M55

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Engine Model: M55/TX-55/Tu-122. Designer: Thiokol. Gross Mass: 23,077 kg (50,876 lb). Empty Mass: 2,292 kg (5,052 lb). Propellants: Solid. Thrust(vac): 792.000 kN (178,048 lbf). Isp: 262 sec. Isp (sea level): 237 sec. Burn time: 60 sec. Diameter: 1.67 m (5.47 ft). Length: 7.49 m (24.57 ft). Chambers: 1. Country: USA. Status: In production. First Flight: 2000. Last Flight: 2006. Flown: 5.00. Engine Model: M55A1. Designer: Thiokol. Gross Mass: 22,900 kg (50,400 lb). Empty Mass: 2,500 kg (5,500 lb). Propellants: Solid. Thrust(vac): 792.000 kN (178,048 lbf). Burn time: 59 sec. Diameter: 1.68 m (5.51 ft). Length: 7.50 m (24.60 ft). Country: USA. M55 used on Rocket Stages Used on stage: M55. on launch vehicle: HOE. Used on stage: M55. on launch vehicle: M55E1. Used on stage: M55. on launch vehicle: Minotaur. Used on stage: M55. on launch vehicle: Minuteman 1. Used on stage: M55. on launch vehicle: Minuteman 2. Used on stage: M55. on launch vehicle: Minuteman 3. Used on stage: M55. on launch vehicle: Saturn I. Used on stage: M55. on launch vehicle: Saturn V. Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2008 except where otherwise noted.