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Journal of Beijing Institute of Technology 2011年第4期20卷 462-465页

作者：王江石正海林德福祁载康 School of Aerospace Engineering Beijing Institute of Technology North Automatic Control Technology Research Institute

The guidance and control strategy for endoatmospheric kinetic interceptor controlled by lateral pulse thrusters was *** pulse thruster control system was firstly *** sample-and-hold approach was introduced to design a novel lateral acceleration autopilot on the basis of traditional two-loop *** with proportional navigation guidance law and the novel autopilot,the overall ballistic trajectory was presented and *** results show that the pulse thruster control strategy can greatly improve the control system response speed and the maximal acceleration capability for realizing kinetic kill interception.

关键词： kinetic interceptor pulse thruster acceleration autopilot proportional navigation

A New Composite proportional navigation Entry Guidance Strategy for Glider under Multiple Uncertainties

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A New Composite Proportional Navigation Entry Guidance Strat...

Extended differential geometric guidance law for intercepting maneuvering targets

第37届中国控制会议

作者： Danyao Zhang Qingyu Du Yijia Xie Jianzhong Qiao School of Automation Science and Electrical Engineering Beihang University Science and Technology on Aerospace Intelligent Control Laboratory Beijing Advanced Innovation Center for Big Data-based Precision Medicine Beihang University

This work presents a high precision entry guidance strategy for the glider subject to uncertainties in both aerodynamic parameters and atmospheric density.A new composite proportional navigation combined with disturbance observer is proposed to improve the precision of entry ***,the multiple uncertainties are analyzed and a dynamic model with uncertainties is established where the multiple uncertainties have been transformed into equivalent ***,a disturbance observer is designed to estimate and compensate the equivalent ***,a proportional navigation law is designed to guide the glider without considering the effect of *** analysis are given to guarantee the closed-loop *** results of X-33 model show the effectiveness and performance of composite proportional navigation entry guidance strategy for glider.

关键词： glider multiple uncertainties disturbance observer proportional navigation entry guidance

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Journal of Systems Engineering and Electronics 2018年第5期29卷 1046-1057页

作者： HUANG Jingshuai ZHANG Hongbo TANG Guojian BAO Weimin College of Aerospace Science and Engineering National University of Defense TechnologyChangsha 410073China China Aerospace Science and Technology Corporation Beijing 100048China

Without assumptions made on motion states of missile and target, an extended differential geometric guidance law is derived. Through introducing a line of sight rotation coordinate system, the derivation is simplified and has more explicit physical significances. The extended law is theoretically applicable to any engagement scenarios. Then, on basis of the extended law, a modified one is designed without the requirement of target acceleration and an approach is proposed to determining the applied direction of commanded missile acceleration. Qualitative analysis is carried out to study the capture performance and a criterion for capture is given. Simulation results indicate the two laws are effective and make up the deficiency that pure proportional navigation suitable for endoatmospheric interceptions cannot deal with high-speed maneuvering targets. Furthermore, the correctness of the criterion is validated.

关键词： missile guidance maneuvering target extended differential geometric guidance law capture performance proportional navigation

Obstacle avoidance for multi-missile network via distributed coordination algorithm

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Chinese Journal of Aeronautics 2016年第2期29卷 441-447页

作者： Zhao Jiang Zhou Rui School of Automation Science and Electrical Engineering Beihang University

A distributed coordination algorithm is proposed to enhance the engagement of the multi-missile network in consideration of obstacle avoidance. To achieve a cooperative interception, the guidance law is developed in a simple form that consists of three individual components for tar- get capture, time coordination and obstacle avoidance. The distributed coordination algorithm enables a group of interceptor missiles to reach the target simultaneously, even if some member in the multi-missile network can only collect the information from nearest neighbors. The simula- tion results show that the guidance strategy provides a feasible tool to implement obstacle avoid- ance for the multi-missile network with satisfactory accuracy of target capture. The effects of the gain parameters are also discussed to evaluate the proposed approach.

关键词： Cooperative guidance Distributed algorithms Impact time Missile guidance Multiple missiles Obstacle avoidance proportional navigation

Optimal terminal guidance for exoatmospheric interception

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Chinese Journal of Aeronautics 2016年第4期29卷 1052-1064页

作者： Yu Wenbin Chen Wanchun Yang Liang Liu Xiaoming Zhou Hao School of Astronautics Beihang University

In this study, two optimal terminal guidance (OTG) laws, one of which takes into account the final velocity vector constraint, are developed for exoatmospheric interception using optimal control theory. In exoatmospheric interception, because the proposed guidance laws give full consideration to the effect of gravity, they consume much less fuel than the traditional guidance laws while requiring a light computational load. In the development of the guidance laws, a unified optimal guidance problem is put forward, where the final velocity vector constraint can be considered or neglected by properly adjusting a parameter in the cost function. To make this problem analytically solvable, a linear model is used to approximate the gravity difference, the difference of the gravitational accelerations of the target and interceptor. Additionally, an example is provided to show that some achievements of this study can be used to significantly improve the fuel efficiency of the pulsed guidance employed by the interceptor whose divert thrust level is fixed. (C) 2016 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license.

关键词： Exoatmospheric interception Explicit guidance Guidance Optimal control proportional navigation Pulsed guidance

Differential geometric modeling of guidance problem for interceptors

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Science China(Technological Sciences) 2011年第9期54卷 2283-2295页

作者： LI KeBot CHEN Lei BAI XianZong College of Aerospace and Materials Engineering National University of Defense Technology Changsha 410073 China

It is a comparatively convenient technique to investigate the motion of a particle with the help of the differential geometry the-ory,rather than directly decomposing the motion in the Cartesian *** new model of three-dimensional (3D) guidance problem for interceptors is presented in this paper,based on the classical differential geometry curve ***,the kinematical equations of the line of sight (LOS) are gained by carefully investigating the rotation principle of LOS,the kinematic equations of LOS are established,and the concepts of curvature and torsion of LOS are ***,the new relative dynamic equations between interceptor and target are ***,it is found that there is an instan-taneous rotation plane of LOS (IRPL) in the space,in which two-dimensional (2D) guidance laws could be constructed to solve 3D interception guidance *** spatial 3D true proportional navigation (TPN) guidance law could be directly introduced in IRPL without approximation and linearization for dimension-reduced 2D *** addition,the new series of augmented TPN (APN) and LOS angular acceleration guidance laws (AAG) could also be gained in *** that,the dif-ferential geometric guidance commands (DGGC) of guidance laws in IRPL are advanced,and we prove that the guidance commands in arc-length system proposed by Chiou and Kuo are just a special case of ***,the performance of the original guidance laws will be reduced after the differential geometric *** last,an exoatmospheric intercep-tion is taken for simulation to demonstrate the differential geometric modeling proposed in this paper.

关键词： kinematic equations of LOS instantaneous rotation plane of LOS proportional navigation augmented trueproportional navigation LOS angular acceleration guidance law differential geometric guidance commands

Optimal Guidance Law of Reentry Vehicle with Terminal Interception and Impact Angle Constraints 36

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Optimal Guidance Law of Reentry Vehicle with Terminal Interc...

Improved differential geometric guidance commands for endoatmospheric interception of high-speed targets

第36届中国控制会议

作者： Dawei Liu China Research Development Academy of Machinery Equipment Department of Automation Tsinghua University

ISBN: (纸本)9781538629185

An optimal guidance law of reentry vehicle both with terminal interception and impact angle constraint is derived,and tow types of optimal guidance law expressions "proportional navigation + Angle Constraint（PN+AC）" and "Velocity Pursuit + Angle Constraint（VP+AC）" are given with lag-free dynamic ***,simulations of non-dimensional miss distance and impact angle error base on statistical linearization adjoint method with first-order lag system show that the guidance performances of the two types are ***,reentry vehicle kinematics model is established,simulations show that the two types of optimal guidance law both can meet the constraint perfectly,but the choice of guidance law in specific project depends on the guidance accuracy requirement and the guidance mode and information can be *** results obtained can improve important theoretical basis to the optimal guidance law of reentry vehicle.

关键词： Terminal interception Impact angle constraint Optimal guidance law proportional navigation Velocity pursuit

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Science China(Technological Sciences) 2013年第3期56卷 518-528页

作者： LI KeBo CHEN Lei TANG GuoJin College of Aerospace Science and Engineering National University of Defense Technology

Pure proportional navigation(PPN) is suitable for endoatmospheric interceptions,for its commanded acceleration is perpendicular to interceptor ***,if the target is much faster than the interceptor,the homing performance of PPN will be degraded *** proportional navigation(TPN) does not have this problem,but its commanded acceleration is perpendicular to the line of sight(LOS),which is not suitable for endoatmospheric *** commanded acceleration of differential geometric guidance commands(DGGC) is perpendicular to the interceptor velocity,while the homing performance approximates the LOS referenced guidance laws(PPN series).Therefore,DGGC is suitable for endoatmospheric interception of high-speed ***,target maneuver information is essential for the construction of DGGC,and the guidance commands are complex and may be without *** the deep analysis of three-dimensional engagement,a new construction method of DGGC is proposed in this *** target maneuver information is not needed any more,and the robustness of DGGC is guaranteed,which makes the application of DGGC possible.

关键词： differential geometric guidance commands endoatmospheric interception high-speed targets proportional navigation robustness

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Deep reinforcement learning based missile guidance law design for maneuvering target interception

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Deep reinforcement learning based missile guidance law desig...