Soyuz-2

Soyuz 2 (2.1a / 2.1b)

A MetOp spacecraft ready for launch atop a Soyuz 2.1a rocket.
Function	Medium-lift launch vehicle
Manufacturer	Progress
Country of origin	Russia
Cost per launch	US$35−48.5 million (Roscosmos)[1][2] US$80 million (Arianespace)[3]
Size
Height	46.3 m (152 ft)[4]
Diameter	10.3 m (33 ft 10 in)
Mass	312,000 kg (688,000 lb)
Stages	3 or 4
Capacity
Payload to LEO[a]
Mass	A: 7,020 kg (15,480 lb) B: 8,200 kg (18,100 lb)[4]
Payload to SSO[b]
Mass	A: 4,230 kg (9,330 lb) B: 4,900 kg (10,800 lb)[5]
Payload to GTO[c]
Mass	A: 2,810 kg (6,190 lb) B: 3,250 kg (7,170 lb)[5]
Payload to TLI[d]
Mass	B: 2,350 kg (5,180 lb)[6]
Payload to GSO[e]
Mass	B: 1,360 kg (3,000 lb)[6]
Associated rockets
Family	R-7 (Soyuz)
Based on	Soyuz-FG
Derivative work	Soyuz 2 (CSG) Soyuz 2.1v
Launch history
Status	Active
Launch sites	Baikonur, Site 31/6 Plesetsk, Site 43 Vostochny, Site 1S Guiana, ELS (2011–2022)
Total launches	169 (+1 suborbital)     A: 78 (+1 suborbital)     B: 91
Success(es)	163 (+1 suborbital)     A: 75 (+1 suborbital)     B: 88
Failure(s)	4 (A: 2, B: 2)
Partial failure(s)	2 (A: 1, B: 1)
First flight	A: 8 November 2004 B: 27 December 2006
Last flight	A: Active B: Active
Type of passengers/cargo	CoRoT Galileo GLONASS Progress Soyuz MS OneWeb
Boosters (First stage)
No. boosters	4
Height	19.6 m (64 ft)
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	39,160 kg (86,330 lb)
Powered by	1 × RD-107A
Maximum thrust	SL: 839.48 kN (188,720 lbf) vac: 1,019.93 kN (229,290 lbf)
Specific impulse	SL: 263.3 s (2.582 km/s) vac: 320.2 s (3.140 km/s)
Burn time	118 seconds
Propellant	LOX / RP-1
Second stage (core)
Height	27.10 m (88.9 ft)
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	90,100 kg (198,600 lb)
Powered by	1 × RD-108A
Maximum thrust	SL: 792.41 kN (178,140 lbf) vac: 921.86 kN (207,240 lbf)
Specific impulse	SL: 257.7 s (2.527 km/s) vac: 320.6 s (3.144 km/s)
Burn time	286 seconds
Propellant	LOX / RP-1
Third stage
Height	6.70 m (22.0 ft)
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	25,400 kg (56,000 lb)
Powered by	A: 1 × RD-0110 B: 1 × RD-0124
Maximum thrust	A: 298 kN (67,000 lbf) B: 294.3 kN (66,200 lbf)
Specific impulse	A: 326 s (3.20 km/s) B: 359 s (3.52 km/s)
Burn time	270 seconds
Propellant	LOX / RP-1
Fourth stage (optional) – Fregat / Fregat-M / Fregat-MT[7]
Height	1.5 m (4 ft 11 in)
Diameter	Fregat / Fregat-M: 3.35 m (11.0 ft) Fregat-MT: 3.80 m (12.5 ft)
Empty mass	Fregat: 930 kg (2,050 lb) Fregat-M: 980 kg (2,160 lb) Fregat-MT: 1,050 kg (2,310 lb)
Propellant mass	Fregat: 5,250 kg (11,570 lb) Fregat-M: 5,600 kg (12,300 lb) Fregat-MT: 7,100 kg (15,700 lb)
Powered by	1 × S5.92
Maximum thrust	19.85 kN (4,460 lbf)
Specific impulse	333.2 s (3.268 km/s)
Burn time	Up to 1,100 seconds (up to 20 starts)
Propellant	N2O4 / UDMH
Fourth stage (optional) – Volga[8]
Height	1.025 m (3 ft 4.4 in)
Diameter	3.2 m (10 ft)
Empty mass	840 kg (1,850 lb)
Propellant mass	300–900 kg (660–1,980 lb)
Powered by	1 × 17D64[9]
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. Notably, its stage numbering differs from some rockets. The boosters are considered to be its first stage, while the central core is the second one. 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 Volga is also an option. These upper stages have their own independent flight control and telemetry systems.

The Soyuz 2 rocket utilizes the existing facilities of its R-7 derived predecessors, Site 31 at the Baikonur Cosmodrome (Russian: Байконур) in Kazakhstan and Site 43 at the Plesetsk Cosmodrome (Russian: Плесецк) in northwestern Russia. Additional launch locations opened at the Ensemble de Lancement Soyouz at the Guiana Space Centre in French Guiana in 2011 and the Site 1S at the Vostochny Cosmodrome (Russian: Восточный) in eastern Russia in 2016. However, Soyuz 2 launches from Guiana were suspended in 2022 after the Russian invasion of Ukraine.^[10]

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. Soyuz rockets that use the larger ST payload fairing are called the Soyuz ST-A or Soyuz ST-B. The derivative Soyuz 2.1v with a more powerful core stage and no boosters was introduced in December 2013.

The Soyuz 2 has replaced the Molniya-M, Soyuz-U and Soyuz-FG rockets since 2010, 2017 and 2019 respectively.^[11][12][13]

Cite error: There are <ref group=lower-alpha> tags or {{efn}} templates on this page, but the references will not show without a {{reflist|group=lower-alpha}} template or {{notelist}} template (see the help page).