Sliding mode guidance of an air-to-air missile

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2013
Ulu, Muharrem
Pursuit of a highly maneuverable aircraft by an air-to-air missile requires a solution to a challenging guidance and control problem. Precision is the most important need for these missiles. Appropriate guidance commands that are generated by the guidance method and an autopilot that can fulfil the agility needs of such a missile are the keys of minimizing the distance between the missile and the target and a successful interception. In this thesis, autopilot and guidance method design of an air-to-air missile(AAM) that has maximum 100 seconds time of flight is studied. As the first step, nonlinear 6 degrees-of-freedom (6DOF) mathematical model of the missile is derived by using the equations of motion with aerodynamic coefficients found by Missile Datcom program. Mathematical model is linearized around chosen flight conditions to design an autopilot. In this thesis, the guidance problem is handled by using first and second order sliding mode control and these guidance rules are compared for different interception scenarios.

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Citation Formats
M. Ulu, “Sliding mode guidance of an air-to-air missile,” M.S. - Master of Science, Middle East Technical University, 2013.