Research On Integrated Design Method Of Missile Guidance And Control

The missile guidance system and the control system itself is a mutually dependent and mutually influenced entity.When considering the integrated design of guidance and control,the mechanical system will show the characteristics of nonlinearity,time variation,uncertainty and strong coupling.Therefore,the nonlinear control problem of the integrated design of guidance and control has important guiding significance and application value to improve the precision strike capability of the missile.In this paper,the integrated design of guidance and control is studied by using nonlinear control theory.Firstly,the dynamic model of the missile is established,and the related theory of nonlinear control is briefly described.Secondly,using the appropriate nonlinear control technology,using different design methods,the integrated control law of missile guidance and control is designed.And the stability proof is given for each design method from the theory aspect,the feasibility and effectiveness of the method are verified by simulation.Finally,we made a summary of the article.The specific research contents are as follows:1.Based on the integrated design of missile guidance and control,the design of the integrated control law is studied by using feedback linearization method,sliding mode control,back-stepping design,adaptive control and so on.Firstly,the mechanical model of the integrated design is established,and the system is simplified by using differential geometry theory,the integrated control law is designed by using feedback linearization method and sliding mode control method.Then,the integrated mechanical model is translated into the form of the lower triangular structure.In order to avoid the problem of calculation of expansion in the traditional back-stepping algorithm,combine adaptive control method,every step of the back-stepping algorithm estimate the upper bound of uncertainties,to simplify the design of control system.Finally,combining the back-stepping control method,adaptive control and sliding mode control,an integrated algorithm for missile guidance and control is presented.2.The integrated design of missile guidance and control needs to consider the dynamic model of the missile,the relative motion between the target and the missile.Due to the maneuvering of the target,the influence of the uncertainty and the coupling between the channels,the control system has the non matching uncertainties.And taking into account the perturbation of the aerodynamic coefficient,the coefficient of the equation is also uncertain.Therefore,based on adaptive control has a strong ability to identify unknown quantities,the sliding-mode control law which has the ability to resist interference,and Nussbaum gain adaptive control can effectively solve the control problem which the system has the uncertain coefficients,the integrated guidance and control law is designed based on Nussbaum gain adaptive sliding mode control.Then,for a class of uncertain systems,the problem of Nussbaum gain output feedback adaptive control is studied.3.When designing the integrated guidance and control system,some control laws contain unknown information.But the passive seeker mounted on the missile can only detect the angle information.Therefore,in order to realize the control law,it is needed to estimate the unknown information from the angle of the information.Therefore,the control law is designed by sliding mode control method,and then the particle filter method is studied to estimate the unknown physical quantity,so as to realize precise control.