The International Sun-Earth Explorer (ISEE) scientific satellite to be stationed in 1978 in the vicinity of the sun-earth interior libration point to continuously monitor the space between the sun and the earth, including the distant geomagnetic tail is described. Orbit selection considerations for the ISEE-C are discussed along with stationkeeping requirements and fuel-optimal trajectories. Due to the alignment of the interior libration point with the sun as viewed from the earth, it will be necessary to place the satellite into a 'halo orbit' around the libration point, in order to eliminate solar interference with down-link telemetry. Parametric data for transfer trajectories between an earth parking orbit (altitude about 185 km) and a libration-point orbit are presented. It is shown that the insertion magnitude required for placing a satellite into an acceptable halo orbit is rather modest.


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    Title :

    Mission design for a halo orbiter of the earth


    Contributors:

    Conference:

    Astrodynamics Conference ; 1976 ; San Diego, CA


    Publication date :

    1976-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Mission design for a halo orbiter of the earth

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