Star 26C (original) (raw)

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Star 26C

Part of Star 26

Thiokol solid rocket engine. In Production. Upper stage motor used the titanium alloy case and nozzle attachment ring of the STAR 26B design to provide high propellant mass fraction and was insulated for high-spin-rate applications.

AKA: 16.8-KS-7,870;TE-M-442-2. Status: In Production. Number: 27 . Thrust: 35.00 kN (7,868 lbf). Gross mass: 264 kg (582 lb). Unfuelled mass: 32 kg (70 lb). Specific impulse: 272 s. Burn time: 17 s. Diameter: 0.66 m (2.17 ft).

Upper stage motor employs the titanium alloy case and nozzle attachment ring of the STAR 26B design to provide high propellant mass fraction and is insulated for high-spin-rate applications. The motor is used as an upper stage in the Sandia National Laboratories Strypi IV vehicle and in the U.S. Army's Designated Optical Tracker vehicle. Total impulse 63,389 kgf-s. Propellant mass fraction 0.88.

Country: USA. Launch Vehicles: DOT. Propellants: Solid. Stages: Star 26C. Agency: Thiokol. Bibliography: 410.

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