This note presents a novel control framework based on disturbance estimation information to exploit the potential performance improvement. Disturbances in the hypersonic reentry vehicles are revisited, and a disturbance effect indicator (DEI) is defined to demonstrate the pros and cons of disturbances' influence on the system. Based on the disturbance estimation, a disturbance estimation-triggered control (DETC) scheme for the attitude tracking is established. Furthermore, the ultimately bounded stability of the closed-loop system is guaranteed. Distinguished from eliminating the disturbance directly in the state-ofthe-art disturbance observer-based control, the proposed control switches its structure to counteract or retain the disturbance according to the DEI, and thus is capable of improving the transient performance. Simulation results verify the effectiveness and superiority of the proposed approach.

This paper presents a performance-guaranteed adaptive asymptotic tracking control scheme for a class of nonlinear systems with unknown sign-switching control direction. By introducing the periodic sliding mode technique and equivalent control-based adaptive mechanism, the proposed control approach ensures that the sliding mode surface is reached in finite time, and thus the asymptotic stability is achieved rather than only signals boundedness. Simultaneously, the tracking performance is strictly guaranteed inside the preassigned performance bounds even when the unknown control coefficients switch to the opposite direction. The effectiveness of the proposed control law is verified by numerical simulations.

This article presents an adaptive dynamic programming-based intelligent control algorithm for the attitude tracking issue of reentry vehicles subject to model and state uncertainties simultaneously. The traditional control approaches struggle to achieve satisfactory tracking performance since the model and state are together influenced and deviated by the both uncertainties. Instead, the attitude tracking issue in this article is first transformed into an optimal regulation issue of the tracking error. Then, a novel cost function inspired by the idea of zero-sum game is introduced to eliminate the model uncertainties, and state uncertainties are handled dynamically by updating weights based on the optimality principle of the critic network. Consequently, the intelligent tracking control law is obtained by the optimal regulation. The stability of the system and the convergence of network weights are further analyzed using the Lyapunov stability theory. The effectiveness of the proposed control scheme is verified by simulations.

This paper investigates the relationship between the tracking performance and coupling effect for attitude tracking issue of hypersonic reentry vehicle (HRV), and proposes a performance-involved coupling effect-triggered robust control (PICETC) scheme. The main feature of the paper lies in that the influence of the coupling effect on the performance is discussed via a defined performance-involved coupling effect indicator. Consequently, the proposed control ensures the transient performance within the prescribed limitation in all phases, and the better transient performance is achieved with the help of the sliding mode control and disturbance observer technique enhancing the robustness. Comparison simulations and Monte-Carlo tests under coefficients perturbation on the HRV system demonstrate the effectiveness of the proposed control strategy.

A complete engagement framework, including evaluation model, intelligent assignment, and cooperative interception is proposed to address the issue of multimissile and multitarget engagement (MME). The concepts of targets threat degree and missiles interception effective degree are included in the evaluation model, which fully considers both the offensive and defensive sides. Then, the multitarget assignment is carried out based on the obtained evaluation model, and a reinforcement learning-based intelligent assignment strategy is adopted. This scheme is capable of quickly generating the optimal assignment in the complex and variable engagement environment by virtue of the self-learning and reward mechanism. Following the optimal assignment, a cooperative interception technique is used to ensure the interception mission efficiently and accurately. Finally, simulation results illustrate the validity of the proposed engagement framework.

This article proposes a novel integrated guidance and control (IGC) law for laser beam riding missiles subjected to power limited laser beam projector unit (LBPU) to ensure the line deviation constraint and fast convergence in a fixed time. By analyzing the LBPU constraints, the improved IGC model is constructed with the help of fixed-time prescribed performance function. Consequently, the LBPU constraints, fast convergence requirement and mismatched uncertainties are involved in this IGC model. The control law is presented by combining sliding mode control and extended disturbance observer. The stability of closed-loop system and the LBPU constraint satisfaction are guaranteed. The effectiveness and robustness of proposed control are illustrated by numerical simulations and Monte Carlo tests.