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Star-24
Credit - Thiokol
Engine Model: Star 24. Manufacturer Name: TE-M-604. Other Designations: 29.6-KS-4,170. Designer: Thiokol. Application: Skynet 2. Gross Mass: 218 kg (480 lb). Empty Mass: 18 kg (39 lb). Propellants: Solid. Thrust(vac): 20.000 kN (4,496 lbf). Isp: 283 sec. Burn time: 30 sec. Chambers: 1. Country: USA. Status: In Production.

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.

Engine Model: Star 24A. Manufacturer Name: TE-M-604-2. Designer: Thiokol. Gross Mass: 198 kg (436 lb). Empty Mass: 19 kg (41 lb). Propellants: Solid. Isp: 282 sec. Diameter: 0.62 m (2.04 ft). Chambers: 1. Country: USA. Status: Out of Production.

Total flown included in total for Star-24C. Total impulse 50,965 kgf-sec. Motor propellant mass fraction 0.903.

Engine Model: Star 24B. Manufacturer Name: TE-M-604-3. Designer: Thiokol. Gross Mass: 219 kg (482 lb). Empty Mass: 19 kg (41 lb). Propellants: Solid. Isp: 283 sec. Diameter: 0.62 m (2.04 ft). Chambers: 1. Country: USA. Status: Out of Production.

Total flown included in total for Star-24C. Total impulse 57,236 kgf-sec. Motor propellant mass fraction 0.915.

Engine Model: Star 24C. Manufacturer Name: TE-M-604-4. Other Designations: 28-KS-4,825. Designer: Thiokol. Gross Mass: 239 kg (526 lb). Empty Mass: 19 kg (41 lb). Propellants: Solid. Thrust(vac): 21.466 kN (4,826 lbf). Isp: 282 sec. Burn time: 28 sec. Diameter: 0.62 m (2.04 ft). Chambers: 1. Country: USA. Status: In Production. Flown: 15.

Apogee motor was designed and qualified for the NASA International Ultraviolet Experiment satellite. It incorporates a 1.5-inch longer cylindrical section with increased propellant weight and a larger nozzle throat and operates at a slightly higher chamber pressure than prior STAR 24 motors. Total impulse 62,573 kgf-s. Propellant mass fraction 0.917.

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