approved for Release 2013/08/09: CIA-RDP81-01030R000100360005-6
QUA I
5oft Deep Drawn Sheet. Metal
39s
SHAPED CHARGE PROJECTILE MR TO
GROUND MISSILE AEIRS-240 (MOLNJA)
Penetration ISO to 200nim Armor Plate
Weight of Explosive 950 Grum*
Composed of- 'Trinitrotoluene 457.
Tetruntethglertetrinitramine 457.
Aluminum Powder to Y.
Total Weight Approninnotell 4.5 Kg.
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5 p 3
Fuse Circuit Diagram
(../
I
run
2
Alternating Current Generator
3
Selenium Rectifier
4
Conetensor
5
Electrical Igniter
6
Contact Cap
Declassified in Part - Sanitized Copy Approved for Release 2013/08/09: CIA-RDP81-070Y36000100360005-6
CONFIDENTIAL
Impact generator fuse with fan
arming device (Type 20H66)
Proposed. electrical 2 wire circuit
with electrical detonator
45% Tri +457. Hex -10% Ala efts
457. Trinitrotoluene
45% Tetramethylenetrinitrainine
10% Aluminum powder
Proposed. binge spring
vat
4
train a
ABRS-240 MR TO AIR GROUND PROJECTILE
(MOLNYAL 2ndt MODEL
? ?
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Toto.1 weight approx. 3.2 Kg.
Penetration required. 220 mm
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50X1
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50X1
off- set
For
rota r
eft:a:et
MODEL NO. 1 RING MAGAZINE AIR TO AIR PROJECTILE
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I%
50X1
/,
z/ z/ ? //
/ /./
1.?` //// /?, / /
?
/// // //'/ '//'/ // / 2 / 41 /JP
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der /-74-/-47t14?7 -.14- -717 1-.C5--/-/e -4" 4
, e M/// // / / / // / / / /
// / / / /// 71
/ o / // , ///-, / /// //
',/// /// / /////////f/jo
,,//, ////////,////n/fr '
///,////////////////// / //// / z;
"""
250
MODEL NO. 2 RING MAGAZINE AIR TO AIR PROJECTILE N's.
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00117IDENTIAL
Page 31 '
50X1
REAR VIEW, RING- MAGAZINE AIR TO AIR
PROJECTILE MODEL NO. t 4 NO. 2
4
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csomm
50X1
o
111"le 554 " trala-EMENERELE
,
- M; k.,, sztar, tsars sa 4
NM.X NX N
?\,i._ %%NW ? X% XV IN 'WV 0 L W 1 . XI ..X% N
A p a r rarstst a w - a/Si 't A
?
s
s ? 1 / / A
MI
S
A'N
RING MAGAZINE AIR TO AIR MISSILE
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pONYIDENTIAL
Page 33
CROSS SECTION, RING MAGAZINE
AIR TO AIR MISSILE
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rSitenalsj Nininakon
?saia 404
50X1
Plena of target
a Self destruction
&wain, enst-.ft
-Nettie, point
L u Flight path of the 6 ?give' projectiles.
1)., Flight path of the 32 projectiles in boat, of
Pins Wiesastne.
TRAJECTORY RING MAGAZINE
AIR TO AIR MISSILE
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. 'r -
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?
ceretritawr /AL,
Page 3C
?ItOTAR.4 ARMED
nthPACT Fuse
SHORT DELAV
POSITION
RETRACTABLE
FUSELAVE
ELS C.TRI C. DRIVEN -
WHEEL
ELEcT R1C AL. ROCKET
rUsc BURNING-
PoWDE-R CRAMMER
NOZZLIZ
420- 460 GRAM EXPLOSIVE
M
AUTOMATIC AIR TO AIR ROCKET
CegyripE WTI AL
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