Soyuz-2

Soyuz-2 (2.1a / 2.1b / ST-A / ST-B)

A MetOp spacecraft ready for the launch atop a Soyuz-2.1a rocket.
Function	Orbital launch vehicle
Manufacturer	TsSKB-Progress (Samara) and Chemical Automatics Design Bureau (Voronezh) [1]
Country of origin	Russia
Cost per launch	US$80 million (Arianespace) [1] US$35-48.5 million (Roscosmos) [2][3]
Size
Height	46.3 m (152 ft) [4]
Diameter	2.95 m (9 ft 8 in)
Mass	312,000 kg (688,000 lb)
Stages	2 or 3
Capacity
Payload to LEO[a]
Mass	2.1a: 7,020 kg (15,480 lb) 2.1b: 8,200 kg (18,100 lb) [4]
Payload to SSO[b]
Mass	ST-A: 4,230 kg (9,330 lb) ST-B: 4,900 kg (10,800 lb) [5]
Payload to GTO[c]
Mass	ST-A: 2,810 kg (6,190 lb) ST-B: 3,250 kg (7,170 lb) [5]
Payload to TLI [d]
Mass	ST-B: 2,350 kg (5,180 lb) [6]
Payload to GSO [e]
Mass	ST-B: 1,360 kg (3,000 lb) [6]
Associated rockets
Family	R-7 (Soyuz)
Launch history
Status	Active
Launch sites	Baikonur, Site 31/6 Plesetsk, Site 43 Kourou, ELS Vostochny, Site 1S
Total launches	176 (+1 suborbital) (2.1a: 74 (+1 suborbital), 2.1b: 90, 2.1v: 12)
Success(es)	169 (+1 suborbital) (2.1a: 71 (+1 suborbital), 2.1b: 87, 2.1v: 11)
Failure(s)	4 (2.1a: 2, 2.1b: 2, 2.1v: 0)
Partial failure(s)	3 (2.1a: 1, 2.1b: 1, 2.1v: 1)
First flight	2.1a: 8 November 2004 2.1b: 27 December 2006 2.1v: 28 December 2013
Last flight	2.1a: Active 2.1b: Active 2.1v: Active
Type of passengers/cargo	CoRoT Galileo GLONASS Progress Soyuz MS OneWeb
Boosters – Blok-B, V, G, D [7]
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	RD-107A
Maximum thrust	Sea level: 839.48 kN (188,720 lbf) Vacuum: 1,019.93 kN (229,290 lbf)
Specific impulse	Sea level: 263.3 s (2.582 km/s) Vacuum: 320.2 s (3.140 km/s)
Burn time	118 seconds
Propellant	LOX / RP-1
First stage – Blok-A [7]
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	RD-108A
Maximum thrust	Sea level: 792.41 kN (178,140 lbf) Vacuum: 921.86 kN (207,240 lbf)
Specific impulse	Sea level: 257.7 s (2.527 km/s) Vacuum: 320.6 s (3.144 km/s)
Burn time	286 seconds
Propellant	LOX / RP-1
Second stage – Blok-I [7]
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	2.1a / STA: RD-0110 2.1b / STB: RD-0124
Maximum thrust	RD-0110: 298 kN (67,000 lbf) RD-0124: 294.3 kN (66,200 lbf)
Specific impulse	RD-0110: 326 seconds RD-0124: 359 seconds
Burn time	270 seconds
Propellant	LOX / RP-1
Upper stage (optional) – Fregat / Fregat-M / Fregat-MT [8]
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	S5.92
Maximum thrust	19.85 kN (4,460 lbf)
Specific impulse	333.2 seconds
Burn time	1100 seconds
Propellant	N2O4 / UDMH
Upper stage (optional) – Volga[9]
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	17D64[10]
Maximum thrust	2.94 kN (660 lbf)
Specific impulse	307 seconds
Propellant	N2O4 / UDMH
[edit on Wikidata]

Soyuz-2 (Russian: Союз-2, lit. 'Union-2') (GRAU index 14A14) is a modernised version of the Soviet Soyuz rocket. In its basic form, it is a three-stage launch vehicle for placing payloads into low Earth orbit. Compared to the previous versions of the Soyuz, the first-stage boosters and two core stages feature uprated engines with improved injection systems. Digital flight control and telemetry systems allow the rocket to be launched from a fixed launch platform, whereas the launch platforms for earlier Soyuz rockets had to be rotated as the rocket could not perform a roll to change its heading in flight.

Soyuz-2 is often flown with an upper stage, which allows it to lift payloads into higher orbits, such as Molniya and geosynchronous orbits. The upper stage is equipped with independent flight control and telemetry systems from those used in the rest of the rocket. The NPO Lavochkin manufactured Fregat is the most commonly used upper stage.

Soyuz-2 rockets were first launched from Site 31 at the Baikonur Cosmodrome, and Site 43 at the Plesetsk Cosmodrome, launch facilities shared with earlier R-7 derived rockets including the Soyuz-U and Molniya. Commercial Soyuz-2 flights are contracted by Starsem and have launched from Site 31 at Baikonur Cosmodrome and Ensemble de Lancement Soyouz (ELS), which has been built at the Centre Spatial Guyanais (CSG) on the northern coast of South America. The Soyuz-2 version ST-B can deliver 3,250 kg (7,170 lb) to geostationary transfer orbit (GTO) from this equatorial site.^[5] As of 2022 Soyuz-2 launches from CSG have been suspended.^[11]

In 2016, the new Vostochny Cosmodrome started operating Soyuz-2 flights as well, from its first launch pad called Vostochny Cosmodrome Site 1S.

The Soyuz-2 has replaced the Molniya-M, Soyuz-U and Soyuz-FG since 2010, 2017 and 2019 respectively.^[12][13][14] TsSKB-Progress halted production of Soyuz-U in April 2015; the final flight of a Soyuz-U rocket took place on 22 February 2017, carrying Progress MS-05 to the International Space Station (ISS).

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