Encyclopedia Astronautica
Star 75



star75.jpg
Star-75
Credit: Thiokol
Thiokol solid rocket engine. 242.8 kN. In Production. Isp=288s. A demonstration motor tested as a first step in the development of a perigee kick motor in the 4080-7940 kg propellant range.

Some of its features include a slotted, center perforated grain in a graphite epoxy filament wound case. with a semi-submerged nozzle with a carbon/phenolic exit cone, and a consumption wafer-type igniter. Burn Rate: 56 mm/s at 34.0 atm and 15.5 Celsius. Burn Time: 105 sec. Action Time: 107 sec. Thrust: 242.83 kN maximum. Total impulse 2,174,539 kgf-s. Propellant mass fraction 0.93.

Chamber Pressure: 34.00 bar.

AKA: 105-KS-45,220; TE-M-775-1.
Status: In Production.
Gross mass: 8,068 kg (17,786 lb).
Unfuelled mass: 565 kg (1,245 lb).
Height: 2.59 m (8.49 ft).
Diameter: 1.91 m (6.25 ft).
Thrust: 242.80 kN (54,584 lbf).
Specific impulse: 288 s.
Burn time: 105 s.
Number: 1 .

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Associated Countries
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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...

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