AbstractThere are four bi-impulsive distinct configurations for the generalized Hohmann orbit transfer. In this case the terminal orbits as well as the transfer orbit are elliptic and coplanar. The elements of the initial orbit , and the semi-major axis of the terminal orbit are uniquely given quantities. For optimization procedure, minimization is relevant to the independent parameter , the eccentricity of the transfer orbit. We are capable of the assignment of minimum rocket fuel expenditure by using ordinary calculus condition of minimization for .We exposed in detail the multi-steps of the optimization procedure. We constructed the variation table of which proved that is a decreasing function of in the admissible interval . Our analysis leads to the fact that for , i.e. the final orbit is a parabolic trajectory.
The optimization of the orbital Hohmann transfer
Acta Astronautica ; 65 , 7-8 ; 1094-1097
2009-03-05
4 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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