Consideration is given to the problem of optimizing the flight of a vehicle sent from a circular orbit around Earth to a circular orbit around Mars. The vehicle is assumed to be powered by an ion engine. Since the thrust of the vehicle would be very small during the middle portion of the flight, an attempt is made to determine whether or not the same trajectory could be accomplished by turning off the motors during that portion.
Optimum Interplanetary Rocket Flights
1959
2 pages
Report
No indication
English
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