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Chang Zheng 4
Part of CZ Family
CZ-4A
CZ-4A
Chinese orbital launch vehicle. The CZ-4 was developed and manufactured by the Shanghai Academy of Spaceflight Technology. Its first stage was essentially the same as that of the CZ-3 and the second stage was identical to that of the CZ-3. The CZ-4's third stage, however, was a development, featuring a thin wall common intertank bulkhead tankage and two-engine cluster with both engines gimbaling about two perpendicular axes. The third stage engine cluster connected to the tank aft bulkhead through the engine bay. The CZ-4 had two payload fairing configurations: Type-A and Type-B. The CZ-4 was designed for launching satellites into polar and sun-synchronous orbits.

AKA: Chang Zheng-4A;CZ-4A;Long March 4A. Status: Retired 1990. First Launch: 1988-09-06. Last Launch: 1990-09-03. Number: 2 . Payload: 4,680 kg (10,310 lb). Thrust: 2,960.00 kN (665,430 lbf). Gross mass: 249,000 kg (548,000 lb). Height: 41.90 m (137.40 ft). Diameter: 3.35 m (10.99 ft). Apogee: 200 km (120 mi).

The CZ-4's typical payload capability is 1,650kg into a 600km sun-synchronous orbits and 4,680 kg into a 200km circular orbit. On September 7, 1988, the CZ-4A made its first flight, successfully launching China's first experimental meteorological satellite. Another meteorological satellite was successfully launched by a CZ-4A on September 3, 1990.

After the development of FB-1 launch vehicle, the Shanghai Administration of Astronautics was assigned development of the CZ-4, using the CZ-3C as the first two stages. The CZ-4's Chief Designer was Sun Jingliang. The three stage liquid propellant booster was designed to place satellites into sun-synchronous or geostationary orbits. The third stage used two new design storable propellant gimbaled rocket engines with a vacuum thrust of 50 kN (5.1 metric tons). The total length of the vehicle was 41.9 m, maximum diameter 3.35 m, lift-off mass 240 metric tons lift-off thrust 2942 kN (300 metric tons thrust). It could send a satellite of 1400 kg into a sun-synchronous orbit of 900 km altitude. The Long March-4 launch vehicle started its conceptual design in 1978; it was assigned to be the launch vehicle of Fengyun-l meteorological satellite in March 1982, and its development work was started in the Shanghai Administration of Astronautics and the liquid rocket engine establishments of the Ministry of Aerospace Industry. The successful development of the Long March-4 launch vehicle added a booster for sun-synchronous satellite to the launch vehicle series of China and made a new contribution to the development of China's space carrier technology.

LEO Payload: 4,680 kg (10,310 lb) to a 200 km orbit. Payload: 1,100 kg (2,400 lb) to a GTO. Launch Price $: 30.000 million in 1985 dollars.

Stage Data - CZ-4A

  • Stage 1. 1 x CZ-4A-1. Gross Mass: 192,700 kg (424,800 lb). Empty Mass: 9,500 kg (20,900 lb). Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 170 sec. Isp(sl): 259 sec. Diameter: 3.35 m (10.99 ft). Span: 6.00 m (19.60 ft). Length: 24.66 m (80.90 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: YF-20B. Other designations: L-180. Status: In Production.
  • Stage 2. 1 x CZ-4A-2. Gross Mass: 39,550 kg (87,190 lb). Empty Mass: 4,000 kg (8,800 lb). Thrust (vac): 831.005 kN (186,817 lbf). Isp: 295 sec. Burn time: 135 sec. Isp(sl): 260 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 10.41 m (34.15 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: YF-25/23. Other designations: L-35. Status: In Production.
  • Stage 3. 1 x CZ-4A-3. Gross Mass: 15,150 kg (33,400 lb). Empty Mass: 1,000 kg (2,200 lb). Thrust (vac): 100.810 kN (22,663 lbf). Isp: 303 sec. Burn time: 400 sec. Isp(sl): 260 sec. Diameter: 2.90 m (9.50 ft). Span: 2.90 m (9.50 ft). Length: 1.92 m (6.29 ft). Propellants: N2O4/UDMH. No Engines: 2. Engine: YF-40. Other designations: L-14. Status: In Production.


More at: Chang Zheng 4.

Family: orbital launch vehicle. Country: China. Engines: YF-25/23, YF-20B, YF-40. Spacecraft: SJ, FY-1. Launch Sites: Taiyuan, Taiyuan LC1. Stages: CZ-4A-3, CZ-4A-1, CZ-4A-2. Agency: CALT.

1988 September 6 - . 20:30 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4.
  • FY-1A - . Payload: Feng Yun 1A. Mass: 750 kg (1,650 lb). Nation: China. Agency: MAI. Class: Technology. Type: Weather technology satellite. Spacecraft: FY-1. USAF Sat Cat: 19467 . COSPAR: 1988-080A. Apogee: 895 km (556 mi). Perigee: 875 km (543 mi). Inclination: 98.8000 deg. Period: 102.70 min. Experimental weather satellite. First use of new launch site and launch vehicle. Failed after 38 days due to problems with attitude control system..

1990 September 3 - . 00:53 GMT - . Launch Site: Taiyuan. Launch Complex: Taiyuan LC1. LV Family: CZ. Launch Vehicle: Chang Zheng 4.
  • FY-1B - . Payload: Feng Yun 1B. Mass: 881 kg (1,942 lb). Nation: China. Agency: MAI. Class: Technology. Type: Weather technology satellite. Spacecraft: FY-1. USAF Sat Cat: 20788 . COSPAR: 1990-081A. Apogee: 897 km (557 mi). Perigee: 875 km (543 mi). Inclination: 98.8000 deg. Period: 102.70 min. Experimental weather satellite. Operated for over a year..
  • QQW 2 - . Payload: QQW 1B. Mass: 4.00 kg (8.80 lb). Nation: China. Agency: MAI. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SJ. Decay Date: 1991-07-24 . USAF Sat Cat: 20790 . COSPAR: 1990-081C. Apogee: 629 km (390 mi). Perigee: 596 km (370 mi). Inclination: 99.0000 deg. Period: 97.00 min. QQW atmospheric balloon..
  • QQW 1 - . Payload: QQW 1A. Mass: 4.00 kg (8.80 lb). Nation: China. Agency: MAI. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SJ. Decay Date: 1991-03-11 . USAF Sat Cat: 20789 . COSPAR: 1990-081B. Apogee: 811 km (503 mi). Perigee: 789 km (490 mi). Inclination: 99.0000 deg. Period: 100.90 min. QQW atmospheric balloon..


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