The report presents a discussion on problems related to orbit transfer of satellites under optimal conditions from a 200 km circular orbit to the 24 hours equatorial orbit. Suitable for this mission there are only such electric propulsion systems, which are able to produce exhaust velocities of about 40000 m/s for a specific power of 0,1 kW/kg, if an optimal payload is requested. After a discussion of the electric propulsion and control systems suitable for such a mission, a comparison is made with a chemical propulsion system, which results in a significant superiority for electric space propulsion, on the other side the transfer time is much longer. (Author)
Elektrische Antriebs- und Steuerungssysteme fuer 24-Stunden-Satelliten(Electrical Drive and Central System for a 24 Hour Satellite)
1962
14 pages
Report
Keine Angabe
Englisch
Electric & Ion Propulsion , Spacecraft Trajectories & Flight Mechanics , Electric propulsion , Transfer trajectories , Satellites(Artificial) , Circular orbit trajectories , Equatorial orbit trajectories , Space propulsion , Satellite attitude , Ion engines , Plasma engines , West Germany , Reprints
Elektrische Antriebs- und Steuerungssysteme fuer 24-Stunden-Satelliten
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