Abstract:

Firstly an expression of the optimal interacting direction of the single highpowered laser pulse about the geostationary earth orbit(GEO) debris is derived. By analyzing approach and generate the optimal direction, the spacecraft is in the need of orbit and attitude coupled control relative to the debris. As models of both translational and rotational dynamics are considered, constraints of terminal state, collision avoidance, keep seeing and finite magnitude of state and control variables are imposed. The problem of by using minimumenergy optimal trajectory is formulated and further decomposed the Pontryagin minimum principle. The problem is solved numerically by using the hpadaptive pseudospectral method and the sequential quadratic programming algorithm. Finally, the obtained solution is verified through the minimum principle. Simulation results show that minimumenergy solution is feasible, and the algorithm is efficient. The investigation provides a technical approach for engineering applications of removing debris.