This page no longer updated from 31 October 2001. Latest version can be found at MB-3-3

MB-1/MB-3 -

Credit: Mark Wade. 6,405 bytes. 127 x 235 pixels.

Designer: Rocketdyne. Used on stages: Delta Thor LT, Delta Thor TA, H-1-1. Used on launch vehicles: Delta 100, Delta D, Delta E, Delta G, Delta J, Delta L, Delta M, Delta N, H-1, LT Thor Agena D, TA Thor Agena B, TA Thor Agena D. Propellants: Lox/Kerosene Thrust(vac): 88,380 kgf. Thrust(vac): 866.70 kN. Isp: 290 sec. Isp (sea level): 253 sec. Burn time: 270 sec. Mass Engine: 723 kg. Diameter: 2.4 m. Length: 1.7 m. Chambers: 1. Chamber Pressure: 39.00 bar. Area Ratio: 8.00. Thrust to Weight Ratio: 122.24. Country: USA. Status: Out of Production. First Flight: 1963. Last Flight: 1992. Flown: 172. Comments: License built in Japan for H-1.
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Last update 12 March 2001.
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© Mark Wade, 2001 .