Seiji Yamaoka/Seiya Ueno
International Journal of Aeronautical and Space Sicences, vol. 10, no. 1, pp.46-57, 2009

Abstract : This paper deals with design procedure of online guidance and control law for future missiles that requires agile maneuverability. For the purpose, the missile with high powered side thruster is proposed. The guidance and control law for such missiles is discussed from a point of view of optimal control theory in this paper. Minimum time problem is solved for the approximated system. It is derived that bang-bang control is optimal input from the necessary conditions of optimal solution. Feedback guidance without iterative calculation is useful for actual systems. In this paper, multiple design point method is applied to design feedback gains and feedforward inputs of the guidance and control law. The numerical results show that the proposed guidance and control law has a high-performance for wide-ranging boundary conditions.

Keyword : Guidance and control, Optimization, High Maneuvering