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Star 26
Star-26
Star-26
Credit: Thiokol
Thiokol solid rocket engine. In Production. Upper stage motor used in the Sandia Strypi IV vehicle. Total flown included in total for Star-26C. Total impulse 62,800 kgf-sec. Motor propellant mass fraction 0.86. First flight 1965. Solid propellant rocket stage. Burner II was a launch vehicle upper stage developed by Boeing for the Air Force Space Systems Division. It was the first solid-fuel upper stage with full control and guidance capability developed for general space applications.

AKA: 17.8-KS-7,500;Burner 2A;TE-M-442. Status: In Production. Number: 7 . Thrust: 39.10 kN (8,790 lbf). Gross mass: 268 kg (590 lb). Unfuelled mass: 37 kg (81 lb). Specific impulse: 271 s. Specific impulse sea level: 220 s. Burn time: 18 s. Height: 0.40 m (1.31 ft). Diameter: 0.66 m (2.16 ft).

Thrust (sl): 30.200 kN (6,789 lbf). Thrust (sl): 3,082 kgf.



Subtopics

Burner 2A Solid propellant rocket stage. Burner II was a launch vehicle upper stage developed by Boeing for the Air Force Space Systems Division. It was the first solid-fuel upper stage with full control and guidance capability developed for general space applications.

Star 26B Thiokol solid rocket engine. In Production. Upper stage motor flown on the Burner IIA spacecraft for Boeing and the U.S. Air Force.

Star 26C 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.

Country: USA. Propellants: Solid. Stages: Burner 2A. Agency: Thiokol.

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