The singly averaged differential equations of satellite motion for e greater than or equal to 0 and less than 1

Details The singly averaged differential equations of satellite motion for e greater than or equal to 0 and less than 1 The singly averaged differential equations of satellite motion for e greater than or equal to 0 and less than 1

Aug 1976

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1976aaas.confr....d&link_type=abstract

American Institute of Aeronautics and Astronautics and American Astronautical Society, Astrodynamics Conference, San Diego, Cali

Astronomy and Astrophysics

Astronomy

Elliptical Orbits, Equations Of Motion, Orbital Mechanics, Satellite Orbits, Satellite Perturbation, Aerodynamic Drag, Circular Orbits, Differential Equations, Eccentricity, Numerical Integration, Planetary Orbits, Radiation Pressure, Solar Radiation, Spacecraft Maneuvers, Zonal Harmonics

Scientific paper

The singly-averaged differential equations of motion of a satellite are developed in terms of parameters valid for all eccentricities less than one. The perturbations included in the acceleration model are due to an aspherical central planet (zonal harmonics up to degree 20 and resonant harmonics up to degree and order 20), atmospheric drag for a time-varying atmosphere, third-body gravity (the sun and moon for an earth satellite), solar radiation pressure with shadowing, and impulsive maneuvers. Analytic averaging is used to remove short-period terms due to the aspherical central planet and third-body gravity. Numerical averaging is used to remove short-period terms due to atmospheric drag and solar radiation pressure.

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