CZ-2E(A) launch vehicle that will be used for manned missions.
Chinese Manned LVs
Chinese Launch Vehicles for Manned Projects. From left: Tsien Spaceplane Launcher, 1978; Project 921 Launch Vehicle, 1992; CZ-2F, 1999; CZ-2E(A), 2000. Only the last two were put into full scale development.
Credit: © Mark Wade
Planned upgrade of CZ-2E with enlarged liquid boosters. Probably intended for launch of Chinese space station modules in the 21st century. Fairing was 5.20 m in diameter and 12.39 m long.
In February 1999 the China Great Wall Company announced that the rocket would be available in 2000 and be launched from the Jiuquan Satellite Launch Center in the northwest part of China.
LEO Payload: 14,100 kg (31,000 lb) to a 200 km orbit at 48.00 degrees. Launch Price $: 55.000 million in 1999 dollars.
Stage Data - CZ-2E(A)
- Stage 0. 4 x CZ-2E(A)-0. Gross Mass: 80,000 kg (176,000 lb). Empty Mass: 8,000 kg (17,600 lb). Thrust (vac): 1,632.800 kN (367,068 lbf). Isp: 291 sec. Burn time: 125 sec. Isp(sl): 261 sec. Diameter: 2.25 m (7.38 ft). Span: 2.26 m (7.41 ft). Length: 27.00 m (88.00 ft). Propellants: N2O4/UDMH. No Engines: 2. Engine: YF-20B. Status: In Production.
- Stage 1. 1 x CZ-2E-1. Gross Mass: 196,500 kg (433,200 lb). Empty Mass: 9,500 kg (20,900 lb). Thrust (vac): 3,265.143 kN (734,033 lbf). Isp: 289 sec. Burn time: 166 sec. Isp(sl): 261 sec. Diameter: 3.35 m (10.99 ft). Span: 6.00 m (19.60 ft). Length: 23.70 m (77.70 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: YF-20B. Other designations: L-180. Status: In Production.
- Stage 2. 1 x CZ-2E-2. Gross Mass: 91,500 kg (201,700 lb). Empty Mass: 5,500 kg (12,100 lb). Thrust (vac): 831.005 kN (186,817 lbf). Isp: 298 sec. Burn time: 295 sec. Isp(sl): 260 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 15.52 m (50.91 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: YF-25/23. Other designations: L-90. Status: In Production.
AKA: Long March 2E(A); Chang Zheng-2E(A).
More... - Chronology...
Status: Design 2000.
Gross mass: 695,000 kg (1,532,000 lb).
Payload: 14,100 kg (31,000 lb).
Height: 53.60 m (175.80 ft).
Diameter: 3.35 m (10.99 ft).
Thrust: 8,910.00 kN (2,003,040 lbf).
Apogee: 200 km (120 mi).
Chinese Space Laboratory Chinese manned space station. Study 2012. The latest models displayed of the Chinese Space Laboratory show it to have a larger-diameter module, about 4 m in diameter, and a narrower module forward, about 3 m in diameter. More...
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-20B Beijing Wan Yuan N2O4/UDMH rocket engine. 816.3 kN. In production. Isp=289s. Boosted CZ-2C, CZ-2D, CZ-2E, CZ-2E(A), CZ-3A, CZ-3B, CZ-3C, CZ-4A. First flight 1988. More...
YF-25/23 Beijing Wan Yuan N2O4/UDMH rocket engine. 831 kN. In production. Cluster of YF-25 and 4 x YF-23 verniers. Isp=295s. First stage engine for CZ-2D, CZ-2E, CZ-2E(A), CZ-3A, CZ-3B, CZ-3C, CZ-4A. First flight 1988. More...
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...
CZ-2E-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 91,500/5,500 kg. Thrust 831.01 kN. Vacuum specific impulse 298 seconds. More...
CZ-2E-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 196,500/9,500 kg. Thrust 3,265.14 kN. Vacuum specific impulse 289 seconds. More...
CZ-2E(A)-0 N2O4/UDMH propellant rocket stage. Loaded/empty mass 80,000/8,000 kg. Thrust 1,632.80 kN. Vacuum specific impulse 291 seconds. More...
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