Encyclopedia Astronautica
YF-22A/23A


Beijing Wan Yuan N2O4/UDMH rocket engine. 762 kN. Out of production. Cluster of YF-22A and 4 x YF-23 verniers. Isp=295s. Boosted CZ-2C, CZ-3. First flight 1975.

Thrust (sl): 697.400 kN (156,782 lbf). Thrust (sl): 71,115 kgf. Chamber Pressure: 71.00 bar. Area Ratio: 10.

Status: Out of production.
Diameter: 3.35 m (10.99 ft).
Thrust: 762.00 kN (171,304 lbf).
Specific impulse: 295 s.
Specific impulse sea level: 270 s.
Burn time: 130 s.
Number: 48 .

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Associated Countries
See also
Associated Launch Vehicles
  • CZ-2C Chinese orbital launch vehicle. The CZ-2C was the definitive low earth orbit launch vehicle derived from DF-5 ICBM. It became the basis for an entire family of subsequent Long March vehicles. Many adaptive modifications were made to the configuration of the CZ-2A to handle a variety of new satellites and upper stages. The CZ-2C had improved technical performance and payload capacity compared to the CZ-2A, with later versions having a payload capability of 2,800 kg into a 200 km circular orbit. More...
  • CZ-3 Chinese orbital launch vehicle. The Long March 3 was a three-stage launch vehicle designed for delivery of satellites of 1,500 kg mass into geosynchronous transfer orbit. The first and second stages were based on the CZ-2C, and designed and manufactured by the Shanghai Academy of Spaceflight Technology. The majority of the technology and flight hardware used in the CZ-3 had been qualified and proven on the CZ-2C. The third stage, manufactured by CALT, was equipped with an LOX/LH2 cryogenic engine. Long March 3 was also capable of placing spacecraft into an elliptical or circular low earth orbit and sun synchronous orbit. More...

Associated Manufacturers and Agencies
Associated Propellants
  • N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...

Associated Stages
  • CZ-2C/SD-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 55,000/5,000 kg. Thrust 761.90 kN. Vacuum specific impulse 298 seconds. Stretched version of CZ-2C second stage. Empty mass estimated. More...
  • CZ-2C-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 39,000/4,000 kg. Thrust 761.90 kN. Vacuum specific impulse 295 seconds. More...
  • CZ-3-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 39,000/4,000 kg. Thrust 761.90 kN. Vacuum specific impulse 295 seconds. More...

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