The change in satellite mean anomaly due to a rotating oblate atmosphere with a diurnal variation in density

Details The change in satellite mean anomaly due to a rotating oblate atmosphere with a diurnal variation in density The change in satellite mean anomaly due to a rotating oblate atmosphere with a diurnal variation in density

Jan 1984

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984rspsa.391..201b&link_type=abstract

Royal Society (London), Proceedings, Series A - Mathematical and Physical Sciences (ISSN 0080-4630), vol. 391, no. 1800, Jan. 9,

Physics

Aerodynamic Drag, Atmospheric Density, Orbit Perturbation, Satellite Drag, Satellite Perturbation, Diurnal Variations, Eccentricity, Kepler Laws, Long Term Effects, Oblate Spheroids, Orbital Elements

Scientific paper

The effect of atmospheric drag on satellite orbits of small eccentricity, e being less than or approximately equal to 0.2, is considered. The atmospheric model allows for oblateness, and has a density profile that approximates to the observed day-to-night variation. The equation governing the changes due to drag in the mean anomaly M during one revolution of the satellite is integrated, assuming that H, the density scale height, is constant. Two particular cases are detailed. In the first, the change in M (delta M) over one anomalistic period is given for eccentricity e in the range where it is less than or approximately equal to 0.2 and greater than or approximately equal to 0.01, and in the second the change in (M + omega) over one draconic period, delta (M + omega), is given for eccentricity e in the range where it is less than or approximately equal to 0.01 and greater than or equal to 0, where omega is the argument of perigee. Finally a compact expression for e times delta M is derived for an atmosphere with a linear variation of H with altitude, if e is less than or approximately equal to 0.2 and greater than or approximately equal to 0.01.

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