PERIGEE PROPULSION FOR ORBITAL LAUNCH OF NUCLEAR ROCKETS
Technical Report
·
OSTI ID:4724403
A thrust program called perigee propulsion which minimizes gravity loss was analyzed. Thrust is applied intermittently in regions of high velocity (near successive perigees). The increased energy-addition efficiency yields mass ratios approaching those for impulsive velocity change. Corresponding times to reach desired energy are in days but are still small relatlve to mission times. For specified orbital-launch missions, perigee-propulsion nuclear rocket systems are shown to equal continuous-thrust performance with reactor powers an order of magnitude less than those of continuous-thrust systems. Application and operational aspects of perigee propulsion are discussed. (auth)
- Research Organization:
- National Aeronautics and Space Administration. Lewis Reseach Center, Cleveland
- NSA Number:
- NSA-17-010198
- OSTI ID:
- 4724403
- Report Number(s):
- NASA-TR-R-140
- Country of Publication:
- United States
- Language:
- English
Similar Records
RESIDUAL-LOAD-PLUS-POWERPLANT WEIGHTS FOR ORBITAL-LAUNCH NUCLEAR ROCKETS
Place of solar thermal rockets in space
A comparison of propulsion systems for potential space mission applications
Technical Report
·
Mon May 01 00:00:00 EDT 1961
·
OSTI ID:4008607
Place of solar thermal rockets in space
Technical Report
·
Fri May 01 00:00:00 EDT 1981
·
OSTI ID:6536738
A comparison of propulsion systems for potential space mission applications
Conference
·
Wed Dec 31 23:00:00 EST 1986
·
OSTI ID:5032614