Soyuz-FG
The launch of Soyuz TMA-3 atop a Soyuz-FG rocket. | |
| Function | Medium-lift launch vehicle |
|---|---|
| Manufacturer | RKTs Progress |
| Country of origin | Russia |
| Cost per launch | 773,600,000 ₽ (2012) |
| Size | |
| Height | 51 m (167 ft) |
| Diameter | 2.7–3.715 m (8.86–12.19 ft) |
| Mass | 310,000–313,000 kg (683,000–690,000 lb) |
| Stages |
|
| Capacity | |
| Payload to LEO | |
| Altitude | 200 km (120 mi) |
| Orbital inclination | 51.8° |
| Mass |
|
| Associated rockets | |
| Family | R-7 (Soyuz) |
| Based on | Soyuz-U |
| Derivative work | Soyuz-2 |
| Launch history | |
| Status | Retired |
| Launch sites | Baikonur, LC-1/5 and LC-31/6 |
| Total launches |
|
| Success(es) | 69 |
| Failure(s) | 1 (Soyuz MS-10) |
| First flight | 20 May 2001 (Progress M1-6) |
| Last flight | 25 September 2019 (Soyuz MS-15) |
| Carries passengers or cargo | |
| Boosters (First stage) – Block B, V, G & D | |
| Height | 19.6 m (64 ft) |
| Diameter | 2.68 m (8 ft 10 in) |
| Empty mass | 3,800 kg (8,400 lb) |
| Gross mass | 43,400 kg (95,700 lb) |
| Propellant mass | 40,350 kg (88,960 lb) |
| Powered by | 1 × RD-107A |
| Maximum thrust |
|
| Specific impulse |
|
| Burn time | 118 seconds |
| Propellant | LOX / RG-1 |
| Second stage (core) – Block A | |
| Height | 27.1 m (89 ft) |
| Diameter | 2.95 m (9 ft 8 in) |
| Empty mass | 6,550 kg (14,440 lb) |
| Gross mass | 99,500 kg (219,400 lb) |
| Propellant mass | 92,600 kg (204,100 lb) |
| Powered by | 1 × RD-108A |
| Maximum thrust |
|
| Specific impulse |
|
| Burn time | 286 seconds |
| Propellant | LOX / RG-1 |
| Third stage – Block I | |
| Height | 6.7 m (22 ft) |
| Diameter | 2.66 m (8 ft 9 in) |
| Empty mass | 2,410 kg (5,310 lb) |
| Gross mass | 25,300 kg (55,800 lb) |
| Propellant mass | 22,800 kg (50,300 lb) |
| Powered by | 1 × RD-0110 |
| Maximum thrust | 297.93 kN (66,980 lbf) |
| Specific impulse | 326 s (3.20 km/s) |
| Burn time | 230 seconds |
| Propellant | LOX / RG-1 |
| Fourth stage (optional) – Fregat | |
| Height | 1.5 m (4 ft 11 in) |
| Diameter | 3.35 m (11.0 ft) |
| Empty mass | 930 kg (2,050 lb) |
| Propellant mass | 5,250 kg (11,570 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 |
The Soyuz-FG was an improved variant of the Soyuz-U launch vehicle from the R-7 rocket family, developed by the Progress Rocket Space Centre in Samara, Russia. It featured upgraded first and second stage engines, RD-107A and RD-108A, respectively, with enhanced injector heads that improved combustion efficiency and specific impulse. The designation "FG" refers to forsunochnaya golovka (injector head) in Russian.
Soyuz-FG made its maiden flight on 20 May 2001, delivering a Progress cargo spacecraft to the International Space Station (ISS). It became the primary vehicle for launching crewed Soyuz TMA, Soyuz TMA-M, and Soyuz MS spacecraft from 2002 until its retirement in 2019.
Launches occurred from the Baikonur Cosmodrome in Kazakhstan: crewed missions from Gagarin's Start (Site 1/5) and satellite launches from Site 31/6.