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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

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

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

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

A micelle-based stage-by-stage impelled system for efficient doxorubicin delivery

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Bioactive Materials 2023年第7期25卷 783-795页

作者： Sunfan Li Fangzhou Li Dong Wan Zuqin Chen Jie Pan Xing-Jie Liang School of Chemical Engineering and Technology Tiangong UniversityTianjin300387PR China CAS Key Laboratory for Biomedical Effects of Nanomaterials and Nanosafety CAS Center for Excellence in NanoscienceNational Center for Nanoscience and Technology of ChinaNo.11First North RoadZhongguancunBeijing100190PR China University of Chinese Academy of Sciences Beijing100049PR China Medical School of Chinese PLA No.28 Fuxing RoadBeijing100853PR China Department of Radiology The First Medical CentreChinese PLA General HospitalBeijingPR China Department of Radiology Chinese PAP Guangxi Corps HospitalNanningGuangxiPR China

Chemotherapy remains the mainstay of cancer treatment,benefiting millions of patients each year,but the side effects of chemotherapy drugs severely limit their clinical use.Doxorubicin(DOX)can cause various side effects such as heart damage and treatment-related tumors.The effective use of active and passive targeting will improve the clinical application of DOX.Here,TPGS3350 and bioactive peptides were utilized to construct a micelle-based stage-by-stage impelled efficient system(Missiles)for DOX delivery(DOX Missiles).By taking advantage of the EPR effect,DOX Missiles are efficiently enriched at the tumor site.After being cleaved by matrix metalloproteinase2(MMP2),the peptide(VRGD)targets tumor cells to facilitate uptake of the Missiles by the tumor cells via receptor-mediated endocytosis.The intracellular activated caspase-3-catalyzed explosion of DOX Missiles further enables efficient tumor killing.This study provides an efficient approach for DOX delivery and toxicity reduction.

关键词： Doxorubicin Delivery Peptide Missiles Chemotherapy

Distributed three-dimensional cooperative guidance via receding horizon control

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Chinese Journal of Aeronautics 2016年第4期29卷 972-983页

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

The paper presents a new three-dimensional(3D) cooperative guidance approach by the receding horizon control(RHC) technique. The objective is to coordinate the impact time of a group of interceptor Missiles against the stationary target. The framework of a distributed RHC scheme is developed, in which each interceptor missile is assigned its own finite-horizon optimal control problem(FHOCP) and only shares the information with its neighbors. The solution of the local FHOCP is obtained by the constrained particle swarm optimization(PSO) method that is integrated into the distributed RHC framework with enhanced equality and inequality constraints. The numerical simulations show that the proposed guidance approach is feasible to implement the cooperative engagement with satisfied accuracy of target capture. Finally, the computation efficiency of the distributed RHC scheme is discussed in consideration of the PSO parameters, control update period and prediction horizon.

关键词： Distributed algorithms Impact time Missile guidance Multiple Missiles Particle swarm optimization(PSO) Receding horizon control(RHC) Three-dimensional(3D)

Trajectory reshaping based guidance with impact time and angle constraints

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Chinese Journal of Aeronautics 2016年第4期29卷 984-994页

作者： Zhao Yao Sheng Yongzhi Liu Xiangdong School of Automation Beijing Institute of Technology Key Laboratory for Intelligent Control and Decision of Complex Systems Beijing Institute of Technology

This study presents a novel impact time and angle constrained guidance law for homing Missiles. The guidance law is first developed with the prior-assumption of a stationary target, which is followed by the practical extension to a maneuvering target scenario. To derive the closed-form guidance law, the trajectory reshaping technique is utilized and it results in defining a specific polynomial function with two unknown coefficients. These coefficients are determined to satisfy the impact time and angle constraints as well as the zero miss distance. Furthermore, the proposed guidance law has three additional guidance gains as design parameters which make it possible to adjust the guided trajectory according to the operational conditions and missile's capability.Numerical simulations are presented to validate the effectiveness of the proposed guidance law.

关键词： Guidance Homing Missiles Impact angle Impact time Trajectory reshaping

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

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 targets.We utilize a fixed-wing UAV(unmanned aerial vehicle)and typical Missiles in simulation.The echo signal modulation characteristic parameters are calculated theoretically by the atmospheric attenuation model,the finite element method and a MUMPS solver.The 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 distribution.The results show that the profile of echo waveform can invert the general shape of the target.The relationship between time and intensity can determine whether the target is moving towards or away from the detector in addition.These 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