DETAILS OF MISSILE GUIDANCE DEVELOPMENTS AT OSTASHKOV

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP81-01030R000100380007-2
• Release Decision: RIPPUB
• Original Classification: C
• Document Page Count: 4
• Document Creation Date: December 23, 2016
• Document Release Date: August 14, 2013
• Sequence Number: 7
• Publication Date: February 5, 1954
• Content Type: REPORT

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Declassified in Part - Sanitized Copy Approved for Release 2013/09/09: CIA-RDP81-01030R000100380007-2
CENTRAL INTELLIGENCE AGENCY
INFORMATION REPORT
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
emended. 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.
NTIAL 50X1
COUNTRY USSR (Kalinin Oblast) REPORT
SUBJECT Details of Missile Guidance DATE DISTR.
5 February 1954
Developments at Ostashkov
NO. OF PAGES 14
DATE OF INFO.
REQUIREMENT
PLACE ACQUIRED.
REFERENCES
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THE SOURCE EVALUATIONS IN THIS REPORT ARE DEFINITIVE.
THE APPRAISAL OF CONTENT IS TENTATIVE.
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CONFIDENTIAL
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REPORT
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COUNTRY t USSR (Kalinin
Oblast)
DATE DISTR. Al 414 C
SUBJECT t Details of Missile Guidance Developments
at Ostaehkov
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NO. OF ENCLS.
ACQUIRED
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REPORT NO.
DATE OF INFORMATION
THIS IS UNEVALUATED INFORMATION
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TYPE DESIGNATIONS
1. T wne nilkna tn nnnenv w? 27REG-162:7 (ballietioian at Ostashkov)
1 [ to correct the discrepancies in type
numbers assigned to the various rocket projects at Ostaehkov.
2. CREG-162j and I concurred on the following designations. 5.,These
numbers agree with previous testimony by REG-162 and REG-154.
a. R-10. Modified A-4 for 300-kilometer range.'
b. S-14. Long-range rocket for approximate range of 3000
kilometers.
o. R-15. Pilotless long-range airdiaa.
d. R-113. Antiaircraft rocket.
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R-113 ANTIAIRCRAFT ROCKET
3. A serious discrepancy was noted between the sffectiveness
diagrams for the R-113 as described and [REG-14g.
We agreed on the diagram shown below:
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W4VW
Thus, the maximum effective altitude is 30 kilometers, minimum
altitude 5 kilometers: The maximum slant range is approxi-
mately 50 kilometers; the missile will only travel between
30 and 40 kilometers under combustion (see dotted line) and
coast the rest of the way. The burning time was to be 30 to
35 seconds, with a final velocity of 1000. meters per second.
4. Two types of explosive charges were mentioned as alternatives
to the proposal for this project. Dr. ALBRING proposed a
single charge, detonated at as close a range as possible. '
Some of the others, including myself,swere in favor of a
splinter charge with a cone of 30 'to 50 degrees.
5. Work on proximity fuses and target seeker heads was carried
? on by groups at Ilinskaya and Moninp. No details on this work
were available to the Ostashkov group.
R-10 MODIFICATION OF A-4 MISSILE
6. The R-10 was designed for a range Of approximately 300 kilo-
meters, with combustion cut-off occurring between' 40 and 50
kilometers.
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7. I submit the following basic control diagram for right-left
direction-finding control. The values should be multiplied by
6 for elevation control.
The totil'direction-finding range is plus or minus 50 minutes;
direction-finding sensitivity plus or.minue 00 minutes., The
possible:approachable accuracy is six times this figure.or
minuted. (The faotoi ()raiz was determined '
experiments.) ,The steering command is limited, after differ-
entiation, to 'i value A which corresponds to an error of 6
minutes.. The differential Die effective Only within the:,
range between plue and minus 6 minutes. The amplitude Of the
maximum steering command .was only so strong that suffioient
rudder deflection was still .available for rocket stabilization.
The integral of the radio command is applied with a very emall
coefficient to the gyroscopes in order to compensate for constant
error as a result of non-;symmetry of the rocket. This integral
.is turned off for the last oscillation of the rocket across the
required_course, to improve the final stability.. ,
8. The characteristic redonance of the Markgraf gyroscopes is at
25 to 30 cycles. Damping of the control circuit in the rocket
is effective up to 8 to 10 cycles.
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I Declassified in Part - Sanitized Copy Approved for Release 2013/09/09: CIA-RDP81-01030R000100380007-2