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Soyuz-FG
Part of R-7 Family
Uprated Soyuz booster designed for high performance Russian government missions and delivery of Soyuz and Progress spacecraft to the International Space Station. Upgraded engines, modern avionics, reduced non-Russian content. Unknown differences to Soyuz ST.

AKA: 11A511FG;A-2;Sapwood;SL-4. Status: Active. First Launch: 2001-05-20. Last Launch: 2017-04-20. Number: 59 . Payload: 7,420 kg (16,350 lb). Thrust: 4,143.00 kN (931,383 lbf). Gross mass: 305,000 kg (672,000 lb). Height: 46.10 m (151.20 ft). Diameter: 2.95 m (9.67 ft). Apogee: 193 km (119 mi).

Modernization of the Soyuz launcher that increased general performance. The basic launch vehicle design remained the same. Changes on the commercial ST version were limited to:

  • The first and second stage engines featured improved performance with new injectors and mixture ratio.
  • The third stage engine performance was increased.
  • The launch vehicle was equipped with a new control system allowing in-flight orbital plane change (whereas all earlier R-7 derived vehicles flew a fixed trajectory, with the launch table rotated before launch to the appropriate azimuth).
  • A new digital telemetry system provided for launch vehicle monitoring.
  • A new, larger-diameter fairing (3.65 meters in diameter) was used.

The standard fourth stage was the Fregat orbital module.

LEO Payload: 7,420 kg (16,350 lb) to a 193 km orbit at 51.80 degrees. Launch Price $: 50.000 million in 1999 dollars.

Stage Data - Soyuz FG

  • Stage 0. 4 x Soyuz ST-0. Gross Mass: 44,400 kg (97,800 lb). Empty Mass: 3,810 kg (8,390 lb). Thrust (vac): 1,021.097 kN (229,552 lbf). Isp: 310 sec. Burn time: 120 sec. Isp(sl): 264 sec. Diameter: 2.68 m (8.79 ft). Span: 2.68 m (8.79 ft). Length: 19.60 m (64.30 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-117. Status: In production. Comments: Gross mass includes 1190 kg of hydrogen peroxide and 280 kg of liquid nitrogen expended during ascent but not contributing to propulsion.
  • Stage 1. 1 x Soyuz ST-1. Gross Mass: 105,400 kg (232,300 lb). Empty Mass: 6,875 kg (15,156 lb). Thrust (vac): 999.601 kN (224,719 lbf). Isp: 311 sec. Burn time: 286 sec. Isp(sl): 245 sec. Diameter: 2.95 m (9.67 ft). Span: 2.95 m (9.67 ft). Length: 27.80 m (91.20 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-118. Status: In production. Comments: Gross mass includes 2600 kg of hydrogen peroxide and 520 kg of liquid nitrogen expended during ascent but not contributing to propulsion.
  • Stage 2. 1 x Soyuz ST-2. Gross Mass: 25,200 kg (55,500 lb). Empty Mass: 2,355 kg (5,191 lb). Thrust (vac): 294.000 kN (66,093 lbf). Isp: 359 sec. Burn time: 300 sec. Diameter: 2.66 m (8.72 ft). Span: 2.66 m (8.72 ft). Length: 6.74 m (22.11 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-0124. Status: In production.


More at: Soyuz-FG.

Family: orbital launch vehicle. Country: Russia. Spacecraft: Kanopus, MKA-FKI, SSTL-900, TET, ISS, MicroSat-100, Radarsat, AMOS, Star bus, Globalstar, MiniSat-400, Progress M1, Kolibri, Soyuz TMA, Mars Express, Venus Express, Galileo Navsat. Projects: Galaxy. Launch Sites: Baikonur, Baikonur LC1, Baikonur LC31. Stages: Soyuz ST-0, Soyuz ST-1, Soyuz ST-2. Agency: Korolev bureau.

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