Design of Guidance and Control Systems for Tactical Missiles presents a modern, comprehensive study of design methods for tactical missile guidance and control. It analyzes autopilot designs, seeker system designs, guidance laws and theories, and internal and external disturbances affecting the performance of missile guidance control systems.
Design of Guidance and Control Systems for Tactical Missiles presents a modern, comprehensive study of design methods for tactical missile guidance and control. It analyzes autopilot designs, seeker system designs, guidance laws and theories, and internal and external disturbances affecting the performance of missile guidance control systems.
Zaikang Qi is a Weapon Guidance and Control Technology Chief Technical Expert. He has served as the Chair Professor of Aircraft Guidance and Control Design in Beijing Institute of Technology, Director of the Institute of UAV Autonomous Control. He has been engaged in teaching and researching in the field of aircraft system design for 60 years. In addition, he has worked as Chief Engineer over several advanced researches and model scientific research projects. He is a member of the State Council Academic Degrees Committee Disciplinary Appraisal Team of the People's Republic of China and International Editor of the American Journal of Computers in Mechanical Engineering. Lin Defu received his Ph.D degree from Beijing Institute of Technology. Currently, he is Director of the Institute of UAV Autonomous Control. He has more than 20 years' experience in the overall design and guidance and control of flight vehicles. He has worked as principle investigators for several key national projects. Due to his outstanding research work, he has been awarded second prize of National Scientific Invention and National Defense Science and Technology. He has more than 80 journal publications and serves as member of multiple academic committees.
Inhaltsangabe
Basic Knowledge of Missile Guidance Control. Missile Trajectory Models, Aerodynamic Derivatives, Dynamic Coefficients and Missile Transfer Functions. Basic Missile Control Component Mathematics Models. Autopilot Design. Guidance Radar. Line of Sight Guidance. Seeker. Proportional Navigation and Extended Proportional Navigation Guidance Law. Proof of the Proportional Navigation Law with the Help of Optimal Control Theory. Adjoint Method. Bibliography. Index.
Basic Knowledge of Missile Guidance Control. Missile Trajectory Models, Aerodynamic Derivatives, Dynamic Coefficients and Missile Transfer Functions. Basic Missile Control Component Mathematics Models. Autopilot Design. Guidance Radar. Line of Sight Guidance. Seeker. Proportional Navigation and Extended Proportional Navigation Guidance Law. Proof of the Proportional Navigation Law with the Help of Optimal Control Theory. Adjoint Method. Bibliography. Index.
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