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HM7-A
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Designer: SEP/Ottobrunn. Propellants: Lox/LH2. Thrust(vac): 61.700 kN (13,871 lbf). Thrust(sl): 42.900 kN (9,644 lbf). Isp: 443 sec. Isp (sea level): 308 sec. Burn time: 563 sec. Mass Engine: 149 kg (328 lb). Diameter: 0.93 m (3.05 ft). Length: 1.71 m (5.61 ft). Chambers: 1. Chamber Pressure: 30.00 bar. Area Ratio: 62.50. Oxidizer to Fuel Ratio: 5.15. Thrust to Weight Ratio: 42.21. Country: France. Status: Out of production. First Flight: 1979. Last Flight: 1986. Flown: 11. The HM-7 rocket engine featured Ottobrunn's unique regenerative cooling technology whereby hydrogen propellant was efficiently used to cool the combustion chamber before being injected for combustion. In 1973, the Ottobrunn team started development of the HM-7 thrust chamber for Ariane's upper stage rocket engine. Six years later, the HM-7 engine was successfully qualified with the first launch of Ariane 1 in December 1979.
HM7-A used on Rocket Stages
Bibliography and Further Reading - Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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