Encyclopedia Astronautica
EPKM


Solid propellant rocket stage. Loaded/empty mass 5,985/541 kg. Thrust 117.00 kN. Vacuum specific impulse 298 seconds. Perigee kick motor for putting CZ-2E payloads into geosynchronous transfer orbit. Thrust, burn time estimated. Specific impulse calculated based on motor payload/delta v performance and masses.

Status: Retired 1995.
Gross mass: 5,985 kg (13,194 lb).
Unfuelled mass: 541 kg (1,192 lb).
Height: 3.10 m (10.10 ft).
Diameter: 1.70 m (5.50 ft).
Span: 2.50 m (8.20 ft).
Thrust: 117.00 kN (26,302 lbf).
Specific impulse: 298 s.
Burn time: 135 s.
Number: 8 .

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Associated Countries
Associated Engines
  • EPKM Fourth Academy solid rocket engine. 189.994 kN. Isp=292s. Chinese kick stage for use on CZ-2E for launch of Asiasat-2 and Echostar-1. Diameter increased to 1.7 m in comparison to basic 1.4 m diameter motor. Spin stabilised. First flight 1990. More...

Associated Launch Vehicles
  • CZ-2E Chinese orbital launch vehicle. The CZ-2E added four liquid rocket booster strap-ons to the basic CZ-2 core to achieve a low earth orbit payload capability approaching the Russian Proton, US Titan, or European Ariane rockets. The Long March 2E had a maximum payload capability of 9,500 kg to low earth orbit. More...

Associated Propellants
  • Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...

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