Soyuz-2

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[1][2]
Size
Height	46.3 m (152 ft)[3]
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[a]
Mass	B: 2,350 kg (5,180 lb)[4]
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[b]
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)[5]
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)[5]
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)[6]
Specific impulse	A: 325 s (3.19 km/s) B: 359 s (3.52 km/s)[7]
Burn time	A: 250 seconds B: 270 seconds
Propellant	LOX / RP-1
Fourth stage (optional) – Fregat / Fregat-M[8]
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[9]
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[10]
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.^[11][12][13]

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