Missile Attitude Control-A Direct Parametric Approach

In this paper, the dynamical model in a matrix second-order nonlinear form with respect to the three Euler angles is firstly established for the attitude system of a rigid missile, which is complete in the sense that no simplification via approximation is taken. It is revealed that this general model is a fully-actuated one without any further assumption. Then, with the help of a recently proposed general parametric design approach for general fully-actuated second-order nonlinear systems, a direct parametric approach for missile attitude control via proportional plus derivative feedback is proposed, which gives a complete parametrization of the pair of feedback gains, and allows usage of the established complete model but not a simplified one. The approach possesses two important features. Firstly, with the proposed controller parametrization, missile attitude systems, though highly nonlinear, can be turned into a constant linear system with desire eigenstructure. Secondly, in such a design there are still degrees of freedom which may be further utilized to improve the system performance. An example is considered to demonstrate the use of the proposed approach.