Encyclopedia Astronautica
Chamber/single nozzle


Notional lox/lh2 rocket engine. 13,231 kN. Study 1963. Isp=455s. 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.

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.

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • DAC Helios ISI American nuclear-powered orbital launch vehicle. As the basic design, but featuring an Improved Specific Impulse chemical stage that used many engines feeding into single large nozzle. More...
  • DAC Helios American nuclear-powered orbital launch vehicle. Douglas/Bono 1963 concept for a chemical-boosted / nuclear upper stage launch vehicle, designed as alternatives to the Convair/Ehricke Helios. The baseline version used a nuclear, recoverable upper stage boosted above the atmosphere by a minimum chemical stage. More...
  • Nova DAC ISI American heavy-lift orbital launch vehicle. Douglas/Bono design for Nova using LH2/Lox in both stages. Improved Specific Impulse chemical stage uses many engines feeding into single large nozzle. More...
  • OOST ISI American SSTO orbital launch vehicle. Alternate version of OOST using Improved Specific Impulse approach: many engines feeding into single large nozzle. More...
  • ROOST ISI American SSTO orbital launch vehicle. Bono's first design for a reusable single stage to orbit LH2/Lox booster, using Improved Specific Impulse approach: many engines feeding into single large nozzle. More...

Associated Propellants
  • Lox/LH2 Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Liquid hydrogen was identified by all the leading rocket visionaries as the theoretically ideal rocket fuel. It had big drawbacks, however - it was highly cryogenic, and it had a very low density, making for large tanks. The United States mastered hydrogen technology for the highly classified Lockheed CL-400 Suntan reconnaissance aircraft in the mid-1950's. The technology was transferred to the Centaur rocket stage program, and by the mid-1960's the United States was flying the Centaur and Saturn upper stages using the fuel. It was adopted for the core of the space shuttle, and Centaur stages still fly today. More...

Associated Stages
  • DAC Helios ISI-1 Lox/LH2 propellant rocket stage. Loaded/empty mass 1,333,000/120,000 kg. Thrust 49,807.00 kN. Vacuum specific impulse 455 seconds. More...
  • DAC Helios-1 Lox/LH2 propellant rocket stage. Loaded/empty mass 1,660,000/149,000 kg. Thrust 52,926.00 kN. Vacuum specific impulse 410 seconds. More...
  • Nova DAC ISI-1 Lox/LH2 propellant rocket stage. Loaded/empty mass 3,084,000/142,000 kg. Thrust 70,146.00 kN. Vacuum specific impulse 350 seconds. Operational date would have been July 1977. Recoverable stage. 10% plug nozzle. More...
  • Nova DAC ISI-2 Lox/LH2 propellant rocket stage. Loaded/empty mass 1,696,000/107,000 kg. Thrust 33,754.00 kN. Vacuum specific impulse 455 seconds. Operational date would have been July 1977. Recoverable stage. More...
  • OOST ISI Lox/LH2 propellant rocket stage. Loaded/empty mass 5,125,000/292,000 kg. Thrust 85,386.00 kN. Vacuum specific impulse 455 seconds. More...
  • ROOST ISI Lox/LH2 propellant rocket stage. Loaded/empty mass 6,218,000/435,000 kg. Thrust 101,842.00 kN. Vacuum specific impulse 455 seconds. More...

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