Abstract
Abstract : This report presents an optimal three burn solution to a class of orbit transfer problems requiring large changes in orbital inclination. A nonlinear programming algorithm was used in conjunction with a simplified trajectory simulation, which used Keplerian orbit transfers and impulsive velocity increments. A number of parametric results were obtained using the simplified simulation. The validity of the simplified simulation was established for specific vehicle configurations with finite burns and oblate earth effects included. The effect of multiple stage rockets has also been treated.
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