Effects of torques due to aerodynamic drag and gravity gradient are computed for satellites orbiting at altitudes of between 80 and 375 mi; equilibrium position is determined as function of altitude for both dumbbell and cylindrical-shaped object; equilibrium position of cylindrical object in three dimensions is considered as function of altitude; equations.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Effect of aerodynamic forces on satellite attitude


    Additional title:

    J Astronautical Sciences


    Contributors:
    DeBra, D.B. (author)


    Publication date :

    1959


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Vehicle Attitude Changes from Aerodynamic Forces

    Guzman, Arturo / Fadler, Gregory / Tripp, John et al. | SAE Technical Papers | 2018


    Vehicle Attitude Changes from Aerodynamic Forces

    Tripp, John / Lounsberry, Todd / Guzman, Arturo et al. | British Library Conference Proceedings | 2018


    Linear Coupled Attitude-Orbit Control Through Aerodynamic Forces

    Harris, Andrew T. / Petersen, Christopher / Schaub, Hanspeter | AIAA | 2018


    Linear Coupled Attitude-Orbit Control Through Aerodynamic Forces (AIAA 2018-0962)

    Harris, Andrew T. / Petersen, Christopher / Schaub, Hanspeter | British Library Conference Proceedings | 2018