Chinese orbital launch vehicle. 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.LEO Payload: 2,000 kg (4,400 lb) to a 200 km orbit at 52.00 degrees. Failures: 1. First Fail Date: 1974-11-05. Last Fail Date: 1974-11-05. 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.
AKA: Long March 2A; Chang Zheng 2A; Chang Zheng-2A; CSL-2.
More... - Chronology...
Status: Retired 1974.
Gross mass: 190,000 kg (410,000 lb).
Payload: 2,000 kg (4,400 lb).
Height: 32.00 m (104.00 ft).
Diameter: 3.35 m (10.99 ft).
Thrust: 2,690.00 kN (604,730 lbf).
Apogee: 200 km (120 mi).
First Launch: 1974.11.05.
Number: 1 .
Shuguang 1 Chinese manned spacecraft. Cancelled 1972. Shuguang-1 (Dawn-1) was China's first manned spacecraft design. The two-man capsule would have been similar to the American Gemini capsule and been launched by the CZ-2 booster. More...
FSW Chinese military surveillance satellite. 24 launches, 1974.11.05 (FSW-0) to 2006.09.09 (SJ-8). 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-22/23 Beijing Wan Yuan N2O4/UDMH rocket engine. 762 kN. Out of production. Cluster of YF-22 and 4 x YF-23 verniers. Isp=295s. Boosted CZ-2A, FB-1. First flight 1972. 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...
Associated Launch Sites
Jiuquan China's first launch center, also known as Shuang Cheng Tzu. Jiuquan Satellite Launch Centre, situated at 100 degrees East, 41 degrees North, is located in the Jiuquan Region, Gansu province, north-western China. It was China's first ballistic missile and satellite launch centre. More...
FB-1-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 150,400/10,000 kg. Thrust 3,000.00 kN. Vacuum specific impulse 289 seconds. More...
FB-1-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 38,300/3,500 kg. Thrust 761.90 kN. Vacuum specific impulse 295 seconds. More...
1974 November 5 -
. Launch Complex
: Jiuquan LA2B
. LV Family
. Launch Vehicle
. LV Configuration
: Chang Zheng 2A CZ2A-1 (3). FAILURE
: Cable carrying pitch rate gyro signal disconnected.. Failed Stage
- FSW-0 - .
Payload: FSW-0 No. A. Nation: China. Agency: PRC. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: FSW. Decay Date: 1974-11-05 . COSPAR: F741105A.
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