A hierarchy-structured predictive controller is designed and analyzed for rotation motion dynamics of a generic hypersonic vehicle(GHV).This vehicle model has fast variability,is highly nonlinear,and includes uncertain parameters.The controller contains two subsystems,the inner-fast-loop nonlinear generable predictive controller(NGPC)and the outer-slow-loop NGPC,both of which are designed by the closed-form optimal generable predictive control method.Thus,the heavy on-line computational burden in the classical predictive control method is avoided.The hierarchy structure of the control system decreases the relative degree of each subsystem and helps increase the dynamic response speed of the attitude controller.In order to improve the robustness of the control system,a feedback correction algorithm is proposed that corrects the calculation error between the predictive model and the real dynamic model.Simulation studies are conducted for the trimmed cruise conditions of an altitude of 33.5 km and Mach 15 to investigate the responses of the vehicle to the step commands of angle of attack,sideslip angle,and bank angle.The simulation studies demonstrate that the proposed controller is robust with respect to the parametric uncertainties and atmospheric disturbance,and meets the performance requirements of GHV with acceptable control inputs. A hierarchy-structured predictive controller is designed and analyzed for rotation motion dynamics of a generic hypersonic vehicle (GHV). This vehicle model has fast variability, is highly nonlinear, and includes uncertain parameters. The controller contains two subsystems, the inner-fast- loop nonlinear generable predictive controller (NGPC) and the outer-slow-loop NGPC, both of which are designed by the closed-form optimal generable predictive control method.Thus, the heavy on-line computational burden in the classical predictive control method is avoided The hierarchy structure of the control system reduces the relative degree of each subsystem and helps increase the dynamic response speed of the attitude controller. In order to improve the robustness of the control system, a feedback correction algorithm is proposed that corrects the calculation error between the predictive model and the real dynamic model. Simulation studies are conducted for the trimmed cruise conditions of an altitude of 33 . 5 km and Mach 15 to investigate the responses of the vehicle to the step commands of angle of attack, sideslip angle, and bank angle. The simulation studies demonstrate that the proposed controller is robust with respect to the parametric uncertainties and atmospheric disturbance, and meets the performance requirements of GHV with acceptable control inputs.