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- For the launch vehicle of the same name see Soyuz (rocket family)
Soyuz spacecraft (TMA version)
|Country of origin||Soviet Union, Russia|
|Operator||Soviet space program/Russian Federal Space Agency|
|Applications||Carry cosmonauts to orbit and back; originally intended for Soviet Moonshot|
|Design life||Up to six months docked to station|
|Regime||Low Earth orbit (circumlunar spaceflight during early program)|
|First launch||Soyuz 1, 1967|
Soyuz (Russian: Сою́з, IPA: [sɐˈjus]), Union) is a series of spacecraft designed for the Soviet space programme by the Korolyov Design Bureau in the 1960s that remains in service today. The Soyuz succeeded the Voskhod spacecraft and was originally built as part of the Soviet Manned Lunar programme.
The Soyuz spacecraft is launched on a Soyuz rocket, the most frequently used and most reliable launch vehicle in the world to date. The Soyuz rocket design is based on the Vostok launcher, which in turn was based on the 8K74 or R-7A Semyorka, a Soviet intercontinental ballistic missile. All Soyuz spacecraft are launched from the Baikonur Cosmodrome in Kazakhstan.
The first Soyuz flight was unmanned and started on November 28, 1966. The first mission with a crew, Soyuz 1, launched on 23 April 1967 but ended with a crash due to a parachute failure, killing cosmonaut Vladimir Komarov. The following flight was unmanned. Soyuz 3, launched on October 26, 1968, became the program's first successful manned mission. The only other flight to suffer a fatal accident, Soyuz 11, killed its crew of three during re-entry when the cabin depressurized prematurely. Despite these early incidents, Soyuz is widely considered the world's safest, most cost-effective human spaceflight system, established by its unparalleled length of operational history.
Soyuz spacecraft were used to carry cosmonauts to and from Salyut and later Mir Soviet space stations, and are now used for transport to and from the International Space Station (ISS). At least one Soyuz spacecraft is docked to ISS at all times for use as an escape craft in the event of an emergency.
- 1 Design
- 2 Variants
- 3 Related craft
- 4 Operators
- 5 See also
- 6 Missions
- 7 Image gallery
- 8 References
- 9 External links
A Soyuz spacecraft consists of three parts (from front to back):
- A spheroid orbital module, which provides accommodation for the crew during their mission;
- A small aerodynamic reentry module, which returns the crew to Earth;
- A cylindrical service module with solar panels attached, which contains the instruments and engines.
The orbital and service modules are single-use and are destroyed upon re-entry in the atmosphere. The orbital and reentry portions are habitable living space.
Soyuz can carry up to three crew members and provide life support for about 30 person days. The life support system provides a nitrogen/oxygen atmosphere at sea level partial pressures. The atmosphere is regenerated through KO2 cylinders, which absorb most of the CO2 and water produced by the crew and regenerates the oxygen, and LiOH cylinders which absorb leftover CO2.
The vehicle is protected during launch by a nose fairing, which is jettisoned after passing through the atmosphere. It has an automatic docking system. The ship can be operated automatically, or by a pilot independently of ground control.
The forepart of the spacecraft is the orbital module (Russian: бытовой отсек (БО); Bytovoi otsek (BO)), also known as Habitation section. It houses all the equipment that will not be needed for reentry, such as experiments, cameras or cargo. The module also contains a toilet, docking avionics and communications gear. Internal volume is 6 m³, living space 5 m³. On the latest Soyuz versions (since Soyuz TM), a small window was introduced, providing the crew with a forward view.
A hatch between it and the descent module can be closed so as to isolate it to act as an airlock if needed, crew members exiting through its side port (near the descent module). On the launch pad, the crew enter the spacecraft through this port.
This separation also lets the orbital module be customized to the mission with less risk to the life-critical descent module. The convention of orientation in zero gravity differs from that of the descent module, as crew members stand or sit with their heads to the docking port. Also the rescue of the crew whilst on the launch pad or with SAS system is complicated because of the orbital module.
Separation of the Orbital Module is critical for a safe landing. Without separation of the Orbital Module it is not possible for the crew to survive landing in the Descent Module. In view of this, the orbital module was separated before the ignition of the return engine until the late 1980s. This guaranteed that the Descent Module and Orbital Module would be separated before the Descent Module was placed in a reentry trajectory. However, after the problematic landing of Soyuz TM-5 in September 1988 this procedure was changed and the Orbital Module is now separated after the return maneuver. This change was made as the TM-5 crew could not deorbit for 24 hours after they jettisoned their Orbital Module, which contained their sanitation facilities and the docking collar needed to attach to MIR. The risk of not being able to separate the Orbital Module is effectively judged to be less than the risk of needing the facilities in it, following a failed deorbit.
The reentry module (Russian: спускаемый аппарат (СА); Spuskaemyi apparat (SA)) is used for launch and the journey back to Earth. Half of the reentry module is covered by a heat-resistant covering to protect it during re-entry; this half faces the Earth during re-entry. It is slowed initially by the atmosphere, then by a braking parachute, followed by the main parachute which slows the craft for landing. At one meter above the ground, solid-fuel braking engines mounted behind the heat shield are fired to give a soft landing. One of the design requirements for the reentry module was for it to have the highest possible volumetric efficiency (internal volume divided by hull area). The best shape for this is a sphere, but such a shape can provide no lift, which results in a purely ballistic reentry. Ballistic reentries are hard on the occupants due to high deceleration and cannot be steered beyond their initial deorbit burn. That is why it was decided to go with the "headlight" shape that the Soyuz uses—a hemispherical forward area joined by a barely angled conical section (seven degrees) to a classic spherical section heat shield. This shape allows a small amount of lift to be generated due to the unequal weight distribution. The nickname was thought up at a time when nearly every headlight was circular. Small dimensions of the reentry module led to it having only two-man crews after the death of the Soyuz 11 crew. The later Soyuz T spacecraft solved this issue. Internal volume of Soyuz SA is 4 m³; 2.5 m³ is usable for crew (living space).
At the back of the vehicle is the service module (Russian: приборно-агрегатный отсек (ПАО); Priborno-Agregatnyi Otsek (PAO)). It has a pressurized container shaped like a bulging can (Instrumentation compartment, PO (Priborniy Otsek)) that contains systems for temperature control, electric power supply, long-range radio communications, radio telemetry, and instruments for orientation and control. A non-pressurized part of the service module (Propulsion compartment, AO (Agregatniy Otsek)) contains the main engine and a liquid-fuelled propulsion system for maneuvering in orbit and initiating the descent back to Earth. The ship also has a system of low-thrust engines for orientation, attached to the Intermediate compartment (PkhO or Perekhodnoi Otsek). Outside the service module are the sensors for the orientation system and the solar array, which is oriented towards the sun by rotating the ship. An incomplete separation between the Service and Reentry modules led to emergency situations during Soyuz 5, Soyuz TMA-10 and Soyuz TMA-11, which led to an incorrect reentry orientation (crew ingress hatch first). The failure of several explosive bolts did not cut the connection between the Service/Reentry modules on the latter two flights.
The Soyuz uses a method similar to the Apollo to deorbit itself. The spacecraft is turned engine-forward and the main engine is fired for deorbiting fully 180° ahead of its planned landing site. This requires the least propellant for re-entry, the spacecraft traveling on an elliptical Hohmann orbit to a point where it will be low enough in the atmosphere to re-enter.
Early Soyuz spacecraft would then have the service and orbital modules detach simultaneously from the reentry module. As they are connected by tubing and electrical cables to the reentry module, this would aid in their separation and avoid having the descent module alter its orientation. Later Soyuz spacecraft detached the orbital module before firing the main engine, which saved propellant. Since the Soyuz TM-5 landing issue, the orbital module is once again detached only after the re-enter firing, which led to (but did not cause) emergency situations of Soyuz TMA-10 and TMA-11. The orbital module cannot remain in orbit as an addition to a space station, as the airlock hatch between the orbital and reentry modules is a part of reentry module, and the orbital module therefore depressurizes after separation.
Re-entry firing is usually done on the "dawn" side of the earth, so that the spacecraft can be seen by recovery helicopters as it descends in the evening twilight, illuminated by the sun when it is above the shadow of the Earth. The Soyuz craft is designed to come down on land, usually somewhere in the deserts of Kazakhstan in central Asia. This is in contrast to early US manned missions which "splashed down" in the ocean.
- Thermal Control System—Sistema Obespecheniya Teplovogo Rezhima, SOTR
- Life Support System—Kompleks Sredstv Obespecheniya Zhiznideyatelnosti, KSOZh
- Power Supply System—Sistema Elektropitaniya, SEP
- Communication and Tracking Systems—Rassvet (Dawn) radio communications system, Onboard Measurement System (SBI), Kvant-V spacecraft control, Klyost-M television system, Orbit Radio Tracking (RKO)
- Onboard Complex Control System—Sistema Upravleniya Bortovym Kompleksom, SUBK
- Combined Propulsion System—Kompleksnaya Dvigatelnaya Ustanovka, KDU
- Chaika-3 Motion Control System (SUD)
- Optical/Visual Devices (OVP)—VSK-4 (Vizir Spetsialniy Kosmicheskiy-4), Night Vision Device (VNUK-K, Visir Nochnogo Upravleniya po Kursu), Docking light, Pilot's Sight (VP-1, Vizir Pilota-1), Laser Range Finder (LPR-1, Lazerniy Dalnomer-1)
- Kurs rendezvous system
- Docking System—Sistema Stykovki i Vnutrennego Perekhoda, SSVP
- Teleoperator Control Mode—Teleoperatorniy Rezhim Upravleniya, TORU
- Entry Actuators System—Sistema Ispolnitelnikh Organov Spuska, SIO-S
- Landing Aids Kit—Kompleks Sredstv Prizemleniya, KSP
- Portable Survival Kit—Nosimiy Avariyniy Zapas, NAZ, containing a TP-82 or other pistol
- Soyuz Launch Escape System—Sistema Avariynogo Spaseniya, SAS
- Soyuz spacecraft
- Orbital module (A)
- 1 docking mechanism,
- 2 Kurs antenna,
- 4 Kurs antenna,
- 3 television transmission antenna,
- 5 camera,
- 6 hatch
- Descent module (B)
- 7 parachute compartment,
- 8 periscope,
- 9 porthole,
- 11 heat shield
- Service module (C)
- 10 and 18 attitude control engines,
- 21 oxygen tank,
- 12 Earth sensors,
- 13 Sun sensor,
- 14 solar panel attachment point,
- 16 Kurs antenna,
- 15 thermal sensor,
- 17 main propulsion,
- 20 fuel tanks,
- 19 communication antenna
The Soyuz spacecraft has been the subject of continuous evolution since the early 1960s. Thus several different actual versions, proposals and projects exist.
|Version:||Soyuz A (1963)||Soyuz 7K-OK (1967–1971)||Soyuz 7K-L3 (LOK)||Soyuz 7K-T (1973–1981)||Soyuz 7K-TM (1975)||Soyuz-T (1976–1986)||Soyuz-TM (1986–2002)||Soyuz-TMA (2003–2012 )||Soyuz TMA-M (2010–.... )|
|Mass||5,880 kg (12,960 lb)||6,560 kg (14,460 lb)||9,850 kg (21,720 lb)||6,800 kg (15,000 lb)||6,680 kg (14,730 lb)||6,850 kg (15,100 lb)||7,250 kg (15,980 lb)||7,220 kg (15,920 lb)||7,150 kg (15,760 lb)|
|Length||7.40 m (24.3 ft)||7.95 m (26.1 ft)||10.06 m (33.0 ft)||7.48 m (24.5 ft)||7.48 m (24.5 ft)||7.48 m (24.5 ft)||7.48 m (24.5 ft)||7.48 m (24.5 ft)||7.48 m (24.5 ft)|
|Max Diameter||2.50 m (8 ft 2 in)||2.72 m (8 ft 11 in)||2.930 m (9 ft 7.4 in)||2.72 m (8 ft 11 in)||2.72 m (8 ft 11 in)||2.72 m (8 ft 11 in)||2.72 m (8 ft 11 in)||2.72 m (8 ft 11 in)||2.72 m (8 ft 11 in)|
|Span||?||9.80 m (32.2 ft)||?||9.80 m (32.2 ft)||8.37 m (27.5 ft)||10.6 m (35 ft)||10.6 m (35 ft)||10.7 m (35 ft)||10.7 m (35 ft)|
|Orbital Module (BO)|
|Mass||1,000 kg (2,200 lb)||1,100 kg (2,400 lb)||–-||1,350 kg (2,980 lb)||1,224 kg (2,698 lb)||1,100 kg (2,400 lb)||1,450 kg (3,200 lb)||1,370 kg (3,020 lb)|
|Length||3.00 m (9.84 ft)||3.45 m (11.3 ft)||2.26 m (7.4 ft)||2.98 m (9.8 ft)||3.10 m (10.2 ft)||2.98 m (9.8 ft)||2.98 m (9.8 ft)||2.98 m (9.8 ft)|
|Diameter||2.20 m (7.2 ft)||2.25 m (7.4 ft)||2.30 m (7.5 ft)||2.26 m (7.4 ft)||2.26 m (7.4 ft)||2.26 m (7.4 ft)||2.26 m (7.4 ft)||2.26 m (7.4 ft)|
|Volume||2.20 m3 (78 cu ft)||5.00 m3 (177 cu ft)||–-||5.00 m3 (177 cu ft)||5.00 m3 (177 cu ft)||5.00 m3 (177 cu ft)||5.00 m3 (177 cu ft)||5.00 m3 (177 cu ft)|
|Reentry module (SA)|
|Mass||2,480 kg (5,470 lb)||2,810 kg (6,190 lb)||2,804 kg (6,182 lb)||2,850 kg (6,280 lb)||2,802 kg (6,177 lb)||3,000 kg (6,600 lb)||2,850 kg (6,280 lb)||2,950 kg (6,500 lb)|
|Length||2.30 m (7.5 ft)||2.24 m (7.3 ft)||2.19 m (7.2 ft)||2.24 m (7.3 ft)||2.24 m (7.3 ft)||2.24 m (7.3 ft)||2.24 m (7.3 ft)||2.24 m (7.3 ft)|
|Diameter||2.17 m (7.1 ft)||2.17 m (7.1 ft)||2.2 m (7.2 ft)||2.17 m (7.1 ft)||2.17 m (7.1 ft)||2.17 m (7.1 ft)||2.17 m (7.1 ft)||2.17 m (7.1 ft)|
|Volume||4.00 m3 (141 cu ft)||4.00 m3 (141 cu ft)||–-||3.50 m3 (124 cu ft)||4.00 m3 (141 cu ft)||4.00 m3 (141 cu ft)||3.50 m3 (124 cu ft)||3.50 m3 (124 cu ft)|
|Service module (PAO)|
|Mass||2,400 kg (5,300 lb)||2,650 kg (5,840 lb)||––||2,700 kg (6,000 lb)||2,654 kg (5,851 lb)||2,750 kg (6,060 lb)||2,950 kg (6,500 lb)||2,900 kg (6,400 lb)|
|Usable fuel (kg)||830 kg (1,830 lb)||500 kg (1,100 lb)||3,152 kg (6,949 lb)||500 kg (1,100 lb)||500 kg (1,100 lb)||700 kg (1,500 lb)||880 kg (1,940 lb)||880 kg (1,940 lb)|
|Length||2.10 m (6.9 ft)||2.26 m (7.4 ft)||2.82 m (9.3 ft)||2.26 m (7.4 ft)||2.26 m (7.4 ft)||2.26 m (7.4 ft)||2.26 m (7.4 ft)||2.26 m (7.4 ft)|
|Diameter||2.50 m (8.2 ft)||2.72 m (8.9 ft)||2.20 m (7.2 ft)||2.72 m (8.9 ft)||2.72 m (8.9 ft)||2.72 m (8.9 ft)||2.72 m (8.9 ft)||2.72 m (8.9 ft)|
Soyuz 7K (part of the 7K-9K-11K circumlunar complex) (1963)
Korolyov initially promoted the Soyuz A-B-V circumlunar complex (7K-9K-11K) concept (also known as L1) in which a two-man craft Soyuz 7K would rendezvous with other components (9K and 11K) in Earth orbit to assemble a lunar excursion vehicle, the components being delivered by the proven R-7 rocket.
The manned Soyuz spacecraft can be classified into design generations. Soyuz 1 through Soyuz 11 (1967–1971) were first-generation vehicles, carrying a crew of up to three without spacesuits and distinguished from those following by their bent solar panels and their use of the Igla automatic docking navigation system, which required special radar antennas. This first generation encompassed the original Soyuz 7K-OK and the Soyuz 7K-OKS for docking with the Salyut 1 space station. The probe and drogue docking system permitted internal transfer of cosmonauts from the Soyuz to the station.
The Soyuz 7K-L1 was designed to launch a crew from the Earth to circle the moon, and was the primary hope for a Soviet circumlunar flight. It had several test flights in the Zond program from 1967–1970 (Zond 4 to Zond 8), which produced multiple failures in the 7K-L1's re-entry systems. The remaining 7K-L1s were scrapped. The Soyuz 7K-L3 was designed and developed in parallel to the Soyuz 7K-L1, but was also scrapped. Soyuz 1 was plagued with technical issues, and cosmonaut Vladimir Komarov was killed when the spacecraft crashed during its return to Earth. This was the first in-flight fatality in the history of spaceflight.
The next manned version of the Soyuz was the Soyuz 7K-OKS. It was designed for space station flights and had a docking port that allowed internal transfer between spacecraft. The Soyuz 7K-OKS had two manned flights, both in 1971. Soyuz 11, the second flight, depressurized upon re-entry, killing its three-man crew.
It was developed out of the military Soyuz concepts studied in previous years and was capable of carrying 2 cosmonauts with Sokol space suits (after the Soyuz 11 accident). Several models were planned, but none actually flew in space. These versions were named Soyuz P, Soyuz PPK, Soyuz R, Soyuz 7K-VI, and Soyuz OIS (Orbital Research Station).
Soyuz 7K-TM was the spacecraft used in the Apollo-Soyuz Test Project in 1975, which saw the first and only docking of a Soyuz spacecraft with an Apollo Command/Service Module. It was also flown in 1976 for the earth-science mission, Soyuz 22. Soyuz 7K-TM served as a technological bridge to the third generation.
The third generation Soyuz-T (T: транспортный, Transportnyi meaning transport) spacecraft (1976–1986) featured solar panels allowing longer missions, a revised Igla rendezvous system and new translation/attitude thruster system on the Service module. It could carry a crew of three, now wearing spacesuits.
The Soyuz-TM crew transports (M: модифицированный, Modifitsirovannyi meaning modified) were fourth generation Soyuz spacecraft, and were used from 1986 to 2003 for ferry flights to Mir and the International Space Station.
Soyuz TMA (A: антропометрический, Antropometricheskii meaning anthropometric) features several changes to accommodate requirements requested by NASA in order to service the International Space Station, including more latitude in the height and weight of the crew and improved parachute systems. It is also the first expendable vehicle to feature "glass cockpit" technology. Soyuz-TMA looks identical to a Soyuz-TM spacecraft on the outside, but interior differences allow it to accommodate taller occupants with new adjustable crew couches.
Soyuz TMA-M (2010—present time)
The Soyuz TMA-M is an upgrade of the baseline Soyuz-TMA, using a new computer, digital interior displays, updated docking equipment and vehicle's total mass has been reduced by 70 kilograms. This new version debuted on 7 October 2010 with the launch of TMA-01M, carrying the ISS Expedition 25 crew.
The Soyuz TMA-08M set a new record for the fastest manned docking into space station, event utilized the new 6-hour fast rendezvous instead of the previous Soyuz launches which had, since 1986, taken two days.
Soyuz MS (2016—)
- more power efficient solar panels
- modified docking and altitude control engines for increased fault tolerance during docking and deorbit burns
- new approach and docking system
- improved communications system
- new TsVM-101 computer almost one tenth the weight (8.3 kg vs. 70 kg) and much smaller than the previous Argon-16 computer
- unified digital command/telemetry system (MBITS) allows to receive telemetry from spacecraft via satellite and control it when it's out of sight of ground stations
- employment of GLONASS/GPS and Cospas-Sarsat satellite systems during search/rescue operations of descent module after landing
The unmanned Progress spacecraft were derived from Soyuz and are used for servicing space stations.
In December 1961, General Electric published the proposal they had submitted to NASA for an Apollo spacecraft feasibility study, at the American Astronautical Society symposium in Denver, CO. GE's design had a separate mission module, and a reentry module shaped similarly to the Russian Soyuz design.
- ISRO Orbital Vehicle
- Orbital Technologies Commercial Space Station
- Sokol space suit
- Space exploration
- Space Shuttle orbiter - American equivalent from 1981 to 2011
- Human spaceflight
- Crew Space Transportation System study to develop a European-Russian successor to Soyuz
- Voskhod Spacecraft "Globus" IMP navigation instrument
- Zarya spacecraft project
- "Soyuz launch vehicle: The most reliable means of space travel". European Space Agency. Retrieved 29 March 2013.
- "France and Russia agree: Soyuz will launch from Kourou in French Guyana". SpaceRef. October 22, 2003. Retrieved 29 March 2013.
- Alan Boyle (September 29, 2005). "Russia thriving again on the final frontier". MSNBC. Retrieved 29 March 2013.
- Anatoly Zak (June 30, 2011). "Russia to rollout a full-scale mockup of a next-generation spacecraft". russianspaceweb.com. Retrieved 29 March 2013.
- Anatoly Zak (August 3, 2007). "Lunar Orbital Spacecraft". russianspaceweb.com. Retrieved 29 March 2013.
- "Soyuz 100 Times More Reliable Than Shuttle". Spacedaily.com. February 8, 2010. Retrieved 29 March 2013.
- Clark, Stephen (5 March 2013). "Soyuz crew approved for fast approach to space station". SPACEFLIGHT NOW. Retrieved 6 March 2013.
- "Topic: Soyuz-MS spacecraft". forum.nasaspaceflight.com. December 17, 2013. Retrieved 28 March 2014.
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- The short film Four in the Cosmos (1969) is available for free download at the Internet Archive
- Russian space agency video of roll-out and launch.
- Apollo D-2 Proposal by General Electric, Encyclopedia Astronautica