Encyclopedia Astronautica
RSRM


Thiokol solid rocket engine. 11,520 kN. Study 1996. After the Challenger disaster the redesigned solid rocket motors had a slight reduction in performance due to reliability improvements. Isp=267s.

Propellant Formulation: PBAN.

Status: Study 1996.
Gross mass: 590,000 kg (1,300,000 lb).
Unfuelled mass: 88,000 kg (194,000 lb).
Height: 45.46 m (149.14 ft).
Diameter: 3.77 m (12.36 ft).
Thrust: 11,520.00 kN (2,589,799 lbf).
Specific impulse: 267 s.
Specific impulse sea level: 235 s.
Burn time: 123 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...

Associated Stages
  • 5 Segment RSRM Solid propellant rocket stage. Loaded/empty mass 751,212/100,350 kg. Thrust 15,480.36 kN. Vacuum specific impulse 265 seconds. Five-segment version of Shuttle RSRM studied in 1999-2003 to increase shuttle payload to ISS. Test fired in 2003 but not proceeded with. Another version proposed in 2005 for use as lateral boosters for the Constellation Cargo Vehicle. More...
  • Shuttle RSRM Solid propellant rocket stage. Loaded/empty mass 590,000/88,000 kg. Thrust 11,520.00 kN. Vacuum specific impulse 267 seconds. After the Challenger disaster the redesigned solid rocket motors had a slight reduction in performance due to reliability improvements. More...

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