ASTP Fact Sheet 1975

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APOLLO SuYUZ TEST PROJECTUSA - USSR

RELEASE NO: 75-9 FACT SHEET

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ITABLE OF CONTENTS

ASTP General............ 1Command and Service Module .....* *.... 2Docking Module and Docking System .............. 2-3Soyuz Spacecraft .........~................... ... 3Launch Vehicle .......*..** . * . . 3Planned Mission Summary . ..................... 9-11ASTP Experiments ..... ............... 11-20U.S. Space Vehicle Configuration.......... 22Crew Assignments.. . . ............ c e 22ASTP Funding and Budget Request .........** 23ASTP Major Ctntractors............ ...*.*.*.* * 23-24Astronaut Biographies . .... ............ 26-40Cosmonaut Biographies........ 42-49I -ii-

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APOLLO SOYUZ TEST PROJECTYears of combined effort and cooperation between theworld's leading space powers will culminate in mid-1975with history's first international manned space mission.A milestone in international space cooperation wasachieved on May 24, 1972, when the United States and theSoviet Union agreed on the organization, development,scheduling, and conduct of a test docking mission inEarth orbit.The Apollo Soyuz Test Pro ect (ASTP) calls for thedocking of a United States Apollo and a Soviet Union Scyuzspacecraft in Earth orbit to test compatible rendezvous anddocking equipment and procedures. A major goal of themission will be the performance of 27 space experiments.Five of the experiments will be conducted jointly by theastronauts and cosmonauts during the joint phase of themission. The remaining experiments will be performed bythe U.S. astronauts and will be spread over the 9-dayspan of the flight.The major objective of the program will be the inflighttesting of a jointly-designed international docking muech-anism. Also, experience will be gained for the conductof potential joint flights by the U.S. and USSR spacecraft,including, in case cf necessity, rendering aid in emergencysituations.Joint U.S./USSR working groups have been meeting ona scheduled basis, both in the U.S. and USSR, to reviewand agree on the technical and operational aspects ofthe joint project.

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Command and Service ModuleThe Apollo spacecraft will be a modified version of'the Command and Service Module (CSM) flown during thefirst several lunar landing missions. Major CSM modifi-cations include provisions for experiments, additionalpropellant tanks for the reaction control system and theaddition of controls and displays required for the properoperation of the Docking Module and docking system.

Dock-&Module and Docking SstemThe Docking Module is cylindrical, approximately1.5 meters (about 5 feet) in diameter and 3 meters (about10 feet) in length. It will serve as an airlock for theinternal transfer of crewmen between the different atmo-srheres of the Apollo and Soyuz spacecraft. The Docking

Module will be equipped with radio and TV communications,antennas, stored gases, heaters, and the displays andcontrols necessary for transfer operations.The Docking Module is designed to handle two crewmensimultaneously. Hatches, having controls on both sides,will be installed at each end of the module. A universaldocking system will be located at the Soyuz end of themodule and will be capable of functioning with similarcomponents on the Soyuz spacecraft. The Apollo end of theDocking Module will use the probe and drogue docking systemused during the Apollo lunar program to permit dockingbetween the Command Module and Lunar Module.In orbit, Apollo's atmosphere is pure oxygen at apressure of five pounds per square inch. Soyuz uses amixture of nitrogen and oxygen at an Earth sea levelpressure of 14.7 pounds per square inch. (Later NASASpacecraft such as the Space Shuttle will use nitrogen-oxygen at sea level pressure.)While the spacecraft are docked, the Soyuz pressurewill be reduced from its normal 14.7 pounds per squareinch to 10 pounds. This will make it possible for crew-men to transfer from Soyuz to Apollo without taking timein the airlock to breathe pure oxygen and force nitrogenfrom their blood. Apollo pressure will remain at five

pounds.

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The Docking Module design erphasized low cost con-struction made possible by the launch weight margin in-herent in the use of the Saturn T3 launch vehicln. Thickaluminum plate was used rather than honeycomb, resultingin a considerable reduction in structural cost.Soyuz Spacecraft

The Soviet Soyuz will also be modified. One importantmodif'cation will be the use of a compatible rendezvous anddocking system which NASA and Soviet engineers hiave design-ed. This system will also be employed on the end of th eDocking Module with which Scyuz will dock.Soyuz has been the primary Soviet manned spacecraftsince its introduction in 1967. It consists of three

basic modules:Orbital module, located at the forward end,used by the crew fo r work and rest during orbit. It is3.35 meters (7.3 feet) in diameter., 2.65 meters (8.7 feet)long, and weighs about 1,224 kg (2,700 pounds).Descent module, with main controls and crewcouches, used by crew during launch, descent, and landing.It weighs about 2,802 kg (6,200 pounds) and is 2.2 meters(7.2 feet) long.

* Instrument module, at rear, with subsystemsrequired for power, communications, propulston, and otherfunctions. It weighs 2,654 kg (5,450 pounds) and is 2.3meters (7.5 feet) long.Launch Vehicle

ASTP will utilize Apollo-Skylab Saturn IB launchvehicle hardware. The Saturn IB, consisting of an S-IBstage, an S-XVB stage, and an instrument unit, will launchthe spacecraft from the Kennedy Space Center.

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Documents

ASTP Fact Sheet 1975