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Two-phase guidance law for impact time control under physical constraints

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Chinese Journal of Aeronautics 2020年第11期33卷 2946-2958页

作者： Yang TANG Xiaoping ZHU Zhou ZHOU Fei YAN National Key Laboratory of Science and Technology on UAV Northwestern Polytechnical UniversityXi’an 710065China UAV Research Institute Northwestern Polytechnical UniversityXi'an 710065China School of Aeronautics Northwestern Polytechnical UniversityXi'an 710072China

An impact-time-control guidance law is required for the simultaneous attack of suicide attack unmanned aerial *** on the nonlinear model,a two-phase guidance strategy is *** impact time is derived in a simple analytical form of initial states and switching states,and it can be controlled by switching at an appropriate ***,a two-phase guidance law is designed to make the magnitude of the heading error decrease monotonically from its initial value to *** then,the feasible interval of the switching ranges and of the impact times under the acceleration constraint are given analytically in ***,a general form of twophase guidance law is proposed,which allows the magnitude of the heading error to increase in the first phase,to improve the applicability of the *** the same structure as proportional navigation guidance with a time-varying gain,the proposed algorithms are simple and easy to *** corresponding feedback form is presented for realistic *** a predefined impact time is taken within its permissible set,the constraints on the acceleration and fieldof-view will not be violated during the ***,simulations validate the effectiveness of the methodology in impact time control and salvo attack.

关键词： Acceleration constraint Field-of-view constraint Guidance impact time control Switching

A hybrid proportional navigation based two-stage impact time control guidance law

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Journal of Systems Engineering and Electronics 2022年第2期33卷 461-473页

作者： HUANG Jia CHANG Sijiang CHEN Shengfu School of Energy and Power Engineering Nanjing University of Science and TechnologyNanjing 210094China The 20th Research Institute of China Electronics Technology Group Corporation Xi’an 710068China

To improve applicability and adaptability of the impact time control guidance(ITCG) in practical engineering, a twostage ITCG law with simple but effective structure is proposed based on the hybrid proportional navigation, namely, the pureproportional-navigation and the *** the case with the impact time error less than zero, the first stage of the guided trajectory is driven by the retro-proportionalnavigation and the second one is driven by the pure-proportionalnavigation. When the impact time error is greater than zero, both of the stages are generated by the pure-proportional-navigation but using different navigation gains. It is demonstrated by twoand three-dimensional numerical simulations that the proposed guidance law at least has comparable results to existing proportional-navigation-based ITCG laws and is shown to be advantageous in certain circumstances in that the proposed guidance law alleviates its dependence on the time-to-go estimation, consumes less control energy, and adapts itself to more boundary conditions and constraints. The results of this research are expected to be supplementary to the current research literature.

关键词： missile guidance law impact time control pure-proportional-navigation retro-proportional-navigation time-to-go estimation

impact time control Guidance Law Design

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Impact Time Control Guidance Law Design

Optimal three-dimensional impact time guidance with seeker’s field-of-view constraint

第37届中国控制会议

作者： Zhongtao Cheng Linren Zhuo Jizhang Xiong Lei Liu Yongji Wang National Key Laboratory of Science and Technology on Multispectral Information Processing School of AutomationHuazhong University of Science and Technology

By combining the Lyapunov stability theorem with the proportional navigation guidance（PNG） law, a novel guidance law which can control the impact time is proposed. This paper treats the impact time control problem as the impact time error regulation problem. The impact time error is defined by the difference between the desired time and the estimated *** Lyapunov candidate function is introduced concerning the impact time error, and the control parameter is proposed to satisfy the Lyapunov stability theorem. The impact time error will go to zero before the desired time, and the singularity issue of the acceleration command has been analyzed. Numerical simulations are carried out to prove the effectiveness of the proposed guidance law.

关键词： Proportional navigation guidance Lyapunov stability theorem impact time control estimated time-to-go

来源： cnki会议评论

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Chinese Journal of Aeronautics 2021年第2期34卷 240-251页

作者： Shaoming HE Chang-Hun LEE Hyo-Sang SHIN Antonios TSOURDOS School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China Department of Aerospace Engineering Korea Advanced Institute of Science and TechnologyDaejeon 34141Republic of Korea School of Aerospace Transport and ManufacturingCranfield UniversityCranfiehMK43 OALUnited Kingdom

This paper proposes a new three-dimensional optimal guidance law for impact time control with seeker’s Field-of-View(FOV) constraint to intercept a stationary target. The proposed guidance law is devised in conjunction with the concept of biased Proportional Navigation Guidance(PNG). The guidance law developed leverages a nonlinear function to ensure the boundedness of velocity lead angle to cater to the seeker’s FOV limit. It is proven that the impact time error is nullified in a finite-time under the proposed method. Additionally, the optimality of the biased command is theoretically analyzed. Numerical simulations confirm the superiority of the proposed method and validate the analytic findings.

关键词： Applied optimal control Field-of-view constraint impact time control Missile guidance Optimal error dynamics