Soyuz-2
Glavkosmos
Soyuz-2 is a series of Russian expendable medium-lift launch vehicles, representing the seventh major iteration of the Soyuz rocket family, featuring upgraded engines and a digital flight control system.
Key figurescomparable across the catalogue
- Mass
- 312,000 kg
- Payload capacity
- 8,670 kg
Normalised to common units so this product can be compared with others in its category. The supplier's own wording is below.
As published by the supplier
- Function
- Medium-lift launch vehicle
- Manufacturer
- RKTs Progress
- Country of origin
- Russia
- 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
- Payload to LEO altitude
- 240 km (150 mi)
- Payload to polar orbit altitude
- 240 km (150 mi)
- Payload to polar orbit orbital inclination
- 98°
- Payload to tli mass
- B: 2,350 kg (5,180 lb)
- Family
- R-7 (Soyuz)
- Based on
- Soyuz-FG
- Derivative work
- Soyuz-ST Soyuz-2.1v
- Status
- Active
- Total launches
- 166 (A: 82, B: 84)
- Success (es)
- 161 (A: 79, B: 82)
- Failure
- 4 (A: 2, B: 2)
- Partial failure
- 1 (A: 1, B: 0)
- Boosters (first stage) – block b, v, g & d no. boosters
- 4
- Boosters (first stage) – block b, v, g & d height
- 19.6 m (64 ft 4 in)
- Boosters (first stage) – block b, v, g & d diameter
- 2.68 m (8 ft 10 in)
- Boosters (first stage) – block b, v, g & d empty mass
- 3,784 kg (8,342 lb)
- Boosters (first stage) – block b, v, g & d gross mass
- 44,413 kg (97,914 lb)
- Boosters (first stage) – block b, v, g & d powered by
- 1 × RD-107A
- Boosters (first stage) – block b, v, g & d maximum thrust
- SL: 838.5 kN (188,500 lbf) vac: 1,021.3 kN (229,600 lbf)
- Boosters (first stage) – block b, v, g & d specific impulse
- SL: 262 s (2.57 km/s) vac: 319 s (3.13 km/s)
- Boosters (first stage) – block b, v, g & d burn time
- 118 seconds
- Boosters (first stage) – block b, v, g & d propellant
- LOX / RP-1
- Second stage (core) – block a height
- 27.1 m (88 ft 11 in)
- Second stage (core) – block a diameter
- 2.95 m (9 ft 8 in)
- Second stage (core) – block a empty mass
- 6,545 kg (14,429 lb)
- Second stage (core) – block a gross mass
- 99,765 kg (219,944 lb)
- Second stage (core) – block a powered by
- 1 × RD-108A
- Second stage (core) – block a maximum thrust
- SL: 792.5 kN (178,200 lbf) vac: 990.2 kN (222,600 lbf)
- Second stage (core) – block a specific impulse
- SL: 255 s (2.50 km/s) vac: 319 s (3.13 km/s)
- Second stage (core) – block a burn time
- 286 seconds
- Second stage (core) – block a propellant
- LOX / RP-1
- Third stage – block i height
- 6.7 m (22 ft 0 in)
- Third stage – block i diameter
- 2.66 m (8 ft 9 in)
- Third stage – block i empty mass
- 2,355 kg (5,192 lb)
- Third stage – block i gross mass
- 27,755 kg (61,189 lb)
- Third stage – block i powered by
- A: 1 × RD-0110 B: 1 × RD-0124
- Third stage – block i maximum thrust
- A: 298.03 kN (67,000 lbf) B: 294.3 kN (66,200 lbf)
- Third stage – block i specific impulse
- A: 325 s (3.19 km/s) B: 359 s (3.52 km/s)
- Third stage – block i burn time
- A: 250 seconds B: 270 seconds
- Third stage – block i 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)
- Fourth stage (optional) – fregat / fregat-m diameter
- Fregat: 3.44 m (11 ft 3 in) Fregat-M: 3.8 m (12 ft 6 in)
- Fourth stage (optional) – fregat / fregat-m empty mass
- Fregat: 945 kg (2,083 lb) Fregat-M: 1,035 kg (2,282 lb)
- Fourth stage (optional) – fregat / fregat-m gross mass
- Fregat: 6,235 kg (13,746 lb) Fregat-M: 7,640 kg (16,840 lb)
- Fourth stage (optional) – fregat / fregat-m propellant mass
- Fregat: 5,307 kg (11,700 lb) Fregat-M: 6,650 kg (14,660 lb)
- Fourth stage (optional) – fregat / fregat-m powered by
- 1 × S5.92
- Fourth stage (optional) – fregat / fregat-m maximum thrust
- 13.93–19.85 kN (3,130–4,460 lbf)
- Fourth stage (optional) – fregat / fregat-m specific impulse
- 320–333.2 s (3.14–3.27 km/s)
- Fourth stage (optional) – fregat / fregat-m burn time
- Up to 1,100 seconds (up to 7 starts)
- Fourth stage (optional) – fregat / fregat-m propellant
- N2O4 / UDMH
- Fourth stage (optional) – volga height
- 1.025 m (3 ft 4.4 in)
- Fourth stage (optional) – volga diameter
- 3.2 m (10 ft 6 in)
- Fourth stage (optional) – volga empty mass
- 840 kg (1,850 lb)
- Fourth stage (optional) – volga propellant mass
- 300–900 kg (660–1,980 lb)
- Fourth stage (optional) – volga powered by
- 1 × 17D64
About
The Soyuz-2 (GRAU index: 14A14) is a series of Russian expendable medium-lift launch vehicles developed and produced by the Progress Rocket Space Centre (RKTs Progress) in Samara. It is the seventh major iteration of the Soyuz rocket family, featuring significant upgrades over its predecessors, including improved engines and a digital flight control system. This digital system enables launches from fixed platforms and supports larger payload fairings. The Soyuz-2 is primarily used to place payloads into low Earth orbit but can also support missions to higher orbits with an additional upper stage, such as the Fregat or the smaller Volga. Since its introduction in 2004, Soyuz-2 has gradually replaced earlier Soyuz variants and is launched from various cosmodromes including Baikonur, Plesetsk, and Vostochny.
The Soyuz-2 family includes several variants. The base model, Soyuz-2.1a, debuted in 2004, introducing the digital flight control system, lighter avionics, and upgraded RD-107A and RD-108A engines, while retaining the RD-0110 engine for the third stage but with enlarged propellant tanks. These changes increased payload capacity by about 300 kg. The Soyuz-2.1b, introduced in 2006, further enhanced performance by replacing the third-stage RD-0110 with the more efficient RD-0124 engine, an oxygen-rich staged-combustion engine, which increased specific impulse and significantly boosted payload capability to low Earth orbit (e.g., from 7,430 kg for 2.1a to 8,670 kg for 2.1b from Baikonur). A derivative version, Soyuz-ST, was developed for operations at the Guiana Space Centre.
Modifications for the Vostochny Cosmodrome included the ability to remain fueled on the launch pad for up to 100 hours, structural and piping changes for vertical payload integration and safe propellant venting, an upgraded computer with six times the performance, and new nickel-cadmium batteries. The rocket can be configured with 3 or 4 stages, with optional Fregat/Fregat-M or Volga upper stages. The first crewed mission of Soyuz-2 took place on April 9, 2020, carrying Soyuz MS-16 to the ISS. Recent developments include successful ground testing and launch with naphthyl fuel, which slightly improves engine performance due to fewer aromatic compounds than kerosene.
Documentation
- Soyuz User's Manual (Baikonur, Fregat) PDF source: newspacemarket.com ↗
- Datasheet PDF source: www.georing.biz ↗
- Datasheet PDF source: www.starsem.com ↗
Need the full ICD, test reports or a specific revision? Ask the supplier directly.