Hou Mingzhe

Integrated Guidance and Control of Homing Missiles Against Ground Fixed Targets

Abstract This paper presents a scheme of integrated guidance and autopilot design for homing missiles against ground fixed targets. An integrated guidance and control model in the pitch plane is formulated and further changed into a normal form by nonlinear coordinate transformation. By adopting the sliding mode control approach, an adaptive nonlinear control law of the system is designed so that the missile can hit the target accurately with a desired impact attitude angle. The stability analysis of the closed-loop system is also conducted. The numerical simulation has confirmed the usefulness of the proposed design scheme.

Longitudinal attitude control of a hypersonic vehicle with angle of attack constraints

An adaptive dynamic surface control algorithm is proposed for longitudinal attitude of the hypersonic vehicle in the presence of angle of attack constraints. The angle of attack constraints are firstly converted into the tracking error constraints, and then a weighted performance function and an error transformation technique are introduced, which guarantee a prescribed performance of tracking error as well as prevent the angle of attack from transgressing the constraints, and the original nonlinear system with constrained tracking error is transformed into an equivalent unconstrained one. An adaptive dynamic surface control algorithm is subsequently proposed to stabilize this transformed error system. It is proved that asymptotic tracking of the longitudinal attitude is achieved without violation of the angle of attack constraints, and all the other signals in the closed loop are uniformly ultimately bounded. The Monte-Carlo simulation results show the effectiveness of the proposed method.