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Star-17
Credit - Thiokol
Engine Model: Star 17. Manufacturer Name: TE-M-479. Other Designations: 17.6-KS-2,460. Designer: Thiokol. Application: Skynet 1, NATO 1, and IMP-H & J. Gross Mass: 79 kg (174 lb). Empty Mass: 9.00 kg (19.80 lb). Propellants: Solid. Thrust(vac): 10.900 kN (2,450 lbf). Thrust(sl): 15.400 kN (3,462 lbf). Isp: 286 sec. Isp (sea level): 220 sec. Burn time: 18 sec. Diameter: 0.44 m (1.44 ft). Length: 0.98 m (3.21 ft). Chambers: 1. Country: USA. Status: Out of production. First Flight: 1963. Last Flight: 1965. Flown: 15.

Orbit insertion motor has been used as the apogee kick motor for the Radio Astronomy Explorer satellite, the SOLRAD satellite, and an S-3 satellite. Total impulse 20,177 kgf-sec. Motor propellant mass fraction 0.881.

Engine Model: Star 17A. Manufacturer Name: TE-M-521-5. Other Designations: 19.4-KS-3,600. Designer: Thiokol. Gross Mass: 126 kg (277 lb). Empty Mass: 14 kg (30 lb). Propellants: Solid. Thrust(vac): 16.014 kN (3,600 lbf). Isp: 287 sec. Burn time: 19 sec. Diameter: 0.44 m (1.46 ft). Length: 0.98 m (3.21 ft). Chambers: 1. Country: USA. Status: In Production. Flown: 19.

Apogee kick motor. Modifications: 175 mm straight section added to the Star 17. The 17A has been used for circularized orbits for the Skynet 1, NATO 1, and IMP-H & J satellites. This motor provides the high case safety factor required for this program. The TE-M-521-7 model used for several Air Force missions provides a typical safety factor with a 1.3 pound weight savings. Total impulse 32,556 kgf-s. Propellant mass fraction 0.89.

Star 17 used on Rocket Stages
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