Encyclopedia Astronautica
Star 26



star26.jpg
Star-26
Credit: Thiokol
Thiokol solid rocket engine. 39.1 kN. 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. Isp=271s. First flight 1965.

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

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

More... - Chronology...


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
  • Burner 2A Solid propellant rocket stage. Loaded/empty mass 353/115 kg. Thrust 39.15 kN. Vacuum specific impulse 285 seconds. 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. More...

Home - Browse - Contact
© / Conditions for Use