Chamber/single nozzle

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Chamber/single nozzle

Notional LOx/LH2 rocket engine. Study 1963. 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.

Status: Study 1963. Thrust: 13,231.00 kN (2,974,447 lbf). Specific impulse: 455 s. Specific impulse sea level: 365 s. Burn time: 249 s.

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.

Country: USA. Launch Vehicles: DAC Helios, DAC Helios ISI, Nova DAC ISI, OOST ISI, ROOST ISI. Propellants: Lox/LH2. Stages: DAC Helios ISI-1, DAC Helios-1, Nova DAC ISI-1, Nova DAC ISI-2, OOST ISI stage, ROOST ISI stage.

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