Robust optimal guidance for hypersonic glide vehicle with hinge moment constraint

The magnitude of hinge moment is a prominent problem for rapid dive maneuver of hypersonic glide vehicles. A robust optimal integrated guidance law considering constraints of hinge moment and terminal impact angle is proposed with excellent performance. Based on the analogy relationship of hinge moment and normal aerodynamic load, the constraint of hinge moment is transformed to normal load constraint; and the optimal guidance law under nominal conditions is derived utilizing optimal control theory. A terminal sliding mode control based guidance modification is designed to eliminate the inevitable departure brought by uncertainties in finite time; and the hyperbolic tangent function is introduced to reduce the high-frequency chatting. The theoretical analysis and simulation results are conducted to illustrate the capability of the proposed integrated guidance law for hypersonic glide vehicle.