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Soyuz‑2 (2.1a / 2.1b)

A Soyuz‑2.1b rocket launches carrying a GLONASS-K2 satellite to orbit
Function	Medium-lift launch vehicle
Manufacturer	RKTs Progress
Country of origin	Russia
Cost per launch	US$35−48.5 million
Size
Height	46.3 m (152 ft)
Diameter	10.3 m (33 ft 10 in)
Mass	312,000 kg (688,000 lb)
Stages	3 or 4
Capacity
Payload to LEO
Altitude	240 km (150 mi)
Orbital inclination	51.6° from Baikonur and Vostochny 72° from Plesetsk
Mass	From Baikonur: A: 7,430 kg (16,380 lb) B: 8,670 kg (19,110 lb) From Plesetsk: A: 6,800 kg (15,000 lb) B: 7,730 kg (17,040 lb) From Vostochny: A: 7,460 kg (16,450 lb) B: 8,600 kg (19,000 lb)
Payload to Polar orbit
Altitude	240 km (150 mi)
Orbital inclination	98°
Mass	From Baikonur: A: 5,830 kg (12,850 lb) B: 7,030 kg (15,500 lb) From Plesetsk: A: 6,130 kg (13,510 lb) B: 7,270 kg (16,030 lb) From Vostochny: A: 6,070 kg (13,380 lb) B: 7,260 kg (16,010 lb)
Payload to TLI
Mass	B: 2,350 kg (5,180 lb)
Associated rockets
Family	R-7 (Soyuz)
Based on	Soyuz-FG
Derivative work	Soyuz-ST Soyuz-2.1v
Launch history
Status	Active
Launch sites	Baikonur, Site 31/6 Plesetsk, Sites 43/3 & 43/4 Vostochny, Site 1S
Total launches	146 (+1 suborbital)     A: 71 (+1 suborbital)     B: 75
Success(es)	141 (+1 suborbital)     A: 68 (+1 suborbital)     B: 73
Failure(s)	4 (A: 2, B: 2)
Partial failure(s)	1 (A: 1, B: 0)
First flight	A: 8 November 2004 B: 27 December 2006
Last flight	A: Active B: Active
Type of passengers/cargo	CoRoT GLONASS Progress Soyuz MS OneWeb
Boosters (First stage) – Block B, V, G & D
No. boosters	4
Height	19.6 m (64 ft 4 in)
Diameter	2.68 m (8 ft 10 in)
Empty mass	3,784 kg (8,342 lb)
Gross mass	44,413 kg (97,914 lb)
Propellant mass	LOX: 27,900 kg (61,500 lb) RP-1: 11,260 kg (24,820 lb)
Powered by	1 × RD-107A
Maximum thrust	SL: 838.5 kN (188,500 lbf) vac: 1,021.3 kN (229,600 lbf)
Specific impulse	SL: 262 s (2.57 km/s) vac: 319 s (3.13 km/s)
Burn time	118 seconds
Propellant	LOX / RP-1
Second stage (core) – Block A
Height	27.1 m (88 ft 11 in)
Diameter	2.95 m (9 ft 8 in)
Empty mass	6,545 kg (14,429 lb)
Gross mass	99,765 kg (219,944 lb)
Propellant mass	LOX: 63,800 kg (140,700 lb) RP-1: 26,300 kg (58,000 lb)
Powered by	1 × RD-108A
Maximum thrust	SL: 792.5 kN (178,200 lbf) vac: 990.2 kN (222,600 lbf)
Specific impulse	SL: 255 s (2.50 km/s) vac: 319 s (3.13 km/s)
Burn time	286 seconds
Propellant	LOX / RP-1
Third stage – Block I
Height	6.7 m (22 ft 0 in)
Diameter	2.66 m (8 ft 9 in)
Empty mass	2,355 kg (5,192 lb)
Gross mass	27,755 kg (61,189 lb)
Propellant mass	LOX: 17,800 kg (39,200 lb) RP-1: 7,600 kg (16,800 lb)
Powered by	A: 1 × RD-0110 B: 1 × RD-0124
Maximum thrust	A: 298.03 kN (67,000 lbf) B: 294.3 kN (66,200 lbf)
Specific impulse	A: 325 s (3.19 km/s) B: 359 s (3.52 km/s)
Burn time	A: 250 seconds B: 270 seconds
Propellant	LOX / RP-1
Fourth stage (optional) – Fregat / Fregat-M
Height	Fregat: 1.875 m (6 ft 1.8 in) Fregat-M: 1.945 m (6 ft 4.6 in)
Diameter	Fregat: 3.44 m (11 ft 3 in) Fregat-M: 3.8 m (12 ft 6 in)
Empty mass	Fregat: 945 kg (2,083 lb) Fregat-M: 1,035 kg (2,282 lb)
Gross mass	Fregat: 6,235 kg (13,746 lb) Fregat-M: 7,640 kg (16,840 lb)
Propellant mass	Fregat: 5,307 kg (11,700 lb) Fregat-M: 6,650 kg (14,660 lb)
Powered by	1 × S5.92
Maximum thrust	13.93–19.85 kN (3,130–4,460 lbf)
Specific impulse	320–333.2 s (3.14–3.27 km/s)
Burn time	Up to 1,100 seconds (up to 7 starts)
Propellant	N2O4 / UDMH
Fourth stage (optional) – Volga
Height	1.025 m (3 ft 4.4 in)
Diameter	3.2 m (10 ft 6 in)
Empty mass	840 kg (1,850 lb)
Propellant mass	300–900 kg (660–1,980 lb)
Powered by	1 × 17D64
Maximum thrust	2.94 kN (660 lbf)
Specific impulse	307 s (3.01 km/s)
Propellant	N2O4 / UDMH
[edit on Wikidata]

Soyuz‑2 (Russian: Союз‑2, lit. 'Union‑2') (GRAU index: 14A14) is a modernized expendable medium-lift launch vehicle and the seventh major version of the Soyuz rocket family. It includes key enhancements over its predecessors, including improved engines along with digital flight control and telemetry systems, enabling launches from fixed platforms and the use of large payload fairings.

In its standard configuration, Soyuz‑2 is a three-stage launch vehicle designed for low Earth orbit missions. Its stage numbering differs from most other rockets: its boosters are considered the first stage, while the central core is the second. For higher orbits like Molniya or geosynchronous, an optional upper (fourth) stage can be added. The most common upper stage is the Fregat, but the smaller, less expensive Volga is also an option. These upper stages have independent flight control systems.

The Soyuz‑2 family has two major variants, with the Soyuz‑2.1a being the base version that first launched on 8 November 2004. The Soyuz‑2.1b, with a 15 percent more powerful third stage, followed on 27 December 2006. In 2011, the Soyuz‑ST was introduced, a derivative version with extensive modifications to launch from the Guiana Space Centre, the European Space Agency's spaceport in French Guiana. Soyuz launches from Guiana were suspended in 2022 after the Russian invasion of Ukraine. The derivative Soyuz-2.1v with a more powerful core stage and no boosters was introduced in December 2013.

The Soyuz‑2 rocket utilizes the existing facilities of its R-7 derived predecessors, Site 31/6 at the Baikonur Cosmodrome in Kazakhstan and Sites 43/3 and 43/4 at the Plesetsk Cosmodrome in northwestern Russia. In 2016, an additional launch location opened at Site 1S at the Vostochny Cosmodrome in eastern Russia.

The Soyuz‑2 has replaced the Molniya-M, Soyuz-U and Soyuz-FG rockets since 2010, 2017 and 2019 respectively.

Variants

Soyuz 2.1a

The key advancement of the Soyuz‑2.1a is its digital flight control system, which replaces the analog system used in earlier Soyuz models. This upgrade allows the rocket to adjust its trajectory mid-flight, a capability the analog system lacked, eliminating the need for a rotating launchpad. The digital system also supports the use of larger payload fairings, enabling the launch of heavier commercial satellites that the analog system could not handle due to the aerodynamic instability the fairings generate.

The 2.1a retains the upgraded RD-107A engines on the first stage boosters and the RD-108A engine on the second stage core, initially introduced with the Soyuz-FG. These engines feature improved injection systems for enhanced performance. The only change for the Soyuz-2 is the addition of a chemical ignition system. Previously, engines were ignited pyrotechnically with a pair of small charges placed on a wooden stick inside each of the 32 combustion chambers.

The Block I third stage continues to use the RD-0110 engine, but its structure has been unified with the upgraded third stage of the 2.1b to streamline production. These changes slightly enlarged the propellant tanks, enabling longer burn times. The extra burn time combined with the physically lighter and more capable digital flight control system increased payload capacity by 300 kilograms (660 lb).

The Soyuz‑2.1a conducted its maiden flight on 8 November 2004, launching from Plesetsk Cosmodrome Site 43 with a boilerplate payload simulating a Zenit-8 spy satellite.

Soyuz 2.1b

The Soyuz‑2.1b has all the same features as the Soyuz‑2.1a but uses improved third stage built around the new RD-0124, an oxygen-rich closed-cycle engine. While the maximum thrust of the engine was slightly decreased from 298 to 294 kilonewtons (67,000 to 66,000 lb_f), specific impulse (a measure of efficiency) was significantly increased 326 to 359 seconds (3.20 to 3.52 km/s) and burn time was increased by 20 seconds on the same quantity of propellants. Taken together, these changes improved payload capability. For example, payload capacity from the Baikonur Cosmodrome to low Earth orbit increased from 7,430 to 8,670 kilograms (16,380 to 19,110 lb).

The first launch of a Soyuz‑2.1b occurred from Plesetsk Cosmodrome Site 43 on 26 July 2008 with a classified military payload.

• Closeup of booster and core stage engines of a Soyuz‑2.1a during launch
• Soyuz‑2.1a prepared for human spaceflight mission Soyuz MS-26
• Soyuz‑2.1b prepared for GLONASS-K2 satellite launch
• From left to right: Soyuz‑2.1v, Soyuz‑2.1b, Soyuz‑2.1a (crewed variant) and the proposed Soyuz‑5

Vostochny modifications

Modifications for the Vostochny Cosmodrome version of the Soyuz include the following:

• Upgraded Computer: The system boasts six times more performance, reduced weight, and significantly simplified cable networks through multiplexing lines and the use of common buses.
• Improved Batteries: New nickel-cadmium batteries eliminate the need for a dedicated battery charging station.
• On-Board Video System: A video system has been added, enabling real-time views of the launch.
• Adaptation for Vertical Integration: Due to the mobile gantry at Vostochny, which supports vertical payload integration, the rockets are equipped with piping to direct oxygen purges outside the gantry.

On 1 October 2015, it was revealed that parts of the assembly complex for the Soyuz-2 at Vostochny Cosmodrome were designed for a different rocket modification and were too small. This issue raised doubts about the planned first launch in December 2015. The first launch successfully took place on 28 April 2016.

Notable missions

Suborbital test flight

On 8 November 2004, at 18:30 UTC, the first Soyuz‑2 rocket, in the Soyuz‑2.1a configuration, was launched from the Plesetsk Cosmodrome in Russia. The rocket followed a suborbital trajectory, with the third stage and Boilerplate landing in the Pacific Ocean.

Maiden launch

The first attempt at launching a Soyuz‑2 to orbit with the MetOp-A satellite occurred on 17 July 2006. It was scrubbed two hours before the launch by an automatic sequence after the onboard computer failed to check the launch azimuth. Fuelling of the rocket was underway at the time, and all launch complex equipment and onboard preliminary checks had proceeded without incident. The rocket was left fuelled on the launch pad for the next attempt on 18 July 2006. Launch was eventually conducted on 19 October 2006.

First crewed mission

The first crewed launch of Soyuz‑2 took place on 9 April 2020, carrying Soyuz MS-16 to the ISS.

Naphthyl fuel

Following successful ground testing, a naphthyl (Russian: нафтил) fueled Soyuz‑2.1b launch took place on 22 October 2022 at Vostochny. Naphthyl is an environmentally safe hydrocarbon fuel with fewer aromatic compounds than kerosene, which also slightly improves engine performance. There are only minor differences in thermal properties, viscosity, and surface tension, so this did not require significant engine changes.

Launch statistics

Since 2006, Soyuz‑2 rockets have accumulated a total of 146 launches, 141 of which were successful, yielding a 97% success rate.

Launch outcomes

•   Failure
•   Partial failure
•   Success

Launch sites

•   Baikonur
•   Plesetsk
•   Vostochny

List of launches

Planned launches

This list is incomplete; you can help by adding missing items. (August 2021)

See also

• Soyuz programme
• List of R-7 launches
• Medium-lift launch vehicle

Notes

1. with Fregat from Baikonur
2. This is a transliteration of the second through fifth letters of the Cyrillic alphabet (Б, В, Г, Д). The English translation is Block B, C, D & E.

References

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External links

• Official website
• Encyclopedia Astronautica article on Soyuz 2.1
• Encyclopedia Astronautica article on Soyuz 2.1/Fregat
• Soyuz User's Manual, from Starsem
• Soyuz-2 launch vehicle, from Roscosmos

v t e R-7 rockets
Missiles	R-7 Semyorka R-7A Semyorka
Launch systems	Sputnik Polyot Voskhod Vostok Luna Vostok-L Vostok-K Vostok-2 Vostok-2M Molniya Molniya Molniya-M Soyuz Soyuz/Vostok Soyuz Soyuz-L Soyuz-M Soyuz-U U2 Soyuz-FG Soyuz 2 Soyuz 2.1a / 2.1b ST-A / ST-B Soyuz 2.1v
Launch sites	Baikonur Site 1/5 Site 31/6 Plesetsk Site 41/1 Site 16/2 Site 43/3 Site 43/4 Vostochny Site 1S Guiana ELS
Launches	1957–1959 1960–1964 1965–1969 1970–1974 1975–1979 1980–1984 1985–1989 1990–1994 1995–1999 2000–2004 2005–2009 2010–2014 2015–2019 2020–2024
Engines	RD-107/108 RD-0110 RD-0124
See also	Korolyov Cross Soyuz at the Guiana Space Centre

• R-7 (rocket family)
• Space launch vehicles of Russia
• Vehicles introduced in 2004