Terminal Angular Constraint Integrated Guidance and Control for Flexible Hypersonic Vehicle with Dead-Zone Input Nonlinearity

V448.12; This paper presents an integrated guidance and control model for a flexible hypersonic vehicle with terminal angular constraints. The integrated guidance and control model is bounded and the dead-zone input nonlinearity is considered in the system dynamics. The line of sight angle, line of sight angle rate, attack angle and pitch rate are involved in the integrated guidance and con-trol system. The controller is designed with a backstepping method, in which a first order filter is employed to avoid the differential explosion. The full tuned radial basis function(RBF) neural net-work(NN) is used to approximate the system dynamics with robust item coping with the recon-struction errors, the exactitude model requirement is reduced in the controller design. In the last step of backstepping method design, the adaptive control with Nussbaum function is used for the unknown dynamics with a time-varying control gain function. The uniform ultimate boundedness stability of the control system is proved. The simulation results validate the effectiveness of the controller design.