Abstract
In this paper, considering a class of skid-to-turn (STT) missile with impact angle constraint to intercept the maneuvering target, a three-dimensional integrated guidance and control law based on the fractional integral terminal sliding mode control (FITSMC) scheme is proposed. Firstly, a three-dimensional integrated guidance and control model is established for missile-target relative motion and nonlinear missile dynamics with multiple system uncertainties and unknown disturbances. Secondly, in order to achieve the desired impact angle in finite-time without singularity, a novel nonsingular FITSMC scheme is employed to construct the sliding surface, and a modified filter is applied to dynamic surface control design. Also, an extended state observer is introduced to estimate and compensate the system uncertainties and unknown disturbances. Then, a robust integrated guidance and control scheme with impact angle constraint is developed using aforementioned techniques. Furthermore, the finite-time stability of the closed-loop system is proven based on Lyapunov theory. Finally, the effectiveness and robustness of the proposed integrated guidance and control algorithm are verified through numerical simulations.
Highlights
Due to the increasingly extensive application in modern warfare, missiles have received more and more attention
3) A novel integrated guidance and control (IGC) law is formulated with nonsingular fractional integral terminal sliding mode control (FITSMC) scheme to achieve the missile with desired impact angles intercepting maneuvering target
DESIGN OF 3-D INTEGRATED GUIDANCE AND CONTROL LAW we develop a novel IGC law based on the nonsingular FITSMC and the extended state observer (ESO) for the uncertain nonlinear system (8)
Summary
Due to the increasingly extensive application in modern warfare, missiles have received more and more attention. In [20], based on the nonsingular terminal sliding mode, an impact angle constrained guidance law is designed to intercept the virtual target in finite time. A modified filter is applied to the DSC design, and the novel DSC method addresses the problem of ‘‘explosion of terms’’ and achieves finite-time convergence. In [34], a new robust 3-D IGC method cater to impact angle constraints is designed for STT hypersonic missile with high uncertainties. The main contributions of this paper are summarized as follows: 1) A novel nonsingular FITSMC scheme is proposed, which guarantees the finite-time convergence of the tracking errors and overcomes the singularity problem in conventional TSMC. 3) A novel IGC law is formulated with nonsingular FITSMC scheme to achieve the missile with desired impact angles intercepting maneuvering target.
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