This page no longer updated from 31 October 2001. Latest version can be found at Redesigned SRM

Other Designations: Space Shuttle Solid Rocket Motor. Designer: Thiokol. Gross Mass: 569,893 kg. Empty Mass: 66,406 kg. Propellants: Solid Thrust(vac): 1,174,736 kgf. Thrust(vac): 11,520.00 kN. Isp: 269 sec. Burn time: 124 sec. Diameter: 3.8 m. Length: 38.5 m. Chambers: 1. Chamber Pressure: 62.40 bar. Area Ratio: 7.72. Country: USA. Status: In Production.

Mass: 569,893 kg. Length: 38.47 m. Diameter: 3847 mm. Propellant Type: TP-H1148 HB Polymer, 16% Al, and 70% AP. Propellant Shape: 11-point star forward with a double taper cylinder . Propellant Mass Fraction: 0.883 (503,487 kg). Burn Time: 123.6 sec action, 111.7 sec web. Thrust: 11.52 MN average vacuum, and 14.77 MN maximum vacuum. Isp: 268.6 sec vacuum. Itotal: 296.3 MNs vacuum. Pressure: 62.4 atm maximum (MEOP 69.1) and 45 atm average. Nozzle Throat Diameter: 136.8 cm. Nozzle Length: 454 cm. Nozzle Exit Diameter: 380.1 cm (expansion ratio 7.72). Nozzle Materials: D6AC steel for fixed housing with throat and forward exit cone housings. aluminum for nose inlet and aft exit cone housing. Casing Materials: D6AC steel with 1.165 cm minimum thickness. Igniter: forward end internally mounted 62.1 kg of TP-H1178 case-bonded 40-point star.

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Last update 12 March 2001.
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© Mark Wade, 2001 .