Star 75
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Credit: Thiokol
Thiokol solid rocket engine. In Production. 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.