AKA: 29.6-KS-4,170;TE-M-604. Status: In Production. Thrust: 20.00 kN (4,496 lbf). Gross mass: 218 kg (480 lb). Unfuelled mass: 18 kg (39 lb). Specific impulse: 283 s. Burn time: 30 s. Diameter: 0.62 m (2.04 ft).
Apogee boost motor was qualified and flown for the Skynet II satellite for Ford Aerospace and Communications Corporation and the United Kingdom. It was also flown as the Timation III (STP 73-3) apogee boost motor for NRL and SAMSO. Versions have been used for orbital insertion of the NASA LAGEOS and IUE satellites and the Hughes Aircraft Corporation Pioneer-Venus spacecraft. Charge: 200 kg of AP/hydrocarbon/Al propellant in a spherical 6Al-4V titanium case with a graphite phenolic nozzle. Total impulse 57,132 kgf-s. Propellant mass fraction 0.916.
Propellant Formulation: hydrocarbon.
|Star 24A Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-24C. Total impulse 50,965 kgf-sec. Motor propellant mass fraction 0.903.|
|Star 24B Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-24C. Total impulse 57,236 kgf-sec. Motor propellant mass fraction 0.915.|
|Star 24C Thiokol solid rocket engine. In Production. Apogee motor designed and qualified for the NASA International Ultraviolet Experiment satellite.|