Encyclopedia Astronautica
RSA-4-1


Solid propellant rocket stage. Loaded/empty mass 66,000/8,000 kg. Thrust 1,520.00 kN. Vacuum specific impulse 270 seconds. Vacuum specific impulse / thrust estimated. Sea leval 139,000 kNs delivered over 73 seconds. Includes 3400 kg mass of fins, interstage and upper-stage constant-diameter fairing ('sleeve') which is jettisoned after first stage burnout.

Status: Development ended 1994.
Gross mass: 66,000 kg (145,000 lb).
Unfuelled mass: 8,000 kg (17,600 lb).
Height: 10.30 m (33.70 ft).
Diameter: 2.40 m (7.80 ft).
Span: 5.90 m (19.30 ft).
Thrust: 1,520.00 kN (341,700 lbf).
Specific impulse: 270 s.
Specific impulse sea level: 244 s.
Burn time: 73 s.

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Associated Countries
Associated Engines
  • RSA-4-1 South Africansolid rocket engine. 1520 kN. Development ended 1994. Isp=263s. Used on RSA-4 launch vehicle. More...

Associated Launch Vehicles
  • RSA-4 South African all-solid orbital launch vehicle. The RSA-4 ICBM / satellite launcher was a planned follow-on to the RSA-3. A large new first stage optimised the vehicle and more than doubled the payload in comparison to the RSA-3. It is not known if the project reached the point of testing of the large motor, which was equivalent to the US Peacekeeper first stage. 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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