Vexin B Designer: SEP. Propellants: N2O4/UDMH. Thrust(vac): 75.400 kN (16,951 lbf). Thrust(sl): 66.400 kN (14,927 lbf). Isp: 251 sec. Isp (sea level): 221 sec. Burn time: 100 sec. Mass Engine: 192 kg (423 lb). Diameter: 0.34 m (1.10 ft). Chambers: 1. Thrust to Weight Ratio: 40.04. Country: France. Status: Out of production. First Flight: 1965. Last Flight: 1967. Flown: 16. Vexin B used on Rocket Stages Used on stage: Diamant-1. on launch vehicle: Diamant A.                   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 - 2007 except where otherwise noted.

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