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首页> 外文期刊>Aerospace science and technology >A novel non-singular terminal sliding mode control-based integrated missile guidance and control with impact angle constraint
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A novel non-singular terminal sliding mode control-based integrated missile guidance and control with impact angle constraint

机译：具有冲击角约束的新型非奇异终端滑模控制一体化导弹制导

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摘要

A novel impact angle constrained integrated guidance and control (IGC) scheme is proposed with non-singular terminal sliding mode control (NTSMC) technique for missile to intercept a maneuverable target. Firstly, an IGC design model is innovatively established in a strict feedback form which selects the normal overload as the system state in replace of the angle of attack so that the system states both are measurable. On this basis, an IGC law is proposed to guarantee the impact angle converge to the expected command within a finite time and to improve the robustness against the multiple disturbances which include the model parameter uncertainties and the target maneuvering by incorporating the NTSMC method and the extended state observer (ESO) technique. In order to avoid the chattering phenomenon, the smooth derivative of the intermediate control command which is obtained by the introduced nonlinear tracking differentiator (TD) is adopted into the control loop. Then, the stability of closed-loop integrated system is rigorously proved by utilizing the Lyapunov theorem. Finally, extensive contrast simulation results are presented to validate the efficiency, superiority and robustness of the suggested IGC scheme. (C) 2019 Elsevier Masson SAS. All rights reserved.
机译：提出了一种新颖的非直角终端滑模控制（NTSMC）技术，用于导弹拦截可操纵目标的冲击角约束综合制导与控制（IGC）方案。首先，以严格的反馈形式创新性地建立了IGC设计模型，该模型选择正常的过载作为系统状态来代替迎角，从而可以同时测量系统状态。在此基础上，提出了IGC定律，通过结合NTSMC方法和扩展方法，保证冲击角在有限的时间内收敛到期望的命令，并提高了对包括模型参数不确定性和目标操纵在内的多种干扰的鲁棒性。状态观察者（ESO）技术。为了避免出现颤动现象，控制回路采用了由引入的非线性跟踪微分器（TD）获得的中间控制指令的平滑导数。然后，利用李雅普诺夫定理严格证明了闭环集成系统的稳定性。最后，提出了广泛的对比度仿真结果，以验证所提出的IGC方案的效率，优越性和鲁棒性。 （C）2019 Elsevier Masson SAS。版权所有。

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