Control integrated design for hypersonic vehicle

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.