Solid propellant rocket stage. Loaded/empty mass 10,971/1,771 kg. Thrust 476.60 kN. Vacuum specific impulse 277 seconds. Source: Missile exhibit and placards, AF Museum, South Africa. Empty mass includes 583 kg for payload shroud, guidance, orientation and spin-up platform that positions stage 3 and payload for final orbital insertion burn.
More... - Chronology...
Gross mass: 10,971 kg (24,186 lb).
Unfuelled mass: 1,771 kg (3,904 lb).
Height: 6.40 m (20.90 ft).
Diameter: 1.30 m (4.20 ft).
Span: 1.30 m (4.20 ft).
Thrust: 476.60 kN (107,144 lbf).
Specific impulse: 277 s.
Specific impulse sea level: 220 s.
Burn time: 52 s.
Number: 10 .
RSA-3-2 South African solid rocket engine. 519 kN. In production. Built in both Israel and South Africa for RSA-3 and Shavit. Source: Missile exhibit and placards, AF Museum, South Africa. Isp=284s. First flight 1988. More...
Associated Launch Vehicles
Shavit Israeli all-solid orbital launch vehicle. Satellite launcher derived from Jericho II MRBM, essentially identical to South African RSA-3. More...
RSA-3 The RSA-3 satellite launcher began development as an IRBM in the 1980's because of the perceived Soviet threat and isolation of South Africa. It was developed with the assistance of Israel and was believed to be essentially identical to the Israeli Jericho missile/Shavit launch vehicle. The objective of the satellite launcher was to place a small surveillance satellite of 330 kg mass into a 41 degree, 212 x 460 km orbit around the earth. Development continued even after South African renunciation of its nuclear weapons. However the launcher was found not to be viable commercially and so was cancelled in mid-1994. More...
Shavit 1 Israeli all-solid orbital launch vehicle. Shavit 1 is an improved version of the original Shavit with a stretched first stage motor. More...
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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