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 | |
Total launches |
|
Success(es) |
|
Failure(s) | 4 (A: 2, B: 2) |
Partial failure(s) | 2 (A: 1, B: 1) |
First flight |
|
Last flight |
|
Type of passengers/cargo | |
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 |
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]
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