Tactical missile guidance and control system design9787568293075
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作者林德福
出版社北京理工大学出版社有限责任公司
ISBN9787568293075
出版时间2021-03
装帧平装
开本16开
定价62元
货号10992860
上书时间2024-12-25
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作者简介
目录
1 The Overview of Missile Guidance and Control
2 Missile Mathematical Models
§2.1 Symbols and Definitions
§2.2 Euler Equations of the Rigid Body Motion
§2.3 Configuration of the Control Surfaces
§2.4 Missile Aerodynamic Derivatives and Dynamic Coefficients
§2.5 Aerodynamic Transfer Functions of the Missile
3 Simplified Models of Missile Control Components
4 Guidance Radar
§4.1 Introduction
§4.2 Motion Characteristic of Line-of-sight
§4.3 Control Loop of the Guidance Radar
§4.4 Effect of the Receiver Thermal Noise on the Guidance Performance
§4.5 Effect of Target Glint on the Guidance Performance
§4.6 Effect of Other Disturbances on the Guidance Performance
4.6.1 Effect of Disturbance Moment
4.6.2 Effect of Target Maneuvers
5 Seekers
§5.1 Definitions
§5.2 Different Kinds of Seekers
5.2.1 Dynamic Gyro Seeker
5.2.2 Stabilized Platform Seeker
5.2.3 Detector Strapdown Stabilized Optic Seeker
5.2.4 Semi-strapdown Platform Seeker
5.2.5 Strapdown Seeker
5.2.6 Roll-pitch Seeker
§5.3 Anti-disturbance Moment of the Seeker
§5.4 Body Motion Coupling and the Parasitie Loop
5.4.1 Body Motion Coupling Dymamics Model
5.4.2 Guidance Parasitic Loop Introduced by Seeker-misile Coupling
§5.5 A Real Seeker Model
5.5.1 A Real Secker Model
5.5.2 Testing Methods
§5.6 Other Parasitic Loop Models
5.6.1 Parasitic Loop Model for a Phase Array Strapdown Seeker
5.6.2 Parasitic Loop Model Due to Radome Slope Error
5.6.3 Beam Control Gain Error AKgof the Phased Array Seeker and the Radome Slope Error R. Effect on the Seckers Performance
5.6.4 A Novel Online Estimation and Compensation Method for Strapdown Phased Array Seeker Disturbance Rejection Effect Using Extended State Kalman Filter
§5.7 Platform Based Seeker Design
5.7.1 Stabilization Loop Design
5.7.2 Tracking Loop Design
5 Missile Autopilot Design
§6.1 Acceleration Autopilot
6.1.1 Two-loop Acceleration Autopilot
6.1.2 Two-loop Acceleration Autopilot with PI Compensation
6.1.3 Three-loop Autopilot with Pseudo Angle of Attack Feedback
6.1.4 Classic Three-loop Autopilot
6.1.5 Discussion of Variable Acceleration Autopilot Structures
6.1.6 Hinge Moment Autopilot
6.1.7 Questions Concerning Acceleration Autopilot Design
6.1.8 The Acceleration Autopilot Design Method
§6.2 Pitch/Yaw Attitude Autopilot
§6.3 Flight Path Angle Autopilot
§6.4 Roll Attitude Autopilot
§6.5 BTT Missile Autopilot
§6.6 Thrust Vector Control and Thruster Control
§6.7 Spinning Missile Control
6.7.1 Aerodynamic Coupling
6.7.2 Control Coupling
7 Line of Sight Guidance Methods
§7.1 LOS Guidance System
§7.2 Required Acceleration for the Missile with LOS Guidance
§7.3 Analysis of the LOS Guidance Loop
§7.4 Lead Angle Guidance Method
8 Proportional Navigation and Extended Proportional Navigation Guidance Laws
§8.1 Proportional Navigation Guidance Law
8.1.1 Proportional Navigation Guidance Law (PN)
8.1.2 PN Analysis without Guidance System Lag
8.1.3 PN Characteristics Including the Missile Guidance Dynamics
8.1.4 Adjoint Method
§8.2 Optimal Proportional Navigation Guidance Laws (OPN)
8.2.1 OPN1:Considering the Missile Guidance Dynamics
8.2.2 OPN2:Considering the Constant Target Maneuver
8.2.3 OPN3: Considering Both Constant Target Maneuvers and Missile Guidance Dynamics
8.2.4 Estimation of Target Maneuver Acceleration
8.2.5 Estimation of t
8.2.6 Extended Guidance Law with Impact Angle Constraint
§8.3 Other Proportional Navigation Laws
8.3.1 Proportional Navigation Law with Gravity Over-compensation
8.3.2 Lead Angle Proportional Navigation Guidance Law
§8.4 Target Acceleration Estimation
§8.5 Optimum Trajectory Control System Design
9 Optimal Guidance for Trajectory Shaping
§9.1 Optimality of Error Dynamics in Missile Guidance
9.1.1 Optimal Error Dynamics
9.1.2 Analysis of Optimal Error Dynamics
§9.2 Optimal Predictor-corrector Guidance
9.2.1 General Approach for Guidance Law Design
9.2.2 Impact Angle Control
9.2.3 Impact Time Control
§9.3 Gravity-turn-assisted Optimal Guidance Law
9.3.1 Zero-control-effort Trajectory Considering Gravity
9.3.2 Optimal Guidance Law Design and Analysis
9.3.3 Characteristics Analysis by Simulations
§9.4 Three-dimensional Optimal Impact Time Guidance for Antiship Missiles
9.4.1 Problem Formulation
9.4.2 Three-dimensional Optimal Impact Time Guidance Law Design
9.4.3 Analysis of Proposed Guidance Law
9.4.4 Numerical Simulations
References
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媒体评论
随着惯导及组合导航在弹上的普遍应用，过去很多无法实现的制导控制方案变为可行。 由于当今对导弹制导精度的需求不断提高，所以对制导控制系统的快速性有了全新的要求，其结果是设计中不再允许接受过去对控制模型所做的很多简化， 从而导致当前的设计模型及可采用的制导控制策略与早期的导弹设计理念有了很大变化。在上述背景下，作者力图使本书的内容与当今制导控制的新理念及应采用的模型密切结合，希望所介绍的多种实用、有价值的设计方法能够对读者有所帮助。书中介绍的内容既涵盖国内、国外新的实用技术，也兼顾东方、西方的设计理念。
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