Since hypersonic vehicles involve characteristics of strong coupling of aerodynamics/propulsion/control and nonlinearity

a suit of control-oriented integrated design tool was developed.In the conceptual design phase

considering the aircraft control performance as the optimization goal

the vehicle was designed based on integrated and optimized parameters of aerodynamic

propulsion

structures and control.Considering the fidelity requirement and computational efficiency of the model generation

a parameterized mathematical model was established and an linear quadratic regulator(LQR) reference command tracking control system was designed.The design parameters were adjusted constantly

and then the trade-off study of the control-relevant static and dynamic properties and the comparison of control effects were accomplished.Finally

a new shape of vehicle was chosen according to the control requirement

and the corresponding validation of simulation was accomplished.Simulation results show that the method of control integrated design applied in the early stage of the conceptual design phase

can expand flight envelope

increase the stall margin effectively

reduce fuel consumption

improve the control surface efficiency

and reduce the engine choking restriction. Thus the method of control integrated design plays a guiding role in improving design efficiency and the performance of control for hypersonic vehicles.