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Soyuz ST / Fregat ST
Part of R-7 Family
Uprated Soyuz booster designed for commercial customers. Upgraded engines, modern avionics, reduced non-Russian content. Uses Fregat upper stage.

AKA: A-2;Sapwood;SL-4. Status: Active. First Launch: 2014-12-18. Last Launch: 2015-09-11. Number: 3 . Payload: 5,500 kg (12,100 lb). Thrust: 4,144.70 kN (931,766 lbf). Gross mass: 305,000 kg (672,000 lb). Height: 46.10 m (151.20 ft). Diameter: 2.95 m (9.67 ft). Apogee: 450 km (270 mi).

Also known as the Soyuz 2, it was a modernization of the Soyuz launcher that increased general performance. The basic launch vehicle design remained the same. Changes 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.

The Fregat upper stage has a flight-proved propulsion subsystem that is based on a single-chamber Lavochkin engine. Four clusters of three 50-N hydrazine thrusters provide attitude control. The Fregat propulsion system powered the Fobos probe to Mars, and the main engine was fitted on nearly 30 interplanetary spacecraft. During its numerous missions, the engine demonstrated the highest reliability under extreme conditions, exceeding technical specifications. This application of proven, in-production hardware ensures high reliability and lower cost for the Fregat upper stage. Fregat operates on UDMH fuel and N2O4 oxidizer, and has a liftoff mass of up to 6,535 kg. The weight at burnout is 950-1,100 kg.. Vacuum thrust is 19.6 kN., and burn time is up to 877 sec. The engine can be restarted as many as 20 times.

LEO Payload: 5,500 kg (12,100 lb) to a 450 km orbit at 51.80 degrees. Payload: 4,500 kg (9,900 lb) to a 800 km SSO. Launch Price $: 35.000 million in 1999 dollars.

Stage Data - Soyuz ST / Fregat ST

  • 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.
  • Stage 3. 1 x Fregat. Gross Mass: 6,535 kg (14,407 lb). Empty Mass: 1,100 kg (2,400 lb). Thrust (vac): 19.600 kN (4,406 lbf). Isp: 327 sec. Burn time: 877 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 1.50 m (4.90 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: S5.92. Status: Out of Production. Comments: Upper stage developed from propulsion bus for Lavochkin lunar and planetary probes (Luna Ye-8, Mars M1, Fobos 1F). 20 restarts.



Family: orbital launch vehicle. Country: Russia. Engines: S5.92. Spacecraft: ELiTeBus, Galileo Navsat, Meteor-M. Launch Sites: Kourou ZLS, Baikonur, Plesetsk, Baikonur LC31, Kourou ELS, Plesetsk LC43. Stages: Fregat, Soyuz ST-0, Soyuz ST-1, Soyuz ST-2. Agency: Korolev bureau.

2014 December 18 - . 18:37 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELS. LV Family: R-7. Launch Vehicle: Soyuz ST / Fregat ST.
  • O3b FM9 - . Mass: 700 kg (1,540 lb). Nation: UK. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 40351 . COSPAR: 2014-083D. Apogee: 8,071 km (5,015 mi). Perigee: 8,061 km (5,008 mi). Inclination: 0.0500 deg. Period: 287.93 min. Second quartet of O3b satellites for broadband internet distribution. Each satellite carried an array of 12 Ka-band spot beam dishes and provided capacity for internet providers in the developing world..
  • O3b FM10 - . Mass: 700 kg (1,540 lb). Nation: UK. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 40349 . COSPAR: 2014-083B. Apogee: 8,070 km (5,010 mi). Perigee: 8,061 km (5,008 mi). Inclination: 0.0400 deg. Period: 287.93 min. O3b satellites launched as part of a constellation for broadband internet distribution..
  • O3b FM11 - . Mass: 700 kg (1,540 lb). Nation: UK. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 40349 . COSPAR: 2014-083B. Apogee: 8,070 km (5,010 mi). Perigee: 8,061 km (5,008 mi). Inclination: 0.0400 deg. Period: 287.93 min.
  • O3b FM12 - . Mass: 700 kg (1,540 lb). Nation: UK. Class: Communications. Type: Communications satellite. Spacecraft: ELiTeBus. USAF Sat Cat: 40350 . COSPAR: 2014-083C. Apogee: 8,070 km (5,010 mi). Perigee: 8,062 km (5,009 mi). Inclination: 0.0400 deg. Period: 287.93 min.

2015 March 27 - . 21:46 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELS. LV Family: R-7. Launch Vehicle: Soyuz ST / Fregat ST.
  • GalileoSat-7 - . Payload: Galileo FOC FM03 / Adam. Mass: 733 kg (1,615 lb). Nation: Europe. Class: Navigation. Type: Navigation satellite. Spacecraft: Galileo Navsat. USAF Sat Cat: 40544 . COSPAR: 2015-017A. Apogee: 23,234 km (14,436 mi). Perigee: 23,210 km (14,420 mi). Inclination: 55.1900 deg. Period: 844.70 min. European navigation satellite..
  • GalileoSat-8 - . Payload: Galileo FOC FM04 / Anastasia. Mass: 733 kg (1,615 lb). Nation: Europe. Class: Navigation. Type: Navigation satellite. Spacecraft: Galileo Navsat. USAF Sat Cat: 40545 . COSPAR: 2015-017B. Apogee: 23,234 km (14,436 mi). Perigee: 23,210 km (14,420 mi). Inclination: 55.2000 deg. Period: 844.69 min. European navigation satellite..

2015 September 11 - . 02:08 GMT - . Launch Site: Kourou. Launch Complex: Kourou ZLS. LV Family: R-7. Launch Vehicle: Soyuz ST / Fregat ST.
  • GalileoSat-9 - . Payload: Galileo FOC FM05 / Alba. Mass: 733 kg (1,615 lb). Nation: Europe. Class: Navigation. Type: Navigation satellite. Spacecraft: Galileo Navsat. USAF Sat Cat: 40889 . COSPAR: 2015-045A. Apogee: 23,233 km (14,436 mi). Perigee: 23,211 km (14,422 mi). Inclination: 57.3800 deg. Period: 844.70 min. Two European navigation satellites in the Galileo system. The Fregat upper stage deployed them in plane A of the system, at an inclination of 57.4 degrees (satellites in the existing B and C planes are in 55.0 degree orbits)..
  • GalileoSat-10 - . Payload: Galileo FOC FM06 / Orlana. Mass: 733 kg (1,615 lb). Nation: Europe. Class: Navigation. Type: Navigation satellite. Spacecraft: Galileo Navsat. USAF Sat Cat: 40890 . COSPAR: 2015-045B. Apogee: 23,231 km (14,435 mi). Perigee: 23,213 km (14,423 mi). Inclination: 57.3800 deg. Period: 844.70 min.


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