A simple family of indirect transfer trajectories between circular orbits is used to evaluate the mass ratio required to complete round-trip interplanetary missions using low-thrust propulsion systems. The results indicate that indirect interplanetary trajectories yield substantial reductions in total round-trip time for low-thrust as well as high-thrust vehicles, and that space vehicles propelled with electric rockets may produce greater reductions in trip time, for a given initial weight, than those propelled by high-thrust nuclear rockets.
Fast Interplanetary Missions with Low-Thrust Propulsion Systems
1960-01-01
Sonstige
Keine Angabe
Englisch
Fast interplanetary missions with low-thrust propulsion systems
Engineering Index Backfile | 1960
|Propulsion for interplanetary space missions
Engineering Index Backfile | 1962
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