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Engine Model: Star 30. Manufacturer Name: TE-M-700-2. Designer: Thiokol. Gross Mass: 492 kg (1,084 lb). Empty Mass: 28 kg (61 lb). Propellants: Solid. Isp: 293 sec. Diameter: 0.76 m (2.50 ft). Chambers: 1. Country: USA. Status: Out of Production.

Total flown included in total for Star-30A. Total impulse 136,455 kgf-sec. Motor propellant mass fraction 0.943.

Engine Model: Star 30A. Manufacturer Name: TE-M-700-4. Designer: Thiokol. Gross Mass: 492 kg (1,084 lb). Empty Mass: 28 kg (61 lb). Propellants: Solid. Isp: 295 sec. Diameter: 0.76 m (2.50 ft). Chambers: 1. Country: USA. Status: Out of Production. Flown: 4.00.

Total impulse 137,095 kgf-sec. Motor propellant mass fraction 0.942.

Engine Model: Star 30B. Manufacturer Name: TE-M-700-5. Designer: Thiokol. Gross Mass: 537 kg (1,183 lb). Empty Mass: 32 kg (70 lb). Propellants: Solid. Isp: 293 sec. Diameter: 0.76 m (2.50 ft). Chambers: 1. Country: USA. Status: Out of Production. Flown: 44.

Total impulse 148,816 kgf-sec. Motor propellant mass fraction 0.941.

Engine Model: Star 30BP. Manufacturer Name: TE-M-700-20. Other Designations: 54-KS-6,070. Designer: Thiokol. Gross Mass: 543 kg (1,197 lb). Empty Mass: 38 kg (83 lb). Propellants: Solid. Thrust(vac): 27.000 kN (6,069 lbf). Isp: 292 sec. Burn time: 54 sec. Diameter: 0.76 m (2.50 ft). Length: 1.51 m (4.94 ft). Chambers: 1. Country: USA. Status: In Production. Flown: 24.

Apogee motor is used for the Hughes Aircraft Company HS 376 satellites and for the RCA SATCOM, Spacenet, and G-STAR satellites. The design incorporates an 89-percent-solids HTPB propellant in a 6AI-4V titanium case insulated with silica-filled EPDM rubber. It has a contoured nozzle with an integral toroidal igniter and a carbon-phenolic exit cone. Ingiter: Aft end. Other versions Star 30C/E (TE-M-700-18/19). Total impulse 148,816 kgf-s. Propellant mass fraction 0.931.

Engine Model: Star 30C. Manufacturer Name: TE-M-700-18. Other Designations: 51-KS-7,340. Designer: Thiokol. Application: AS 3000. Gross Mass: 630 kg (1,380 lb). Empty Mass: 39 kg (85 lb). Propellants: Solid. Thrust(vac): 32.600 kN (7,329 lbf). Isp: 287 sec. Burn time: 51 sec. Length: 1.49 m (4.90 ft). Chambers: 1. Country: USA. Status: In Production. Flown: 10.

Apogee motor is used for the RCA G-STAR and Martin Marietta series 3000 telecom satelllites. The design incorporates a case cylinder 5 inches longer than the STAR 30BP and an 89-percent-solids HTPB propellant in a 6AI-4V titanium case insulated with silica-filled EPDM rubber. It has a contoured nozzle with an intregral toroidal igniter and a carbon-phenolic exit cone. Total impulse 171,002 kgf-s. Propellant mass fraction 0.939.

Engine Model: Star 30E. Manufacturer Name: TE-M-700-19. Other Designations: 49-KS-7,955. Designer: Thiokol. Application: Koreasat. Gross Mass: 667 kg (1,470 lb). Empty Mass: 45 kg (99 lb). Propellants: Solid. Thrust(vac): 35.400 kN (7,958 lbf). Isp: 291 sec. Burn time: 49 sec. Length: 1.68 m (5.52 ft). Chambers: 1. Country: USA. Status: In Production. Flown: 7.00.

Apogee motor is used for the BAe Skynet 4 satellite, Koreasat and by the ORBEX small orbital launcher. The design incorporates a case cylinder 7 inches longer than the STAR 30BP and an 89-percent-solids HTPB propellant in a 6AI-4V titanium case insulated with silica-filled EPDM rubber. It has a contoured nozzle with an integral toroidal igniter and a carbon-phenolic exit cone. Total impulse 182,216 kgf-s. Propellant mass fraction 0.932.

Star 30 used on Spacecraft
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© Mark Wade, 1997 - 2008 except where otherwise noted.