CZ-2E

The CZ-2 was originally designed for launch of the FSW-1 recoverable military reconnaissance satellite. 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 gimballed liquid rocket engines with a total ground thrust of 2746 kN (280 tonnes) powered the first stage at lift-off. Second stage propulsion consisted of one fixed main engine with a vacuum thrust of 716 kN (73 tonnes thrust) and four sets of swivelling vernier engines with a total thrust of 46 kN (4.7 tonnes thrust). The computerised guidance system used an inertial platform. The development team was led by Tu Shou'e.

Manufacturer: CALT. Launches: 1. Failures: 1. Success Rate: 0.00%. First Launch Date: 1974-11-05. Last Launch Date: 1974-11-05. Launch data is: complete. LEO Payload: 2,000 kg (4,400 lb). to: 200 km Orbit. at: 52.00 degrees. Apogee: 500 km (310 mi). Associated Spacecraft: FSW, Shuguang 1. Liftoff Thrust: 2,690.000 kN (604,730 lbf). Total Mass: 190,000 kg (410,000 lb). Core Diameter: 3.35 m (10.99 ft). Total Length: 32.00 m (104.00 ft). Launch Price $: 20.000 million. in: 1994 price dollars.

• Stage Number: 1. 1 x Stage: 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: Out of production.

• Stage Number: 2. 1 x Stage: 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.

1974 November 5 - Launch Site: Jiuquan. Launch Complex: LA2. Launch Pad: LA2B. Launch Vehicle: CZ-2A. Model: Chang Zheng 2A. LV Configuration: Chang Zheng 2A CZ2-1 (3). FAILURE: Cable carrying pitch rate gyro signal disconnected.

• FSW-0 Nation: China. Payload: FSW-0 No. A. Class: Surveillance. Type: Military. Spacecraft: FSW. Agency: PRC. COSPAR: F741105A. Decay Date: 1974-11-05. References: 5.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...

• Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al. ISBN: 0710618107. The most comprehensive source of information for current space projects. Too expensive for human beings and most libraries. More at amazon.com...

• Wen-Rui Hu, Editor, Space Science in China, Gordon and Breach Science Publishers, China, 1997.. ISBN: 9056990233. More at amazon.com...

• Chen Shilu, Yan Hui, Cai Yuanli, and Zhu Xiaoping, Acta Astronautica, "Progress and Development of Space Technology in China", Vol 46, No 9, p. 559, 2000. Paper IAA-96-IAA.2.2.05 presented at the 47th IA Congress, Beijing, 1996.