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Research of Dynamic and Control of Spinning Ballistic Missile

Author: YuanTianBao
Tutor: QinZiZeng
School: National University of Defense Science and Technology
Course: Aeronautical and Astronautical Science and Technology
Keywords: Laser kill Spinning Ballistic Missile Attitude control uncoupling control Generalized Predictive Control Internal Modal Control flying simulation
CLC: TJ761
Type: PhD thesis
Year: 2005
Downloads: 1623
Quote: 8
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Penetration of missile became more and more important with the research and deployment of ballistic missile defense system. Spinning flight of ballistic missile in boost phase is a new idea in order to penetrate laser’s interception. Spinning missiles may be unstable due to dynamic and control interactions. It is a crucial question to stabilize missiles under stronger interactions, which has been hardly studied before. In this dissertation many significant result are given from the research of several correlative dynamic and control topics.An exhaustive summarization is made for free flight motion of spinning missiles. The dynamic modal of spinning missiles is developed and the method of property analysis is discussed. Attitude movement of spinning missiles is explained as two vectors’complex motion. Several forces are discussed to show the effect on stability. Attitude feedback control stability is analyzed based on the close loop stability criterion, which gave a reference for attitude control system design of spinning ballistic missile.The method for designing of spinning ballistic missiles’attitude control system is put forward. Based on the spinning ballistic missiles’dynamic and control modal in frequency domain, designing of attitude control system is studied by classic and modern frequency method. The problem of attitude stabilization under stronger interactions is resolved by single channel PID controller, dynamic pre-compensator, adaptive parameter schedule and subsection control maneuver. By three channels attitude tracking simulation and 6 DOF simulation and disturbed movement simulation, the system is proved to be exact and robust, which has good feasibility for simple configuration.The idea of attitude stability by servo system design is constructed. Continuous generalize predictive control (CGPC) is used in the design of servo system to weaken the interaction between pitching and yawing control system. Mixed weights CGPC is constructed for constrained CGPC, which has advantage in simplicity and efficiency. Performance of ballistic missile’s servo system is improved by approximate constrained arithmetic.The effect of side force on stability of spinning missiles is studied by Routh criterion, which proved to be more universal than others’work. By this method, the same problem of spinning ballistic missiles is analyzed approximately.

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