Soyuz-FG

This article is about the Soyuz-FG rocket. For other Soyuz variants, see Soyuz (rocket family).
Soyuz FG (Soyuz-FG/Fregat)

The launch of Soyuz TMA-3 atop a Soyuz-FG rocket.
Function Orbital carrier rocket
Manufacturer TsSKB-Progress
Country of origin Russia
Size
Height 49.5 m for Soyuz-FG and 42.5 m for Soyuz-FG/Fregat
Diameter 2.95 m
Mass 305,000 kg (672,000 lb)
Stages 2 (Soyuz FG) or 3 (Soyuz-FG/Fregat)
Capacity
Payload to LEO 6900 kg[1] for Soyuz-FG and 7,800 kg for Soyuz-FG/Fregat
Payload to
800km SSO
(only for Soyuz-FG/Fregat)		 4,500 kg (9,900 lb)
Associated rockets
Family R-7 (Soyuz)
Launch history
Status Active
Launch sites

Soyuz-FG: LC-1/5 & LC-31/6, Baikonur

Soyuz-FG/Fregat: LC-31/6, Baikonur
Total launches 58 (FG: 48, FG/Fregat: 10)[2][3]
Successes 58[2][3]
First flight Soyuz-FG: May 20, 2001
Soyuz-FG/Fregat: June 2, 2003
Last flight Soyuz-FG: November 17, 2016
Soyuz-FG/Fregat: July 22, 2012
Notable payloads
Boosters - Blok-B,V,G,D[4]
No. boosters 4
Length 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)
Engines RD-107A
Thrust Sea Level: 838.5 kN (188,500 lbf)
Vacuum: 1,021.3 kN (229,600 lbf)
Specific impulse Sea Level: 263.3 s (2.582 km/s)
Vacuum: 320.2 s (3.140 km/s)
Burn time 118 seconds
Fuel LOX/RG-1
First stage - Blok-A[4]
Length 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)
Engines RD-108A
Thrust Sea Level: 792.48 kN (178,160 lbf)
Vacuum: 990.18 kN (222,600 lbf)
Specific impulse Sea Level: 257.7 s (2.527 km/s)
Vacuum: 320.6 s (3.144 km/s)
Burn time 280 seconds
Fuel LOX/RG-1
Second stage - Blok-I[4]
Length 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)
Engines RD-0110
Thrust 297.93 kilonewtons (66,980 lbf)
Specific impulse 326 seconds
Burn time 230 seconds
Fuel LOX/RG-1
Upper stage (optional) - Fregat[5]
Length 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)
Engines S5.92
Thrust 19.85 kilonewtons (4,460 lbf)
Specific impulse 333.2 seconds
Burn time 1100 seconds
Fuel N2O4/UDMH

The Soyuz-FG launch vehicle is an improved version of the Soyuz-U, from the R-7 family of rockets, designed and constructed by TsSKB-Progress in Samara. It made its maiden flight on May 20, 2001, carrying a Progress M1-6 cargo spacecraft to the International Space Station (ISS).

Since October 30, 2002 the Soyuz-FG has been the only vehicle used by the Russian Federal Space Agency to launch Soyuz-TMA and Soyuz-MS manned spacecraft to the ISS. All launches have been successful.[2]

Another version of the Soyuz-FG is the Soyuz-FG/Fregat with Fregat as its 3rd stage, developed and produced by Lavochkin Association in Khimki. A European-Russian company Starsem owns all rights to launches using this version. As of December 2014 there have been 10 launches of Soyuz-FG/Fregat with commercial payloads.[3] Its maiden flight occurred on June 2, 2003.

The analog control system of this spacecraft significantly limits its capabilities, and it will eventually be replaced by the Soyuz-2 launch vehicle.

The Soyuz-FG is launched from the Baikonur Cosmodrome in Kazakhstan, using launch site LC-1/5 for Soyuz-FG and LC-31/6 for Soyuz-FG/Fregat.


Launch history

See also

The Soyuz TMA-13 spacecraft arrives at the launch pad at the Baikonur Cosmodrome in Kazakhstan October 10, 2008.

References

  1. ↑ "SOYUZ-FG Launch Vehicle". TsSKB-Progress. Retrieved 1 April 2016.
  2. 1 2 3 Krebs, Gunter. "Soyuz-FG (11A511U-FG)". Gunter's Space Page. Retrieved 2016-10-28.
  3. 1 2 3 Krebs, Gunter. "Soyuz-FG Fregat (11A511U-FG)". Gunter's Space Page. Retrieved 2016-04-02.
  4. 1 2 3 "ФЕДЕРАЛЬНОЕ КОСМИЧЕСКОЕ АГЕНТСТВО (РОСКОСМОС)". www.federalspace.ru. Retrieved 2016-04-07.
  5. ↑ "Конструкция разгонного блока "Фрегат"". NPO Lavochkin (in Russian). Retrieved 10 March 2016.
  6. ↑ "Soyuz FG". Encyclopedia Astronautica.
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