MB-3-3

MB-1/MB-3
Credit - © Mark Wade

Designer: Rocketdyne. Propellants: Lox/Kerosene. Thrust(vac): 866.700 kN (194,842 lbf). Thrust(sl): 756.100 kN (169,978 lbf). Isp: 290 sec. Isp (sea level): 253 sec. Burn time: 270 sec. Mass Engine: 723 kg (1,593 lb). Diameter: 2.44 m (8.00 ft). Length: 1.70 m (5.50 ft). 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: 1964. Last Flight: 1992. Flown: 96.

License built in Japan for H-1.

MB-3-3 used on Rocket Stages

Used on stage: Delta Thor LT. on launch vehicle: Delta 0100.

Used on stage: Delta Thor LT. on launch vehicle: Delta L.

Used on stage: Delta Thor LT. on launch vehicle: Delta M.

Used on stage: Delta Thor LT. on launch vehicle: Delta N.

Used on stage: Delta Thor LT. on launch vehicle: Thorad Agena D SLV-2G.

Used on stage: Delta Thor TA. on launch vehicle: Delta D.

Used on stage: Delta Thor TA. on launch vehicle: Delta E.

Used on stage: Delta Thor TA. on launch vehicle: Delta G.

Used on stage: Delta Thor TA. on launch vehicle: Delta J.

Used on stage: Delta Thor TA. on launch vehicle: Thor Agena B SLV-2A (B).

Used on stage: Delta Thor TA. on launch vehicle: Thor Agena D SLV-2A.

Used on stage: H-1-1. on launch vehicle: H-1.

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© Mark Wade, 1997 - 2007 except where otherwise noted.

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