SUMMARY OF RESULTS OF THE JOINT US/USSR WORKING GROUP MEETINGS

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP74B00681R000100150001-5
• Release Decision: RIFPUB
• Original Classification: K
• Document Page Count: 41
• Document Creation Date: December 16, 2016
• Document Release Date: January 10, 2005
• Sequence Number: 1
• Publication Date: December 10, 1971
• Content Type: MF

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NATIONAL AERONAUTICS AT\ID SPACE ADMINISTRATION
REPLY TO
ATTN OFWX
(SP
WASHINGTON, 0.C. 20546
OEC 1 0 1971
MEMORANDUM FOR: Dr. Donald Steininger
Assistant Deputy Director of Science & Technology
Central Intelligence Agency
SUBJECT: Summary of Results of the Joint US/USSR Working Group Meetings
Attached is a copy of the Summary of Results of the Joint US/USSR
Working Group meetings of November 29 - December 6, 1971, on
rendezvous and docking in implementation of the NASA/Soviet Academy
agreement of October 1970. We would appreciate any comments you may
have prior to January 24 when'NASA plans to dispatch a letter approving
these recommendations.
Please note the restriction on release of these results.
,Jacob E. Smart
'Assistant Administrator
for DOD and Interagency Affairs
Attachment
as stated
NASA review completed
?
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TEXT NOT FOR RELEASE UNTIL
P
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OF RTSULTS
Of the third meeting of snecialists of the USSR
Academy of Sciences and the U.S. National Aero-
n(utics and Space .Administration, November 29 -
December 6, 1971, on comnatible systems ler the
rendezvous and docking of manned spacecraft and
stations.
I. INTRODUCTION
1. In accordance with the Summaries of Results of technical talks
between representatives of the USSR Academy of Sciences and the U.S..
NrtionAl leronautics and Space Administration) held October 26-28, 1970,
and on June 21725, 1971, on questions of providing for compatibility of
manned spacecraft and space station ronJezvous and docking systems.,
meeting of three Joint working Groups was held in YoScow (USSR),
November 29 December 6, 1971, for the purpose of:
(a) further discussing, coordinating and approving technical
requirements for compatibility of such systems in the
future; and
(0) .further considerina7 possible flight missions to test
compatible systems in the mid-15:70ts period.
In the period between the meetings, technical docup.ers were exchaned and
aTreed technical tnsks performed for subsequent apnroval.
11. r:,SUITS 027 "=.77
2. .:ne Joint drkin roups considerr.,,d both the lon7-ter:!:
requirements for comp,tfrie syst,:m;,3 rnd pozsil-ae fli-ht
such systems, givin-4 considerrtion at this ti. thc
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3. The second stage of possible tests of technical requirements
and solutions for compatible rendezvous end docking systems will 1:e
considered later, as nrovided in the Summery of results of June 1971,
namely the docking of a Soviet Soyuz-type spacecraft with n U.S. orbital
station of a Skylab or another type to be put in orbit after 1975. The
technical desirability of .both stages of tests is recognized both .
parties, considering also that the sizes and other characteristics of
the compatible systems used in the first stage may be altered for the
second star7,e by mutual agreement.
L. The results of the Joint Wbrkinr; Group meetincr.s are ncted in
their minutes which are attached as an integral part of this Surrmary
of Pesults (Attachments A, P., and C) and which list documents developed
and exchanged by the Working Groups. The main aspects of their minutes
are briefly listed as' follows:
5. Joint Werking Group No. 1 completed general documentation on
liie support systems, coordinate systems, constraints upon spacecraft
configuration, and communications between control centers. Withresnect
to the propesed joint Apollo/Salyut test mission, agreements were reached
on the objectives of the objectives of the mission and on a list of
proposed project documents for the mission. The group agreed to a mutual
exchange on launch windows in two months, programs for the test mission
by April, and communications channels fcr the resnective control onters
within three months. The U.S. side will provide a pro7osed interface
organizational plan for the rroject for comment by the Soviet side.
6. Working Group No. 2 determined the list of guidance and control
systems and onboard equipment of USA/CSSP spacecraft which is to 'c..?
compatible. The documentation on the subjects of lights, dockin:-?
and chreti:rittfacinageicaa?e(21105/02/137,,TMAATIAERWO RIPARCI-1- 9911
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very nearly completed. The Group plans to reorganize its documentation
into two volumes covering respectively the future general requirements
and the proe.osed Apollo-Salyut test mission.
rdssion, it is agreed that the two sides develop a
With
respect to the teat
communicatipns systel:
and a treckin;; system to an agreed set of technical requirements and to
provi6e for the installation of the Apollo-type UF ranging system as a
beck-up. The Soviet side will consider whether to build its part of this
system or utilize equipment provided by the U.S. side. Docking contact
criteria have been agreed as a basis for docking system design. ;'7rea:rent
:IFS also been reached on a docking target for installation in the canter
c: the docking hatch. This target will provide a compatible docking
alinement system. A docking target, similar -Le that used in the Ppollo
proeram, will also be installed on the Salyut to facilitate alinement.
some perameters may require review as design problems are uncovered.
Additional work will be undertaken by one or both sides on control
stabilization requirements and their relationship to spacecraft size,
and on the design, development schedule, evaluation and installation of
the new docking target concept. The Working Groun recognizes the useful-
ness of a meetin7 in the very near future.
7. Joint Working Grcup No. 3 discussed and agreed on the decument
"Technical Pequirements for Compatible USA and USSF Lockin7 Systc:Ls"
agreed to a series of basic parameter values of Apollo/Salyut deckin7
system., including the diameter of the transfer tunnel. The workine ercueJ
e;:chaneed and discussed material on P docking system concent. 7et,s4C
features of a joint concept were developed that will permit further
develoeent work. Further study and aereement are required for the
devclonment of a sinFflejoint concept, listin of perametere and esteb-
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lishing their values 50 as to ensure co7.pctibility. Also needed
01 CCnd'aCtinS tests at various
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str7,e,s, c,f develoPment. The -:!?orkir.':--, Crux') a7reed also to create a see]
mode: a dockin?; system that will allow a verification of the 3:r7retc:;-s
tnnt ensure compatibility at an early strge of development. rine Yorkin,
Croup recognized the usefulness of a meetin; in the very near -future 211
outlined the questions that must be discussed end creed at that neetin.
III. OPJECTIVES APOIIO-SIIYUT JOINT '7,ST
8. The rrimary objective of a joint flight involving, an f,pollo-
tyne spacecraft and a manned orbital station of the Salyut-tyne wo.uld
to conduct space experiments to test the technical requirements and
solutions for compatibility of systems for docking of future manned z;p:co-
craft and stations. Such testing should include the rendezvous pnd dockini
of Apollo-Salyut with the active use of all the new equipment required for
compatibility which could be available by the time of the mission. rlhe
performance of this test mission would include the following,':
(a) testing of a compatible rendezvous system in orbit.
(b) testing of androgynous docking assenblies.
(c) verifying the techniques of transfer of cosmonauts Pnd
astronauts.
(d) the performance of activities of U.S. end Ts:'SS7, crews in
docked flight in accordance with a program that will be determined later.
(e)
gaining of experience in conducting joint flights by U.S.
and USSR spacecraft, including rendering aid in emergency situations.
IV. OTHEP COrSin7TATIONS FOR A77,ST--------
APOITO-StIYUT JOINT
--
9. With particular regard to anossible first jc,int test mission,
involving the rendezvous and docking of an /polle-type spacecraft and a
ut-tyTe space station, representatives of the two sides reach e:.' th,1
follewin; conclusions:
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(b) The baseline for discussion, definition ond develeennt
cf the competible dockinr!, system for the initial test mission wlll
based on the agreed concept of an androynous, peripheral system rdepted
to the particular requirements of the Salyut space station and the
'Apollo dcckine, module.
(c) A preliminary list of milestones, or major events in t'.c
planning, design end implementation of the first prorosed tact mission,
is provided in Attachment D. The parties should exchange pronosrls
before April 1972 for this schedule of activities and its finalizetion.
(d) The parties consider it essential, in order to begin
designing and mcdelin?, the components, units, and systems which are
required for consideration and rossible implementation of the first
joint test mission, to provide for continuing direct contact through
appropriate organizational and cornunications arrangements:
(1) Ornelnization. The Project Directors on loth sides
shall be reseonsible for direct and continuing contact between them and
for taking all technical stens relating to the test Mission. They shad]
utilize Deputy Project Directors as desired, drew on experts from the
three Working groups, and utilize such additional experts frcm their
respective sides as they may require.
(2) Communication. The two sides agree that the develop-
ment and accomplishment of the test mission require the establishment of
rapid and effective communications between the Project Directors and
others designated by them.
The U.S. side considers the informal direct com-
munication should begin immediately ley voice telx cha1 d
that it sholad thcri ?
coon as this
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WORM
The telex chennei will be used as required
to establish and record understandings FS
. well as to trzrnsmit desired information. It
will also be used to organize and arrange in
advance the agenda for scheduled weekly voice
co.onunications so that such weekly voice oc1,7
ferences will be discirlined and efficient.
^ Voice communications shell be for discussion
purposes only. /ction should be taken only on
the basis of confirming telex messages.
- Each side will meet the cost of its telex
messages. The two sides will share equally
the cost of a d.edicated voice channel.
The U.S. side considers that such a coordinated system of telex and
voice communications is essential for proceeding 'qith:the rroposed joint
mission. The Soviet side will study this question and. transmit its
pronosals simultaneously with the confirmation of this Summary of results.
The two sides agree that documentation should be exchanged by the most
raid means, utilizing the assistance of Embassies. In addition, Small -
groups of experts shall exchange brief visits as required on particular
problems.'
Ce) Since an early final decision would be essential to permit
a flight schedule for the mid-19701s, it is necessary that each pr.rty
cene: the other, by April 1, 1972, a statement of its position on the
'prospects f-r the actual conduct of the test mission in 1975. (Th2
side pronosed Spring or Summer.) The rarties will also exchange mision
concepts b5. April 1, 1972.
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7
V. corciusIoN
10. This SI;nmary of Eesults is subject to confirmation by the
VSSP AccdeMy of Sciences and NASA; parties shall inform each other
accordingly in writing within two months.
11. The next meeting of the Joint Working Groups is planned for
late Xay vs' June 1972 in the United States.
Done in Yoscow, December .6, 1971, in Russian and in :English.
B.
Robert P. Gilruth
. P. Rurruant
wow.'
Irnold W. Frutki.1
1
V. S. Vereschetin
Chr opher C.Kme
PROJECT DIPECTOP3 AND }FADS OF
WORKING GROUP
K. D. Bushuyev
HEADS OF WORKING
V. P. Iegostayev
GROUP 2
PI
ynn S. Iunney
HEADS OF WORKING GROUP 3
464;;;;Ii6
Donald C. CheathEm
nald C. Wade
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ATTACHN.=_Nr_r A
. WORKING GROUP NO. 1
NOV. 30 - DEC. 6, 1971
MINUTES OF NEIETINCS ON 0012TIR.I.LITY OF GENEFAL
METHODS AND MEANS TOR RENDEZVOUS AND DOCKING
PART I. COEPATIBILIlY CP UTUFE SYSTE:ES
In the discussion of the agenda items., the following results end
conclusions were reached:
a. Coordinate Systems and Units
Group I agreed to accept the doeurrJant prepared by the US entitled,
"Coordinate Systems Standards for International Rendezvous end Docking of
Spacecraft," end it was signed by both parties. This d'ocument is included
as Enclosure 1.
b. Atr.osrhere, Pressure and Yethods of Transfer
The document prepared by the USSR. entitled "Specifications for
Crew Compartrient Atmosphere, Transfer Y.ethods, (and Units and Systems Needed
to Provide for ths Transfer of Crews after USSR and USA Spacecraft end Space
Stations Have Docked" was accepted after modification.and then was signed by
both parties. This document is included e.s Enclosure 2. We reached en under-
standing that within two months of this Meeting both parties shell exchange
information on questions relating to the connection of liquid-cooled garments
of the sr.:ace suits to on-board thermal regulation systems. Data also to be
-
exchanged includes ? quantitative characteristics (possible times, release of
? -
oxygen into the cabin atmospheres) and possille. oPerational solutions (pre-
breathing in airlock chambers under lowered pressure in a two-component ?
atmosphere) with a view of finalizing these questions at the next meeting.-
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siEned by both parties. This document is included as niclosure 3.
was
d. Commur.ic ati ons F.etween 'Control Centers
TI??. US side presented a paper entitled, "Proposal Pequirerr.ents for
Communications between Central Centers," arid the USSR side agreed to review
the paper and transmit comments to the US within 3 months. Group I is confi-
dent that agreernnt will be reached on this subject.
. e. Hatch Sizes
The subject of a clear hatch opening size for future space systems
should be discussed further. The 7resent US requirement for future systems
is l.5 meters in diameter. The USE agrees that it is desirable that hatch
sizes for future .space systems be larger than those on present spacecraft.
^
f. Techr.icues for Assurin.:7 Compatibility. of Overall lf.et'nods and Yeans
Group I .agreed that the Apollotpalyuttest mission being considered
is a good opportunity to test our joint solutions for assuring overall technical
compatibility. ,
Cc/MP/ail:Win' A0/2.
PART II -,,APOLIO/SAITLIT-TYPE HISSION
In addition to discussing future system rquirements, Group I also dis
cussed the proposed test mission involving an Apollo-type spacecraft zmd a
Salyut-type 'manned orbital station. The results conclusions, and work to
be continued are sunnerized as follcras:
a. In-forma ti on Exchange
Bah sides presented papers covering Several subjects at the
beginning of the meetings which were very helpful in the discussions and will
be valuable as reference material in the work to continue.
b. Project 'Documentation
Group I agreed that a nu:raper of documents are necessary for planning
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an Apollo/Salyut mission ar.d established a list_of documents which need to be
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prepa2eo ana signed. This list is included- as Enclosure h. As work
progresses., other necessary documents ray be identified ar.c1 included on
the list by mutual agreement. The group a?rreed on the general technical
content of these documents., although further definition is necessary. 7,
agreed that both sides will exchange outlines of these documents within
tIvee months along with .a proposed schedule for the preparation of these
documents.
c. Organizational Plan
The U.S. side presented an outline of a typical organizational
plan for consideration. Group I gave general agreement to :the content of
such a document.. The US will transmit aiproposed organizational plan to the
'USSR within three months.
d. Project ?Technical Proecsal Document _
Group I agreed upon the need for a project concept proposal document
which would give ,an overall conceptional description of all the .elements
involved in the test mission. This dccument should include a brief description
of major items of eqvipment anfi mission model. An example of This type of data
is sham in the U.S. document entitled "Desigi end Operational Description of
the US F,quipment for Use in the Apollo/Salyut Test Nission." `1*7?.f
k -'Ar 8.^.?:,c4.en /t4 i.e./ Orr*/ ie; 7 1cy7,... a Co dui. on
le. Aro lo/Salyut Test Mission Objectives 64c-c-Y1',4fit /so- dP-v4-1:e4
j our /7
Our group decided that the primary objective of a joint flight
involving an Apollo-type spacecraft and a manned orbital station of the
Salyut-type. would be to corthict, space experiments to test the technical
requirements for compatibility of systems for rendezvous end docking with
the active use of all the new equipment required for compatibility which
could be available by the time of the mission. The performance of this test
mission woad include the following: (1) testing of a compatible rendezvous
sys t em;(2) te stinr
lfn261-1/Wdr-Wii84MYing the
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techniques,of transfer (the transfer of up to two US 'crewmen to the Salyut
).;
end -413013416d*41- EZZ insit 200.5t02/37a ok-FIQE74PW1P.09211M79?P.1117,5y. 061.11);
(4) the performance of activities of US and USSR crews in docked fliEht
in accordance with a program that will be determined later, and (5) gpin of
experience in conducting joint flights by US and USSR spacecraft, including
rendering aid in emlirgency situations.
f. Atrosnhere8 Comnatibility and Crew Transfer
The group accepted in principle the concept of the use of a speciE,1
US docking module for use as an airlock between the different atmospheric
pressures of Apollo and Salyut. We agreed on a set of preliminary ground rules
and have includedthem as Enclosure 5.
g. Xission:Plan
In the course of discussion agreed decisions were reached on some
questions; on a nunber of questions the direction of further studies was
defined. The resits reached are contained in Enclosure 6.
The parties have agreed to conduct further studies on the possible
ranges of launch tines for their spacecraft witll a view of finding a mutually
acceptable solution so as to ensure a daylight Apollo launch. It was decided
to exchange _the results of these studies within two months.
-
h. Communications Channels between Control Centers
Group I agreed that the previously exchanged papers on this subject
contained the basis for agreenent. We areed that the USSR will review the
US proposal and transmit comments to the US within three months. We also agreed
that,efter.the requirenents were established and signed, communications
specir.lists.from each country should meet to determine how these communications
channels would be implemented.
In sumffvry, WorkinF Group I exchanged views on the Apollo/Salyut test
mission and reached an understanding of the main elements required for such a
mission. '3e have reached agreenent on mission objectives, document reqlirements,
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on mooed., enc. sone other technical
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E. G. Iineterr,r
.1
K. D. Eushuyev
I. P. Ramyants6v
V. N. Bobkov
L. -A. Gorshkov
I. V. Iavrov
K. S. Shustin
0. G. Sytin
); ?
B. F. Artemov
(de(!),(47-?
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EAT TAC11,4NT B)
1,:inutes of the Working Group No. 2
Novcm1;er 29 - December 7, 1972? Moscow
1,0 The sides continued discussion of the following questions concerning
USA/USSR spacecraft rendezvous and docking.
- external lights (flashing light beacons, onboard orientation
lights, floodlight),
-- docking target and sighting devices,"
? voice communication radio systems,
- rendezvous radio systems,
-- initial contact conditions for designing the docking unit,
-- requirements for spacecraft control systems operation in rendezvous
and docking modes and docked mode,'
-- documentation format.
2.0 External lirthts
2.1 Both sides confirm the agreements on the flashing light beacon, the
onboard crientation lights and the floodlight which were agreed upon at
the second meeting in Houston in June 1971 with the following 'changes and
definitions.
a) Acknowledging the desirability for providing the detection of flashing light
beacons in any direction up to the range of 50 _kilometers, the sides may
assume a reduction of these requirements for a particular spacecraft. In
these cases the specific characteristics of beacons will be included in the
general technical requirements defined for the appropriate spacecraft, and
these will be agreed to by both sides.
b) Both sides permit the presence of regions of no coverage for the onboard
orientation lights. The preferred values for these regions and their locations
for each spacecraft will be agreed to byoth sides.
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c) The sides agree to change the agreement with respect to the number of
onboard orientation lights and their locations according to the document
"General Technical Requirements for Onboard Orientation Lights for
Application to USA/USSR Spacecraft During Compatible Rendezvous and
Docking."
2.2 Both sides agreed to the format of the following documents: (See Appendix 3
for correct titles for this and all following sections.)
a) General Technical Requirements for Onboard Orientation Lights for
Application to USA/USSR Spacecraft During Compatible Rendezvous and
Docking.
b) General Technical Requirements for Flashing Light Beacons for -
Application to USA/USSR Spacecraft During Compatible Rendezvous and
Docking.
c) General Technical Requirements -for Floodlights for Application to
USA/USSR Spacecraft During Compatible Rendezvous and Docking.
Both sides have agreed to certain technical specifications in these
documents, but both sides consider that it would be expedient on the
following technical questions:
a) flashing light beacon turn-off range;
b) beacon shading in emergency conditions;
c) onboard orientation light locations, and;
d) color coordinates for white lights, to carry out further analyses,
to define technical specifications, and to exchange these in the form of
technical documents in preparation for their discussions at the next
meeting.
2.3 The parties consider that the general technical requirements for
spacecraft external lights may be extended to the Apollo/Salyut
international mission with the appropriate modifications and agreement
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Pap:e 3 of b
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will be made upon the technical requirements for such devices.
For this purpose both sides have agreed upon the following
documents:
a) General Technical Requirements for Onboard Orientation Lights of the
USSR Orbital SpaceStation Salyut-type During Rendezvous and Docking with
the USA Spacecraft Apollo-type.
b) General Technical Requirements for Flashing Light Deacons of the USSR
Orbital Space Station Salyut-type During Rendezvous and Docking with
the USA Spacecraft Apollo-type.?
c) General Technical Requirements for Onboard Orientation Lights of the
USA Spacecraft Apollo-type During Rendezvous and Docking with the USSR
Orbital Space Station Salyut-type.
d) General Technical Requirements for Flashing Light Beacons of the USA
Spacecraft Apollo-type During Rendezvous and Docking with the USSR
Orbital Space Station Splyut-type.
e) General Technical 7eouirerrents for Floodlight of the USA Spacecraft
Apollo-typo During Rendezvous and Docking.with the USSR Orbital Space
Station Salyut-type.
Some characteristics of the external lights of the Salyut space station
and the Apollo Command/Service Module, in particular the Apollo floodlight
location, the orientation light shading and location and the Salyut
flashing light beacon intensity require further analyses and definitions.
The results of these analyses will be exchanged between the sides for
information and further discussion.
2.4 Roth sides consider that the passive spacecraft nust have devices for
shading of optical sighting and measuring instruments from damage by the
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? 3.0 Targets
3.1 It is agreed that a standardized docking target will be designed for
future USSR and USA spacecraft and spac- stations. The target will be
mounted on the docking mechanism hatc. .s of each country's spacecraft
and space stations. The target desig:. location requirements will be
specified in the "General Technical R6quirenents for Docking Alinenent
Targets for Application to USA/USSR Spacecraft During Compatible
Rendezvous and Docking." (to be completed and approved at a later date).
The standardized target design has been tentatively described. A final
design will be discussed and adopted at the next meeting. In the event
that significantly new docking devices are developed, then modifications
to the standardized target design may be necessary and changes will be
made by mutual agreement.
3.2 For the performing of the Apollo/Salyut mission it is agreed to mount
on the Soviet Salyut station 2 docking.targets, one of them being made in
accordance with " General Technical Requirements for Locking Alinement
Targets for Application to USA/USSR Spacecraft During Ccinpatible
Rendezvous and Docking."
The second docking target for the Apollo/Salyut mission will be mounted on
the Salyut and located coincident with the Apollo line of sight. The target
will generally be of the type sh.oWn in Figures 1 and 2. (General dimensions
are shown on Figure 1.) The back of the target will be located on the
Salyut within 1 meter of the docking interface and shall not be more than
0.6 meters in diameter. The USA will select the final design of the target
and inform the USSR about this choice. The location accuracy and manu-
1 f acturing tolerances_ ,for the, tar2at. Wila .44e Qila
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4.0 .,'.c.m.,r.,anication System
4.: The sides confirm the agreements achieved on radio communication at
the second meeting in Houston (June 1971) and consider that these agree-
m,nts should be cktended to the particular Apollo/Salyut mission.
4.2 Standard radio communication equipment, the composition of which waa
determined at the second meeting, should not be used for other tasks
(range measurements) as such a multi-purpose use of the equipment limits
the possibilities of spacecraft-ground stations-astronaut communication
in international missions*
4.3 The Soviet operating frequency is 121.75 MHz. The American operating
frequency is chosen from frequency band of 100-300 MHz. The USA will inform
the USSR about the exact frequency during arch 1972. After this, the
sides agree to proceed with preliminary designs.
4.4 The parties agreed on the preliminary common technical requirements for.
the compatible station for radio communication (see Ippendix I).
4.5 The sides agreed that the Apollo VHF Communications and Tracking System
will be placed as a back-up system on both spacecraft during the Apollo-
Salyut mission at the same time with the standard communication station
corresponding to Appendix 1. The USA will send the documentation of the
1.pollo VHF Communication and Tracking System during January 1972 so that
the USSR can determine the possibility of manufacturing this system.
4.6 It is agreed that the primary communication mode will be simplex,
simultaneously on both operating frequencies.
4.7 The following questions will be discussed in the future:
a) :he final agreement of the requirements on the compatible radio
communication equipment and their refinement;
b) Characteristics of antennas and their locations;
c) n aietr-fg fie 164i412b65107/174021PARDP14130D6i3JELN tODAS 0.99.1 cal-
culations;
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".
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d) Techniques and the order of checking the equipment for compatibility;
e) The Soviet possibilities of manufacturing the Apollo VHI" Communications
and Tracking System.
5.0 Trackinc. Systems
Loth sides continued discussion of requirements for radio guidance systems
during rendezvous operations and came to the agreement that:
5.1 The fina] goal for both sides is the development of a compatible,
ccmmon system which provides for radio guidance during rendezvous operations. ?
The transponder for the passive spacecraft will be developed to meet the
common technical requirements mutually agreed to by both sides. Both
sides will design, independently, the equipment for the active spacecraft.
5.2 Euring the Apollo/Salyut rendezvous experiment, the existing US
ranging system will be considered as a backup system. The transponder for
this system will be installed on the Salyut space station together with the
ccmpatible common transponder. For determining the possibilities of the
US system manufacture by the USSR, the American side will submit detailed
technical requirements for this system during January 1972.
5.3 Taking into account that the standardized waveband 3-10 CM suggested
by the Soviet side ineiudes part of the waveband 8-15 CM suggested by
the American side, both sides came to a preliminary agreement to develop
a compatible common radio guidance system for rendezvous operations in the
10 CM waveband. The accurate values for interrogator and transponder carrier
frequencies will be coordinated during the next working group meeting.
suggestions of each side on nominal carrier frequencies of the interrogator
and transponder shall be communicated by mail for review by each side before
the meeting. Each side will send to the other the draft of technical require-
ments for the transponder for review by each side before the meeting.
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6.0 initis Contact Conditions for the flosining of Docking 2,:chanisms
6.1 The sides agreed to dofine the form of technical specifications of
contact conditions for the designing of docking mechanism.
6.2 The sides agreed to be governed in further investigations by the
following values of parameters for future space vehicles and for
Apollo/Salyut missions:
-- closing velocity 0.05 - 0.3 m/sec
-- for Apollo/Salyut mission .a question
should be discussed concerning increase
of the lower limit up to 0.1 m/sec
lateral velocity 0.1 m/sec
-- lateral misalinement 0.4 meters
angular misalinement 7.0 degrees
-- roll misalinement 7.0 degrees
-- angular velocity ( active vehicle)
-- angular velocity ( passive vehicle)
1.0 decree/second
(around any axis)
0.1 degree/second
(around any axis)
These parameters are defined in a document titled "Docking Initial-contact
Condition Criteria for Application to the USA Spacecraft Apollo-type and
the USSR Orbital Space Station Salyut-type."
6.3 The sides agreed to exchange the results of their investigations
and to conform finally the values of the parameters for the Apollo/Salyut
mission at the next mission.
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7.0 Contl.ol Systems
7.1 DiJ d ons have been conducted concerning the requirements 2or the
attitude control system of the Srut spr.cecraft durinr: the dockinl'
m=euvor nd the docked flight of the 4ol1o/Salyut mission. It
n7reed that the document submitted (see Appendix 2) by the USA will
serve as a basis for exchange of data. The USSR agrees to prepare a.
correspondilw, document and the format will be agreed to at the next
7.2 noth countries have agreed to study the question of allcwable angular
rates for unstabilized vehicles. The studies will evaluate anp7ult_r
rate values between 0.05 - 0.1 der:Tees/second.
7.3 It is agreed to exchange necessary data on the moments of inertia)
bendinq fu el slosh, mass distribution, thruster oc at ion, block
diagram and phase plane of the attitude control system, etc., to
evaluate the control system requirements of the docked *ilo/Salyut.
8.0 Documentation
It is agreed that both sides shall prepare and exchange required
documents for application to USA/USSR compatible rendezvous end
docking. These documents will further define the system parameters
set out in these minutes. The documents will be i ndividually approved
by each side after they are exchanged and studied. The sides have
preliminary versions of these documents and a list is given in
Appendix 3. The documents are a pert of the minutes. This list may
be added to through mutual agreement.
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1-PFz,NDIX
C110N TLCHNICAL RLQUINTS FOR Ta COMPATIELL RADIO
Ck.Y.IC.I.T10N STATIONS
1.1 General Parameters
This document formulates the requireMents for radio stations
intended to ensure:
--simplex voice and AT (audio tone) telegraph comunicaticns-
on FY, at a frequency fFM equal 121.75 MZ.
--simplex voice and AT telegraph communicatons on AM at a
frequency of 100 ? 300 MHZ -
--duplex telephone and AT telegraph communication at
frequencies fFM and fFM.
The primary communication mode is simplex, simultaneously on
the frequencies fAM and fFM. In the duplex mee.e, the active
spacecraft transmits fFM and receives fAM;? the passive spacecraft
transmits fAM and receives LF. AT telegraph is used according to
the discretion of each side.
It is proposed that each side develop its radio stations
sparately. The basic parameters and structural elements of the
stations required to ensure compatibility will he standardized in
these technical specifications.
:ach space vehicle will be equipped with a ra6io station in
cases wheve possibility of rescuing the crew must be provided,
as will every rescue vehicle.
Tc operating frequencies of the radio station are selecteu
on the losis that it may be possible for stations or ship stations
of both countries to monitor conversations and contact the,r, from
the ground.
1.2 General Technical Specifications
1.2.1 The radio station must include:
-- a transmitter for fFZ;
-- a transmitter for LAM;
-- a receiver for fFM;.
-- a receiver for LAM;
-- antenna switches
,-
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-- control panel
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2
tpe recorder and teleraph key (according to discretion
' of each side)
1.2.2 The radio station assembly on each spacecraft includes the following:
-- the radio station itself;
-- instructions for operation in flight;
-- dictionary of accepted words and expressions;
and set of magnetic tape cassettes (if necessary);
1.2.3 The radio station mast ensure radio communication between vehicles
at distances of 0 to at least 150 km at any flight altitude (after
antennas are deployed) and in any mutual position.
1.2.4 It is assamed, if one of the parties considers it desirable, that
the individual devices in the radio station or the radio station
itself will be able to be used for other forms of communication.
This will require elaboration of all reqUirements discussed in
these technical specifications and will not limit voice radio
communication.
1.2.5 The radio stations mast accept leads from low frequency modulated
inputs and have outputs from the receivers to other onboard
communication systems.
1.2.6 The receivers must 11.2.ve squelches. The threshold of squelch
operating must be e.g.
1.2.7 The compatible parameters of the radio station Will be as follows:
operating frequency fFM of the first receiver-transrlitter.
(121,75 MHZ)
operating frequency fAM of the second receiver-trancaitter
(. . .
permissible frequency variati6n of transmitters and
receiver heterodynes not to exceed 50x10-6
output power of transmitters in series with 50 ohms not
less than 5-10W
coefficient of nonlinear distortion for transmitters 10%
for fFM and 15% for fAM.
frequency variation of transmitter at fFM with modulating
frequency of 1,000 Hz. 10 peak KZ.
Peroenta..7e modala,,
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attenuation of parasitic radiations in transmitters with
reflectivity of 5 MHz, at least 80 db
-- receiver sensitivity when S/N ratio on audio output is
equal 10db
must be less or equal to 1.5,1V at fFM
2.0)1V at fAX
-- pass band of receivers at 0.7 level 80 KHz (Amplitude of
frequency curve)
-- attenuation of spurious channels at least 80 db
-- receiver selectivity with 100 KHz misalignment 60 db
1.2.8 The. antenna-feed must allow transmission or reception for an: direction
of a co:nounicating station relative to the vehicle on both frccucncies
fFM or fAM. The antenna radiational pattern of each antenna system
must not contain dead areas below 10 db for any size vehicle, even
during simultaneous operation at both frequencies. The antenna
radiational patterns for each frequency must have a fill factor of
at least 0.9 at .10 db.
The antenna feed loss (including diplexer loss) must not be
greater than 3.0db.
1.2.9 The control panel must have the following Controls:
_ _ _ .
fFM simplex, off and on;
fAM simplex, off and on;
-- duplex off and on;
-- mode switch for voice/telegraph
-- switch squelch, off and on
-- tape recorder, off and on (according to discretion of each
side)
-- volume control knob.
1.2.10
The AT telegraph must use L-leslulatin,g voltage at a frequency of
800 +100 Hz, with deviation of the operating frequency fFM by 10 K'Hz
and percentage. of modulation to be at... least 80% of the operating
frequency. filM.
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1.2.11 The radio station must function normally under cabin conditions
in space vehicles and stations.
1.3 As the. progmm develops, it is allowed that changes moy be made
to this document after mutual agreement by both sides.'
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APPenciix II
PI:Ir]-2,!ENTS O STAPILIZATION AND
CONTROI. 6-YSTE1v.: 1?1:3U1.7,SL\SNT.'S APPIICATION .TO I:SA/
USSR CC...1';:l'ATIBIS P.1771.1DEZVOUS AID DOCKI17G STWJY APOSIO/SAITU
1.0 .11;1P.O1)IZTION
1.1 Scone
This document defines the stabilization and control system requirements
on the a:....tive .(ApoliO) and passive (Salyut) vehicles for the dockinr,'./
undockins, operations and the docked fldght regime.
1.2 General Peouirems nts
The control systems of the active ar. passive docking vehicles, Apollo
and Salyut, respectively., will ze capable of performing certain control
functions for the above stated flint o-eration's and fliT:ht regime..
Bach control system will be capable of attitude maneuvering or holding
the combined configuration after docking, and also of limited translation
of the combined confi;uretion along its longitudinal axis for orbit
maintenance or otl-sr TED purpose.
Re quire-7ents on the individual vehicle control systems are given below,
section 3.0.
2.0 urrs
2.1 Stabilization and Control of the Passive 'Vehicle
Th passive vehicle (Salyut) will provide an inertially stable dockin7
tarFf,et for the active vehicle (Apollo) du-rill-7, dockin,.?:. This stability
will be achieved by means of the attitude hold control ca.nability of
the passive vehicle. Meximun attitude an1es and In a'X i1111.1n atttude
rates will e +1 degree and. +0.1 degrees/second., respectively, about
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the mode CLC CL2 J doros r_c3r second oi-out Fry
fixed. nor :'ore thPn T dc:-roes second about each
of its throe rrincinr1 axes sauJtnneou5ly.
2.2 :::.trbili7,rtion and 7,en -ol Docked Con i-Tration
The Salyut -and the iccollo control systems will each be cable ofni docked kpollq/Snlyut confi uration to a solr inartinl refe=ce,
a local vertical reference, or a TIED reference within p toleroncu of
+TBD degrees attitude and -:-T3D degrees per second residua
rate. Each control system will be capable of a ;7,F,E mode in both the
soft latch and hard latch docked confiurations.
'3oth the Salyut and the CSM control sy-sterz be carz"cle
maneuverin::: the docked configuration to any T:PD
at an anulpr rate not to exceed 'TBD degrees per second.
3.0 VEH7CT7 .ASS PROPERTIES
(See 'fable 1.)
4.0 CajT.ROI. 57STEY CHAlt.CTEPESTI CS
4.1 Anol lo
locations
Thruster Ch.Frccmcz-f.stic
-.1.2.2 mar. ..mpu
4.1.2.3 Cued Configuration
4.1.3
Attitude Control System
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4.2.2.1 Tot.,1 Impulse
4.2.2.3 Qud ConfiFurations
4.2.3 Attitude Control System
5.0 SUPPIEK4NTAL INFORVIATION
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APP :MIX 3
LIST OI? THE DOCW.ENTS OF WORKING GROUP 2
1. General Technical Requirements for Flashing Light Ecacons for Application
to USA/USSR Spacecraft During Compatible Rendezvous and Docking.
2. General Technical Requirements for Onboard Orientation Lights for
Application to USA/USSR Spacecraft During Compatible Rendezvous and
Docking.
3. General Technical Requirements for Floodlights for Application to
USA/USSR Spacecraft During Compatible Rendezvous and Docking.
L. General Technical Requirements for Flashing Light Beacons of the
USI Orbital Space Station Salyut-type During Rendezvous and Docking with
the USA Spacecraft Apollo-type,
5. General Technical Requirements for Onboard Orientation Lights of the
USSR Orbital Space Station Salyut-type During Rendezvous and Docking with
the USA Spacecraft Apollo-type.
6. General Technical Requirements for Onboard Orientation Lights of the
USA Spacecraft Apollo-type During Rendezvous and Docking with the USSR
Orbital Space Station Salyut-type.
7. General Technical Requirements for Flashing Light Beacons of the USA
Spacecraft Apollo-type During Rendezvous and Docking with the USSR Orbital
Space Station Salyut-type.
8. General Technical Requirements for Floodlight of the USA Spacecraft
Apollo-type During Rendezvous and Docking with the USSR Orbital Space
Station Salyut-type.
9. General Technical Requirements for Docking Alinement Targets for
Application to USA/USSR Spacecraft During Compatible Rendezvous and
Dockikki
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10. Docking Initial-contact Condition Criteria for Application to the
pacecraft Apollo-type and the 'USSR Orbital Space Station Salyut-type.
11. Docking Initial-contact Condition. Criteria. for Application to USAAR
Spacecraft During Compatible Rendezvous and Docking.
12, General Technical Requirements for Guidance and Control Systems and
Cnbord Equipment to be Standardized for-.Application to USA/USSR Spacecraft
During Compatible Rendezvous and Docking,
13. General Technical Requirements for Docking Alinement Target of the USA
Spacecraft Apollo-type During Rendezvous and Docking with the USSR Orbital
Space Station Salyut-type.
1)4. General Technical Requirements for Docking Alinement Target of the
USSR Orbital Space Station Salyut-type During Rendezvous and Docking with
the USA Spacecraft Apollo-type.
15. Format for Combined Documentation Related to USAATSSR Compatible
Rendezvous and Docking..
Document I. General Technical Requirements for Guidance and Control
. . _
Systems End.Ghboard.Fquipment_to be Stendardized for Application to
? USA/USSR Spacecraft During Compatible Rendezvous and Docking.
Document II. General Technical Requirements for Guidance and Control
SystQLsand Onboard Equirjment to oe Stanoar J.ze0 for - _ _ .
the USA Apollo-type Spacecraft and the USSR Salyut-type Spacecraft
During Compatible Rendezvous and Docking.
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.40
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(ATTACHMENT. C
C
GROU:-) ;,.6. 3
NOVLI,MER 29 ? DECI.:Isa3ZR 6, 1971
OF ;.:...i;TINGS. ON 1,SSURING THE CUOATIBILI=
Grocp ND '3, rpoi-,sible for a ssurif-,th cj:_jt...-1.1).-1
dki.n hs discussed the items o.7 o.creec'
eo...lent as follows:
:11. .ror of
Decin-7
raviewed, d.iscli:?sed and a3reed on the ',.iccv..lent,,
fOf Cz..,-,-,patible and 1.;;:-;::;R CYL:teri.s." It
tht-:: pars.lr,eter.s di srsr.d n hz; .
L/ fl thi,3 p?iroccs th?
2re:::.,..s.recft. onL.f,:ceer: velucs e;f'
?th .insure tr ecpatf?;bility. Solr.?:: the.se :t
-.nceo to at this meeting and ar shown aaSection I.
?-?? ? dec.n.:17:ents.'dill be prepared on :::.crot:ci parax,ctcrs t..
? dockin,f: systems for 1.17o110 .1..nd Salyut
? cec:tft.
. S?rtem or)t
P:.th iciesexchzAh--od material relatiA,L,-. to the ..oreept of an
'locking vste;ri. They .'zi.;--Det?sssed :7.atorial '
3.. The. b.ascline for discussiori, and o:
dicking, system for the. initial .t,eot rtission
concept of an androgynous, peripheral adapted ?Lc
requirements of the Salyut space station ;:zid th,
The design concept .includes a ring ecillipped
thatar located on J-:lovable rods which serv,:-. as attenato.:"
tractin: au:cuators, ane a docking ring on v'hich are locaed
cap,t,..rc 1:,...,c;heF; with. the dockinc
?
2. The basic geometry and dimcnriion of the rir,s-
will )-(2 three., Contort, to -.:,'iLure 1.: The ei.:7,011,7ion
inure c..;pture duringinitial ,.:ontLct con.onz
3 (L;) 3 .etiOn III.
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Available
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latch.;s, :;cher;,11:' will h oenstr,:.,tod as f.r
funishel by the US side; th,. 1:Aches on th riv veh;ele
loc:tc..1 on the docking ring Ls 21rovided for in the material
5oviet side.
The emstruction of th Lttenuator rods L:h,.1. retractin
on ring w..tL guides is located m,Ly be different. 3tat ach.-ii'
1n3G1-,? the synchronizL.tion of the mov,ment of all rods in the coa,-..; .
3. The deckins interf.%ce generally will
fLzrnished by the Coviet side. (Fi,sure 2)
6. The nuber, location, crinciples of act n.J nf
-:nerally will be as .flovided in
L- Soviet F.idc. If nocessary,.the force exertek.1 by the latches th.
len;;,h of Lheir movement will be Increased. .
7. It is reognized that the b,Isic vnriant
of the location ond oonf1,2uration o: th :Ls Lh
in the furnished by the S:)viet "L.
by the US side also must 1AJ studi The hatL.J.,
:s well as its cross eeetior, are cl:osen
In co..!etioil, it is? recon-aizee, that the.eriphdi latch *eir
cc.nni'tl.ohs will be subject to space environment.
S. The :7-aiding f)ins Lad their socts that serve as hyalic
ec.nne::tions,as shown in material furnished by the Soviet side, will
solely to F..1i,gn the docking ring interfaces.
9. The confur.ations and the dimensions of the dceUn7 rin not
7reolud the location of electrical connections, as shown in mr%tcril
hy the So-fict side.
be as i...0o-iined r,.-)r in
The variant providinz for locating the electrcal
the ..h?.-.Jr walls of the transfer tunnel to permit manual eoanection
be :-t,: C(.
1:-). The hilmber location of the sprin thruFlers on 1.h.
as shown in the material provided by the Sovet
The sides also a[;rced tht a scylc model of the d.:;en: ?
d to 1-,omit verific;Aion of the pL.rarlicter3 th;.t, d
%arly t%e of development. The methoci of verifying
i3 3UhiCt to a7,recent,' In this conneet,lon,
1n11.:;:nty w;:ich elements .67L1.1 oe aetve pnd whioo uiA1 nottf-
ra.;-:_mcters of thi$ model are :;ubject to azrtlesnt :It the
Th,; se:Av i$ chosen t bc cciu-.:1 to 2.5.
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VL1?,1cs of.Parametorejor Docking Systems of P.pollo/Salyut Spacecraft
To allow for the investigation and de:;i6n of coliTatible docking ustems,
1,oth countrios have agreed to thu follon values of parameters for docking, .
sys'Lof: to be used in an Apollo/Salyut mission. These parameters are based on
at:ints
defined in the document, "Technic:J.Requirements for Cowatible
US,S1:: Docking Systems."
pro;!.ented
1. Ynvirow,.cn
a. Pressure: 760 mm HE to 10-9 mm Hz
b. Solar Intensity: 1400 liatts/moter2
c. Earth Planetary
Lmission: 216 watts/meter2
d. Average Albedo (Earth) 0.39
2. Mass Properties of the Spacecraft
The mass properties and basic dimensions of the sidacecraft
in Fizure 3.
are.
Docking Interfac:e Contact Condition Limits
a. At initial contact:
Closinc., Velocity 0.05 to 0.30 meters/sec.
0.ne proposal to increase the lower limit to 0.10 meters/sec
should be studied.)
Velocity 0.1 meters/sec.
2.fisaliprment 0.40 meters
(T'r:e *proposal to decrease the uPper limit to 0.33 meters shoi1c P.
narMisalipnment 7.0 degrees
F.otational Misalignment 7.0 degrees
AriP-,u1%.r Velocity 1.0 degrees/see.
(ixtive 3pacecraft)
Lnrwlar Veloctit,r 0.1 derc:es/sec.
(Passive Spacecraft)
b. At structural ring contact:
Iteral Misalip:nment 2 zailimeters
Anular Minalirynnent 0.1 derees
(about any axis)
(about any axis)
Rotational Misalipnment. 0.2 defil;oli
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Cr,ntact Velocity 0.03 meters/,Tec.
4. Internal Diameter of Structural Ring
The internal diameter of the structural ring will be 800 milimeters.
5. Other Parameters
There are other parameters, the values of which cannot be
ideptified at this time. In accordance with the basic technical requirements
document, these parameters and their values will be identified at a later date.
IV. FI:ture Joint Work M5lestones
Fcilowing are the principal steps. In the joint development and testing of
th,:: compatible docking systems for the Apollo and Salyut spacecraft. These
steps are subject to further study by both sides for the purpose of establish?
ing do.tes of completion of the steps, including preparation of the joint
documents required therefor.
1. :Development and agreement of docking system concept.
2. Manufacture and tests of scale model.
3. Agreement on a final interface control document with values of
all parameters for compatibility defined.
4. Completion of development and manufacturing of docking system.
5. Joint development tests.
6. Completion of technical specifications for qualification testing
of the docking systems.
7. Independent qualification testing.
8. Joint qualification testing.
9. Interface checkout of flight docking systems.
10. Flight
To ensure compatibility in the joint development process, the following
addonal groups of documents will be created:
a. List of values of the parameters that ensure compatibility of
cocking systems.
b. Method of conducting and programing of joint tests.
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Approved For Release 2005/02/17 : CIA-RDP74600681R000100150001-5
joint development plan, including the creation of the additional
documents, will be discussed and agreed to at an early future meeting.
In establishing the dates for completion of the major milestones, each
side Jl be guided by the fact that the joint Apollo-Salyut flight will
take place in mid-1975.
01-,jectives of the Next Meeting
The members of this Workine: Group agreed thot it will be necessary to
meet soon to agree on technical .cuustions that must be decided during the
initial stages of the development of docking systems, in accordance with the
basic features of the docking system concept agreed to at this meeting.
5".;ecifiCal1y, the following items should be accomplished:
1. Confirm the possibility of creating a docking system in
accordance with the concept adopted at this meeting and introduce improve-
ments if necessary.
2. ?urther convergenr,e toward final docking system geometry and
co:aponent design concept.
3. Exchange and coordinate preliminary development plans and
- - -
schedules.
.4. Discuss requirements and details of a scale model of the docking
system.
5. Further establish values of those parameters necessary fur
compatibility.
Approved For Release 2005/02/17 : CIA-RDP74600681R000100150001-5
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