ROCKET AND AIRCRAFT DEVELOPMENT AT BRANCH NO. 1, INSTITUTE 88, GORODOMLYA ISLAND

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP80-00810A001100310009-6
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 41
• Document Creation Date: December 22, 2016
• Document Release Date: June 30, 2010
• Sequence Number: 9
• Publication Date: June 17, 1953
• Content Type: REPORT

Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
CENTRAL INTELLIGENCE AGENCY
INFORMATION REPORT
SECRET
SECURITY INFORMATION
This Document contains information affecting the Na-
tional Defense of the United States, within the mean-
ing ,of Title 18, Sections 793 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.
Rocket and Aircraft -Development at Branch DATE DISTR.
No. 1, Institute 58, Gorodomlya Island
NO. OF PAGES
THE SOURCE EVALUATIONS IN THIS REPORT ARE DEFINITIVE.
THE APPRAISAL OF CONTENT IS TENTATIVE.
(FOR KEY SEE REVERSE)
G-1 ROCKET GUIDANCE DEVELOPMENT WORK AT NII--88
General Description of Work al d Problems Encountered
1. Work was started by the Soviets in 148 at NII-88 on a modification of the German
A-4 (V-.2) rocket. A meeting held in Moscow from 20-30 December 1948 was attended
by the following German spesi.aiists: WOLFF, GROETRUPP, HOCH$ ALBRING, Rudolf 25X1
MUELLER, Gerd MUELLER, BLASIG, BLASS, UMPFENBACH At this conference
preliminary plans for the A.4 modification, to be designated. n1, were discussed.
2. The accuracy planned for the G-1 missile-was to be 50 per cent hits within plus or
minus one-thousandth of the range. Thus, for the planned range of 300 loll, the
required accuracy would be plus or minus 300 meters. In. order to achieve this
accuracy the flight path must be accurate to within plus or minus three minutes
in azimuth and 0.05 degre s in elevation.
3. Work on this modification was started by the Germans when they arrived on Gorodomlya
Island near Ostashkov. The following major physical changes were made. The stab-
ilizing gyroscopes and electronics equipment were moved down below the fuel tanks
41
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
4.
near the combustion chambers and it was decided to use integral
fuel tanks, i.e., the wall of the rocket was to be the tank it-
self. The antennas were to be modified as described in the
paragraph on the airborne receiver and transmitter (See Page 31).
UMPF'ENBACH redesigned the rocket engine so that exhaust gases are
fed from the combustion chamber to drive the turbine. During
the feed-back these gases are cooled by the unburned fuel. To
keep the pressure in the combustion chamber constant, it was de-
cided to use an "Alpha Regler" (regulator). This used a pressure
gauge which operated as follows" an iron membrane is placed
between two pairs of coils, which are connected in a bridge
circuit;and,,when pressure causes the membrane to deflect, the
inductance of one pair of coils is increased, and the other
is decreased. Since a 500-cycle voltage is applied to the bridge,
the output is a signal proportional to the deflection. This signal
is applied to a magnetic amplifier whose output drives an actuator
similar to the one used to actuate the rudders in the missiles.
This actuator operates a butterfly valve which controls the flow
of gases driving the turbine.
5. It was calculated that at combustion cut-off the acceleration
of the missile would be five to ten g. Cut-off was to occur
at a distance of 45 kilometers. A number of problems were
also worked on in order to prevent errors from arising after
combustion cut-off. Rotation of the rocket about the longi-
tudinal axis after cut-off is of no consequence. However,
since there is little air resistance the rocket may swing
about its other axes, which would cause it to come into the
lower atmosphere sideways or backwards. In this position
the increased air pressure may cause a sudden shock which
might explode the warhead. It was decided, therefore, to
use a warhead which would be detached from the rest of the
rocket after combustion cutoff. This could be done in one
of two ways. The warhead could be set on the rest of the
rocket loosely so that it would automatically separate at
the end of acceleration; or the warhead could be shot off
by an explosive charge. The latter plan, however, would
give the warhead additional velocity and might, therefore,
introduce an error. It was also proposed that velocity
and range could be measured after combustion cut-off and
that a command be transmitted to cause one of several
different sized charges to blow off the warhead in order to
compensate for any errors introduced in combustion cut-off.
this method was somewhat far-fetched and too
complicated and could cause a serious error if the rocket
had changed direction after cut-off; therefore, the first
system, using a loose warhead, will probably be accepted.
The proposed warhead was to weigh 300 kg.
6. Another problem discussed was the glowing of the warhead as
it travels through denser atmosphere. It was proposed,
therefore, to cover the warhead with a thin layer of wood
which would carbonize, but protect the warhead. It was
planned to place a solid steel point on the tip. The wood
covering was to extend slightly farther back than the war-
head in order to keep the center of pressure behind the
center of gravity so that the warhead would fall point first.
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
SECRET'
-3-
A number of Soviets frequently came to Ostashkov to keep track
secret papers had to be kept in a suitcase assigned to each of
chief engineers, directors, and other scientists from Zavod 88;
(b) groups of men from the Ministry for Armament;; (c) KONOPLOV,
who was presumably working on similar developments in Leningrad,
and several of his engineers; (d) scientists from other groups.
The following security measures were taken at Ostashkov. All
of the developments there. This group usually included (a)
.night all the suitcases had to be locked in room No. i ?
the more important specialists. Each paper was numbered, and
a list of the numbers kept in the suitcase as a check, lEverr3r
and in the morning proper identification ha-d--to
and passes was used to allow only authorized persons to enter
the various laboratories and offices in which secret work was
being performed.
be presence to?obtain one's suitcase. A system of badges
In the fall of 1951 the work of the Guidance Group
was taken over by a Soviet group whose chief was
F M r. After this time none of the Germans were permitted to
enter the laboratories where this work was continued.
10. Flight tests were made in 1951-52.of the guidance system
developed for the G-1 missile using PO-2, AN-2,, and Li-2 air-
craft. The equipment to be carried on the rocket was installed
in the aircraft and flights were made usually heading north
from Gordomlya, over Lake Seliger, up to a distance of 100 km
By flying circles around the ground station on the island it
was determined that a relative velocity of 0.1 meters per
second could be detected by the equipment. The PO-2 usually
landed on a field on the mainland shore west of Gorodomlya,
while the other aircraft had to land on a larger field located
28 km'. south of Ostashkov. The field was about two km square.
Both fields were not airports, but merely meadows maintained..
enough to permit these planes to land. no information
.. on the maintenance schedules, repair difficulties, etc., of
the maintenance was performed in Moscow. None of these planes
these planes
was flown at Ostashkov in the winter. To have a plane avail-
able for a test flight it was necessary to order it one month
ahead of time. Zavod 88 had three or four PO-22s, 3 Li-2's,
and .AN-2 assigned to it.
Evaluation of Soviet Progress
11:. 'In the fall of . 1951 a conference was held in Moscow to discuss
.the G-1 development. This conference was attended by FOMIN, who
reported what the G-1 was criticized, but that it was also
said that it is better to have this than, nothing at all.
25X1
25X1
25X1
75X1
25X1
25X1
25X1
12. I 25X1
t e Sovie::s were no entirely happy w
surface-to-surface guided missiles. this might 25X1
be due to the fact that the Soviets do not have enough competent
engineers to carry on such work, and that very few of them have
the self-confidence to be willing to take on a responsibility
of this type, since failure is not tolerated. Even FOMIN was
apparently trying to be transferred to another project.
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
13.
25X1
Evidence of Soviet incompetence is reflected in the firing
tests made with German A-4 missiles in 1947. These missiles
had been put into operating condition in Moscow and were placed
on an'A-4 train. This train went to Kapustin, where the firing
tests were to be made,' At first. the firing tests were un-
successful and Dr. HOCH was called to Kapustin to straighten
the situation out. Future tests were successful, and HOCH
received a 'bonus equivalent to two months salary. This
indicated that HOCH had helped the Soviets out of a very tight
spot. At the same time these 25X1
indications of incompetence may be deliberate in order to
conceal their real progress in this field. (The "A-k train"
was'a special train fitted out with all the equipment necessary
to transport and fire A-4 rockets. It included cars for
measuring and control apparatus, Messina, telemetering equipment,
workshops, several sleepers used as living quarters, and confer-
ence cars, Three cattle,ears with the ends removed, were used
to carry the rocket. Two of these trains went to Kapustin in
September 1947, and sections of them returned to Moscow in early
Specialists who had 25X1
been at Bleleherode after the war told that they had equipped
two such trains. From the train, the rocket is transferred
to a "Meiler Wagen", which is a special truck designed to pick
up the 'rocket, carry it,and set it up on end on a launching
table.)
1'4,
a Soviet, KONOPLOV,
apparently was developing, another guidance system for the
rocket in Leningrad. KONOPLOV also was part of the group
Which visited Ostashkov at frequent intervals. 25X1
the 50-centimeter wave e
for guidance would be seriously attenuated by the 25X1
jet stream of the rocket.
160
it will be approximately two years before the 25X1
Soviets will be able to fire a rocket using the guidance system
developed 25X1
~KONOPLOV was working on a wave length
of five to six meters an these objections were
voiced by KONOPLOV in order to find -fault with his "competitors".
The reasonfor this opinion on 50-centimeter waves may be due to
the fact that on initial firing tests the A-4 used a slot
antenna near the tip of the rocket which would have characteris-
tic loops, 'adjacent to the surface of the antenna, but not
directly back from the center...of t,lrae rocket.
150 Rockets of this type should be launched at an angle of 450
instead of vertically in order to have a sufficiently simple
method of control,,, With vertical launching, it is necessary to
have the antennas a distance of 2.6 kilometers from the launcher.
This means that once the stations are set up it is possible to
fire missiles in only one direction. With slanted, launching it
is possible to have the ground equipment adjacent to the
launcher and it would be easy to change the direction of firing.
Slanted launching would, of course, involve some type of
starting aid.
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
SECRET
Components
17. Whenever. peseibl , electronic oomponente such
as transformers, resonant cavities, special potentiometers,
etc.gwere.produced at Ostashkov, Vacuum tubes were obtainable
in sufficient quant&;ty.
The metal-ceramic tubes used were mostly o East
German manufacture.(Oberspreewerk - OSW). Soviet copies.of
these types frequently had leaks at the metal-ceramic seal.
h
ese caste
An attempt had been made at the factory in t
The boxes in which
they were shipped were marked with a pentagon:
.One type of tube, which was available in very
large quantitie's was a voltage regulator tube
laving five electrodes, the, STV 280/0, 60, 80, and 150.
This'is an old German design and was included in the circ^ui
developed at Ostashkov whenever a voltage regulator tube was
neededThe most popular tube manual in the Soviet Union is
one edited by 0URFINKEL.
.18, The magnetic amplifiers to be used in the rocket were units
taken out of a German direct current - three-phase converter
apparatus. They were designed for two 0 inputs of 0.5 m.a.
with a 2000-ohm winding resistance. A 1-ivolt, 500 cps volt-
agq is applied, and a DO output is obtained from two bridge
rectifier circuits. This output has a maximum value of 15
m.a. working into a 500-ohm load. Physicallythe magnetic
difficulty may be encountered, with these amplifiers
due to voltage breakdown between windings at high aititude.,.7
19. The small gyroscopes to be used in the rocket and in the
path simulator were at first obtained from German
Later exact Soviet copies were
delivered. These were probably made by the Institute fuer
Automatik and Telemechanik. The characteristic resonant
frequency of vibration of these gyros is approximately.
40 cps. It was found, therefore, that the gyros could not
be used to stabilize oscillation above 25 cps.
206
some components shipped to Ostashkov a ng exact soviet
copies of SCR 584 components. These parts included crystal
detectors, thyratrons, cathode-ray tubes for PPI and A-
scopes, 10 cm. d never saw any Soviet-built
magnetrons, but ey were being manufactured
there,
Ground Transmitter
21. The ground transmitter transmits a 600 inc. signal at a
power of 80 watts. This signal is produced as follows ZS-ee
Page 3-37-
A crystal oscillator, generating a frequency of 12.5 mc.,
feeds a frequency doubler, which uses Class C operation with
SECRET
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
a tank circuit tuned to 26 me. This frequency Is tripled
in a similar circuit tuned to 5 mc. Subsequent stages consist
of alternate amplifiers and frequency doubler stages until the
frequency is up to 600 mc. The stages operating at 300 mc.use
LD-12.lighthouse tubes, while the 600 me stages use LD-9 and
LD-7 metal ceramic tubes (German types, copied by the Soviets).
23. A signal is fed from the first 600 me amplifier to the ground
receiver,where it acts as local oscillator, Amplitude modu-
lation is applied to the second 600 me amplifier stage. Four
modulation signals are applied at this point: azimuth steering
command, elevation steering command, combustion cut-off command,
and the pulse for range-measurement. The modulation signals
are mime at the outputs of the command generators and applied
directly to the cathode of the LD-9 tube.
240. In each of the LD-9 and LD-7. amplifier stages the r-f power
input is applied to the cathode cavity, and the output tsk'en
from the anode cavity. Oee ;E for sketch of the
construction of these cavities Go-axial cable is used to
feed the signal from the last amplifier stage to the antenna,
which is a horizontal dipole in a 3-meter diameter parabolic
reflector. An alternate circuit, having one less power ampli-
fier stage, was also used successfully.
25. Initially it was planned to use a single frequency multiplier
stage to multiply the crystal frequency of 12.5 Ac bar .six,
producing a 75 me signal. However, it was found that an
additional amplifier stage would have been necessary, due to
too small a voltage output for such a frequency multiplier.
Ground Receiver and Veloeity Measurement
26. The receiving antenna is identical 'to the transmitting antenna;
ire,, a dipole in a 3-meter diameter parabolic reflector. The
carrier frequency of the received signal is 605 me , with
15 inc. side-bands, only the lower one of which (590 me ) is of
interest. (The carrier frequency actually varies with the
velocity of the missile due to the Doppler effect. This will
be discussed in a later paragraph.)
27. A co-axial cable is used to connect the antenna to the crystal
detector. In order to match the impedance of the line (60 ohms)
to that of the detector (150-300 ohms) a co-axial. "transformer"
is used, in which a 1/20 wave length stub is located 1/4 wave
length from the detector. A 600 me signal from the ground
transmitter is used as local oscillator and applied to the co-
axial line at the point at which the stub is connected. This
results in intermediate frequencies of 5 and 10 me after
detection (the difference btween 600, 605, and 590 me ). The
output of the detector is fed to two tank circuits, resonant
at 5 and 10 me respectively. These are d t pre-
amplifiers using 6AC and 6AG tubea
28. The circuitry from the dipole to the pre-amplifiers is all
located near the antenna. The output of the pre-amplifiers
are coupled to co-axial cables running to the mobile van
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
-7-
SECRET 25X1
where most of the equipment is located. Here the lines are
coupled to'two 5-stage IF amplifiers, using 6AB7 tubes, with
the automatic gain control fed back from the fifth stage to
the first by means of a 6X6 dual diode. The second section of
the 6X6 at the output of the 10 me. IF. amplifier is used as
detector for the range measurement pulse,, which is then fed
to the range measuring circuits.
29. The output of.the 5-me IF amplifier is doubled in frequency
by using a 6AB7 in Class C operation with a tank circuit in
the plate resonant at 10 me. The two IF signals are then
applied'to two grids of a 6A8 converter whose output feeds a
low-pass filter which cuts off at approximately 20 kc. Thus
the only remaining frequency is the one resulting from the
Doppler effect, indicating velocity of the missile.
30. This Doppler frequency is mathematically derived as follows:
Frequency of ground transmitter (600 me.)
Frequency of airborne transmitter T$ (605 me.)
Velocity of rocket V
Velocity of electromagnetic radiation G
Frequency received by rocket: 1 M
o
Airborne Receiver IF: f$ - t -FO
IF is tripled: 3f$- 3f~, 3FOZ
Frequency of Airborne Transmitter: A and side bands ~$ t 3 IF
but only lower side 'band is of interest.
Therefore: f , -3%t3f0-3fac 2fF5 -r 3f-3f0
Frequency Received on ground:
a - fa 2f6+3fa3;aGxl-
Vs.3foc+2G -3fo~ + 6.
$u~ C,, . is negligibly small.
collecting terms;~g-8 h
tzf$ ,
-2f313fp-~fO CO
These are mixed with fo in ground receiver to form intermediate
frequencies: +Zf~- 3fo t6fp-2F8
Doubled: = 2.fg-2o~~oc "2
These two. frequencies are mixed in a 6A8 converter, resulting
in the difference frequency:
a t6f~ %/
Of [2c5-2fa-2lVJ
This, then, is the frequency which appears at the output of the
low-pass filter, The signal is amplified by two stages of volt-
age amplification and a power amplifier which feeds the primary
SECRET
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
SECRET
_$_
of an audio-frequency transformer, The secondary is connected
to a special frequency bridge which has two outputs Zee
P a g e 35 7. (A) has constant phase, while (B) has a phase
angle of either plus or minus 900 with respect to A
( ). The
amplitude of '(B) is zero at the frequency at which the phase
changes. The 100,000-ohm potentiometer in the frequency
bridge is adjusted so that this zero point occurs at the
frequency corresponding to the desired missile velocity at
combustion cut-off.
31. The two outputs, (A) and (B), are amplified and applied to a
gesteuerter Gleichrichter" (controlled rectifier).. This is
essentially a bridge rectifier circuit, which receives two
sets df signals from transformer secondaries. The output is
taken from the center taps of these secondaries. It will be
DC voltage, with zero amplitude corresponding to the desired
combustion cut-off point., The DC voltage is fed to the com-
b
t
us
ion cut-off command generator through a low-pass filter
which cuts off at- approximately 300 cps, to reduce ripple.
32. The ground receiver, frequency bridge, etc. were designed b
.1 meters per second can be detected, as
slight variation of, this method to be--sed for
highly accurate location measurement. This could be used for
surveying (e.g.,,coastlines) with an airplane, or for air
reconnaissance to pinpoint targets,, The aircraft would fly
over a known fixed point, and from then on its velocity, as
measured by the above principle, is integrated and thus shows
the exact path. Of course, two separate ground stations would
be necessary if the aircraft flies anything but a straight
path. To pinpoint a target the aircraft would transmit a
signal when it is over the target,
Range Measurement
33.. The measurement of range is accomplished by transmitting a
pulse and comparing the time it takes the echo to return with
the time between the echo and the next 'transmitted pulse.
34. The output of a variable 40 to 60 kc oscillator is fed to a
pulse generator Z gee P a e, 36 W% The rectifier used in
the anode circuit of the.pulse generator is an aluminum
selenium rectifier and serves to damp oscillations after the
pulse is formed. A 3 to 4 microsecond pulse, having a repeti-
tion rate of 40 to 60 ke , is thus produced. The 40 to 60 ke
sine wave is also applied to two multivibrators which successive-
ly produce a 2:1 countdown. Their outputs are thus a 20 to 30
kc, and a 10 to 15 kc square wave. These square waves and the pulse
are all added together and applied to a trigger amplifier in
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
SECRET 25X1
-9-
such a way that only every fourth pulse will cause the amplifier
to conduct (See p a g e 6 J. This pulse, having a repeti-
tion rate of 10 to 15 kc., is then applied to the transmitter as
modulation.
35. The pulse is also applied to a third multivibrator. The returned
(echo) pulse is received by the ground receiver and fed to this
same multivibrator from the 10 me IF amplifier through a 6x6
detector. The multivibrator will be flipped one way by the
transmitted pulse and back by the returned pulse. A square
wave is thus obtained, with its length proportional to the
range measured. This square wave is coupled from the two plates
of the.multiVibrator tubes to the grids of two triodes whose
plate circuits include large (1 to 2 microfarad) capacitors. A.
DC voltmeter is connected between the two plates. It indicates
a voltage proportional to the difference in the periods of each
of the two conditions of the multivibrator. This indication is,
therefore, proportional to the range of the missile.
36. The time between transmitted pulses, at a repetition frequency
of 10 to. 15 kc , corresponds to a range of approximately 9 to
13 km. The voltage, V. will, therefore, start at a maximum
negative value, increase linearly to maximum positive value, at
the above-mentioned range, then drop sharply to the maximum
negative and start over again.
37. The frequency of the 40 to 60 kc oscillator is adjusted so
that the range at which the combustion cut-off is desired will
correspond to zero voltage in the fifth saw-tooth cycle. Assume
that the cutoff range is to be 45 km; Then the frequency of
oscillation will be set to 52.4 kd so that the time between
transmitted pulses (at a repetition frequency of 13.1 kc ) will
correspond to a range of 10 km. An operator watches the volt-
meter and throws a switch at the end of. the fourth saw-tooth
cycle, which closes the circuit to the cut-off command generator.
The voltage, V, is then added. to the velocity-indicating voltage,
resulting in the cut-off command being generated at the required
range and velocity. this system will prove to be 25X1
'very poor in operation, primarily because of the noise which will
accompany the echo pulse. this noise may frequently 25X1
be of sufficient amplitude to trigger the multivibrator so that
incorrect range readings will result. It would be better to use
some type of cathode-ray tube presentation, such as an A- or
J-scope, and to have an operator keeping track of the range,
since an operator can distinguish between the returned pulse
and noise. This circuit was essentially a development by Prof.
Theodor SCHMIDT.
Direction Finding
38. For direction finding in azimuth and elevation, four antennas
are used.. These will be designated right upper, right lower,
left upper,,and left lower. The distance from the right to
the left antennas is 17.5 meters; that between upper and lower,
3 meters. Each antenna is a dipole in a 3-meter diameter
parabolic reflector.
39. A 66-ohm co-axial line connects the left upper antenna to the
right lower, anc the left lower to the right up ,e , A switch
is connected to these lines ~ee P a g e 37 _fschema:kieally.
The switch may be considered a two-bladed vibrating type
with-an operating cycle as shown.
SECRET
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
40. If the missile is on the correct path the signal amplitudes
at all four switch contacts will be the same. If the missile
moves out of this path, a difference in signal strength will
be observed between the corresponding pairs of antennas. There-
fore, in the four-part cycle of the switch, a comparison of
parts I and III will indicate deviation in azimuth, and parts
II and IV deviation in elevation. The cycle is repeated 25
times per second; thus each position of the switch is maintained
for 1/100 second. The switch is driven by a 25 r.p.s. motor.
ketches of the actual construction of the switch and the co-
axial lines are shown on page 38A7
41. From the switch the signal goes through a detector, a 5 me
amplifier, and a second detector, which are identical to the
circuits used in the ground receiver. The signal after the
second detector will be a 4-section square wave with each
section having a period of 1/100 second. This square wave is
fed through a low-pass filter having a 1000 cycle cut-off
frequency to eliminate ripple without rounding off the corners
of the square wave.
42. The resulting signal is amplified in a special low-frequency
amplifier: one or two stages using 6AC7?s and one stage using
a 6F6. The amplified signal then goes through another rotat-
ing switch which is driven by the same 25 r.p.s. motor that
drives the first switch jee Pages 32 and 38 7 Bach part of
the switch has three positions. 1, 2 (ground, and 11 (no contact),
The positions during the /}-part switching cycle will be as
follows::
I II III IV
Switch A 1 N 2 N
N 1 N 2
The voltage across capacitors C3 and 04 will, therefore,
indicate the difference between alternate parts of the cycle,
and thus the deviation of the missile in azimuth and/or eleva-
tion. These voltages can attain a maximum value of plus or
minus 80 volts. They are applied to differentiating circuits
to produce a signal proportional to $ where $ is the
angle of deviation of the missile from the desired path. This
signal is then applied to the command 41 enerator for transmission
to the missile. he reason for the part of the signal
will be discussed in the section on rocket steering and stabili-
zation (paragraph 6o),,,7
Co~nd Generator
43. With respect to the combustion cut-off command, not
certain of the details of this circuit and can only discuss
the principles involved. The circuit was signed by Prof.
Theodor SCHMIDT.
44. Two DC signals, representing the distance and velocity of the
missile, are produced as discussed in previous paragraphs.
These signals have zero amplitude at the required combustion
cutoff values. It normally happens, however, that one of
these values will be attained before the other, so that the
missile would fall short of the target if the rocket engine
were cut-off then.
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
45. For this reason the two signals are added, so that the cut-off
command is produced when their sum is equal to zero. The
signals have positive slopes for increase in distance and
velocity, and the slopes are adjusted in such a way that when
the sum of the signals is zero, regardless of the value of
the individual signals, the missile will till hit the same
target. The circuit is designed for a maximum deviation from
the desired cut-off values of approximately plus or minus ten
per cent for distance, three per cent for velocity.
469 The sum of these two signals is applied to one grid of a 6A8
pentagrid converter. The cathode of this tube is biased so
that no plate current will flow until the grid potential is
at least zero volts. The output of a 6 kc L-C oscillator is
connected to another grid of the 618. Thus, when plate
current is drawn, a 6 ko output signal is obtained. This,
combined with the other commands, is fed to the ground trans-
mitter as amplitude modulation. After the 6A8 has conducted
for approximately one-tenth second it is cut off by a time-
delay relay.
47. The time used in transmission, generation of command, etc., is
predictable, and, therefore? introduces no appreciable errors.
A much larger and less accurately predictable error is caused
in the extinction of combustion in the rocket engine. The
exact amount of fuel left in the lines between the shut-off
valve and the engine, and the burning time of this fuel,can-
not be accurately predicted and this, therefore, is the major
error to be taken into consideration,
48. The azimuth and elevation command circuit was developed by
Dr. Franz LAME. ~
49. Two identical command, generators are used: one for azimuth,
one for elevation. Basically the generator consists of an
R-C oscillator using a 6X7 tube (similar to US 6K7 with
linear characteristic). One of the resistors in the R-C
circuit consists of the variable plate resistance of a 617
tube, whose grid potential is controlled by the azimuth (or
elevation) signal from the direction finding equipment. The
maximum variation of this grid bias is from cut-off to zero
bias.
50. By means of the grid bias variation the frequency of the R-C
oscillator is varied about a center frequency of 2.5 kc
for the azimuth command generator, and 3.7 kc for elevation.
The maximum frequency variation is plus or minus seven or eight
per cent.
51. A reactor tube (Blindr8hre) was also used in this circuit
The frequency control
in the R -O was very complicated; an L-C oscillator
would have been simpler and more stable.
52. The azimuth and elevation command signals are combined in a
resistance network and the combination amplified by a 6P6
power amplifier.
53, not remember how this signal is combined with the
combustion out-off command signal and the range measurement
pulse, but all these signals are jointly amplified by a 6L6
(Soviet 6B3) tube and then applied to the cathode of an LD-9
tube to modulate the carrier of the ground transmitter.
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
CRf
-?12-
Airborne Receiver and Transmitter
54. The airborne receiving and transmitting antennas consisted of
dipoles with reflectors. These were to be placed either in-
side-a. nonmetallic section at the bottom ends of the rocket
fins, or in the area between the fins and the jet stream.
55. A 60-ohm co-axial line from the antenna leads into an imped-
ance matching section, where a 605 me signal, to be used as
local oscillator, is also introduced. A crystal detector thus
produces a 5 me intermediate frequency, which is amplified in
an IF pre-amplifier and sent on a co-axial cable to the
electronic apparatus, which is to be located below the fuel
tanks near the rocket combustion chamber.
56. Here the signal is amplified by an IF amplifier using 6AG5
tubes, with feedback for automatic gain control. The band-
width.of the IF amplifier is approximately 0.5 me. The
second detector is a 6X6 dual diode. The low frequency
command signals are then amplified by a 6AG5 in whose plate
circuit are three tank circuits. These are tuned to 2.5 for
the azimuth command, 3.7 for the elevation command and 6 ke
for the combustion cut-off command,.
57. Each of these tank circuits is coupled to another 6AG5
amplifier whose output is fed into a. discriminator circuit.
This results in a positive or negative voltage which corre-
sponds to the given command.
58. A 5 me IF signal Is taken off before the second detector and
fed to a frequency tripler. This is a class C operated tube
with a special plate circuit which is resonant at 15 me , but
shunts 5 me to ground. A bandwidth of approximately 1 me
about a center frequency of 15 me is thus passed to a 15 me
IF amplifier. Its output is fed to the transmitter circuit
where it is further amplified and applied as modulation to
the LD-11 transmitting tube.
59. The transmitter uses a 12.6 me quartz crystal. This frequency
is tripled to 37. 8 me and then doubled four times to attain
a frequency of 605 inc. The first four stages of this multi-
plie3? use two 6j6 tubes. Succeeding stages use LD-l's work-
ing into resonant cavities. The second LD-1 puts out'a 0.5
watt signal into an LD-1l amplifier cavity. This is coupled
into the cathode cavity of the final stage, also an LD-ll.
The 15 me modulating signal is applied to the grid of this
tube, and the transmitting antenna is coupled into the anode
cavity. A 7?-watt signal is thus sent out to the antenna.
Rocket Steering and Stabilization
60. The outputs of the command discriminators are DC voltages,
the polarities of which indicate the desired direction of
the command. These voltages are applied to magnetic amplifiers,
which also receive signals from the-stabilizing gyroscopes of
the corresponding axes. The primary AC voltage applied to
the magnetic amplifier is 40 volts at 50 cps0 A bridge
rectifier in the secondary produces a DC voltage, the polarity
of which again corresponds to the direction of command.
SECRET
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
MOB"
-13-
1. This DC voltage controls the position of a coil in a magnetic
field. This coil is wound on an iron core and,as it moves
changes the direction of a small nozzle ZS-ee Pa g a 39 ~.
The direction of the spray controls the up-and-down movement
of a "Steuerkolben" (control piston). This piston is on a
common shaft with two smaller ;pistons which act as valves
to open one and close the other two lines which carry the
operating fluid under pressure. These lines go to the two
ends of the cylinder which contains the main operating
piston, whose shaft is coupled to the rudder. As pointed
out previously, the guidance system of G-l was never:
actually installed in a rocket. For this reason, the steer-
ing mechanisms discussed here were merely proposals,, and
frequently alternate systems were proposed without a final
decision on which is to be used.
62. Three-alternative fluids were proposed to operate the steer-
ing mechanism: alcohol, compressed air, and hydraulic oil.
Thee disadvantage cited for alcohol is that it would tend to
soak into the electrical insulation and thus destroy its
insulating properties. It would be satisfactory to use
alcohol for actual operation however, since in the time
of one firing of the rocket it would not have a chance to do.
appreciable damage. Compressed air is compressible, and
therefore apt to oscillate. It would also be necessary,
when using air, to use an oil-soaked felt piston ring for
lubrication of the cylinder walls, and regular piston rings.
Nevertheless, compressed air is the most likely 25X1
to be used. The time cons ant of this actuation mechanism
was expected to be 1.0 to 20 milliseconds.
63. The transmitted steering Comm ds correspond to the deviation
angle a plus its derivative The derivative is included
in. the signal to reduce the o ershoot as the missile approaches
and goes through the correct path.
64. Stabilizing "Markgraf Kreisel"ee Path Simulator description
Sri -'Page j7, gyroscopes are CO be used in each axis of the
missile. The gyro itself is small so that its characteristic
frequency of oscillation will be much higher than that of the
guidance system of the rocket. This type of gyro was called
the "rasende Wailnuss" (racing walnut). Its synchronous speed
is'approximately 30,000 rpm.
65. The voltage corresponding to the gyro's angle of precession is
taken off a special center-tapped potentiometer made of resist-
anc,e wire wound on an anodized aluminum bar. The moving non
tact'consists of a very light pressure (low friction) platinum.'
wire loop. The voltage taken off here is proportional to the
angle _' ;between the path of the rocket and its longitudinal
axis, plus its derivative dVY/dt. This signal is applied to
the magnetic amplifier whose output actuates the .rudders.
66.. Approximately one-tenth of the transmitted f+Sf./4t command.
signal is applied to the "steering coil" of the gyroscope.
This is necessary for the. following reason: Before firing,
the capacitor in the Markgraf circuit is short -circuited. At
the instant of firing, this short circuit is opened so that
the gyro will-try to maintain the position it has at this
moment. Since this position may deviate slightly from the
SECRET
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
desired path, the signal is applied to turn the axis of the
gyro towards the correct position. The derivative of P, is
not necessary for this operation it is included only because
it is contained in the transmitted signal.
67. The "Drehmagnet'O (turn magnet), which is controlled by the
output of the magnetic amplifier, is copied from a design by
the Askania company (German). It consists of a bar which is
turned by an electromagnet, and coupled to the spray nozzle
of the control piston. An inclined surface, which moves with
the main operating piston, is set up to tilt the housing of
the turn magnet jSee Page t so that the main piston will not
move to the and of its travel for each command signal; I. e.,
so that maximum rudder angle will only result from maximum
command signal.
68. Four rudders are used; two in the Y-axis and two in the Taxis.
They are designed in an LAshepe fee Page 40 7 so that, as the
exposed sections gradually burn off, the center of pressure
will remain close to the fulcrum of the rudder. The rudders
are to be made of graphite.
69. A signal from the Z axis gyro will cause the Taxis rudders
to deflect to opposite directions, so as to compensate for
twisting moments of the rocket. On the original A=-k,trim
tabs on the fins were used to compensate for any constant
twisting moment. These, however, were to be omitted on
the G?1 modification.
,antenna Follow U-o System
70. Six antennas are used for the G-l guidance system, as described
previously. Each antenna consists of a dipole in a 3-meter-
diameter parabolic reflector. The reflectors used were made
of solid sheet metal, but it was recommended that they be
punched full of holes to reduce wind resistance, The maximum
wind velocity at which the equipment has to operate is 15
meters per second, since the rocket cannot be launched at
higher wind velocities. The antenna characteristics were
such that a sector of 200 was Included between zero points,
and l00betveen half-power points.
71.
Direction finding antennas are set up in two vertical pairs
17.5 meters apart. The transmitting and receiving antennas
are set up on tripods between the direction-finding antennas.
All six antennas are adjusted for the correct flight direction
of the missile. The angle of elevation of the antennas is
controlled by a selssyn system. The selsyns, used to indicate
the position of the antennas, have a speed of one revolution
per ,50 of antenna angle. For the direction finding antennas,
two. extra selsyns are used for higher accuracy. These have
a speed of one revolution per 30. The selsyns for the right
direction finding antennas act as selsyn generators and thus
control the positions of all the other selsyns. The error
signals from the selsyns are hd to a A?controlled rectifier"
similar to the one used at the output of the direction find-
ing receiver. The DO output of the rectifier is applied to
a system of pistons which is very similar to the one used to
actuate the rudders in the missile. It consists of a "turn
magnets which changes the position of a nozzle that Is used
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
1
15
to push a control piston. This, in turn, is on a common shaft
with a double piston which acts as a valve, controlling hydraulic
lines to the main operating piston that controls the position of
the antenna. A. special circuit is used at the output of the
controlled rectifier for the signal which controls the position
of the direction finding antennas. This circuit consists of a
network of resistors arranged as follows: The command signal
is applied to both the right and left direction-finding antennas.
At the same time, the DO voltage, corresponding to the error signal
from the left antenna, is applied to both direction-finding
antennas, but in opposite polarities. Thus the error between
the two pairs of direction-finding antennas is reduced to a
minimum.
72. Initially a similar system was to be designed by the Institute
for Automatik and Telemechanik in Moscow using amplodynes to
replace the hydraulic system used here.- l- a finished
design was never obtained, they may eventually
end up using an aznplidyne system. The viscosity of the oil
used in the hydraulic system becomes a problem in cold weather.
It was frequently necessary to add a large percentage of kero-
sene to keep the equipment operating.
73? The selsyns used were German types rated at 40 volts, 500 cps.
They were approximately y centimeters long and 5 centimeters
in diameter. The selsyn generators, used for the right
direction finding antenna, were approximately 8 to 9 centi-
meters in each d.imensio These were all German units produced
during the r ar _ l o Soviet selsyra,s, but they were
rated for 50 ops. operat on and proportionately bigger. They
were exact copies of U. S. selsyns. They were supplied by the
institute for Steuering (guidance). which also sent a number
of amplidynee to Ostashkov.1
25X1
25X1
74. When firing a missile, the following sequence of operations
takes place: a *program' motor drives a number of came which
open and close switches, necessary for the initial operations
to fire the missile-, after ten seconds this motor is stopped.
The rocket is fired vertically,an.d,until its elevation angle,
as seen from the antenna, is 200p no guidance signals are trans-
mitted. Instead the position of the antennas is controlled
by commands from the direction-finding receiver. When an
elevation angle of 200 is obtained, a relay disconnect t:s the
direction-finding receiver and connects two selsyns which are
driven by the program motor, At this point the program motor
starts to raun again. From an elevation angle of 200 to 42.50
the position of the antenna controls the missile. Any error
between the antenna and. 'the missile is transmitted as a
command signal to the missile for correction, At the elevation
angle of 42.5? the program motor stops, since it i.s cesired to
hold the rocket at this elevation angle until combustion cut-
off. When the combustion cut-off command is transmitted
another relay is actuated. and the antennas again take the
command from the direction-finding receiver. This is main-
tained until the end of radio contact,
75. Thus, during the first fourteen seconds, i. e., until the rocket
is at 200 elevation, the antennas follow the rocket. From 200
to 42.50, a time of approximately 26 seconds, the rocket is
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
SECRET 25X1
-16--
controlled by the antenna position. This continues for another
twenty seconds, at which time the combustion is out off. After
this, the antennas again follow the rocket, since It is im-
possible to control the rocket when there is no combustion.
76. The selsyhs driven by the program motor have the same speed
as the two selsyns used for the direction-finding antennas.
77. .The Soviet servomechanism capabilities are generally good.L
have no basis for judging their servo development abilities.
Path Simulator
78. The path simulator is an analogue computer which is designed
to simulate the aerodynamic properties of a rocket, as well as
its characteristics in responding to commands and to the stabi-
lizing effects of its gyros. It could be modified' to be used
in the analysis of ordinary aircraft as well as all types of
rockets, but the unit to be discussed here was designed es-
pecially for the 4-1 modification of the A-4 rocket. For this
reason,many of the components are Identical to the ones designed
for the G--1.
79. The chief designer of the "Bahnmodell", as the path simulator
was designated, was Dr. Hans HOCH. He had done work on such
an instrument in Germany in 1946, and brought a primitive
design with him to the USSR. By the middle of 1948 the first
unit ofa new design was completed, to be used in the labora-
tory at Ostashkov. HOCH's closest co-worker on this project
was Gerd MMLER.
80. In December 1948 and summer 1949, two more units were completed.
and delivered to Moscow. These early instruments were suc-
cessively improved, but they still had frequent breakdowns.
They used DC amplifiers which were replaced in later models by
AC amplifiers
81. In 1949 and 1950, five improved units were built. Of these,
the first and second went to VII 88, and the third went to an
institute in Moscow whose address is Post Office Box 906.
this is the institute to which HOCH,
0PpER, STODPE, et a1 were sent in November 1950, and where
BUSCHBECB is also located. It has been established beyond
reasonable doubt, that the address of this institute is P.O.
Box 908, not 906j.In winter 1950-51, approximately three
82. Work was done at Ostashkov on a path simulator to simulate
the three axes of the rocket instead of only one. This unit
more units were built for a destination not know,
was never completely finished
In principle its operation was identical to the two-axis
model.
83. Before discussing details of the Bahnmodell, it would be
appropriate to describe the ballistics Involved. The follow-
ing angles are of importance Ztt'e Page gip:. -7--
e angle between rocket and desired course
*tangle between rocket axis and actual course
SECRET
25X1
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
-l7-
10 angle between rocket axis and redder
77 angle between actual course and desired course
84. Assume that initially the angle E is between three and six
minutes. A steering command will be transmitted to the
rocket causing the rudder to be deflected. This will cause
the whole rocket to turns but it will only gradually change
the direction of its flight'since there is very little air
resistance. Gradually,, however, the flight direction will
become parallel to the rocket axis. Thus the rocket will
again approach the desired, course; I. e., will approach zero.
The following course of events takes place:-
+ results, In leering command transmission
ZT
results in rudder control from stabilizing
gyro in rocket
Both together cause change in f-'
110 causes change in
OC causes change in 7
71 causes change in E
85. The heart of the path simulator, as well as of the G-l
stabilization systems is the *Markgraf Kreieelf?, a small
gyroscope in a special circuit, which operates in such a
manner that the angle of precession indicates a change in
external forces, but does not return to zero when the forces
stop changing. Thus the indication is proportaional to the
force plus the differential of the force. In principle the
circuit for the Markgraf Kreisel consists of a center-tapped
potentiometer, a large capacitor,and a movable coil on a bar
magnet core. A DC voltage is applied across the potentio-
meter; the movable arm is at center when the precession angle
is zero. As the gyro precesses,, a voltage appears between
the center tap and the movable arm. This voltage is applied
to the capacitor and coil in series, resulting in the neces-
sary spring action by movement of the coil which is attached
to the frame of the gyro. When the precession stops charging,
the capacitor charges to the same voltage as-that between the
center tap and the arm of the?potentiometer, so that the
current in the coil becomes zero and no force exists to return
the precession angle to zero. The precession angle indicator
thus remains at a position which is proportional to the sum
of the applied force plus the derivative of that force.
86. In the actual Bahamodell,two turntables are used. The gyro
is mounted on the upper turntable which, in turn, sits on a
ball bearing on the lower turntable. The lower one is also
mounted on a ball bearing. The following angles will again
be of importance in this discussion:
E angle between rocket and desired course
Q'e, angle between rocket axis and actual course
angle between rocket axis and rudder
angle between actual course and desired
course
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
The angular position of the lower turntable corresponds toy.,
The relative angle between the two turntables thus indicates
c.'C . Steering commands and the effect of one angle on
others are simulated by rotation of the respective turntable
which causes the gyro to precess. Thy precession signal then
corresponds, as explained above, to OC + -d <
87. The rotation of the turntable is accomplished by a steering
coil. This is a movable coil which operates in a very uniform
magnetic field. When a DC current flows through it, it moves
and thus turns the turntable. The circuits used in connection
with the mechanical parts are largely the same as those used
in the actual missile guidance; omitting, of course, the high
frequency parts used for, radio transmission.
88. The gyro in the Bahumod.ell acts exactly as the stabilizing gyro
used for each axis of the rocket. The mass of the rocket is
represented by weights placed on the turntable while electro-
magnets placed at the turned down edge of the turntable simulate
inertia by inducing eddy currents in the turntable.
89. A *program" apparatus is used in the Bahnmodell to simulate the
predetermined varbables such as:: variation in air density as
rocket increases in altitude, reduction in weight of rocket
as fuel is expended, initial changes in direction while rocket
changes from vertical to desired course, etc. This program
apparatus consists of a number of came, one for each variable,
rotated by a motor. The came act on potentiometers which apply
a signal to the amplifier of the corresponding steering coil.
90. Three sets of signals are applied to the magnetic amplifier
which drives the upper steering coil., and the
preset initial steering program. These are mixe by the magnetic
amplifier which is the same as the magnetic amplifier used in
the rocket to produce the signal for the rudder actuation system.
The output of the magnetic amplifier corresponds to the rudder
steering command signal. It is applied to a two-stage amplifier
and a time constant circuit which simulates the time constant
of the rudder actuation. The resulting signal thus corresponds
to f . the rudder angle. This signal is fed into a pair of
Soviet 6n3 tubes in push-pull, whose plate load consists of
the two parts of the steering coil. The rudder angle is thus
applied as a force to the axis of the upper turntable. This
responds gradually, in accordance with the mass and inertia
of the rocket so that the angular position of the upper turn-
table always corresponds to OC o the angle of the rocket
axis. The AC signal representing CC is fed to a 2-stage
amplifier whose output controls the steering coil of the lower
turntable; i. e. 7'1 . The resulting AG 'Q signal is applied to
an integrating gyro, whose output Ia Jf7 oL E . This gyro
operates as follows: The y signal drives a steering coil
which acts as a force on the gyro,causing it to precess. Since
the precession angle is proportional to the product of the
force and the time over which it acts, it will indicate the
integral of 7 , which is the angle .
91. The G signal is fed through a circuit similar to the low
frequency sections of the direction-finding receiver, command
generator, and the airborne command receiver. The output signal
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
of this is proportional to E- 016 . This is fed back to the
magnetic amplifier whose output 3s applied to the upper (oC )
steering coil. A small fraction (ca. 1/10) of this signal is
also applied to another steering coil in order to apply a pro-
portional force to the axis of the gyro to effect a permanent
change in its direction. The reason for this is explained in
the paragraph on rocket steering and stabilization.
92. Physically, the Bahnmodell is in a cabinet resembling a desk.
The center section houses controls and measuring instruments
(one meter to indicate each angle). The left section houses
the turntables with their indicating Instruments, while the
electronic and magnetic amplifiers and the "coefficient cams"
are located in the right section. The 3-axis path simulator
was quite similar to the single-axis model, except that, of
course, all equipment was tripled. Its purpose was to simulate
the interaction between axes.
93.I know of no other Bahnmodell developments in the USSR.
94. This was one of the three major projects which were developed
only on paper. No experimental or laboratory work-was ever..,
done on it. The project was worked on during the year 1949,
It was presented at a conference in Moscow at the end of 1949.
No German attended this meeting.
95. The missile was designated R.44. It was to have a range of
3000 km., with an a~curacy of fifty per cent hits within 1/1000
of the range (i.e.,3 km.). The approximate weight was 75 metric
tons with a 300 kg. warhead. (O not sure that this is the
correct warhead weight.) After combustion cut-off, the war-
head,which was cylindrical, was to separate from the rest of
the missile. A cylinder was considered to be the most advan-
tageous shape for the free flight.
96. The missile was to be in the form of a cone, approximately 25
meters tall with a base diameter of 3 meters. It was to be a
two-stage rocket, with the separation occurring by means of
an internal program time mechanism at an altitude of approxi-
mately 60 km. Combustion cut-off of the second stage was to
occur at a distance of approximately 280 km., which was the
expected maxima.- range of the radio control. The velocity at
this point would be approximately Mach 10. The peak altitude
attained during the flight was to be 100 km.
97. The guidance system for the R-14 was to be the same as the one
designed for the 0-1, with only minor modifications. The
antennas on the rocket were to consist of a number of dipoles
mounted on four pieces of pipe which acted as co-axial lead-
in. These pipes were in the form of a 90-degree arc, mounted
in two concentric pairs on opposite sides of the rocket engine
exhaust. This arrangement was mounted on the base of each
stage of the rocket.
98. The power plant for this rocket was to include a 60-atmosphere
engine for the first stage, and a 15-atmosphere engine (with a
long high-altitude nozzle) for the second stage. Earlier plans
had called for four A-4 engines (15-atmosphere) to be used for
the first stage, but this was dropped in favor of the
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
SSCR
- 20 -
single high-pressure unit. It was also dhbated at one time
to use a bundle of five complete A-4 rockets. Your of these
would fall away after the initial stage, and the fifth would
continue on to the target. The main difficulty expected with
these multiple engine systems., is that normally every tenth
engine misfires; therefore, in a five-engine system, every
other launching would be a failure.
99. The steering was to be accomplished by one of two systems:
(a) to use small jet nozzles at various angles, driven by
the compressed gas output of the turbine; (b) to mount the
rocket engine in a ball and socket joint, or, on gimbals,
and steer the whole rocket by changing the direction of the
thrust. For the second system, small jet nozzles would still
be necessary to prevent rotation about the rocket's longitudi-
nal axis. The steering actuation system was to be the same
in principle as the one designed for the Q-1. The capacity
of the system would, of course, have to be somewhat larger.
100. The rocket was to use integral feel tanks for both stages.
It was never decided whether to put the second stage engine
inside the upper first stage fuel tank, or whether free space
should be left between them. Since the electronic and gyro-
scopic apparatus was to be located around the top of the
second stage engine, it would be necessary to seal it if it
is to be immersed in fuel,
101. At an altitude of approximately 10 km., a ring was to be
shot off from around the base of the first stage. This acted
only to keep the center of gravity low at the start. A
problem which was never finally solved was the question of
how to ignite the second stage engine. The first stage was
to be ignited by small rocket twirlers placed in the combus-
tion chamber of the engine.
102. One question was brought up and never settled because no
experimental work was done on this project. This was the
question of what happens to the 50-cm. waves in the extremely
high altitude through which the missile is to be controlled.
At these altitudes the flight path will more closely approx-
imate an ellipse than a parabola.
103. In connection with this project, GRONTRUP developed plans
for an underground launching site for the R-1k, as well as
for the Q-1. The plan was developed further to include an
entire subterranean assembly plant designed so that final
assembly would take place right at the launching site, which
would be a vertical shaft, 5 to 6 meters in diameter and
about 30 meters deep. A large network of tunnels connecting
to this, shaft were planned for the storage of parts and the
sub-assemblies. It was also planned to have the ground station
for the guidance system on a circle of tracks having a radius
of 25 to 30 km,, so that the missile could be fired in any
direction. While the idea for this underground factory and
launching station was (JROITTRUP's, JA7IKz and members of his
group carried out the design and made the drawings for it,
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
SECRET
-21-
,SUPERSONIC PILOTLESS AIRPLANE
I.04. This project, designated R-15, was also worked on during the.
year 1949., It was another one of the projects which were
carried out only on paper with no experimental work being done
at all.
.105. The airplane was designed to be approximately 15 meters long
with a wing span of 5 meters. not certain of the form
of the wings. The span of the horizontal stabilizers was
to be 1 1/2 to 2 meters; they were triangular in shape.
Steering was to be accomplished'by the use of ailerons, with
no rudder. Elevators were attached to the horizontal stabi-
lizers. The fuselage was to consist of two arts, both
approximately 60 centimeters in diameter. See Page 41 . *J
The forward part was to be lower than the a t part. Fuel was
to be contained in both parts, while the warhead, electronics,
and gyroscopic equipment were to be housed in theldwer for-
ward section.
106. An A-4 rocket mounted directly behind the lower portion of
the plane was to be used as a starting aid to launch the
missile vertically. The engine for the plane operated on
the principle that at supersonic speeds the incoming air
would be compressed as the shock wave is formed. At the
point of maximum compression, fuel is added and ignited in
a number of combustion chambers arranged in a circle. The
fuel is pumped into the combustion chambers by a gasoline
engine.
107. The range of. the rocket was to be 6000 kilometers, and it
was to fly at an.altitude of 20 to 30 kilometers. When the
starting rocket is cut off the plane would be. flying at a
velocity of approximately Mach 2. This occurs at a range
of 12 to 15 kilometers. The warhead was to have a weight of
300 kilograms.
108. Various schemes were discussed for guiding this airplane;
one was to use a gyroscopic horizon,which involved a gyro-
scope acting as a pendulum having a period of 86 meters,
and thus always pointing to the center of the earth as a
reference. Another scheme was the use of an optical horizon;
this, however, would involve serious inaccuracies. These
two schemes were discarded as being too complicated to obtain
the required accuracy. The system which was finally pro-
posed was a hyperbolic navigation system. Oswald SCHMIDT Jhad
done work on wave propagation around the earth at frequencies
of' 0 to 30 megacycles. He had discovered that accuracies with-
in -five kilometers were obtainable for transmission around
the earth; The optimum time for the transmission. of these
waves was at twilight when the ionosphere is bent down and
will guide the waves around the earth. It was proposed to
use a system employing these frequencies to be transmitted
by a keying transmitter and two transmitters for producing.
the navigational hyperbolas. A third transmitter would be
used for determining the range of the plane, and for trans-
mitting a drop command signal. An over-all accuracy obtain-
abl'e with this system would be 20 to 30 kilometers, on the
basis of SCHMI:DT's measurements. It was planned to use pulse
-SECRET
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
SECRET
--22-
transmission,as this would be more difficult to jam.
l09J~consider transmission at this frequency extremely important,
and recommend that the United States carry on experiments at
these frequencies for long-ra a transmission, if such work
has not already been done. he Soviets expressed great
interest in this system and asked for more detailed reports
after the main report on the R-15 had been turned over to thems.7
angeffort be made by the United
States to monitor signals in those frequencies.
110. It was proposed to use transmitters having an output power
of 10 to 20 megawatts, with 10 microsecond pulses, at a pulse
repetition frequency between 10 and 50 pulses per second. The
rise time of these pulses was to be one microsecond. By delay-
ing the transmission of the pulses of the second transmitter
in accordance with a given code, it would be possible to cause
the plane to fly in curves in order to hide its target. It
would be also possible to use additional transmissions of pulses
at various adjacent frequencies in order to confuse the enemy's
Jamming efforts. The airborne. equipment was to consist of two
receivers, one for each frequency of the two navigational trans-
mitters. Thus,the time of each transmission is compared and
commands are applied to the ailerons to steer the plane along
the correct path. Gyroscopes are used to keep the plane horizon-
tal and going straight ahead. The velocity and altitude of the
plane are preset so that the final falling pattern maybe cal-
culated. At the time of the drop commend, the Angs and possi-
bly all other parts of the plane could be shot off and the warhead
alone would fall toward the target. .
111. It was estimated that the temperature at the surface of the
plane would be approximately 1500 0. Therefore, it would be
necessary to use a fuel that could stand this temperature.
The electronics apparatus was to be cooled by insulation from
the outer surface, and by water which would steam at approxi-
mately 40 degrees centigrade due to the low pressure at which
the plane flies. It was planned to use two wire antennas, one
wave length long, attached to the top and bottom of the
vertical stabilizer and flying behind the airplane.
112. The completed project was presented to the Soviets at a meet-
ing around Christmas 1949. This meeting was not attended by
any Germans. Early in 1950 the more detailed report on radio
navigation was completed.
ANTIAIRCRAFT ROCKIT
113. During the early part of 1950 the group at Ostashkov was given
a project to design an antiaircraft rocket, to be designated
R-10,$ This project was to be worked out only on paper; there-
fore no experimental work was done on it at Ostashkov, and all
design work was in the form of proposals.
114. The rocket to be used for this project was almost identical
to the German Wasserfall. The only change from this German
rocket was that it was to have two wings instead of four.
This change was debated by the Germans at great length.
steering by remote guidance would be far
simpler four w ngsrAere used. With only two wings, it will
SECRET
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
SECRET
-23-
be necessary for the rocket to make 900 turn about its
longitudinal axis in order to obey commands which first
require a change in the Y - axis, and then in the X - axis.
However, some of the other. Germans, principally HOCH, advocated
the 'use of only two wings; this plan was finally adopted.
115, A number of different guidance principles were discussed,
the first and simplest was one designated "Hund" (dog).
This is essentially a system in which the missile follows the
target. It results in a.large radius of curvature of the flight
path at the beginning of the flight and a very short radius just'
before the intercept is made. The second principle discussed
was called "Schielender Sound" (cross-eyed dog). In this system
the target'is illuminated by ground radar and/or a homing instru
ment is installed in the missile in such a way that a constant
angle is kept between the flight path of the missile and t}
target. The misoile is fired towards the initially-calculated
point of intercept, and by me i.ntaini.ng this constant angle the
intercept would be made. Another principle is that of a target--
covering type of guidance which is probably the simplest ground.-
controlled flight and involves the use of one radar which locates
'the target and on whose beam the missile will fly _ advocated
this system to be used with a large number of smaller rockets, 25X1.
which must be fired, directly into the beam of the radar rather
than launched. vertically.
116. The system decided. on was called "Hund auf der Kugel" (dog on
the sphere). The reason for this designation is that if.the
flight path of tho rocket and the target were to be projected
onto a sphere whose center was at the launching site, then a
curve similar to the "Hand" flight path would be obtained. In
actual flight, however, the path of the missile has a short
radius of curvature at the beginning and a long one at the end
of its flight. This is desirable for accurate interception.
117. The guidance system for this rocket was to involve the use of
two type SCR 584 radar units. One of these was to act as target
locater while the other followed the missile and would give
eomi nds to the missile until it intercepted the target. The
radar equipment was to be modified in such a way that the
antenna reflector would be mounted on gimbals instead of the
,suspension used on the original type, which permits movement
only in polar ooordinatds, This would simplify .movement of
the reflector through the vertical position.
118. Another small modification to be used in the command unit was
an attenuation in the transmitter wave guide to reduce the out-
put power while the missile is so close that its detectors
might be burned out by the high energy of'the radiation. This
attenuation was to be accomplished by inserting a section of
carbon wall into the wave guide. This section would be auto-
matically shortened during the flight of the missile by slid-,
ink; a metallic section inside the carbon wall.
119. In'.order.to achieve the flight path described above, a computer
was designed to cause the command unit to follow the locator.
This computer was developed by Dr. MOLLWO and Werner, MUELLER.
It involved a fairly complicated system of selsyne. 25X1
In principle it operates .
25X1
SECRET
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
as follower Selsyn generators in the locator indicate the
angles of position in the "I9? and 'Te axes, The signals from
these selsyns are compared with similar signals from the
command unit. The distance between the target and the missile
is obtained by similar means. A voltage which is a function
of the difference in angle as well as of the rat.ib of target
distance to missile distance is applied to a servomotor which
drives the command antenna. By this means the beam inter-
secting the missile will always follow the beam intersecting
the target but the difference between them will b3 reduced
as the target approaches the missile. It would be necessary
to use a homing system for the final path, and a proximity
fuse, but these items were not a part of the project. The
proximity fuse would possibly fire at a distance of 30 meters
from the target,
120. The accuracy of the SCR 584 is plus or minus five minutes.
The maximum accuracy obtainable in the selsyn system between
the two radars would be plus or minus ten minutes, while
the error in the rocket could add up to another ten minutes.
At a 30 kilometer range, all of these errors would total
approximately 300 meters. An error of this magnitude would
involve a very complicated homing system to insure inter-
ception. The-missile itself was to have two antennas arranged
perpendicular to each other. The rocket receiver would use
a crystal detector for each antenna, to be followed by a low
frequency amplifier stage. The purpose of having two such
antennas is to indicate rotation of the missile about its
longitudinal axis.
121. Three rudders were to be used with the two-winged missile.
This makes it possible to keep the rudders out of the turbu-
lent stream behind the two wings. All three rudders were to
be used for alignment about the longitudinal axis. Two of
them were to react to steering commands and to commands from
the gyro stabilization equipment. It was planned to use gyro
stabilization in each axis, but a proposal was also included
in the final report to use instead an acceleration indicator
which would react to vibrations and other accelerations. To
actuate the rudders, It was planned to use a system similar
to the one designed for the G=1, using compressed air.
Spherical compressed air containers were also to be used at
100-atmosphere pressure to feed fuel into the engine,
aircraft rockets, using a large number of rockets, at
the orginial project meeting in 1950, the Soviets were
very obvious about not discussing this project and passed
over it quickly, this may have been for
security reasons, the Soviets were already working on
such a project.
the target-covering principle for anti-
123. Several times the Soviets suggested that the Germans
develop an antiaircraft rocket to shoot down enemy rockets.
The Germans, however, consistently turned them down on this
idea, claiming that it was an impossibility.
124. I the effective range of the Wasserfall rocket
would be 30 kilometers, and that the weight of the warhead
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
SECRET
-25-
was to be approximately 500 kilograms.
TEST STANDS
125.
This was the test stand on Gorodomlya Island. It consisted
of the test stand itself on the edge of a swamp with a con-
troller bunker adjacent to it. In the bunkers were located
all the necessary controls and test instruments. Below it
was a pump for water cooling of the stand, The controller
could watch the combustion chamber through a small window
built into the concrete walla
126. The test stand was used primarily for experiments on cooling
exhaust gases from 2500 to 500 degrees.C so that they could
be used to drive the turbine. Fuel and alcohol were injected
.into the jet stream for cooling. The fuel to be used in the
experiments was stored near the bunker. Across the road
from the "test stand there was a small building in which liquid
oxygen was produced. The process used was that of the Lind
liquefaction plant. The oxygen produced by this method was
80 to 90 per cent pure. Some of the oxygen produced here
was also used fortivlding purposes on the island, and some was
sent to neighboring towns for similar purposes.
127. A short distance from the test stand, adjacent to the main
north-south road, another small building housed offices and
storage of material for the test stand.. The whole area around
these buildings was #enced in, and after 1950 only authorized
persons were admitted,
1281P, there wab a -test stand located next to the air- 25X1
field at Factory 88 for testing Wasserfall missiles.
it* 25X1
*
129.. In 1947, JAFFKE surveyed an area near Zagorsk (56108N -3807E)
on a steep bank of a river. According to-JAPPI ,a test stand
was to be installed at this location, and he and.others in
his group made the construction drawings for such a stand;
however he never saw the actual construction. BUGAYEV, who.
worked in Moscow,was reportedly living in Zagorsk 25X1
in the s ring of 1950 after he had joined the. rocket engine
group. assume,' therefore, that the test stand was built
at this location.
130. there were several large test stands at
apus-in 4834N 4543E). These were designed for firing
of A-4 missiles. sent a large amount of pressure-measuring 25X1
equipment to Kapusti this is where experi--
ments were ma with ee ac o combustion gases to drive
the turbine, never saw the test stands there and no 25X1
Germans were there after the first trials in 1947. At that
time HOCH, MA.GNUS,and Werner MUELLER were at Kapustin,
among others.
MISCELLANEOUS TEST EQUIPMENT DEVELOPMENTS
131, The following items of equipment were designed by various
engineers at Ostashkov, partly to be used for their experi-
SECRET
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
SECRET
ments there, and' partly to fulfill orders by agencies in
Sine Wave Generator
1320 Two of these units were built in 1948 and 1949 on orders
of NII 88; they were delivered in the spring of 1949. The
generator was to be designed for frequencies from ORO1 to 50
cycles per seoondQ The sine wave generated had to be a
perfect sine wave .:without any discontinuity so that the
second derivative of,the wave would still be a sinusoidal.
An B-O generator was used.to produce such a wave. Automatic
gain control was not used'as the AGO time constant is too
fast for such low frequencies? The output of this generator'
was 30 - 40 milliamperes at 80 -- 100 volts. In 1951 - 1952,
two more such generators were built but these used a gonio-
meter instead of the R-C generator. This involved the use
of two coils, one turning inside the other. A 100 ko. volt-
age was applied to the stator coil, inducing in the rotor a
voltage corresponding to its angular position, This voltage
was rectified in a bridge rectifier whose output frequency
would thus correspond. to the speed of rotation of the rotor.
At very low frequencies, problems were encount ered due to
mechanical, play between the motor and the rotor coil. The
bridge rectifier feeds apush-pull amplifier using the Soviet
equivalent of 616 tubes; the rectifier used two .6X6 tubes,
These generators were designed and. built and
they were to be used for testing rocket a eer ng devices.
Qsoii1losco2e
133# A. large oscilloscope incorporating eight separate cathode-
ray tubes was built for use at Ostaehkov. In fall 1951,
construction was started on a similar unit for NII 8
The
ose oecope was es gne so a a mov a camera could be
mounted on it to take continuous pictures of the eight
cathode-ray tubes. For this purpose no horizontal sweep
would be used; 'instead, a spot would be deflected vezrtioally
in accordance with the value to be presented., The cathode-
ray tubes. used were German.types LB-1 and LB-8,
134. One of the tubes presented time marks at intervals of 1,
1/l0,and 1/500 second . These were produced by counting
down from a'500-cycle crystal generator. Another one of
the scopes presented the Doppler frequency resulting from
velocity measurements in a special way so that it may be
accurately determined,. The Doppler frequency was counted
down by four multivibrators to produce a ratio of 16 to 1.
The outputs of the multivibrators were combined to produce
saw-tooth waves having a frequency 1/16 of the Doppler
frequency, and having 16 steps in each saw-tooth. By
comparing the steps with-the time marks, it would be
possible to determine the exact Doppler frequency very
accurately, The other six scopes were used to present
various other values to be measured during ' the flight
of a missile. The oseilloscope,whioh was to be built for
NII 88, was not to include the special scope for measuring
the Doppler frequency.
SECRET
25X1
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
SECRET
-4 27 -
135.
35-millimeter film was used at a speed of 10 centimeters
per second. The camera used was a normal news-reporter-
type movie camera made In the USSR since the war. It had
three lenses which were interchangeable. The lens used for
the oscilloscope was a wide-angle lens. The distance from
the lens to the face of the cathode-ray tube was one meter.
Films, which could be handled up to 40 meters long, had to
be threaded into the camera. A special attachment was
designed to hold 150 meters of film. Originally, panchro-
matic film was used, but later a Soviet-made x-ray film,
sensitive to the light of the cathode-ray tube screen, was
substituted.
Staadard Frequency Generator
136. This was designed by Dr. M(]LLWO. It was quite similar to a
frequency generator manufactured by General Electric or
General Radio Company. The frequency of this generator was
accurate to one part in 101? which is the equivalent of
1/100 second per day. A 100 kc crystal housed in a thermo-
statically-controlled copper cylinder produced the reference
frequency. Frequency dividers are used to reduce this
frequency to 50 cycles and this signal drives a synchronous
clock. The clock is compared. with a time signal received
from a radio station. The signals from the clock and from
the radio receiver are compared on a cathode-ray tube and
the error of the clock is thus very accurately determined.
The crystal frequencies also multiplied to increase the rang
Test Equipment for, Determining Antenna Characteristics
137.
This equipment was designed by me between December 1951 and
April 1952. It consisted of a 15-inch diameter turntable,
driven by a motor, for mounting a transmitting or receiving
antenna. If a receiving antenna is to be tested, the received
signal is detached in the equipment, r.ectified7and applied to
a PPI or A scope. The sweepsof the scopes are synchronized
with the rotation of the turntable, and thus the antenna
pattern is presented on the scope. If a transmitting antenna
is to be tested, another receiving antenna must be used at a
remote point. A line feeds the signal from this point to the
receiver in this equipment. The turntable was designed to
accomodate antennas and mounts weighing up to 20 kilograms.
At one time the Soviets asked about building a much bigger
equipment similar to this that it might be
intended for mounting entire rockets. This project, however,
was not worked on.
Sweep Frequency Gen rator
138. This equipment was designed by Dr. LANG between fall 1951
and April 1952 for NII 88. It was designed to weep the
frequencies from 27 to 33 megacycles. This was accomplished
by the use of a rotating capacitor turning at the rate of
25 rps. A saw-tooth voltage is produced simultaneously to
produce the sweep voltage for an oscilloscope, so that the
pattern from 27 to 33 megacycles can be presented on a
cathode-ray tube. this equipment was to be
used for tuning IF amplifiers.
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
SECRET
_28-
Stan Signal Generator
:.139,..This equipment was also designed by Dr. LANGE between fall
:1551 and, April 1952. L. masterL-C generator was used to
;produce a signal continuously variable from 16 to 35 mega-
cycles. The signal is amplified and may be amplitude mode
lated by a pulse. Multiplier circuits are included in the
amplifier stage so-that a continuously variable output can
be obtained from 16 to 70 megacycles. Tuning is accomplished
.'by the range switch and tuning condensers.
Pre,_ genet' Meter
140. This unit was designed by RANDS, who worked in the labora-
tory headed by SCI' .JETZ in fall 1951. The meter was designed
to measure frequencies from 0.01 to 50 cycles per second.
The measurement was accomplished by the discharge of a ca-
pacitor through a. r ectifier and a meter,, For the frequencies
from 0,.,,81. to 3 or 4 cps. the frequency would be measured by
counting the swings of the needle on the, meter agaim t a stop
watch. Above that.frequency the steady meter reading indicates
the frequency to be measured.
Vibration Table
141?
These were, designed only on paper by the drafting section
n-naAr : nlrk r 5. The basic calculations were made by TOEBE
The table was designed to vibrate on three axes. 25X1
was necessary first to design a support for the table
having a high characteristic resonance. Three pairs of
eccentric masses were used to produce the vibration in the
three axes. The way in which the masses in each pair
compensate each other determines the direction of vibration
resulting from that pair. Vibrations between 10 and 50 cps %
were to be obtainable with an amplitude up to five millimeters
in each axis. The table was designed for testing apparatus
weighing between five and tan kilograms. The table.was 15
inches in diameter. The eccentric weights are driven by a
motor through a long thin shaft made of steel so that the
motor does not feel the .:bratione. The motor speed is
controllable for varying the frequency of the vibrations.
Apparatus for Balancing G~yrosces
142, This apparatus was designed by BANGS in 1949 and 1950 for
Nil 88. The gyroscope to-be tested s mount ed on two leaf
springs which are alternately held rigid, The loose spring,
has a magnet attached to it to induce current in a coil as
.it moves. This current is applied to an oscilloscope. A
black spot is painted on the gyroscope and seen by a photo-
cell as the gyroscope rotates. Output of the photocell is
a "pip" which is also applied to the oscilloscope. It is
thus possible to note on the oscilloscope which part of
the gyroscope causes the eccentricity. Holes aredrilled
into the gyro to compensate for this eccentricity*
Pressure Gauges
143.u These were designed for use at Ostashkov as well as. on
orders from Nll 88 and opus tin, They were primarily
SECRET
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
SECRET
-29-
;, esigned by CCBP.MANN and SCHOLZ. The gauge consists of a
membrane made of sheet steel. When pressure is applied the
membrane will deflect a maximum of approximately 0,005
millimeters. The membrane is mounted in an induction bridge.
Two inductors are located on each side of the membrane, and
the bridge is balanced at zero pressure. When pressure is
applied, the inductance of two of the coils is increased
while that of the other two coils is reduced. .& signal is
thus obtained from the bridge. These pressure gauges are
designed to measure either direct pressures or relative
pressures,
ftales for Wind Tunnel
144. This equipment was designed by COERMANN in the fall of 1950
for the wind tunnel built at Ostashkov. The scale operates
to measure the forces in three axes exerted on a test body
in the wind tunnel. The force is measured by twisting a
specially machined piece of metal against a oounterw6tkhts
The advantage of this method is that no friction is in-
volved. The units are calibrated by adding a lever with
weights to exert forces similar to those which occur in the
experiments. Moments of forces applied to the test body
are measured by determining the difference of the forces
indicated at both sides of the wind tunnel. One of the
major problems incurred in the design of this equipment
was the 'sealing of all of the instruments, as the tur--
bul during the experiment would seriously affect the
readings taken.
Scale for Water Canal
145. These instruments were designed by ARNOLD for use at
Ostas`kov. In the water canal the measurement of forces
is made in only one axis. The arm holding the body in
the water is held in position against a counterweight so
that a scale can be read to indicate the forces on the
body. In the water canal the depth of the water at any
point corresponds to the air pressure in a wind tunnel.
The test body may be marked in millimeters and pictures
taken of the water running along it to obtain arecord of
the corresponding pressure. Similarly, the turbulence
of the water may be recorded by putting colored ps in
the water and photographing it a PRIESER was 25X1
in charge of the water canal at Ostashkov. a ma :e the
calculations for equivalent pressures and test bodies at
reduced scales.. Measurements in the water canal were
generally made by PEIREN'MEYER and. o*,>;ine: for Measuring Dined ance
JUt 146, This equipment was designed by SCHMIDT between fall 1951
and spring 1952 on orders of XII 88. It was to be designed
for a wave length of six meters, and this 25X1
indicates that the Soviets are still interested in six-
meter wave length work for rocket guidance. The equipment
was delivered to the same personas the apparatus for
measuring antenna characteristics. Thee quipment included
SECRET
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
- 30 -
a frequency generator for wave lengths from two to seven
meters. The
test line was approximately four meters long. A variable
impedance ratio transformer was used to match the impedance
of the test line to other lines.
Acceleration Measuring A,paratus
147.
This apparatus was ordered by NII 88 in 1949 and 1950. It
was primarily designed by CORMM
the high
25X1
frequency design may be used wit Messina
25X1
telemetering equipment. The purpose of these instruments
was to measure acceleration and vibration of test rockets.
Basically, the instrument is very similar to the pressure
gauges described above. The membrane must have a mass
whose own characteristic resonant frequency lies above
the frequency of any vibrations which are to be measured.
Due to the inertia of the membrane, acceleration and vibra-
tion are indicated by the output of the Induction bridge.
The output signal of the induction lridge was between 0.1
and 0.5 volts at 500 cycles. This signal was transformed
up to 0,5 to 2.5 volts, rectified, and applied as modula-
tion to the telemetering equipment.
Normal Preauency Generator
148. This generator was designed to produce an accurate frequency
signal for calibrating frequency bridges used in the measure-
ment of missile velocity. The apparatus was developed for
NII 88 in the fall of 1950. An L-C generator was used
to generate the signal. To obtain high q and sharp tuning, a
high gain tube was used and only a small fraction of the signal
fed back from the anode through a large resistance. The
frequency was tunable by means of a 1,000 mmf tuning capacitor.
The frequency range was from 400 to 500 cps. The output
signal of the generator was applied to a cathode-ray oscillo-
scope. Pulses from a crystal oscillator are also applied to
the oscilloscope. These pulses are produced by count-down
multivibrators and are obtained at pulse repetition fre-
quencies of 100, 50, 10, land 0.1 cps. By successive selec-
tion of the pulses, it is possible to tune the L-0 generator
to the desired frequency to an accuracy within one-twentieth
cycle. This signal is then applied to the frequency bridge
to be calibrated. This bridge is tuned to give a null in-
dication at the selected frequency.
Colloidal Mill
149. This was a unit to be used presun,b for rinds metals to
be used in colloidal suspensions.
it was designed at 0stashkov in 1951.
the colloidal suspension might be used to increase the weight
of fuel burned in rocket engines and thus increase the thrust.
11 Cormenv. The correct title of this institute has
not been determined.
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
SECRET
-31-
P~ R~DRNC
GROUsb STATIO.J
}f
TRANfIN-rr
REC& IVY
$OW
AMP.
4
F~tt4.
MUt r.
I Iz,a
MMC
rP
10
MCI
V EL,
MGRS,
AAIMUr
CIMMJO
6eu.
COMMAND
46VATION
MObU.
4ATO
a,F. Am rl;w IJA ,
--J
Ce~~
CUT ORP
coMMM3
b1O C K D IA-O kkM of 6-1 G U ID&R CE, taU I PM EIS)T
SIrCRCT
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
- StC'cT-
- 32-
94
U.
T
I-
CIRCUIT DIAGRAM of StCOND' w SWITCI-t ' in DIRtCTIO
FIIJDIG CIRCUIT
--StGRL'T
25X1
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
StCF~ET
33 ~.
.c a
0
V
la V,
5 .
pO
BLOCK AGNAM GROUND TRANSMITTEK
SCCNtT
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
34-
ILVEREQ
BRASS or
BRfltt9 SPiRI
+1400V
SKCTCEI of CAU11Y 1DU14it b ;or CiR4UN1FO
GRUO METAL- CegAv IC TU? USED IQ
'GROUND ZR~~1~te~IT'~i~
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
5'ECKET_ 25X1
m35-
RECEIVER CIRCUITS ~y PLE
DOPR F.RLQUEIJC~1
MEASURING CIRCUIT
SCCRCT
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
SECRET'
-36-
ca U
,g ?
w
CIRCUIT 4 WAvt oRMS -fbr RANGE. MENSUREM JS T
- vi F-c RET-
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 _
W-000-
-
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
SECRET
/4a
10Vr rANrANIOUS
0tit aefOO1%
OF In LICINT
ANGLE of IMTERtST
in bALLIST ICS DISCUSSION
GROUND srAT i ON
wtRE AnrEt4W c
*4 -f
SrA I'ts' 1 NQ
KOC. K Er
ELECTRONIC
EQUIPMENT
PROPOSED 'DF-SIGIJ D4 PILOTLESS, SUPERSOMIC.
MRCRAF-T, R i5
& 1 C ZET
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
SKETCH of GYROSCOPE.
Datt'gd lines iv-d icate
burn wn9 of Rudder
SKETCH of. RUDDCR
Sr-CReT
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
- C R E T- 25X1
39
RUOo6R ACTUAT IO C-C UINAGO
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
sec^eT
_38-
COMSTRUCTIN of DIRECGT(OIJ FINDING SWITCH
(OUe o; Two' ro NTICAL sPEcT1,014s)
Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-00810A001100310009-6
 Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6
S C_ izc--r - 25X1
-a 37 -
LEFT ;VPPER
PARr of
s w -'TGH
D. F. BY
.C CLE
o$t Tl o n-
TE~VMA
?
RIGHT
E F T
o
X0
UPPER ,
1 WHY UPPER
EACH PART
c1V CycLs
LASTS .,1- SEGo
too
= f?StGr
ONt CYCLIC
SC~IENIATIC REPRESEN3T1T14.,i
o '''D-RECTIOI1 51iM1NG SWITCH
- sac .E-
j--Sanitized Copy Approved for Release 2010/06/30: CIA-RDP80-0081 OA001100310009-6