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 a 1 , e 1 and the semi-major axis a 2 of the terminal orbit are uniquely given quantities. For optimization procedure, minimization is relevant to the independent parameter e T , 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 | Δ V A | + | Δ V B | = S .We exposed in detail the multi-steps of the optimization procedure. We constructed the variation table of S ( e T ) which proved that S ( e T ) is a decreasing function of e T in the admissible interval [ e T min , e T max ] . Our analysis leads to the fact that e 2 = 1 for e T = e T max , i.e. the final orbit is a parabolic trajectory.


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    Titel :

    The optimization of the orbital Hohmann transfer


    Beteiligte:

    Erschienen in:

    Acta Astronautica ; 65 , 7-8 ; 1094-1097


    Erscheinungsdatum :

    2009-03-05


    Format / Umfang :

    4 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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