The control method for rotating missile with three pieces of steering wings

Abstract

Due to the limitation of structure, weight and other factors, one rotating missile cannot be controlled by double channels of four pieces of steering wings, and the control effect with the single channel of two pieces of steering wings is dissatisfactory at low speed. In this case, a control method with three pieces of steering wings is proposed. In this paper, the mounting position of the steering wings and the polarity of the angle are defined under the quasi-body system, the control principle of three pieces of steering wings, the control command distribution, the calculation of control force and moment are described in detail. the rationality and validity of the method has been verified by mathematical simulation.