Encyclopedia Astronautica
FB-1



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FB-1 Launch
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FB-1 Engine
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FB-1
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Chinese RV Test
Test of low drag Chinese re-entry vehicle, 1998.
Credit: Richard D. Fisher, Jr
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FB-1
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FB-1
Chinese orbital launch vehicle. The FB-1, like the CZ-2 launch vehicle begun the following year, was a two-stage booster developed from the DF-5 intercontinental ballistic missile. Payload for the booster was the JSSW, believed to have been a television-transmission military reconnaissance satellite. The incredible decision to develop two nearly identical rockets concurrently can be blamed on the turbulent factional politics after the Cultural Revolution.

The 'Gang of Four' was formed by Mao Zedong's wife Jiang Qing, a Shanghai Propaganda Department official, a literary critic, and a Shanghai security guard. They rose to power during turbulent period of the Cultural Revolution (1966-1976) and dominated Chinese politics during that time. Development of the FB-1 (Feng Bao-1 = Storm-1), the first Chinese heavy-lift launch vehicle, began under their auspices in the autumn of 1969. A development team was formed with the Shanghai No. 2 Bureau of Mechanic-Electrical Industry as the leader. General system design was started in December the same year.

After Mao's death in September 1976, the Gang of Four was arrested and orbital flights of the FB-1 and JSSW came to a halt. In 1980 the Gang of Four were tried in court and given lengthy prison sentences. The final FB-1 made its last flight a year later with a payload of assorted scientific satellites. The FB-1 had slightly lower performance than the CZ-2 and no useful results from the series of JSSW satellites launched have been reported. However the Shanghai facility remained in use, being assigned development of the CZ-4 variants of the triumphant CZ-2 design.

LEO Payload: 2,500 kg (5,500 lb) to a 200 km orbit. Failures: 4. First Fail Date: 1973-09-18. Last Fail Date: 1979-07-28 in 1985 dollars. Flyaway Unit Cost $: 6.000 million.

Stage Data - FB-1

  • Stage 1. 1 x FB-1-1. Gross Mass: 150,400 kg (331,500 lb). Empty Mass: 10,000 kg (22,000 lb). Thrust (vac): 3,000.000 kN (674,400 lbf). Isp: 289 sec. Burn time: 128 sec. Isp(sl): 258 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 20.10 m (65.90 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: YF-20A. Status: In Production.
  • Stage 2. 1 x FB-1-2. Gross Mass: 38,300 kg (84,400 lb). Empty Mass: 3,500 kg (7,700 lb). Thrust (vac): 761.900 kN (171,282 lbf). Isp: 295 sec. Burn time: 127 sec. Isp(sl): 270 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 7.40 m (24.20 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: YF-22/23. Status: Out of Production.

AKA: Feng Bao 1; Storm 1; Feng-Bao-1.
Status: Retired 1981.
Gross mass: 191,700 kg (422,600 lb).
Payload: 2,500 kg (5,500 lb).
Height: 33.00 m (108.00 ft).
Diameter: 3.35 m (10.99 ft).
Thrust: 2,679.00 kN (602,263 lbf).
Apogee: 200 km (120 mi).
First Launch: 1972.08.10.
Last Launch: 1981.09.19.
Number: 11 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • JSSW Chinese military surveillance satellite. 6 launches, 1973.09.18 (JSSW 1) to 1976.11.10 (JSSW 6). Mysterious early Chinese satellite, orbited by the cancelled FB-1 launch vehicle. More...
  • SJ Chinese communications technology satellite. First launch 1979.07.28. SJ (Shijian) series were Chinese scientific research, technological experiment and military operational satellites of a variety of configurations. More...

Associated Engines
  • YF-20A Beijing Wan Yuan N2O4/UDMH rocket engine. 750.2 kN. Out of production. Isp=289s. Boosted CZ-2A, CZ-2C, CZ-2E(A), CZ-3, FB-1. First flight 1972. More...
  • YF-22/23 Beijing Wan Yuan N2O4/UDMH rocket engine. 762 kN. Out of production. Cluster of YF-22 and 4 x YF-23 verniers. Isp=295s. Boosted CZ-2A, FB-1. First flight 1972. More...

See also
  • CZ China's first ICBM, the DF-5, first flew in 1971. It was a two-stage storable-propellant rocket in the same class as the American Titan, the Russian R-36, or the European Ariane. The DF-5 spawned a long series of Long March ("Chang Zheng") CZ-2, CZ-3, and CZ-4 launch vehicles. These used cryogenic engines for upper stages and liquid-propellant strap-on motors to create a family of 12 Long-March rocket configurations capable of placing up to 9,200 kg into orbit. In 2000 China began development of a new generation of expendable launch vehicles using non-toxic, high-performance propellants with supposedly lower operating costs. However these encountered development delays, and it seemed the reliable Long March series of rockets would continue in operational use for nearly fifty years before being replaced. More...

Associated Manufacturers and Agencies
  • CALT Chinese manufacturer of rockets, spacecraft, and rocket engines. China Academy of Launch Vehicle Technology, Beijing, China. More...

Associated Launch Sites
  • Jiuquan China's first launch center, also known as Shuang Cheng Tzu. Jiuquan Satellite Launch Centre, situated at 100 degrees East, 41 degrees North, is located in the Jiuquan Region, Gansu province, north-western China. It was China's first ballistic missile and satellite launch centre. More...

Associated Stages
  • FB-1-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 150,400/10,000 kg. Thrust 3,000.00 kN. Vacuum specific impulse 289 seconds. More...
  • FB-1-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 38,300/3,500 kg. Thrust 761.90 kN. Vacuum specific impulse 295 seconds. More...

FB-1 Chronology


1972 August 10 - . 00:32 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-02.
  • Shiyan Peizhong - . Nation: China. Agency: PRC. Apogee: 200 km (120 mi). Summary: Research and Development Suborbital Flight.

1973 September 18 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-03. FAILURE: Failure. Failed Stage: U.
  • JSSW 1 - . Payload: JSSW 1. Nation: China. Agency: PRC. Spacecraft: JSSW. COSPAR: F730918A.

1974 July 14 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-04. FAILURE: Vehicle lost attitude stability and destroyed by range safety.. Failed Stage: G.
  • JSSW 2 - . Payload: JSSW 2. Nation: China. Agency: PRC. Spacecraft: JSSW. COSPAR: F740714A.

1975 July 26 - . 13:28 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-05.
  • JSSW 3 - . Payload: JSSW 3. Mass: 1,107 kg (2,440 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: JSSW. Decay Date: 1975-09-14 . USAF Sat Cat: 8053 . COSPAR: 1975-070A. Apogee: 455 km (282 mi). Perigee: 190 km (110 mi). Inclination: 69.0000 deg. Period: 90.90 min. Summary: Photo surveillance; radio transmission. .

1975 December 16 - . 09:19 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-06.
  • JSSW 4 - . Payload: JSSW 4. Mass: 1,110 kg (2,440 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: JSSW. Decay Date: 1976-01-27 . USAF Sat Cat: 8488 . COSPAR: 1975-119A. Apogee: 387 km (240 mi). Perigee: 186 km (115 mi). Inclination: 69.0000 deg. Period: 90.30 min. Summary: Photo surveillance; radio transmission. .

1976 August 30 - . 11:53 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-07.
  • JSSW 5 - . Payload: JSSW 5. Mass: 1,108 kg (2,442 lb). Nation: China. Agency: MAI. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: JSSW. Decay Date: 1978-11-25 . USAF Sat Cat: 9394 . COSPAR: 1976-087A. Apogee: 2,145 km (1,332 mi). Perigee: 195 km (121 mi). Inclination: 69.2000 deg. Period: 108.80 min.

1976 November 10 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701-08. FAILURE: Failure. Failed Stage: U.
  • JSSW 6 - . Payload: JSSW 6. Nation: China. Agency: PRC. Spacecraft: JSSW. COSPAR: F761110A.

1977 September 14 - . 00:15 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701(II)-01.
  • DDDS test - . Nation: China. Agency: PRC. Apogee: 200 km (120 mi).

1978 April 15 - . 16:39 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701(II)-02.
  • DDDS test - . Nation: China. Agency: PRC. Apogee: 200 km (120 mi).

1979 July 28 - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 XCZ-1-02. FAILURE: Second stage failure.. Failed Stage: 2.
  • SJ-1 - . Payload: Shi Jian 1. Mass: 221 kg (487 lb). Nation: China. Agency: PRC. Spacecraft: SJ. COSPAR: F790728A. Summary: The SJ-1 was similar in appearance to the American Telstar and conducted communications technology tests..

1981 September 19 - . 21:28 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 XCZ-1-02.
  • SJ-2A - . Payload: Shi Jian 2B. Mass: 257 kg (566 lb). Nation: China. Agency: MAI. Class: Technology. Type: Navigation technology satellite. Spacecraft: SJ. Decay Date: 1981-09-26 . USAF Sat Cat: 12842 . COSPAR: 1981-093A. Apogee: 1,598 km (992 mi). Perigee: 232 km (144 mi). Inclination: 59.5000 deg. Period: 103.30 min.
  • SJ-2B - . Payload: Shi Jian C. Mass: 28 kg (61 lb). Nation: China. Agency: MAI. Class: Technology. Type: Navigation technology satellite. Spacecraft: SJ. Decay Date: 1982-10-06 . USAF Sat Cat: 12843 . COSPAR: 1981-093B. Apogee: 1,615 km (1,003 mi). Perigee: 233 km (144 mi). Inclination: 59.4000 deg. Period: 103.50 min. Summary: Balloon for drag studies..
  • SJ-2 - . Payload: Shi Jian 2. Mass: 483 kg (1,064 lb). Nation: China. Agency: MAI. Class: Technology. Type: Navigation technology satellite. Spacecraft: SJ. Decay Date: 1982-08-17 . USAF Sat Cat: 12845 . COSPAR: 1981-093D. Apogee: 1,608 km (999 mi). Perigee: 232 km (144 mi). Inclination: 59.4000 deg. Period: 103.40 min.

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