Abstract
This paper provides a simple yet accurate method for computing the long-term effects of impulsive and short-term perturbing forces on a body in elliptical orbit. The solutions are cast in a form which requires integration over a maximum of one orbit period, and thus avoids the high cost and low accuracy normally associated with deriving perturbations over many orbit periods. The basic equations solved are the nondimensionalized Tschauner-Hempel Equations, and their correspondence to Inertial Guidance Position and Velocity Error Equations for systems in orbit is pointed out.
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