This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Used on stages: DAC Helios ISI-1, DAC Helios-1, Nova DAC ISI-1, Nova DAC ISI-2, OOST ISI, ROOST ISI. Used on launch vehicles: DAC Helios, DAC Helios ISI, Nova DAC ISI, OOST ISI, ROOST ISI. Propellants: Lox/LH2 Thrust(vac): 1,349,250 kgf. Thrust(vac): 13,231.00 kN. Isp: 455 sec. Isp (sea level): 365 sec. Burn time: 249 sec. Chambers: 1. Country: USA. Status: Design concept 1960's.
Before moving to favored plug nozzle designs, Bono at Douglas considered having multiple combustion chambers exhaust into a single large nozzle to obtained Improved Specific Impulse. Used in Nova DAC ISI, ROOS ISI, OOST ISI, and DAC Helios ISI designs. Status: Study 1963. Operational date would have been July 1977. Values shown were maximum considered.
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Last update 12 March 2001.
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© Mark Wade, 2001 .