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首页> 外文期刊>Aerospace science and technology >A new sliding mode control design for integrated missile guidance and control system
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A new sliding mode control design for integrated missile guidance and control system

机译：综合导弹制导系统的新型滑模控制设计

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A new sliding mode control algorithm for integrated guidance and control (IGC) system is proposed in this paper. Firstly, the IGC model is established and the nonlinearities, target maneuvers, perturbations caused by variations of aerodynamic parameters, etc. are viewed as disturbance, so that the IGC system becomes a mismatched uncertain linear system. Secondly, a second-order disturbance observer is used to estimate the disturbances and their derivatives. Thirdly, an integral sliding mode surface is designed to obtain the rudder deflection command directly instead of the back-stepping control (BC) algorithm used in conventional IGC system, which achieves the real sense of IGC, and the stability of the system is proven strictly by Lyapunov stability theory. Finally, the superiority of the proposed IGC method is verified by comparing the simulation results of different methods under different cases. (C) 2018 Elsevier Masson SAS. All rights reserved.
机译：提出了一种新的IGC系统滑模控制算法。首先，建立了IGC模型，将非线性，目标操纵，由空气动力学参数变化引起的扰动等视为扰动，使IGC系统成为不匹配的不确定线性系统。其次，使用二阶扰动观测器来估计扰动及其导数。第三，设计了一个完整的滑模曲面来代替传统IGC系统中的反步控制（BC）算法直接获得舵的偏转指令，达到了IGC的真实感，并严格证明了系统的稳定性由Lyapunov稳定性理论得出。最后，通过比较不同情况下不同方法的仿真结果，验证了所提IGC方法的优越性。 （C）2018 Elsevier Masson SAS。版权所有。

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