Optimization of reorientation maneuvers for a spacecraft

Аuthors

Levsky M. V.

Khrunichev State Research and Production Space Center, 18, Novozavodskaya St., Moscow, 121087, Russia

e-mail: niiks@knrunichev.com

Abstract

A control problem for a spatial maneuver is described and solved to change a spacecraft orientation during minimum time interval. An analytical solution is found for the problem under angular momentum constraint. Necessary optimality conditions are derived based on quaternion technique. A complete solution of the reorientation problem is obtained in closed form for a case of dynamically symmetric spacecraft. Results of mathematical modeling are given to demonstrate a practical possibility of on-board implementation for the proposed technique.