A thrust program called perigee propulsion which minimizes gravity loss is 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 relative 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.
Perigree Propulsion for Orbital Launch of Nuclear Rockets
1961-08-31
Sonstige
Keine Angabe
Englisch
Perigee propulsion for orbital launch of nuclear rockets
TIBKAT | 1962
|PERIGEE PROPULSION FOR ORBITAL LAUNCH OF NUCLEAR ROCKETS
NTRS | 1962
|Perigee propulsion for orbital launch of nuclear rockets
Engineering Index Backfile | 1962
|Perigee propulsion for orbital launch of nuclear rockets
SLUB | 1962
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