A New Analytical Approach in Determination of Nonlinear Optimal Guidance Law for Satellite Injection Mission

In this paper an optimal terminal guidance approach for nonlinear injection to a final target orbit is presented to minimize control effort. This problem is formulated as an optimal control problem considering the thrust direction as a control variable. The final orbital states are expressed as terminal constraints. By considering the control effort as performance measure and using a new analytical technique the optimal trajectory and optimal control are obtained. By using the methods of calculus of variations and applying a trigonometric series for approximating the performance measure, the optimal thrust angle is determined. In the next, for computing optimal trajectory, the governing state-space equations should be transformed to a new differential equations expressing with respect to control variable. Finally by using the proposed analytical technique, the optimal trajectory and control could be obtained for injection problem in the exact form.

کلیدواژه ها:

Nonlinear Optimal Control ، Boundary Value problem ، Exact Solution ، satellite injection