By applying an averaging method to the Gauss equations, the perturbing accelerations acting on a satellite can be represented as a function of 14 constant thrust Fourier coefficients. Time rates of change of mean orbital elements due to these thrust Fourier coefficients are analyzed, and the representation of these thrust coefficients as a function of the change in orbit states is studied. A selected minimum set of six thrust Fourier coefficients is able to provide a finite basis representation of arbitrary orbital maneuvers that allow the authors to dynamically interpolate between states across an unknown maneuver. Using this essential thrust-Fourier-coefficient set, different types of solutions are obtained, and a comparison study of these solutions is also conducted.
Essential Thrust-Fourier-Coefficient Set of Averaged Gauss Equations for Orbital Mechanics
Journal of Guidance, Control, and Dynamics ; 37 , 4 ; 1236-1249
2014-02-21
14 pages
Article (Journal)
Electronic Resource
English
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