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A terminal guidance Law Based on Motion Camouflage Strategy of Air-to-Ground Missiles

INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING 2016年第Pt.2期2016卷 9218754.1-9218754.1页

作者： Gao, Chang-sheng Li, Jian-qing Jing, Wu-xing Harbin Inst Technol Dept Aerosp Engn Harbin Peoples R China

A guidance law for attacking ground target based on motion camouflage strategy is proposed in this paper. According to the relative position between missile and target, the dual second-order dynamics model is derived. The missile guidance condition is given by analyzing the characteristic of motion camouflage strategy. Then, the terminal guidance law is derived by using the relative motion of missile and target and the guidance condition. In the process of derivation, the three-dimensional guidance law could be designed in a two-dimensional plane and the difficulty of guidance law design is reduced. A two-dimensional guidance law for three-dimensional space is derived by bringing the estimation for target maneuver. Finally, simulation for the proposed guidance law is taken and compared with pure proportional navigation. The simulation results demonstrate that the proposed guidance law can be applied to air-to-ground missiles.

关键词： relative motion SURFACE AIR three-dimensional space guidance terminal guidance Camouflage mimicry (behavior)

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A Three-Dimensional Anti-Saturation terminal guidance Law with Finite-time Convergence

A Three-Dimensional Anti-Saturation Terminal Guidance Law wi...

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American Control Conference

作者： Guilin Li Ming Xin Department of Electrical Engineering and Automation Jiangsu Normal University 221116 China Department of Mechanical and Aerospace Engineering University of Missouri Columbia 65211 USA

ISBN: (纸本)9781509045839

In a practical terminal guidance process, missile acceleration may be saturated and the saturation can lead to degraded interception performance. This paper presents an anti-saturation guidance law with finite-time convergence for a three-dimensional maneuvering interception, using the theories of finite-time boundedness (FTB) and input-output finite-time stability (IO-FTS). With this law, the line-of-sight (LOS) angular rates converge in finite time while guaranteeing the missile accelerations do not exceed their physical limits. A sufficient condition for FTB and IO-FTS of a class of nonlinear systems is given, and is used to design the guidance law. Quasi-one-sided Lipschitz condition is employed to address the nonlinear term, and transforms the problem of ensuring the system FTB and IO-FTS simultaneously to that of solving a differential linear matrix inequality (DLMI). Simulation results verify the effectiveness of the new guidance law design.

关键词： terminal guidance Converge Lipschitz condition guidance Finite time thermodynamics interceptions

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A Three-dimension terminal guidance Method Based on Adaptive PN Law and Convex Optimization 35

A Three-dimension Terminal Guidance Method Based on Adaptive...

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第35届中国控制会议

作者： ZENG Xijuan CHENG Xiaoming ZHANG Ran LI Huifeng The School of Astronautics Beihang University

ISBN: (纸本)9781509009107

A three-dimension guidance method is proposed for the multi-constrained optimal terminal guidance problem. First, an adaptive proportion navigation(PN) guidance law is designed to obtain a nominal trajectory of the guidance task, and the guidance logic is designed to allocate the guidance commands. Then, the guidance problem is linearized as a linear time-varying quadratic convex optimal problem based on the nominal trajectory, and the discretization is done to convert the infinite-dimensional optimization problem to a finite-dimensional one. Finally, the linearized quadratic convex optimal problem can be solved by a convex optimization method with deterministic convergence properties, and the optimal guidance command is obtained. Simulation results show that the proposed method can satisfy the terminal state constraints and control constraints, and reduce the control consumption significantly.

关键词： terminal guidance adaptive PN guidance law convex optimization control consumption

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NASA Technical Reports Server (Ntrs) 19810006476: Flight Evaluation of the terminal guidance System

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2016年

NASA Technical Reports Server (Ntrs) 19810006476: Flight Evaluation of the terminal guidance System by NASA Technical Reports Server (Ntrs); published by

关键词： (ntrs) 19810006476: aircraft equipment aircraft landing approach control cessna aircraft evaluation flight flight paths guidance nasa technical reports server (ntrs) pilot performance sandlin, d. r. terminal guidance workloads (psychophysiology)

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Target Recognition in the terminal guidance Process: A Novel Algorithm for Resource Allocation

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IFAC-PapersOnLine 2015年第28期48卷 835-840页

作者： Zhang, Silun He, Fenghua Yao, Yu Harbin Institute of Technology Harbin150080 China

This paper provides a novel algorithm to allocate the limit detecting and processing resource to different suspected targets in the terminal guidance process of missile-defense interceptors. It can effectively accelerate the process of target recognition in terminal guidance. To model this allocating process, time distribution and interest value distribution are firstly introduced in such kind of problems, which distinctly describe the current allocation and the desired allocation respectively. Then we transfer this problem into a control task, where the control law guarantees the convergence of the error between these two allocations. At last, we illustrate the effectiveness of the proposed strategy by a group of numerical simulation. © 2015

关键词： Resource allocation Target tracking Missile defense Multi targets Novel algorithm Processing resources Target recognition terminal guidance Time distribution Value distribution

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Impact angle and impact velocity constrained terminal guidance for stationary target

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AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY 2015年第5期87卷 454-464页

作者： Zhou, Hao Rahman, Tawfiqur Chen, Wanchun Beihang Univ Sch Astronaut Beijing 100191 Peoples R China

Purpose - The purpose of this paper is to present a novel guidance law for hypervelocity descent to a stationary target such that the impact angle and impact velocity can be constrained. Design/methodology/approach - The proposed method is based on inverse dynamics and is designed using a third-order Bezier curve approximation to the reference trajectory. Findings - Simulations indicate that the proposed law is able to satisfy impact angle and impact velocity constraints as well as follow control and path limitations in the case of guidance under perturbations. Comparisons with other methods also indicate better performance. Research limitations/implications - The onboard implementation requires an offline selection of Bezier parameters. Practical implications - The presented scheme could be extremely important for further research on automated onboard control of impact angle and velocity for both re-entry and terminal guidance laws. Originality/value - This paper presents an innovative method for the solution of an inverse dynamics-based guidance law using Bezier curve approximation.

关键词： Bezier curve Inverse dynamics Multi-constraints terminal guidance

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Bounds on the Miss of Multiple-Model-Based terminal guidance Laws

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JOURNAL OF guidance CONTROL AND DYNAMICS 2015年第6期38卷 1001-1011页

作者： Rusnak, Ilan RAFAEL IL-3102102 Haifa Israel

In previous papers, bounds on the root-mean-square miss of a radar-guided missile for different types of target maneuvers and the terminal phase period have been presented. In this paper, bounds on the miss of multiple-model-based terminal guidance laws are presented. Analytical formulas of bounds on the root-mean-square miss of a radar-guided missile that implements multiple-model estimation and guidance scheme against a maneuvering target are presented. These formulas use a set of core parameters that affect the miss distance, thus, they can be used for synthesis and analysis of the performance of radar-guided tactical missiles with the multiple-model estimation and guidance. The bounds are derived subject to the assumption that the missile guidance law and the estimator are fully matched to the missile dynamics, target maneuver, and glint noise. The glint is the dominant noise source, the missile applies frequency agility, there is no missile acceleration limit and heading error, and there is no limitation on the computing resources.

关键词： terminal guidance Radar Guided Missiles RADAR Computing Resources Missile Dynamics Tactical Missiles guidance Laws Kalman Filter Algebraic Riccati Equation Spectral Density

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Observability analysis of feature aided terminal guidance systems

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Journal of Systems Engineering and Electronics 2015年第1期26卷 127-133页

作者： Shijie Fan Hongqi Fan Huaitie Xiao Jianpeng Fan Qiang Fu National Key Laboratory of Automatic Target Recognition National University of Defense Technology College of Electronic Science and Engineering National University of Defense Technology

Feature aided design of estimators and guidance laws can significantly improve the interception performance of the terminal guidance system. The achieved enhancement can be effectively assessed by observability analysis methods. This paper first analyzes and discusses the existing assessment methods in a typical endgame scenario with target orientation observations. To get over their deficiencies, a novel singular value decomposition（SVD） method is proposed. Employing both theoretical analysis and numerical simulation, the proposed method can represent the degree of state observability which is enhanced by integrating target features more completely and quantitatively.

关键词： terminal guidance feature aided observability singular value orientation observation

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Design and Realization of terminal guidance Law for Passive Homing Interceptors 27

Design and Realization of Terminal Guidance Law for Passive ...

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第27届中国控制与决策会议

作者： HUANG Jingshuai ZHANG Hongbo LI Guanghua TANG Guojian College of Aerospace Science and Engineering National University of Defense Technology

ISBN: (纸本)9781479970186

It is of the essence for passive homing interceptors to acquire information required to implement guidance *** practical applications,the accuracy of obtained information directly exerts an influence on terminal guidance *** order to achieve hit-to-kill,a modified three-dimensional proportional guidance law designed to enhance observability of passive guidance of interceptors is presented in this *** dynamic model of three-dimensional interception based on Singer model and observation equation of infrared seeker are established.A real-time two-step estimator is adopted to estimate the states used to realize the modified guidance law,solving the problem of practical application of guidance *** results indicate that the modified guidance law in cascade with the real-time two-step estimator produces small miss distance,satisfying the requirement of terminal guidance accuracy of interception.

关键词： Passive homing interceptors modified three-dimensional proportional guidance law Singer model real-time two-step estimator terminal guidance

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Integration of CFO-based three-dimensional target manoeuver compensation guidance rate and transition region optimisation algorithm

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AERONAUTICAL JOURNAL 2025年

作者： Qi, G. Y. Zhang, X. L. Li, L. Y. Wang, S. S. Zhang, H. Y. Tiangong Univ Sch Control Sci & Engn Tianjin Peoples R China Chongqing Technol & Business Univ Natl Res Base Intelligent Mfg Serv Chongqing Peoples R China

To address the challenges of high-manoeuver targets and limited line-of-sight from the interceptor's side window, this paper proposes a three-dimensional target manoeuver compensation control (TMCC) guidance law based on compensation function observe (CFO) and a method for studying the terminal guidance handover region. First, a relative model of the missile-target engagement is established. Secondly, the CFO is used to estimate the target manoeuver state, and the estimated information is fed back to the controller of the orbit control engine to make the interception more accurate. Considering the limited line of sight of the side window, the body line of sight angle is constrained by controlling the attitude control engine. Then, the problem description for solving the handover area and the definition of the terminal guidance handover area were provided, and the algorithm design for the handover area was conducted, simplifying the solving process through the concept of area substitution. Simulation results indicate that the proposed terminal guidance law offers higher interception accuracy compared to traditional proportional guidance, and effectively validates the accuracy of the handover region calculation.

关键词： terminal guidance mid-course and terminal handover maneuver compensation control interceptor

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