Mathematical analysis of problem for rocket with constant thrust acceleration going from one planetary orbit to another, employing formal methods of calculus of variations; results of numerical integration for thrust-to-mass ratio of 10-4 "g" 's and final to initial radius ratio of 1.5.
Low-thrust rocket steering program for minimum time transfer between planetary orbits
Soc Automotive Engrs -- Paper
Society of Automotive Engineers -- Meeting ; 1958 Thrust
1958
20 pages
Conference paper
English
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LOW-THRUST ROCKET STEERING PROGRAM FOR MINIMUM TIME TRANSFER BETWEEN PLANETARY ORBITS
SAE Technical Papers | 1958
|British Library Conference Proceedings | 1998
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