Encyclopedia Astronautica
Star 48B


Thiokol solid rocket engine. 66 kN. In Production. Isp=286s. Long nozzle upper-stage motor qualified for the McDonnell Payload Assist Module (PAM) Delta.

Long nozzle upper-stage motor is qualified for the McDonnell Payload Assist Module (PAM) Delta. The basic version for Delta-launched missions contains 2011 kg of propellant (an increase of 11 kg over STAR 48) and has the same 80-inch length as the Delta 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. Propellant: 2011 kg charge of AP/HTPB/Al in 6Al-4V titanium case. Total impulse 591,142 kgf-s. Propellant mass fraction 0.939.

Propellant Formulation: HTPB.

AKA: 87.2-KS-17,735; TE-M-799.
Status: In Production.
Gross mass: 2,137 kg (4,711 lb).
Unfuelled mass: 126 kg (277 lb).
Height: 2.03 m (6.67 ft).
Diameter: 1.25 m (4.08 ft).
Thrust: 66.00 kN (14,837 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...

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