ROCKET PROPULSION WITH NUCLEAR POWER
Journal Article
·
· ARS (Am. Rocket Soc.) J.
OSTI ID:4098432
The nuclear reheat scheme for rocket propulsion using hydrogen propellant is briefly described, and then a scheme using a closed-cycle regenerative gas turbine working between the reactor as a heat source and the liquid hydrogen as a heat sink is treated in detail. The turbine, an AK unit, is filled with high-pressure helium. The maximum gain obtainable from this scheme and the effects of finite regenerator size on its thermodynamic properties are calculated, and the regenerator size needed to accomplish the required heat transfer is then estimated. The advantages of this scheme are discussed. (D.L.C.)
- Research Organization:
- Cornell Univ., Ithaca, N.Y.
- NSA Number:
- NSA-15-008356
- OSTI ID:
- 4098432
- Journal Information:
- ARS (Am. Rocket Soc.) J., Journal Name: ARS (Am. Rocket Soc.) J. Vol. Vol: 30
- Country of Publication:
- Country unknown/Code not available
- Language:
- English
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