| Guidance and control system of missile is a kind of automatic control system. It plays an important part in missile system. Guidance law and controller are the two main points which should be studied. According to the missile itself and the project experience, and meantime, considering the open questions of the guidance law and controller, the main results of this thesis are as follows:Firstly, analyses on guidance and control system. The principle, composition and sorts of guidance and control system are introduced. And also the request of it is explained. According to the subject studied in this thesis, the homing guidance and control system is discussed in detail.Secondly, study on mathematical model. System of coordinates and the transfer of axes are introduced to analyze the force and the moment of force. Based on this, the dynamic equation and the kinematics equation are built. Combining with the mass changes and the control relationship, the kinematics model of missile is completely set up. According to the subject studied in this thesis, and based on some assumptions, the model of Bank-to-Turn missile is built.Thirdly, study on guidance law. According to the characteristic of the air to air missile, aiming at the robust and accuracy, based on the Sliding-Mode Variable Structure control theory and the L2 Gain Performance control theory, the Adaptive Sliding-Mode Guidance, Optimal Sliding-Mode Guidance Law and Robust Guidance Law Based on L2 Gain Performance are studied. Compare with the classical Proportional Navigation Guidance Law, simulations on these three kinds of guidance laws are done.Lastly, study on control law. The three independent dynamic models of the Bank-to-Turn missile are deduced. The H_∞ feedback control theory which is a kind of Robust Control Theory is introduced to design the state feedback controller. Considering the coupling between these three channels, they are combined together and simulated. The results show that the control effect is satisfactory.
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