Encyclopedia Astronautica
RSA-4-3


Solid propellant rocket stage. Loaded/empty mass 2,000/100 kg. Thrust 59.13 kN. Vacuum specific impulse 292 seconds. Essentially identical to RSA-3 third stage. Oriented and spun up by 1000 kg avionic section/spin platform, which separates prior to ignition.

Status: Development 1988.
Gross mass: 2,000 kg (4,400 lb).
Unfuelled mass: 100 kg (220 lb).
Height: 2.10 m (6.80 ft).
Diameter: 1.30 m (4.20 ft).
Span: 1.30 m (4.20 ft).
Thrust: 59.13 kN (13,293 lbf).
Specific impulse: 292 s.
Burn time: 92 s.

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Associated Countries
Associated Engines
  • RSA-3-3 South Africansolid rocket engine. 51 kN. In production. Israeli AUS-51 rocket motor, built in both Israel and South Africa. Isp=292s. Upper stage engine for RSA-3, RSA-4, Shavit, Shavit 1. First flight 1988. 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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