RESEARCH AND DEVELOPMENT ACTIVITIES ON ROCKET FUELS AND TEST APPARATUS AT BRANCH NO. 1 OF NII-88, GORODOMLYA IS.

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP80-00810A001500580003-9
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 11
• Document Creation Date: December 16, 2016
• Document Release Date: June 30, 2005
• Sequence Number: 3
• Publication Date: August 20, 1953
• Content Type: REPORT

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CENTRAL INTEL' ..GENCE AGENCY
INFORMATION REPORT
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DATE OF INFO.
USSR (Kalinin Oblast)
Research and Development Activities on
Rocket Fuels and Test Apparatus at
Branch No, 1 of NII-889 Gorodomlya Is.
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.
REPORT NO.
DATE DISTR.
NO. OF PAGES
REQUIREMENT NO.
REFERENCES
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20 August 1953
47 25X1
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INTRODUCTION
I a era l
was a Nava r?ace eseare roup- headed ng, ummert a submarine torpedo
wl- ,.T9 4 fn-rmAr1,T with the Walther plant at Kiel
Now
Nass;
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GOtashkov at that, time had no organization, laboratories, or working
space. Paoilities consisted of an old school building and. clinic,
and wigs f lap i ed ?aly; with restaurant tables and chairs.. No tech-
i~'l,
flied]. equips t was available, 'except for that which belonged to the
individuals` personally. The Soviet scientific. director, Fish
B bi k 1, .:w'*s es. yo" ..man who had just graduated from school.
8ediuse..of the total lank of guidance, the German specialists grouped
themselves together, usually with other members of the organization
fr+apa rrhioh..thsy. deported,, and assigned
...been depor rtep themselves some type,.:.
of Mpsperwork pro jeotN,` The ur p ose of this was (1) to
ass the time until laboratory f,oilities could be completed; and
tiblish some sort of a collective technical library where
U
e
i
s
to
z
25X1 they could rater to problems concerning rocket 'd'evelo meht with which
they mi ht.not be o?mpletely.familiar. texts
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a. Temperature measuring methods.. A basic paper. to be used in the
library and etretl~sir~g .methods as related to rocket test and
stand procedure, i.e., mogLsurement of inside and outside wall
temperatures, ga$ temperatures, etc.;
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for a fuel laboratory.
e.,.The'orstioal,calculation of the magnitude gf'the time of hyper-
golio ignition le stressing how it'develope, and: how it ;may
be oaloulated
d. A study of the use of gas pressure,as .a,.pria,e mover . for rocket
fuels and' the effect of e~bsorbed gas on the fuel! s performance.
Thu. s' was primarily: as adapted to anti-aircraft type missiles.
No further fork was done along these lines
e. Calculations governing t4j relationship ,between .the length of
time , f uels remained in the combustion chamber and the amount
of ' thrust received from them.
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Tie Germane, at Peinemuende had- had certain Norma
they were
,Times that they used in design problems'.
not accurate. enough
f. Mathematical relation between thrust and the distance between
'
in the exhaust s.treamo
the shook diamonds formed
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S E C R E T
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Deign of a rocket fuse. This was a time-consuming project that
was a oarry-over from activities at .Gemao 25X`1
missile a short distance above the ground.. The task was never
completed.
It ,was not to
employ either radar or electronics, and was to detonate the
scot
physicist, In
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Prof Wilhelm SCHUTZ,
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Ing. Helmut GROSTTRUP, the German engineer whom.the Soviets ha4 appointed
Ohiaf of the German specialists Rroup,F
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S E C R E T
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20 ... The. ab; ct of this 'under-taking was to determine the optimum gedatettioal
form for ati exhaust flame detl8otor so that$ (a) in launching a mi
the fiake- could : be. deviated 90 evenly and throughout all 360 of a
circle, aird (b) go' that the design could utilize normal Russian steel
.(Soviet designation .#17). The forms used' at Peei.emuende were not
adequate. They gave uneven flame distribution and sometimes caused,.
the missile . to . tilt., the .point of the sohurre continually burned off,
etc.
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S E C R E T
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29. The first designs were _st.udied with the aid of the two-kilogram test
stand, but were later repeated with the 20-kg unit. Upon Soviet
r.queat,.all experimental. were conducted on actual metal. models with
work supported by photographs, rather than working with mathematical
25X1. designs.
T8*Rs , a STUDIES
Zak 30. In thi"e specific instance, the two-kilogram stand was used primarily
as a squrce.of heat energy for heat transfer studies. Average tempera-
ture; of the flame used was about 200000. First measurements were
made on one-m1 limetez-.thick sheets of normal Soviet steel #17,
steel #13, and aluminum alloy 1JG 35. In these studies,the flame was
allowed to Impinge upon the metal with an angle varying from 90
through
3).
32.
3.3 ?
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'Bonding between ,the glans wool and the 'wood was waterglass in the
Following the experiments with plywood, samples of glass wool of
Russian origin. were received for testing." Drs. MATTHES and OTTO
rude test panels from this material according to Soviet specifica-
tione,wherein the glass wool was compressed into a sheet one centi
.meter thick, and'.held between.twp 0.1 mm. veneer sheets of walnut.
first: sample, and aircraft glue 'liergerleim of Russian origin
in the second. The
bonding forge use .was 20 g. per square ec meter.
Burning and heat transfer?teat$ were, also conducted:: on these panels
through angles varying from 90 ?to-.00, as with the plywood sheets.
The walnut veneer burned away very quickly, but the wool itself
remained intact. Insulating qualities of these sheets were very
good,and the. paneling made with aircraft glue withstood the test'
better-.that the other. No furth r tests were conducted with' lass
These panels were also propose ,: y. e
Soviets
or missile heads.
2QLZN ;ALCO OL FUEL RATIO
35 Prior to this time, Dr. Heino ZEE$ had"conducted theoretical computa-
tione as to the thrust values possible with various aloohol-oxygen
ratios,, using a ran e f .-C hamber Pressures from six atmos hexes. to
1.6 atmosbhorend
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e ,ZEISE had previously compiled volumes of. tables to be used in the
deeig of rocket motorsa work requiring four years, all of which were
rov
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r r~in..wa i r
37..
By the and of December 1948, a new two-kilogram, .and the 20-kg. test
,stands were completed and ready for operation.. The entire. unit was
designed and built in Ostashkov, except for the compressor, which
was taken from an old refrigeration unit All the work
stand waa clone by aermansl
T e e ec r c va ves an gauges.
necessary or s, opera ion came from Peenemuende.
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38.. First experiments began in January 1949, and again, all orders for
tests,to?be conducted came from the Soviet thief engineer K- RG.ANOV
with one etoeption, an order from a Soviet ' civilian, 25X1
oono.4rning the study of the ionization of the exhaust flame.
IGNITION PROBLEM, TWO-KILOGRAM STAND
39. The,Germans at Peeuemuende, prior to 1943, had had.difficulties with
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the initial ignition of the oxygen-alcohol fuel combination and .
several,,explosions had resulted. They had solved the problem suffi-
ciently. 'well, but the Soviets continued to have 'o.ifficulty, not only
with oxygen-alcohol, but also with oxygen-kerosene fuels. 25X1
this was because they worked with a...much higher inject on
pressure than the Germans, yet did not alter the rocket motor. The
task, - therefore,- was. to find the best method of igniting fuel mixtures,
especially the oxygen-kerosene combination. Problems which had to
be resolved for this fuel were:
a. Which to inject first,..
b. How much time to allow between the injection of one component
and the other.
C! Thae, pressures to be used in the start.
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45..
Following is.a list of the experiments conducted with the use of the
20 kgo teat stands
a. Repetition of the determination of the optimum mixing propor-
tion for the 75 per cent alcohol-liquid oxygen fuel at chamber
_pra.ssures varying from 8 to 22 atmospheres.
, zilar?determinations with 80 per cent alcohol and within the
same chamber pressure range,
c. Measurement of gas temperatures inside and outside of chamber
when fueled with 75 per cent alcohol.
d. Spectroscopic determinations of gas composition inside and
outside of the chamber.
e. Repetition of the."Sohurre" study.
46.
f. Experiments with the coloring of the exhaust flame using
sodium and lithium salts (for gas density studies).
g., Ionization measurements of the exhaust.
An optical pyrometer using a tungsten element was used. to measure the
gas temperature both inside and outside. of the chamber. The purpose
of this tryst was to determine the highest temperature encountered for
comparisorwith Dr. ZEISE's previously mentioned calculations. Tem-
peratures' were taken for various alcohol mixtures and at various
chamber, pressures.
47. Professor FROST, a famous physical chemist and well-known member of
the Soviet Academy of Sciences and a Stalin.prize winner, proposed
the theory that re-combination of gases, previously dissassociated
in-the combustiol.chamber of a rocket motor, occurred in the laval
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48. a ily r , director of Plant 88 and successor to General GONOR,
supported this theory, while KURGANOY, who had previously been Soviet
chief engineer. at Ostashkov and who had been transferred to Plant 68,
25X1 refused to, accept,. the thesis.
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49.
S E C R E T
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