Soyuz-FG
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The Soyuz-FG launch vehicle was an improved version of the Soyuz-U from the R-7 family of rockets, designed and constructed by TsSKB-Progress in Samara, Russia. Guidance, navigation, and control system was developed and manufactured by "Polisvit" Special Design Bureau[6] (Kharkov, Ukraine).
This rocket article contains payload capacity, but does not include orbital altitude or inclination, which greatly affects the capacity. |
Function | Orbital carrier rocket |
---|---|
Manufacturer | TsSKB-Progress |
Country of origin | Russia |
Size | |
Height |
|
Diameter | 2.95 m[citation needed] |
Mass | 305,000 kg (672,000 lb) |
Stages | 2 (Soyuz FG) or 3 (Soyuz-FG/Fregat) |
Capacity | |
Payload to LEO | |
Mass |
|
Payload to SSO | |
Mass | FG/Fregat: 4,500 kg (9,900 lb)[citation needed] |
Associated rockets | |
Family | R-7 (Soyuz) |
Launch history | |
Status | Retired |
Launch sites | |
Total launches | 70 (FG: 60, FG/Fregat: 10)[2][3] |
Success(es) | 69 |
Failure(s) | 1 |
First flight |
|
Last flight |
|
Type of passengers/cargo | |
Boosters – Blok-B,V,G,D[4] | |
No. boosters | 4 |
Height | 19.6 m (64 ft) |
Diameter | 2.68 m (8.8 ft) |
Empty mass | 3,800 kg (8,400 lb) |
Gross mass | 43,400 kg (95,700 lb) |
Powered by | RD-107A |
Maximum thrust |
|
Specific impulse |
|
Burn time | 118 seconds |
Propellant | LOX/RG-1 |
Second stage – Blok-A[4] | |
Height | 27.1 m (89 ft) |
Diameter | 2.95 m (9.7 ft) |
Empty mass | 6,550 kg (14,440 lb) |
Gross mass | 99,500 kg (219,400 lb) |
Powered by | RD-108A |
Maximum thrust |
|
Specific impulse |
|
Burn time | 280 seconds |
Propellant | LOX/RG-1 |
Third stage – Blok-I[4] | |
Height | 6.7 m (22 ft) |
Diameter | 2.66 m (8.7 ft) |
Empty mass | 2,410 kg (5,310 lb) |
Gross mass | 25,300 kg (55,800 lb) |
Powered by | RD-0110 |
Maximum thrust | 297.93 kilonewtons (66,980 lbf) |
Specific impulse | 326 seconds |
Burn time | 230 seconds |
Propellant | LOX/RG-1 |
Upper stage (optional) – Fregat[5] | |
Height | 1.5 m (4.9 ft) |
Diameter | 3.35 m (11.0 ft) |
Empty mass | 930 kg (2,050 lb) |
Propellant mass | 5,250 kg (11,570 lb) |
Powered by | S5.92 |
Maximum thrust | 19.85 kilonewtons (4,460 lbf) |
Specific impulse | 333.2 seconds |
Burn time | 1100 seconds |
Propellant | N2O4/UDMH |
Soyuz-FG made its maiden flight on 20 May 2001, carrying a Progress cargo spacecraft to the International Space Station (ISS). It was retired after the 25 September 2019 launch of Soyuz MS-15 to the ISS; the analog control system significantly limited its capabilities and prompted its replacement by Soyuz-2.[7] From 30 October 2002 to 25 September 2019, the Soyuz-FG was the only vehicle used by the Russian Federal Space Agency to launch Soyuz-TMA and Soyuz-MS crewed spacecraft to the ISS.
For uncrewed flights, Soyuz-FG optionally flew with a Fregat upper stage, developed and produced by Lavochkin Association in Khimki. The maiden flight of this configuration occurred on 2 June 2003, the first of ten such launches.[3] Launches of the Soyuz-FG/Fregat configuration were marketed by a European-Russian company called Starsem.
Soyuz-FG was launched from the Baikonur Cosmodrome in Kazakhstan, from Gagarin's Start (pad LC-1/5) for crewed missions, and from LC-31/6 for satellite launches with the Fregat variant.
The Soyuz-FG performed 64 successful launches until its first failure on 11 October 2018 with the Soyuz MS-10 mission. A video recording of the spaceflight released several weeks later suggested a faulty sensor, resulted in the destruction of the rocket. The crew, NASA astronaut Nick Hague and Russian cosmonaut Aleksey Ovchinin, escaped safely.[8]