Design of Guidance and Control Systems for Tactical Missiles 1st Edition by Qi Zaikang, Lin Defu 1000681215 9781000681215

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ISBN-10 :  1000681215 

ISBN-13 :  9781000681215

Author: Qi Zaikang, Lin Defu 

  Design of Guidance and Control Systems for Tactical Missiles presents a modern, comprehensive study of the latest design methods for tactical missile guidance and control. It analyzes autopilot designs, seeker system designs, guidance laws and theories, and the internal and external disturbances affecting the performance factors of missile guidance control systems. The text combines detailed examination of key theories with practical coverage of methods for advanced missile guidance control systems. It is valuable content for professors and graduate-level students in missile guidance and control, as well as engineers and researchers who work in the area of tactical missile guidance and control.

Design of Guidance and Control Systems for Tactical Missiles 1st Table of contents:

1. The Basics of Missile Guidance Control
1.1 Overview
1.2 Missile Control Methods
2. Missile Trajectory Models, Aerodynamic Derivatives, Dynamic Coefficients and Missile Transfer Functions
2.1 Symbols and Definitions
2.2 Euler Equations of the Missile Rigid Body Motion
2.3 Configuration of the Control Surfaces
2.4 Aerodynamic Derivatives and the Missile Control Dynamic Coefficient
2.5 The Transfer Function of a Missile as the Object Being Controlled
3. Basic Missile Control Component Mathematical Models
3.1 Seeker
3.2 Actuator
3.3 Angular Rate Gyro
3.4 Accelerometer
3.5 Inertial Navigation Components and Integrated Inertial Navigation Module
4. Autopilot Design
4.1 Acceleration Autopilot
4.1.1 Two-Loop Acceleration Autopilot
4.1.2 Two-Loop Autopilot with PI Compensation
4.1.3 Three-Loop Autopilot with Pseudo Angle of Attack Feedback
4.1.4 Classic Three-Loop Autopilot
4.1.5 Discussion of Variable Acceleration Autopilot Structures
4.1.6 Hinge Moment Autopilot
4.1.7 Several Questions Concerning Acceleration Autopilot Design
4.2 Pitch/Yaw Attitude Autopilot
4.3 Flight Path Angle Autopilot
4.4 Roll Attitude Autopilot
4.5 BTT Autopilot
4.6 Thrust Vector Control and Thruster Control
5. Guidance Radar
5.1 Introduction
5.2 Motion Characteristic of the Target Line-of-Sight
5.3 Loop of the Guidance Radar Control
5.4 Effect of the Receiver Thermal Noise on the Performance of Guidance Radar
5.5 Effect of Target Glint on the Performance of Guidance Radar
5.6 Effect of Other Disturbances on the Performance of Guidance Radar
5.6.1 Effect of Disturbance Moment on the Performance of Tracking Radar
5.6.2 Effect of Target Maneuvers
6. Line of Sight Guidance
6.1 LOS Guidance System
6.2 Analysis of the Required Acceleration for the Missile with LOS Guidance
6.3 Analysis of the LOS Guidance Loop
6.4 Lead Angle Method
7. Seekers
7.1 Overview
7.2 Electromechanical Structure of Commonly Used Seekers
7.2.1 Dynamic Gyro Seeker
7.2.2 Stabilized Platform-Based Seeker
7.2.3 Detector Strapdown Stabilized Optic Seeker
7.2.4 Semi-Strapdown Platform Seeker
7.2.5 Strapdown Seeker
7.2.6 Roll-Pitch Seeker
7.3 Mechanism Analysis of the Anti-Disturbance Moment of the Seeker’s Stabilization Loop and Tracking Loop
7.4 Transfer Function of Body Motion Coupling and the Parasitic Loop
7.4.1 Transfer Function of Body Motion Coupling
7.4.2 Seeker-Missile Coupling Introduced Guidance Parasitic Loop
7.5 A Real Seeker Model
7.5.1 A Real Seeker Model
7.5.2 Testing Methods for Modeling the Real Seeker
7.6 Other Parasitic Loop Models
7.6.1 Parasitic Loop Model for a Phase Array Strapdown Seeker
7.6.2 Parasitic Loop Due to Radome Slope Error
7.6.3 Beam Control Gain Error ∆KB of the Phased Array Seeker and the Radome Slope Error Rdom Effect on the Seeker Output
7.7 Stabilization Loop and Tracking Loop Design of the Platform-Based Seeker
7.7.1 Stabilization Loop Design
7.7.2 Tracking Loop Design
8. Proportional Navigation and Extended Proportional Navigation Guidance Laws
8.1 Proportional Navigation Guidance Law
8.1.1 Proportional Navigation Guidance Law
8.1.2 Analysis of Proportional Navigation Guidance Law with No Guidance System Lag
8.1.3 The Proportional Navigation Guidance Characteristics with the Missile Guidance Dynamics Included
8.2 Extended Proportional Navigation Guidance Laws (Optimal Proportional Navigation, OPN)
8.2.1 Optimal Proportional Navigation Guidance Law (OPN1) with the Consideration of the Missile Guidance Dynamics
8.2.2 Optimal Proportional Navigation Guidance Law (OPN2) Considering the Constant Target Maneuver
8.2.3 Extended Proportional Navigation (OPN3) Considering Both Constant Target Maneuvers and Missile Guidance Dynamics
8.2.4 Estimation of Target Maneuver Acceleration
8.2.5 On the Estimation of tgo
8.2.6 Proportional Navigation Guidance Law with Impact Angle Constraint
8.3 Other Types of Proportional Navigation Laws
8.3.1 Gravity Over-Compensated Proportional Navigation Law
8.3.2 Lead Angle Proportional Navigation Guidance Law
8.4 Target Maneuver Acceleration Estimation
8.5 Optimum Trajectory Control Design

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Tags: Design of Guidance, Control Systems, Tactical Missiles, Qi Zaikang, Lin Defu