GEM 40

GEM 40

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Engine Model: GEM 40. Designer: Hercules. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Propellants: Solid. Thrust(vac): 499.200 kN (112,225 lbf). Thrust(sl): 446.000 kN (100,264 lbf). Isp: 274 sec. Isp (sea level): 245 sec. Burn time: 63 sec. Diameter: 1.02 m (3.34 ft). Length: 12.96 m (42.51 ft). Chambers: 1. Chamber Pressure: 56.00 bar. Area Ratio: 11.00. Country: USA. First Flight: 1990. Last Flight: 2006. Flown: 936.

Air-ignited versions have nozzle ratio of 16:1, specific impulse of 283.4 sec.

GEM 40 used on Rocket Stages

Used on stage: Castor 4. on launch vehicle: ait.

Used on stage: Castor 4. on launch vehicle: Athena.

Used on stage: Castor 4. on launch vehicle: Athena RTV.

Used on stage: Castor 4. on launch vehicle: Atlas.

Used on stage: Castor 4. on launch vehicle: Castor 4B.

Used on stage: Castor 4. on launch vehicle: Conestoga.

Used on stage: Castor 4. on launch vehicle: Delta.

Used on stage: Castor 4. on launch vehicle: H-2.

Used on stage: Castor 4. on launch vehicle: Maxus.

Used on stage: Castor 4. on launch vehicle: Orbus.

Used on stage: Castor 4. on launch vehicle: Prospector.

Bibliography:

Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004.

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© Mark Wade, 1997 - 2008 except where otherwise noted.