The orbital decay of the International Sun-Earth Explorer (ISEE-1) and ISEE-2 spacecraft was studied. The perturbative forces due to the nonspherical components of the earth's gravitational field, atmospheric drag, solar radiation pressure, and third-body perturbations are examined. The dynamics of the earth-spacecraft-moon system is analyzed as well. Various scenarios using the perturbative forces in conjunction with propulsive energy are evaluated to determine the requirements for extending the lifetime of this type of mission.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    ISEE orbital decay due to lunar third-body perturbations


    Contributors:

    Conference:

    AAS/AIAA Astrodynamics Conference ; 1987 ; Kalispell, MT, United States


    Publication date :

    1988-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :



    Trajectories and orbital maneuvers for the ISEE-3/ICE comet mission

    Farquhar, R. / Muhonen, D. / Church, L. C. | NTRS | 1984


    Trajectories and orbital maneuvers for the ISEE-3/ICE comet mission

    FARQUHAR, R. / MUHONEN, D. / CHURCH, L. | AIAA | 1984


    Surrogate Modeling of Orbital Decay of Lunar Orbits

    Varoqui, Maxime / Steffens, Michael J. / Mavris, Dimitri N. | TIBKAT | 2023


    Surrogate Modeling of Orbital Decay of Lunar Orbits

    Varoqui, Maxime / Steffens, Michael J. / Mavris, Dimitri N. | AIAA | 2023