The Changzheng 2D (CZ-2D, or "Long March 2D") was developed by the Shanghai Academy of Spaceflight Technology (SAST) as a medium-lift launch vehicle for LEO launch missions. The two-stage rocket was derived from the CZ-2, but had been incorporated with designs and technologies of the CZ-4A for improved performance. The rocket was slightly heavier than the CZ-2C, with a payload capacity of 3,100kg to LEO.
The Chinese military began to develop the improved FSW-2 (Jianbing 1B) reconnaissance satellite with increased mass in the mid-1980s. As the CZ-2C didn't have enough payload capacity to put the satellite into orbit, a heavier launch vehicle was needed. Initially CALT proposed to redesign the CZ-2C to further increase its payload capacity, but it was rejected due to the high cost. Finally the Ministry of Astronautics decided in early 1990 to adopt the CZ-2D design proposed by SAST for launching the new FSW satellite .
The development of the CZ-2D began in February 1990 and took two years to complete. The first rocket was rolled out in 1992 and was launched from the Jiuquan Satellite Launch Centre on 9 August 1992, successfully sending the 2,600kg FSW-2-01 satellite into orbit.
|Overall length||33.67 m|
|Core stage diameter||3.35 m|
|Take-off mass||237 tonnes|
|Take-off thrust||2,961.6 kN|
|LEO capacity||3,100 kg|
|Length||24.66 m||9.007 m|
|Diameter||3.35 m||3.35 m|
|Gross mass||192 tonnes||40.644 tonnes|
|Empty mass||9.82 tonnes||3.122 tonnes|
|Propellant mass||183 tonnes||34.736 tonnes|
(Swivelling) 4 X YF-23
|Thrust*||2,961.6 kN||(Main) 719.8 kN
(Swivelling) 46.1 kN
|Isp*||2,550 N.s/kg||(Main) 2,822 N.s/kg
(Swivelling) 2,762 N.s/kg
|Burn time||154.2 sec||(Main) 113.48 sec
(Swivelling) 274.42 sec
* Sea-level values for the first-stage, and vacuum values for the second-stage
- 李成智 [Li Cheng-zhi], "中国航天技术发展史稿 中部" ["A Draft History of Space Technology in China (Part 2 of 3)"], 山东教育出版社 [Shandong Education Press], 2005, pp. 442-444.
Last updated: 23 February 2012