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.
Attitude control Rigid missiles Fully-actuated second-order systems Direct parametric approach Nonlinear systems
DUAN Guang-Ren
Harbin Institute of Technology,Harbin 150001,P. R. China
国际会议
The 33th Chinese Control Conference第33届中国控制会议
南京
英文
2414-2421
2014-07-28（万方平台首次上网日期，不代表论文的发表时间）