Abstract A non-singular analytical theory for the motion of high eccentricity satellite orbits under the influence of air drag is developed in terms of the Uniformly Regular Kustaanheimo and Stiefel (URKS) canonical elements, by assuming the atmosphere to be oblate with variation of density scale height with altitude. The series expansions include up to fourth-order terms of an independent variable Δ=λ 2 (function of eccentric anomaly) and c (a small parameter dependent on the flattening of the atmosphere). Only two of the nine equations are solved analytically due to symmetry in the equations of motion. Comparison of the important orbital parameters semi-major axis and eccentricity up to 1000 revolutions, obtained with the present analytical solution and the KS theory, shows the superiority of the present solution over the KS elements analytical solution. The theory can be used effectively for the orbital decay of aero-assisted orbital transfer orbits during mission planning.


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    Title :

    Decay of high eccentricity satellite orbits with air drag using uniformly regular KS canonical elements


    Contributors:
    Anitha, C.S. (author) / Sharma, R.K. (author)

    Published in:

    Acta Astronautica ; 68 , 11-12 ; 1865-1871


    Publication date :

    2011-01-11


    Size :

    7 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






    Contraction of High Eccentricity Satellite Orbits Using KS Elements in an Oblate Atmosphere

    Sharma, R. K. / International Council of Scientific Unions; Committee on Space Research; Technical Panel on Satellite Dynamics | British Library Conference Proceedings | 1999