Soyuz (spacecraft)

Soyuz (spacecraft)

By Wikipedia,
the free encyclopedia,

http://en.wikipedia.org/wiki/Soyuz_spacecraft

Soyuz ([sɐˈjʉs], Russian: Союз, lit. ‘Union’) is a series of spacecraft designed for the Soviet space program by the Korolyov Design Bureau (now RKK Energia) 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 programs. 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.

**Soyuz**
Specifications
Soyuz spacecraft (TMA version)

Manufacturer	RKK Energia
Country of origin	Soviet Union, Russian Federation
Operator	Soviet space program (1967–91) Roscosmos (1991 onwards)
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)

Production
Status	In service
First launch	Soyuz 1, 1967

History

The first Soyuz flight was unmanned and started on November 28, 1966. The first Soyuz 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 when the cabin depressurized prematurely just before reentry. These were the only humans to date to have died above the Kármán line. Despite these early incidents, Soyuz is widely considered the world’s safest, most cost-effective human spaceflight vehicle, 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. The spacecraft is intended to be replaced by the six-person Federation spacecraft.

Design

Diagram showing the three elements of the Soyuz TMA spacecraft.

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 payload fairing, which is jettisoned along with the SAS at 2-1/2 minutes into launch. It has an automatic docking system. The ship can be operated automatically, or by a pilot independently of ground control.

Launch Escape System

The Vostok spacecraft utilized an ejector seat to bail out the cosmonaut in the event of a low-altitude launch failure, as well as during reentry, however it was likely ineffective in the first 20 seconds after liftoff when the altitude would be too low for the parachute to deploy. Inspired by the Mercury LES, Soviet designers began work on a similar system in 1962. This included developing a complex sensing system to monitor various launch vehicle parameters and trigger an abort if a booster malfunction occurred. Based on data from R-7 launches over the years, engineers developed a list of the most likely failure modes for the vehicle and could narrow down abort conditions to premature separation of a strap-on booster, low engine thrust, loss of combustion chamber pressure, or loss of booster guidance. The Spacecraft Abort System (SAS; Russian: Система Аварийного Спасения, translit. Sistema Avarijnogo Spaseniya) could also be manually activated from the ground, but unlike American spacecraft, there was no way for the cosmonauts to trigger it themselves.

Since it turned out to be almost impossible to separate the entire payload shroud from the Soyuz service module cleanly, the decision was made to have the shroud split between the service module and descent module during an abort. Four folding stabilizers were added to improve aerodynamic stability during descent. Two test runs of the SAS were carried out in 1966-67.

The basic design of the SAS has remained almost unchanged in 50 years of use and all Soyuz launches carry it. The only modification was in 1972 when the aerodynamic fairing over the SAS motor nozzles was deleted for weight-saving reasons as the redesigned Soyuz 7K-T spacecraft carried extra life support equipment. The unmanned Progress resupply ferry has a dummy escape tower and deletes the stabilizer fins from the payload shroud. There have been two failed launches of a manned Soyuz vehicle, Soyuz 18-1 in 1975 and Soyuz T-10-1 in 1983, but the former was aborted after escape tower jettison. The latter successfully rescued the cosmonauts from an on-pad fire and explosion of the launch vehicle. This is the only time a launch escape tower has been used in an abort with a crew aboard.

Orbital module

Soyuz spacecraft’s Orbital Module

The forepart of the spacecraft is the Orbital Module (Russian: бытовой отсек, translit. bytovoi otsek), 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 (212 cu ft), living space 5 m³(177 cu ft). 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 a micro-g environment 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 the 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.

Descent module

Soyuz spacecraft’s Descent Module

The Descent Module (Russian: спускаемый аппарат, translit. spuskaemyi apparat), also known as a reentry capsule, is used for launch and the journey back to Earth. Half of the Descent Module is covered by a heat-resistant covering to protect it during reentry; 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 Descent 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 — as the pioneering Vostok spacecraft’s Descent Module used — 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 (seven degrees) conical section 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. The small dimensions of the Descent 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 (141 cu ft); 2.5 m³ (88 cu ft) is usable for crew (living space).

Service module

Soyuz spacecraft’s Instrumentation/Propulsion Module

At the back of the vehicle is the Service Module (Russian: приборно-агрегатный отсек, translit. priborno-agregatnyi otsek). It has a pressurized container shaped like a bulging can (instrumentation compartment, 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, 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 (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.

Re-entry procedure

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 travels 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 Descent Module. As they are connected by tubing and electrical cables to the Descent 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 the 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.

Spacecraft systems

Soyuz diagram

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

Orbital module (A): 1 docking mechanism; 2, 4 Kurs rendezvous radar 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, 18 attitude control engines; 12 Earth sensors; 13 Sun sensor; 14 solar panel attachment point; 15 thermal sensor; 16 Kurs antenna; 17 main propulsion; 19 communication antenna; 20 fuel tanks; 21 oxygen tank

Variants

The Soyuz spacecraft has been the subject of continuous evolution since the early 1960s. Thus several different versions, proposals and projects exist.

Specifications

Total
Version:	Soyuz A (1963)	Soyuz 7K-OK (1967–1971)	Soyuz 7K-L3 (LOK)	Soyuz 7K-T 1973–1981)	Soyuz 7K-TM (1975)
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)
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)
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)
Span	?	9.80 m (32.2 ft)	2.930 m (9 ft 7.4 in)	9.80 m (32.2 ft)	8.37 m (27.5 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)
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)
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)
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)
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)
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)
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)
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)
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)
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)
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)
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)

Specifications

Total
Version:	Soyuz-T (1976–1986)	Soyuz-TM (1986–2002)	Soyuz-TMA (2003–2012)	Soyuz TMA-M (2010–2016)	Soyuz MS (2016–….)
Mass	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	7.48 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	2.72 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	10.6 m (35 ft)	10.6 m (35 ft)	10.7 m (35 ft)	10.7 m (35 ft)	?
Orbital Module (BO)
Mass	1,100 kg (2,400 lb)	1,450 kg (3,200 lb)	1,370 kg (3,020 lb)	?	?
Length	2.98 m (9.8 ft)	2.98 m (9.8 ft)	2.98 m (9.8 ft)	2.98 m (9.8 ft)	2.98 m (9.8 ft)
Diameter	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	5.00 m³(177 cu ft)	5.00 m³(177 cu ft)	5.00 m³(177 cu ft)	?	?
Reentry module (SA)
Mass	3,000 kg (6,600 lb)	2,850 kg (6,280 lb)	2,950 kg (6,500 lb)	?	?
Length	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)	2.17 m (7.1 ft)	2.17 m (7.1 ft)	2.17 m (7.1 ft)
Volume	4.00 m³(141 cu ft)	3.50 m³(124 cu ft)	3.50 m³(124 cu ft)	?	?
Service module (PAO)
Mass	2,750 kg (6,060 lb)	2,950 kg (6,500 lb)	2,900 kg (6,400 lb)	?	?
Usable fuel (kg)	700 kg (1,500 lb)	880 kg (1,940 lb)	880 kg (1,940 lb)	?	?
Length	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	2.72 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)

Soyuz 7K manned spacecraft concept (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.

First generation

Soyuz 7K-OK(A) spacecraft with an active docking unit.

Soyuz 7K-OKS for Salyut space stations.

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.

Second generation

Upgraded Soyuz 7K-T version.

The second generation, called Soyuz Ferry or Soyuz 7K-T, comprised Soyuz 12 through Soyuz 40 (1973–1981).

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).

The Soyuz 7K-T/A9 version was used for the flights to the military Almaz space 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.

Third generation

Soyuz-T spacecraft.

The third generation Soyuz-(T: Russian: транспортный, translit. transportnyi, lit. ‘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.

Fourth generation

Soyuz-TM (1986–2003)

Soyuz-TM spacecraft. Compare the antennas on the orbital module to those on Soyuz-T. Differences reflect the change from the Igla rendezvous system used on Soyuz-T to the Kurs rendezvous system used on Soyuz-TM.

The Soyuz-TM crew transports (M: Russian: модифицированный, translit. modifitsirovannyi, lit. ‘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 (2003–2012)

The Soyuz TMA-6

Soyuz TMA (A: Russian: антропометрический, translit. antropometricheskii, lit. ‘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 (2010–2016)

The Soyuz TMA-M was an upgrade of the baseline Soyuz-TMA, using a new computer, digital interior displays, updated docking equipment, and the vehicle’s total mass was reduced by 70 kilograms. The new version debuted on 7 October 2010 with the launch of TMA-01M, carrying the ISS Expedition 25 crew.

The Soyuz TMA-08M mission set a new record for the fastest manned docking with a space station, event utilized the new six-hour fast rendezvous instead of the previous Soyuz launches which had, since 1986, taken two days.

Soyuz MS (since 2016)

Soyuz MS-01 docked to the ISS

Soyuz MS is the final planned upgrade of the Soyuz spacecraft. Its maiden flight was in July 2016 with mission MS-01. Major changes include:

more efficient solar panels
modified docking and attitude control engine positions for redundancy during docking and de-orbit burns
new Kurs NA approach and docking system which weighs half as much and consumes a third of the power of previous system
new TsVM-101 computer, about one eighth the weight (8.3 kg vs. 70 kg) and much smaller than the previous Argon-16computer
unified digital command/telemetry system (MBITS) to relay telemetry via satellite, and control spacecraft when out of sight of ground stations; also provides the crew with position data when out of ground tracking range
GLONASS/GPS and Cospas-Sarsat satellite systems for more accurate location during search/rescue operations after landing

The Soyuz MS-02 spacecraft had its maiden flight on October 19, 2016, to launch Expedition 49-50 from Baikonur with three crew members.

Related craft

The unmanned Progress spacecraft were derived from Soyuz and are used for servicing space stations.

While not being direct derivatives of Soyuz, the Chinese Shenzhou spacecraft and the Indian Orbital Vehicle follow the same general layout as that pioneered by Soyuz.

Text from Wikipedia is available under the Creative Commons Attribution/Share-Alike License; additional terms may apply.

Published in October 2017.

Click here to read more articles related to aviation and space!