The use of lunar-swingby maneuvers to transfer a spacecraft from an equatorial orbit to a polar orbit has been investigated in order to verify the technical feasibility of the NASA/ESA equatorial science phase (ESP)/Cluster mission. The solar aspect angle constraints of the spacecraft spin-axis and the dependence of the total Delta-V cost of the transfer on the initial ESP orbital parameters (particularly perigee radius and inclination) have been studied. The results indicate that a satisfactory ESP-to-Cluster orbit transfer can be achieved using a double lunar-swingby sequence.


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    Titel :

    Large inclination change using lunar-swingby techniques


    Beteiligte:
    Lee, T. (Autor:in) / Dunham, D. W. (Autor:in) / Hsu, S. (Autor:in) / Roberts, C. E. (Autor:in) / Engel, C. (Autor:in)

    Kongress:

    AIAA/AAS Astrodynamics Conference ; 1988 ; Minneapolis, MN, United States


    Erscheinungsdatum :

    1988-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Large inclination change using lunar-swingby techniques

    LEE, T. / DUNHAM, D. / HSU, S. et al. | AIAA | 1988


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    Betts, John T. | Springer Verlag | 2007


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    Optimal lunar swingby trajectories

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    MUSES-A double lunar swingby mission

    Uesugi, Kuninori / Hayashi, Tomonao / Matsuo, Hiroki | Elsevier | 1987