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.

This article proposes a strongly coupled integrated guidance and control (SCIGC) law for accurately intercepting the near-space hypersonic target under attitude/orbit engine compound control subjected to discrete-time inputs and multiple constraints. Based on the characteristics of attitude/orbit pulsed engine and full strapdown seeker, the discrete-time SCIGC model is constructed including control inputs coupling, guidance/control system coupling, field-of-view (FOV) constraint and impact angle constraint. The proposed control law adapted to the discrete-time inputs is presented by combining the high-order multi-dimensional sliding mode control (SMC) for utilizing the couplings, the prescribe performance function (PPF) for satisfying FOV constraint without ignoring the couplings and the extended disturbance observer (EDO) for estimating the mismatched unknown uncertainties. The stability of proposed control law-based closed-loop system is guaranteed. The effectiveness and robustness of proposed control law are illustrated by numerical simulations and Monte Carlo tests.

This article proposes a construction method of capture region subject to input constraints of pulsed engine, field-of-view (FOV) constraint and impact angle constraint based on the finite-time convergent guidance law. Firstly, the pulsed engine model, interceptor-target engagement kinematic model and impact angle model are constructed by combining with the discrete and nonlinear characteristics of pulse thrust, full strapdown seeker and head-on approach. Secondly, the finite-time convergent sliding mode guidance (FTC-SMG) law-based capture region is constructed under the zero-effort interception condition (ZEIC). Then, by analyzing the effects of input constraints, FOV constraint and impact angle constraint on the FTC-SMG law-based capture region, the capture region with multiple constraints is constructed. Finally, the FTC-SMG law-based capture regions with and without constraints are displayed by numerical simulations, as well as the reliability of capture regions are verified by comparison simulations and Monte Carlo tests.

A three-dimensional (3D) integrated guidance and control (IGC) law for divert and attitude control system (DACS) based strapdown interceptor subjected to strong couplings and complex constraints is proposed in this paper. The 3D kinematic and dynamic equations reflecting the couplings of the interceptor are constructed by combining the characteristics of DACS and strapdown seeker. An improved IGC model is established by employing the proposed adaptive fixed-time prescribed performance function (AFTPPF). This model takes into account the boundary, terminal and convergence time constraints of strapdown interceptor, along with the mismatched unknown uncertainties. An IGC law is developed within the high-order multi-dimensional sliding mode control (SMC) framework, integrating the AFTPPF to handle the complex constrains without computational singularities and the extended disturbance observer (EDO) for uncertainty estimations. Finally, the stability and performance of the proposed control method are proved.

This paper proposes a Koopman-predictor-based integrated guidance and control (IGC) law for the hypersonic target interceptor under the multi-force compound control. The strongly coupled and nonlinear guidance and control systems including the characteristics of the aerodynamic rudder, attitude control engine and orbit control engine are described as a linear IGC model based on the Koopman predictor. The proposed IGC law adapted to the linear IGC model is presented by combining the sliding mode control (SMC), the extended disturbance observer (EDO), and the adaptive weight-based control allocation scheme for being robust against the uncertainties and optimizing the fuel allocation for the fuel limited interceptor while intercepting the targets precisely. The stability of the proposed control law-based closed-loop system is guaranteed. The effectiveness and robustness of the proposed control law are proved by simulation comparisons and Monte Carlo tests.