An antisaturation backstepping control scheme based on constrained command filter for hypersonic flight vehicle (HFV) is proposed with the consideration of angle of attack (AOA) constraint and actuator constraints of amplitude and rate. Firstly, the HFV system model is divided into velocity subsystem and height subsystem. Secondly, to handle AOA constraint, a constrained command filter is constructed to limit the amplitude of the AOA command and retain its differentiability. And the constraint range is set in advance via a prescribed performance method to guarantee that the tracking error of the AOA meets the constraint conditions and transient and steady performance. Thirdly, the proposed constrained command filter is combined with the auxiliary system for actuator constraints, which ensures that the control input meets the limited requirements of amplitude and rate, and the system is stable. In addition, the tracking errors of the system are proved to be ultimately uniformly bounded based on the Lyapunov stability theory. Finally, the effectiveness of the proposed method is verified by simulation.
This paper proposes a three-dimensional laser beam-riding guidance (LBRG) scheme with finite distance convergence for the interception guidance problem of laser beam-riding guided missiles (LBRGMs). First, the motion relationship between the guidance station, missile, and target is constructed, and a three-dimensional LBRG model based on position deviation is designed. Considering the finite range of the laser beam and convergence performance of the guidance system, a finite-distance convergence performance function is proposed, and its guidance law is designed by combining the prescribed performance and sliding mode control methods. Then, considering the unknown maneuvering information of the target, the acquired maneuvering information is converted into an estimation of the line-of-sight angle and its rate, estimated by designing the command filter. In addition, Lyapunov theory is employed to prove the stability of the guidance scheme. The position deviation converged to the steady-state value within the prescribed flight distance, thereby satisfying the prescribed transient and steady-state performance requirements and realizing the interception of the maneuvering target. Finally, the effectiveness of the guidance scheme is verified through simulations.
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