Electric propulsion and control system for 24-hr satellites; problems related to orbit transfer of satellites under optimal conditions from 200 km circular orbit to 24-hr equatorial orbit are considered; only such electric propulsion systems are suitable for mission, which are able to produce exhaust velocities of about 40,000 m/sec for specific power of 0.1 kw/kg, if optimal payload is requested; comparison is made with chemical propulsion system, which results in significant superiority for electric space propulsion; however, transfer time is much longer.
Elektrische Antriebs- und Steuerungssysteme fuer 24-Stunden-Satelliten
Raketentechnik u Raumfahrtforschung
Raketentechnik u Raumfahrtforschung ; 7 , n 1
1963
13 pages
Aufsatz (Zeitschrift)
Deutsch
© Metadata Copyright Elsevier B. V. All rights reserved.