Encyclopedia Astronautica
Star 48B s



str48bsn.jpg
Star-48B Short
Credit: Thiokol
Thiokol solid rocket engine. 77.109 kN. In Production. Isp=286s. Short nozzle upper-stage motor qualified for the McDonnell Douglas Payload Assist Module (PAM) Space Transportation System (STS).

The basic version for STS missions contains 4430 pounds of propellant (an increase of 25 pounds over STAR 48) and has the same 72-inch overall length as the STS version of the STAR 48. The design incorporates the same high-energy propellant and high-strength case as the STAR 48. The semi-submerged nozzle uses a carbon-phenolic exit cone. Total impulse 578,461 kgf-s. Propellant mass fraction 0.942.

AKA: 87.2-KS-17,335; TE-M-711-17.
Status: In Production.
Gross mass: 2,134 kg (4,704 lb).
Unfuelled mass: 124 kg (273 lb).
Diameter: 1.24 m (4.08 ft).
Thrust: 77.11 kN (17,335 lbf).
Specific impulse: 286 s.
Burn time: 87 s.

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Associated Countries
See also
Associated Manufacturers and Agencies
  • Thiokol American manufacturer of rocket engines and rockets. Thiokol Corporation, Ogden, UT, USA. 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...

Bibliography
  • Thiokol Corporation Web Site, As of May, 1999. Web Address when accessed: here.

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