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Chang Zheng 2

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AKA: Chang Zheng 2A;Chang Zheng-2A;CSL-2;CZ-2A;Long March 2A. Status: Retired 1974. First Launch: 1974-11-05. Last Launch: 1974-11-05. Number: 1 . Payload: 2,000 kg (4,400 lb). Thrust: 2,690.00 kN (604,730 lbf). Gross mass: 190,000 kg (410,000 lb). Height: 32.00 m (104.00 ft). Diameter: 3.35 m (10.99 ft). Apogee: 200 km (120 mi).

Development of the launcher was begun in 1970 by the Chinese Academy of Launch Vehicle Technology (CALT) under president Ren Xinmin. The DF-5 intercontinental ballistic missile was the starting point for the design. Four gimbaled liquid rocket engines with a total ground thrust of 2746 kN (280 metric tons) powered the first stage at lift-off. Second stage propulsion consisted of one fixed main engine with a vacuum thrust of 716 kN (73 metric tons thrust) and four sets of swiveling vernier engines with a total thrust of 46 kN (4.7 metric tons thrust). The computerized guidance system used an inertial platform. The development team was led by Tu Shou'e.

LEO Payload: 2,000 kg (4,400 lb) to a 200 km orbit at 52.00 degrees. Launch Price $: 20.000 million in 1994 dollars.

Stage Data - CZ-2A

• 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.

• FSW-0 - . Payload: FSW-0 No. A. Mass: 2,500 kg (5,500 lb). Nation: China. Agency: PRC. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Decay Date: 1974-11-05 .