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SPACE PROGRAMS

"Vostok"
"Voskhod"
"Salyut"
"Soyuz"
"Almaz"
"Mir"
"Buran"
International Space Station

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"Vostok"

"Vostok" is the name of the series of the Soviet single-seat manned spacecraft and the programme of the low Earth  orbit flights. These spacecraft were created under the direction of Korolyov S.P.

The aims of the "Vostok" programme were as follows:

• investigate orbital flight effects on physical status and performance of a cosmonaut;
• test the spacecraft design principles;
• work out the future spacecraft design and systems.

Main characteristics:
 

Weight	- 4,73 tons;
Maximal mission duration	- 5days.;
Length (without antennas)	- 4,4meters;
Maximal diameter	- 2.43meters.

Complement: The "Vostok" spacecraft consists of two main modules: a descent (orbital) module (DM) and instrument module (IM). These modules are connected together by metal webbing and pyrotechnic latches.

The "Vostok" spacecraft is equipped with:

automatic and manual control system;

automatic orientation to the Sun and manual orientation to the Earth system;

life support system (LSS);

electric power supply system;

thermal mode control system;

touchdown system;

radio telemetry equipment;

command radio link;

TV system intended for observing a cosmonaut from the ground;

orbital tracking and navigation radio system;

deorbit propulsion system TDU-1.

Launches in the frame of the "Vostok" programme

First flight Date of launch: 12/04/1961 Vehicle Commander: Gagarin Yu.A. Mission duration: 108 minutes	Fourth flight Date of launch: 12/08/1962 Date of landing: 15/08/1962 Vehicle Commander: Popovich P.R. Mission duration: 70 hours 44 minutes
Second flight Date of launch: 06/08/1961 Date of landing: 07/08/1961 Vehicle Commander: Titov G.S. Mission duration: 25 hours 11 minutes	Fifth flight Date of launch: 14/06/1963 Date of landing: 19/06/1963 Vehicle Commander: Bykovsky V.F. Mission duration: 118 hours 56 minutes
Third flight Date of launch: 11/08/1962 Date of landing: 15/08/1962 Vehicle Commander: Nikolayev A.G. Mission duration: 94 hours 10 minutes	Sixth flight Date of launch:16/06/1963 Date of landing: 19/06/1963 Vehicle Commander: Tereshkova V.V. Mission duration: 70 hours 40 minutes

 

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"Voskhod"

"Voskhod" is the name of the series of the Soviet multiseat spacecraft and the programme of the low earth orbit flights. These spacecraft were created under the direction of Korolyov S.P.

The aims of the "Voskhod" programme were as follows:
 

work out cooperation of crew members during flight; investigate capabilities of a man to work in outer space; perform bio-medical investigations; conduct technical experiments.

Main characteristics:
 

Length	- 5 meters;
Diameter	- 2,43 meters;
Weight	- 5,32 tons;
Descent module weight	- 2,9 tons.

The designs of the "Voskhod" and "Vostok" spacecraft are similar. The "Voskhod" series spacecraft are additionally equipped with:

soft landing system; backup solid rocket motor; new instrumentation (additional ionic sensor-based orientation system, modified TV and radio systems, etc.)

Launches in the frame of the "Voskhod" programme

First flight
Date of launch: 12/10/1964.
Date of landing: 13/10/1964.
Crew members:
Crew Commander – Komarov V.M.,
Scientific worker – Feoktistov K.P.,
Doctor – Yegorov B.B.
Mission duration: 24 hours 17 minutes.

Mission aims: spacecraft testing; investigations of cosmonaut work capacity and cooperation of different specialists – crew members; physical, technical, and bio-medical experiments.

Second flight
Date of launch: 18/03/1965.
Date of landing: 19/03/1965.
Crew members:
Crew Commander – Belyaev P.I.,
Second pilot –Leonov A.A.
Mission duration: 26 hours 02 minutes.
Mission aims: exit of a man into outer space; investigation of a possibility of working in outer space; bio-medical experiments.

The general-arrangement diagram and system complement of the "Voskhod" and "Vostok" spacecraft are similar.
The "Voskhod" series spacecraft included additionally:

air lock chamber, air locking system , elements of EVA support and control system.

The lock chamber is attached to the external surface (on the upper hemisphere) of the descent module. During the spacecraft insertion to orbit the lock chamber is folded. In orbit it is repressurized and fixed in the needed position. The cylindrical lock chamber has two hatches: one is used for communication with the descent module and another – for exit into outer space and coming back. The lock chamber provides pressure integrity of the descent module during EVA.

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"Salyut"

"Salyut" is the name of the series of the Soviet orbital stations (OS) intended for flying in orbit around the Earth. Space flights were performed in manned and unmanned modes.

Purpose

Stations of the "Salyut" series are intended to solve different scientific and technological problems, among them:
 

bio-medical researches with the aim to study the long-duration spaceflight effects on human body; astrophysical investigations in different wavelength ranges; investigations of the Earth including its surface and atmosphere; conduction of scientific and technical experiments as well as development of some technological processes in weightless environment; evaluation of the orbital stations and equipment design concepts.

Main characteristics:
 

Weight of completely fueled and equipped orbital   station after insertion to the satellite orbit	- 18.9 tons
Weight of scientific equipment	- up to 2.5 tons
Number of crew members	- up to 6 persons
Maximal mission duration of a crew	- 237 days
Length	- 13.6-16.0 meters
Maximal diameter of the station body	- 4.15 meters
Length of solar arrays	- 16.4 meters
Volume of habitable modules	- 82.5 m2
Free volume	- 47 m2
Number of pressurized modules	- 3

Crews and payloads intended for the first modifications of the "Salyut" orbital station were delivered aboard the "Soyuz" spacecraft. Besides, the "Soyuz-T" spacecraft and the "Progress" cargo transportation vehicles were used for delivering crews and payload to the "Salyut-6" and "Salyut-7" modifications.

The "Salyut" orbital station consists of a pressurized transfer compartment, working compartment, intermediate chamber, and nonpressurized instrument module as well.

The "Salyut" orbital station has the following onboard systems:
 

attitude and motion control system, which provides orientation of the station in manual or automatic modes; thermal mode control system; radio communication system; electric power supply system; docking system; onboard complex control system; life support system; scientific equipment.

The equipment complement of the module may be changed depending on mission objectives. The rendezvous radio system's antennas, sensors, plants of the temperature control system, scientific equipment, etc. are located outside. Two solar arrays are mounted on the instrument module of the station first modification. Externally the module is protected by vacuum shield thermal insulation. During insertion to the satellite orbit the instrument module is faired. The fairing ejection occurs after passing through the dense layers of the atmosphere.

Missions of the "Salyut" stations

Orbital station	Date of launch and activity termination	Number of spacecraft, performed docking	Number and duration of expeditions	Main mission results
"Salyut"	19.04 - 11.10 1971	2	One: 22 days	Testing of equipment and instrumentation operational capacity and design quality. Complex scientific and technological researches and experiments.
"Salyut - 4"	26.12.1974 - 3.02.1977	3	Two: 28 and 63 days	Complex scientific and technological researches and experiments.
"Salyut - 6"	29.09.1977 - 29.07.1982	31	5 primary: 96,139,174, 185,74 days; 11 visits: from 3 to 12 days	Complex scientific and technological researches and experiments; EVA operations; preventive maintenance
"Salyut - 7"	19.04.1982 - 1987	11	5 primary: 211,150, 237,112, 65,125 days; 3 visits – to 8 days, 4-th visit – 12 days	Complex scientific and technological researches and experiments. Working out of modified systems and equipment.



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"Soyuz"

The "Soyuz" spacecraft creation activity began in 1962. The launches of the unmanned modifications started in 1966.

The Chief Designer is Korolyov Sergey Pavlovich

The "Soyuz" spacecraft was created at NPO "Energia".

The "Soyuz" spacecraft are intended for:

• working out autonomous navigation, control, maneuvering, rendezvous and docking operations,
• investigation of long-duration spaceflight effects on human body,
• evaluation of principles of the manned spacecraft use for the Earth investigation purposes in the national economy interests,
• evaluation of principles of the manned spacecraft use for transport operations,
• conduction of scientific and technological experiments in space.

Main characteristics:

 

Weight	- up to 6.8 tons
Length	- 7.13 meters
Diameter	- 2.72 meters
Solar arrays span	- 8.37 meters
Internal pressurized volume	- 10.45 m3

The "Soyuz" spacecraft comprises three main modules, they are:

• orbital module;
• descent module;
• equipment bay.

Main equipment:

• attitude and motion control system;
• reaction control system jets;
• approach-correction engine;
• touch-down and soft landing system;
• life support system;
• onboard instrumentation and equipment control system;
• radio communication, electric power supply, docking, radio guidance, rendezvous and docking systems.

The parameters of the "Soyuz" spacecraft orbit are the following:

 

perigee, km	- 183 – 208,
apogee, km	- 220 – 293,
inclination, deg.	- 51.6,
period of revolution, min	- 89.0

Launches in the frame of the "Soyuz" programme

40 spacecraft of the "Soyuz" series were put into orbit from 1967 to 1981, among them 3 unmanned spacecraft: "Soyuz-2", "Soyuz-20" and "Soyuz-34".

Mission objectives were as follows:

• The "Soyuz-1" spacecraft was launched on April 23, 1967 with the aim to test the vehicle, onboard systems and equipment. The vehicle commander Komarov V.M. perished because of a parachute system failure during landing.
• During the joint flight of the "Soyuz-2" (unmanned) and "Soyuz-3" (commander – Beregovoy G.T.)  spacecraft  rendezvous and maneuvering systems were tested and worked out.
• During the joint flight of the "Soyuz-4" (commander –Shatalov V.A.) and "Soyuz-5" (crew: Volynov B.V., Yeliseev A.S., Khrunov Ye.V.) spacecraft  automatic rendezvous and manual berthing and docking were performed. After docking two cosmonauts moved from one spacecraft into another through open space.
• During the joint flight of the "Soyuz-6" (crew: Shonin G.S., Kubasov V.N.), "Soyuz-7" (crew: Filipchenko A.V., Volkov V.N., Gorbatko V.B.) and "Soyuz-8" (crew: Shatalov V.A., Yeliseev A.S.) spacecraft the navigational equipment was tested and interaction between several spacecraft and between spacecraft and ground mission control stations was worked out as well as the simultaneous  control of three spacecraft.
• During the "Soyuz-9" spacecraft flight (crew: Nikolayev A.G., Sevastyanov V.I.) means needed for long-duration missions without creation the artificial gravity environment were worked out.
• The "Soyuz-10, 11, 14, 17, 18, 21, 24, 26 to 32, 35 to 40" provided crews delivery to the station and their return.
• The  "Soyuz –15", "Soyuz – 23", "Soyuz – 25" and "Soyuz – 33" spacecraft docking with the orbital station did not take place because of the onboard equipment failures so they performed autonomous flights.
• During the "Soyuz –12" spacecraft flight (crew: Lazarev V.G., Makarov O.G.) the system of a crew rescue in emergency depressurization was worked out.
• During the "Soyuz –13" spacecraft flight (crew: Klimuk P.I., Lebedev V.V.) asrtophysical observations and spectrography in ultraviolet range were performed with the help of the telescope complex.
• During the "Soyuz – 16" spacecraft flight (crew: Filipchenko A.V., Rukavishnikov N.N.) testing of the onboard equipment modified for the joint Soviet-American flight purposes was performed.
• In the frame of the International Programme APAS the "Soyuz – 19" spacecraft flight (crew: Leonov A.A., Kubaso v V.N.) was performed. Two docking with the "Apollo" American spacecraft and five joint scientific and technological experiments were conducted.
• During the "Soyuz – 20" spacecraft flight the vehicle life tests were conducted.
• The "Soyuz – 22" spacecraft flight (crew: Bykovsky V.F., Aksenov V.V.) was performed for the purpose of working out equipment and methods of the Earth investigation from space in the Interkosmos programme frame.

 

The following vehicles were created on the basis of the "Soyuz" spacecraft:

• "Progress" transport vehicle;
• "Soyuz – T" spacecraft;
• "Soyuz TM" spacecraft.

 

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"Almaz"

The creation of the complex began in 1965. The preliminary design was developed and approved by an inter-departmental board in 1967.
The Chief Designer is Chelomey Vladimir Nikolaevich.
The "Almaz" rocket and space complex was created at the Central design bureau of machine manufacturing.

The rocket and space complex comprises:
 

base module; resupply transport vehicle fitted out with a return vehicle; "Proton" launch vehicle.

Main characteristics:
 

Weight	- 18.9 tons
Length	- 11.61 meters
Diameter	- 4.14 meters
Internal pressurized volume	- 90 m3

The orbital manned station consists of pressurized and nonpressurized modules.

Purpose designed equipment:
 

"Agat -1" apparatus, comprised a big optical telescope and ASA-34R roll-film camera; onboard film developing machine; "Pechora" television apparatus; onboard information retrieval system; OD-5 optical measuring sight; POU-11 panoramic observation device.

The parameters of the "Almaz" station orbit:
 

perigee, km	- 215 – 219,
apogee, km	- 260 – 270,
inclination, deg.	- 51.6,
period of revolution, min	- 89.0

Launches in the frame of the "Almaz" programme

The first station of "Almaz"(OMS-1, № 101) was launched on April 3, 1973. After insertion to the orbit it received a name of "Salyut –2". During unmanned flight depressurization of the station occurred and telemetry information ceased to come.  The station activity was terminated on May 28, 1973.

The second station of "Almaz" (OMS-2, № 102) was launched on June 25, 1974.
After insertion to the orbit it received a name of "Salyut – 3".

The first expedition (3/7 – 19/7/1974) was delivered to the station aboard the "Soyuz –14" spacecraft. Crewmembers:
 

Popovich Pavel Romanovich, Artyukhin Yury Petrovich.

Mission duration – 15 days.

The second expedition was launched aboard the "Soyuz-15" spacecraft on August 28, 1974 and performed an autonomous flight because of a rendezvous and docking system failure. Crewmembers:

Sarafanov Gennady Vasilyevich,  Demin Lev Stepanovich

The termination of the station activity took place on January 24, 1975.

The third station "Almaz" (OMS-3) was launched on June 22, 1976. After insertion to the orbit it received a name of "Salyut -5".

The first expedition (6/7 – 24/8/1976) was delivered to the station aboard the "Soyuz-21" spacecraft. Crewmembers:
 

Volynov Boris Valentinovich, Zholobov Vitaly Mikhaylovich.

Mission duration – 49 days.

The second expedition (7/2 – 25/2/1977) was delivered to the station aboard the "Soyuz 24" spacecraft. Crewmembers:
 

Gorbatko Viktor Vasilyevich, Glazkov Yury Nikolayevich.

Mission duration – 17 days.

The termination of the station activity took place on August 8, 1977.

Scientific and technical experience acquired in the course of the "Almaz" programme fulfilment was successfully used for development of the next orbital stations: "Salyut", "Mir", and ISS.



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"Mir" long-term orbital station

Purpose

The purposes of the "Mir" long-term orbital station are as follows:
 

provide structural integrity of all modules included in the manned orbital complex; provide centralized control of all modules included in the manned orbital complex; provide crew life and work support environment during a long duration flight; correct the complex's orbital parameters using the own propulsion system and propulsion systems of modules and cargo transport vehicles as well; maintain the complex orientation (liquid propellant jet engines and gyroscopic stabilizers can be used as actuating devices); provide a centralized data exchange with the ground mission control complex; provide all objects included in the complex with electrical power as well as the transport vehicle's storage batteries recharge; maintain the preset air temperature, ventilation, and drying regime; accept and accommodate payloads delivered by Shuttles and cargo transport vehicles for the purpose of resupplying the "Mir" manned complex's systems; provide the EVA operations of two crew members.

 

Main characteristics: Insertion orbit altitude: Hmin= 179 km;Hmax= 325 km; Operational orbit altitude: H= 350 - 400 km; Inclination: i = 51.6o; Launch weight: 20 tons; Maximal length (of the body): 13 meters; Solar array span: 30 meters;  Volume (of gas): 80 m3

Design

The "Mir" station base unit comprises:
 

transfer compartment; working compartment; transfer chamber.

These modules of the base unit are pressurized and intended for living and working of human beings and accommodation of the main part of onboard systems, equipment, and payloads.

The working compartment comprises:

small diameter working area; cone; large diameter working area; lock chamber.

The instrumental module and nose fairing which protects the transfer and working compartments from aerodynamic and thermal loads during insertion to orbit are the nonpressurized modules of the "Mir" base unit. The nose fairing ejection occurs after passing the dense layers of atmosphere.

There are ten windows in the pressurized module of the "Mir" base unit.
 

The following modules are docked to the base unit:
special-purpose experiment module ("Kvant");
special-purpose add-on module ("Kvant-2");
special-purpose technological module ("Kristall");
"docking module" compartment;
special-purpose scientific module (Priroda);
special-purpose optical module ("Spectr").

Special-purpose experiment module ("Kvant")

The "Kvant" module was docked to the "Mir" orbital station on May 31, 1987. The purpose of the module is to provide operation of the base module, extension of the scientific research programme, and developing advanced life support systems.

The module comprises three compartments, they are:
 

nonpressurized intermediate compartment, which provides the module docking to the launch vehicle; pressurized laboratory compartment, intended for accommodation of the onboard systems and equipment; nonpressurized scientific instrumentation compartment, intended for accommodation of the spectrometric equipment.

Main technical characteristics:
 

Length	- 5800 mm;
Extreme diameter	- 4100 mm;
Volume	- 40 m3
Transfer chambers diameter	- 800 mm.

There are three windows in the module.

Special –purpose add-on module ("Kvant-2")

The "Kvant-2" module was docked to the "Mir" orbital station on December 6, 1989. The purpose of the module is to resupply the station with the special-purpose equipment, EVA support aids, life support means and electric power supply as well as replacement units and plants.

The special-purpose equipment allows performing of scientific and applied researches and conduction of experiments pertaining to the national economy.

The EVA support equipment allows the EVA operations to be made both with the use of cosmonaut translational aids and without them.

The module comprises three compartments, they are:
 

cargo instrumentation compartment, intended for accommodation of the main part of onboard system units; scientific instrumentation compartment, intended for accommodation of scientific equipment and also preparation, air locking and reverse air locking of cosmonauts if the special air lock compartment is unpressurized or when operating with large-size equipment; special air lock compartment, intended for accommodation of the equipment needed for preparation, air locking operations, EVA operations support and reverse air locking of cosmonauts.

Main technical characteristics:
 

Maximal diameter	- 4 100 mm
Length	- 13 000 mm;
Orbital mass	- 19 500 kg;
Module span (solar array)	- 24 000 mm;
Electrical power supply	- 6.3 kW;
Transfer hatches diameter	- 800 mm;
Exit hatch diameter	- 1 000 mm;
Cargo instrumentation compartment volume	- 45 m3;
Scientific instrumentation compartment volume	- 8 m3;
Special air lock compartment	- 8 m3.

There are five windows in the module.

Special-purpose technological module ("Kristall")

The "Kristall" module was docked to the "Mir" orbital station on June 10, 1990.

The purpose of the module is to resupply the station with the special-purpose equipment, androgynous peripheral docking system, electric power supply systems as well as replacement units and plants.

The special-purpose equipment allows performing of scientific and applied researches and conduction of experiments pertaining to the national economy.

The androgynous peripheral docking system is intended to support docking with the "Buran" and Space Shuttle type reusable vehicles and also rescue transport vehicle.

The module comprises two pressurized compartments, they are:
 

cargo instrumentation compartment, intended to accommodate the majority of the onboard system units and scientific equipment; instrument and docking compartment, intended to accommodate a part of scientific equipment and equipment needed for docking with vehicles of the "Buran", Shuttle, and rescuer type.

Main technical characteristics:
 

Maximal diameter	- 4 100 mm
Length	- 13 000 mm;
Orbital mass	- 19 500 kg;
Module's solar array span	- 28 000 mm;
Electrical power supply	- 7.0 kW;
Transfer hatches diameter	- 800 mm;
Cargo instrumentation section volume	- 45 m3;
Instrument and docking compartment volume	- 16 m3;

There are four windows in the module.

"Docking module" compartment

The docking module was inserted to the orbit on November 12, 1995 and docked to the "Kristall" module.

Main technical characteristics:

Length	- 5094 mm;
Diameter	- 2200 mm;
Volume	- 13.7 m3.

The purpose of the module is to provide safe docking of the Space Shuttles with the "Mir" orbital station in the frame of the "Mir"- NASA programme.

Special-purpose scientific module "Priroda"

The special-purpose scientific module "Priroda" is intended for:
 

remote sensing of the Earth to solve fundamental and applied ecological and nature resources problems; getting of extra pure biological preparations under weightlessness conditions; investigations with the use of NASA instrumentation in the frame of the ISS programme, among them: bio-technical experiments (protein crystal growth); gas analysis systematization of the "Mir" orbital station; experiments in the field of materials science.

The "Priroda" special purpose module comprises a pressurized cargo instrumentation compartment and nonpressurized instrument compartment. The purpose of a cargo instrumentation compartment is to accommodate onboard systems and the main part of the scientific instruments. The purpose of an instrument compartment is to accommodate the units of scientific equipment.

Main characteristics of the "Priroda" module:
 

Launching weight	- 22 000 kg;
Scientific equipment installed weight	- 2 400 kg;
Length	- 13 000 mm;
Extreme diameter	- 4 100 mm;
Transfer hatch diameter	- 800 mm.

There are no solar arrays on the "Priroda" module.

The "Priroda" module's system complement:
 

onboard complex control system; automatic re-docking system; telephone/telegraph communications system; thermal control system; data collection system; TV system; jet operation support means; pressure control means; fire detection and fire suppression system; electric power supply system; lighting equipment.

"Spektr" special-purpose optical module

The purpose of the module is to resupply the station with Soviet and American scientific equipment, intended for investigation of the upper atmosphere and the Earth natural resources, electric power supply means, consumables and replacement loads.
The station onboard systems provide the module operation while it is docked.
The "Spektr" module comprises a pressurized cargo instrumentation compartment and nonpressurized compartment.

The main characteristics of the "Spektr" module:
 

Launching weight	- 22 000 kg;
Payload weight	- 2 400 kg;
Length	- 13 000 mm;
Extreme diameter	- 4 100 mm;
Module's main solar array span	- 25 000 mm;
Module's auxiliary solar array span	- 25 000 mm;
Solar arrays total power	- 15 kW;
Transfer hatch diameter	- 800 mm.

The "Spektr" module's system complement:
 

onboard complex control system; automatic re-docking system; telephone/telegraph communications system; thermal control system; data collection system; TV system; jet operation support means; pressure control means; fire detection and fire suppression system; electric power supply system; lighting equipment.

Scientific instruments of the "Spektr" module allow conduction of the following experiments:
 

astrophysical; geophysical; bio-medical.

In August, 1998 the "Spektr" module was deactivated because of breakage and the electric power supply of the base unit was provided by auxiliary solar arrays.
 
 



Missions in the framework of the MIR program

In the framework of the Mir program 28 primary and 9 visiting expeditions were achieved; 8 docking of the Shuttle type vehicles were fulfilled.

The first flight was performed by the primary expedition of Kizim L.D. and Solovyov V.A. They stayed aboard Mir station from March 13 till July 16, 1986.

Mission duration - 125 days.

The last flight was performed by the primary expedition of Zalyotin S.V. and Kalery A.Yu. They stayed aboard Mir station from April 4 till June 16, 2000.

Mission duration - 72 days 19 hours.

The total duration of the primary expeditions staying aboard the station is more than 12,348 days. 16 missions of international crews were performed.
Mir station functioned in orbit from February 22, 1986 till March 23, 2001.

Russian Mir Space Station ceased to operate on March 23, 2001. It entered into atmosphere dense layers, flamed and disintegrated. The debris dropped north-west of the expected area in the south part of the Pacific Ocean. Solar arrays were the first to break and then the heated station case disintegrated into fragments.

In its life time the station made 86,331 revolutions around the Earth.

The coordinates of the area of dropping of the Russian Mir Space Station debris are 40° of southern latitude, 160° of western longitude ± 1,000 km along the flight track.

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"Buran"

The creation of the Reusable Space System began in 1976 in accordance with the Government Decree.

The Head Designer is NPO "Enegria".

The Reusable Space System comprises: acceleration stage, orbital aircraft, orbital transfer vehicle, system control complex, launch and landing complex, and maintenance and repair complex.

Characteristics:
 

Launch weight, t	- 2 375;
Total length, m	- 58.765;
Maximal width, m	- 23.92;
Mass of payload, delivered to orbit, t	- up to 30;
Mass of return payload, t	- up to 20;
Number of usage:
orbital vehicle first stage second stage	- 100; - 10; - 1.

Number of crewmembers:

• vehicle crew – 2-4 persons,
• mission specialist – 6-8 persons.

The orbital aircraft characteristics:
 

Length, m	- 36.37;
Wing span, m	- 23.92;
Height at rest, m	- 16.35;
Wheel-base, m	- 7.00;
Payload bay length, m	- 18.55;
Payload bay diameter, m	- 4.7;
Weight, t	- 105;
Propulsion engine thrust, t/s	- 8.8.

In 1978 the GCTC in collaboration with other Ministries and departments began selection of cosmonaut-candidates and their training in the frame of the "Buran" expendable orbital vehicle programme. In pursuance of resolutions of leading bodies a group of test pilots from the USSR Ministry of Defense and Ministry of Air Industry was enrolled with the aim to provide the "Buran" flight tests. Among them were: Volk I.P., Levchenko A.S., Shyukin A.V., Stankyavichus R.A.A., Kononenko O.G. (Ministry of Air Industry) and Bachurin I.I., Chirkin V.M., Boroday A.S., Mosolov V.E., Sokovykh A.M., Sattarov N.Sh. (Ministry of Defense).

From March, 1979 to December, 1980 they completed the course of basic training. With the aim to gain spaceflight experience Volk I.P. was included in the crew of the "Soyuz t-12" spacecraft and took part in the expedition, visited the "Salyut-7" orbital station from 17/7 to 29/7/1984 (Crew: Dzhanibekov V.A., Savitskaya S.E., Volk I.P.). Levchenko A.S. performed spaceflight aboard the "Soyuz TM-4" spacecraft and took part in the expedition, visited the "Mir" orbital station from 21/12 to 29/12/1987.

One more group of test pilots from the Flight and Research Institute of the Ministry of Air Industry and State Test-and Research Institute of Air Force completed the course of basic training in 1985-1987. They were: Afanasyev V.M., Artsebarsky A.P., Manakov G.M., Zabolotsky V.V., Sultanov U.N., Tolboyev M.O., Tresvyatsky S.N., Sheffer Yu.P.

Flight training was performed aboard the analogue of the "Buran" flight model, which had similar dynamic characteristics. Besides, for crew training purpose a specialized pilot training simulator was constructed. It comprised:

• crew cabin mock-up,
• "Buran" analogue motion simulator,
• external visual environment simulator,
• computer,
• instructor panels.

The first flight of the "Buran" unmanned orbital vehicle was performed on November 15, 1988.

The launch took place at 06:00:01,25. The vehicle separated from the central unit at 06:08:00 and settled into orbit with apogee of 154.2 km. After two corrective impulses it was placed into orbit with an altitude of 263-251 km and inclination of 51.6^o. All systems operated in normal mode. On the second orbit passing at 08:20:00 a deceleration impulse of 175 m/s was given. At 09:24:42 the orbital vehicle landed. Its velocity at a moment was 260 km/h. Landing was performed in unmanned mode.

Thereafter works on the rocket and space transportation system "Energia"-"Buran" were ceased.