The third satellite of the international Sun-Earth Explorer program was inserted into a periodic halo orbit about L sub 1, the collinear libration point between the Sun and the Earth-Moon barycenter. A plan is presented that was developed to enable insertion into the halo orbit in case there was a large underperformance of the Delta second or third stage during the maneuver to insert the spacecraft into the transfer trajectory. After one orbit of the Earth, a maneuver would be performed near perigee to increase the energy of the orbit. A relatively small second maneuver would put the spacecraft in a transfer trajectory to the halo orbit, into which it could be inserted for a total cost within the fuel budget. Overburns (hot transfer trajectory insertions) were also studied.


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    Titel :

    Contingency study for the third international Sun-Earth Explorer (ISEE-3) satellite


    Beteiligte:
    Dunham, D. W. (Autor:in)

    Erscheinungsdatum :

    01.05.1979


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch