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Iterative Learning Control for homing guidance design of missiles

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Defence Technology（防务技术） 2017年第5期13卷 360-366页

作者： Leonardo Acho Escola d'Enginyeria de Barcelona Est-EEBE Universitat Politecnica de Catalunya-UPCSpain

This paper presents an Iterative Learning Control design applied to homing guidance of missiles against maneuvering targets. According to numerical experiments, although an increase of the control energies is appreciated with respect to a previous published base controller for comparison, this strategy, which is simple to realize, is able to reduce the time to reach the head-on condition to target destruction. This fact is important to minimize the missile lateral force-level to fulfill engaging in hyper-sonic target persecutions.

关键词： Terminal guidance law missiles Iterative learning control

THE GLOBAL DEFORMATION AND LOCAL DAMAGE ANALYSIS OF FILLED METALLIC CYLINDRICAL SHELLS IMPACTED BY missiles

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Acta Mechanica Solida Sinica 1999年第3期12卷 255-262页

作者： Li Zhu Zhang Shanyuan Yang Guitong Taiyuan Univ Technol Inst Appl Mech Taiyuan 030024 Peoples R China

A group of theoretical models has been developed for analyzingtransient dynamic re- sponse to filled metallic cylindrical shellsimpacted by flat-nosed missiles at normal obliquity on the ba- sis ofthe analogy modeling method of beam-on-foundation. It can be used forsolving the global defor- mation and the local failure of cylindricalshells in the impact process. the ballistic limit speed and im- pactresponse history have been calculated by this group of theoreticalmodels, and the inner pressure effect on the ballistic limit speedand some parameters are discussed at length.

关键词： missiles filled metallic cylindrical shells perforation

Stealth Considerations for Aerodynamic Configurations Design of missiles

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Computer Aided Drafting,Design and Manufacturing 2009年第1期19卷 8-16页

作者： QASIM Zeeshan ALI Kamran AMER F Rafique KHURRAM Nisar School of Astronautics Beijing University of Aeronautics and Astronautics

The aerodynamic design of a strategic weapon is of interest, especially when the radar signatures are included in the conceptual design phase. The basics of stealth configurations and stealth mechanisms for missiles are reviewed. The Radar Cross Sections （RCS） of some generic missiles are predicted and compared to analyze the trade-offs involved between low RCS and aerodynamic performance. The consideration of RCS prediction in the conceptual design phase gives a quick insight into the stealth performance prior to detailed design.

关键词： aerodynamic configuration missiles radar cross section radar absorbent material stealth

Optimal Guidance Law to Maximize Terminal Velocity for missiles with Impact Angle Constraint

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Journal of Harbin Institute of Technology(New Series) 2016年第2期23卷 72-78页

作者： Chao Ming Ruisheng Sun Chuanjie Sun School of Energy and Power Engineering Nanjing University of Science and Technology Institute of Structural Mechanics China Academy of Engineering Physics

In this paper,an optimal guidance law for missiles with impact angle and miss distance constraints is proposed to achieve the maximal terminal velocity. The normal acceleration command that includes the timevarying coefficients is introduced to satisfy the desired impact angle as well as zero miss distance according to the geometric relation and relative motion parameters between missile and target. The problem is formulated as an optimal control problem by defining the angle of velocity error and flight-path angle as state variables and maximizing a performance index of the terminal velocity. The analytical form of the proposed guidance law is obtained as the solution of the optimal control problem combining optimal control theory and numerical value computation method. Nonlinear simulations of various situations demonstrate the performance and feasibility of the proposed optimal guidance law.

关键词： optimal guidance law maximum terminal velocity missiles impact angle and miss distance constraints analytical for^m

Design of Time-constrained Guidance Laws via Virtual Leader Approach

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Chinese Journal of Aeronautics 2010年第1期23卷 103-108页

作者： Zhao Shiyu Zhou Rui Wei Chen Ding Quanxin School of Automation Science and Electrical Engineering Beijing University of Aeronautics and Astronautics Beijing 100191 China National Defense Key Lab of Fire Control Technique Luoyang Institute of Electro-optical Equipment of A VIC Luoyang 471009 China

Guidance problems with flight time constraints are considered in this article. A new virtual leader scheme is used for design of guidance laws with time constraints. The core idea of this scheme is to adopt a virtual leader for real missiles to convert a guidance problem with time constraints to a nonlinear tracking problem,thereby making it possible to settle the problem with a variety of control methods. A novel time-constrained guidance （TCG） law, which can control the flight time of missiles to a prescribed time,is designed by using the virtual leader scheme and stability method. The TCG law is a combination of the well-known proportional navigation guidance（PNG） law and the feedback of flight time error. What＇ s more, this law is free of singularities and hence yields better performances in comparison with optimal guidance laws with time constraints. Nonlinear simulations demonstrate the effectiveness of the proposed law.

关键词： guidance missiles salvo attack time constraint virtual leader

Analysis of echo signal modulation characteristic parameters on aerial and space targets

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Defence Technology（防务技术） 2023年第10期28卷 146-154页

作者： Si Chen Hai-yang Zhang Chang-ming Zhao Yu Fan Hong Chen Lin Wang School of Optics and Photonics Beijing Institute of TechnologyBeijing100081China Key Laboratory of Electro-Optical Countermeasures Test&Evaluation Technology Unit 63891 of the Chinese People's Liberation ArmyHenan461002China Key Laboratory of Optical Radiation Beijing Institute of Environmental CharacteristicsBeijing100854China

Based on the scattering characteristic,the comparison of RCS(radar cross-section)at different positions of a target in the same direction of incidence can be obtained first by extruding or deleting part of the entity.A simulation method of aerial&space targets echo characteristics(A&STEC)is proposed that is universal to aerial and space *** utilize a fixed-wing UAV(unmanned aerial vehicle)and typical missiles in *** echo signal modulation characteristic parameters are calculated theoretically by the atmospheric attenuation model,the finite element method and a MUMPS *** verification simulations show that this method can analyze the influence of the target shape,incident direction,detection position and detection frequency on echo waveform,intensity and energy *** results show that the profile of echo waveform can invert the general shape of the *** relationship between time and intensity can determine whether the target is moving towards or away from the detector in *** conclusions can provide a reference for the ballistic missile target tracking and the defense against UVA intrusion in theory.

关键词： Echo signal modulation characteristic parameters Simple targets The fixed-wing UVA missiles Scattering characteristics

Output-feedback based partial integrated missile guidance and control law design

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Journal of Systems Engineering and Electronics 2016年第6期27卷 1238-1248页

作者： Xuejiao Sun Rui Zhou Delong Hou School of Automation Science and Electrical Engineering Beihang UniversityBeijing 100191China Beijing Institute of Electronic System Engineering Beijing 100854China

An output-feedback based partial integrated guidance and control (IGC) law for missile interceptor is proposed with the smooth finite time convergence property. Firstly, a novel outputfeedback based smooth sliding mode control is proposed for a class of nonlinear systems in the presence of immeasurable state and disturbance. The finite time convergence property of this control scheme is proved based on the Lyapunov stability and homogeneous principle. Then, the proposed control method is applied to the design of partial IGC law. A kind of scaling methods is also developed to reach the rapid convergence of the system. An important dominance of this control scheme is the smooth characteristic, which may result in chattering free convergence. The simulation results indicate the high precision and smooth elevator deflection of the proposed output feedback base partial IGC law. © 2016 Beijing Institute of Aerospace Information.

关键词： Control system synthesis Control theory Electronic guidance systems Guided missiles missiles Sliding mode control

Hypersonic Vehicle Trajectory Prediction Algorithm Based on Hough Transform

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Chinese Journal of Electronics 2021年第5期30卷 918-930页

作者： LI Fan XIONG Jiajun LAN Xuhui BI Hongkui TAN Xiansi Air Force Early Warning Academy Unit 95980 of the PLA

Trajectory prediction is a prerequisite for missile and high-speed vehicle guidance interception. To address the trajectory problem for the near space hypersonic unpowered gliding vehicle. Firstly, the trajectory prediction mechanism is analyzed. Based on the existing NSHV trajectory prediction method, the key techniques of trajectory prediction are discussed from the perspectives of prediction parameter selection and prediction parameter description. Then, a trajectory prediction method based on Hough transform is proposed. The core of the method is to select the longitude latitude, and high direction positions as prediction parameters, and use the Hough transform to fit the prior basis functions. In the latitude and longitude direction, the rationality of predicting parameters is discussed from two aspects: position extreme point and lateral maneuverability. In the height direction,for the NSHV oscillation drop characteristic, two Hough transforms are used to separate the periodic term from the linear term. In addition, we give the approximate interval of the parameter values of the method, and design a parameter adaptive scheme. Finally, trajectory prediction is performed on two different control patterns. The error of the prediction time of 100 s is within 25 km, and the results show the effectiveness of the proposed method.

关键词： radial basis function networks hypersonic vehicle trajectory prediction algorithm missile prediction parameter selection NSHV oscillation drop characteristic Hough transform attitude control near space hypersonic unpowered gliding vehicle Hough transforms control system synthesis trajectory control high-speed vehicle guidance interception NSHV trajectory prediction method aircraft control missiles

Research on the Hardware-in-the-loop Simulation of Guidance System

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Journal of Systems Engineering and Electronics 1994年第3期5卷 41-48页

作者： Shan, Jiayuan Li, Zhongwu Beijing Inst of Technology Beijing China

In this paper, the composition of the hardware-in-the-loop simulation system of missile guidance system and the characteristic and function of every equipment in this simulation system are discussed. Then the principle of this system is discussed in terms of theory, and the resemblance of prototype system with simulation system is analyzed. Also, many key problems such as equipment interface, equipment installation, modelling and software design are dealt with. At the end, the error source of simulation system is analyzed, and a strong base is built for the study of simulation system precision.

关键词： Animation Computer simulation Computer software Data acquisition Error analysis Installation Interfaces (computer) missiles