This paper discusses the potential application of electric propulsion for orbit transfer of a large spacecraft structure from low earth orbit to geosynchronous altitude in a deployed configuration. The electric power was provided by the spacecraft nuclear reactor space power system on a shared basis during transfer operations. Factors considered with respect to system effectiveness included nuclear power source sizing, electric propulsion thruster concept, spacecraft deployment constraints, and orbital operations and safety. It is shown that the favorable total impulse capability inherent in electric propulsion provides a potential economic advantage over chemical propulsion orbit transfer vehicles by reducing the number of Space Shuttle flights in ground-to-orbit transportation requirements.
Orbital transfer of large space structures with nuclear electric rockets
Goddard Memorial Symposium
01.03.1980
Aufsatz (Konferenz)
Keine Angabe
Englisch
Engineering Index Backfile | 1951
Perigee propulsion for orbital launch of nuclear rockets
SLUB | 1962
|Perigee propulsion for orbital launch of nuclear rockets
TIBKAT | 1962
|Perigee propulsion for orbital launch of nuclear rockets
Engineering Index Backfile | 1962
|