Source: astronautix.com

10-21-2007 10:21

The Long March 3A was a three-stage launch vehicle. By incorporating the mature technologies of the CZ-3 and adding a more powerful cryogenic third stage and more capable control system, the CZ-3A had a greater geosynchronous transfer orbit capability, greater flexibility for attitude control, and better adaptability to a variety of launch missions.

The CZ-3A's geosynchronous transfer orbit payload capability was 2,700kg. By June 30, 1998, the CZ-3A had made three consecutive successful launches, and was offered to international customers.

Manufacturer: CALT. Launches: 14. Success Rate: 100.00%. First Launch Date: 1994-02-08. Last Launch Date: 2007-05-31. Launch data is: continuing. LEO Payload: 7?00 kg (15?00 lb). to: 200 km Orbit. at: 28.50 degrees. Payload: 2?00 kg (5?00 lb). to a: Geosynchronous transfer trajectory. Apogee: 40?00 km (24?00 mi). Associated Spacecraft: Beidou, DFH-3, FH-1, SJ. Liftoff Thrust: 2?60.000 kN (665?30 lbf). Total Mass: 241?00 kg (531?00 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 52.50 m (172.20 ft). Launch Price $: 55.000 million. in: 1999 price dollars.

Stage Data - CZ-3A

Stage Number: 1. 1 x Stage: CZ-3A-1. Gross Mass: 179?00 kg (394?00 lb). Empty Mass: 9?00 kg (19?00 lb). Thrust (vac): 3?65.143 kN (734?33 lbf). Isp: 289 sec. Burn time: 155 sec. Isp(sl): 259 sec. Diameter: 3.35 m (10.99 ft). Span: 7.00 m (22.90 ft). Length: 23.08 m (75.72 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: YF-20B. Other designations: L-180. Status: Development ended 1997.

Stage Number: 2. 1 x Stage: CZ-3A-2. Gross Mass: 33?00 kg (74?00 lb). Empty Mass: 4?00 kg (8?00 lb). Thrust (vac): 831.005 kN (186?17 lbf). Isp: 297 sec. Burn time: 110 sec. Isp(sl): 260 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 11.53 m (37.82 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: YF-25/23. Other designations: L-35. Status: In production.

Stage Number: 3. 1 x Stage: CZ-3A-3. Gross Mass: 21?00 kg (46?00 lb). Empty Mass: 2?00 kg (6?00 lb). Thrust (vac): 156.000 kN (35?70 lbf). Isp: 440 sec. Burn time: 470 sec. Diameter: 3.00 m (9.80 ft). Span: 3.00 m (9.80 ft). Length: 12.38 m (40.60 ft). Propellants: Lox/LH2. No Engines: 2. Engine: YF-75. Other designations: H-18. Status: Development ended 1997.

 

Editor:Yang Jie