B. Semerci, O. Merttocuoglu, and O. Tekinalp (Turkey)
modeling spinning missile, proportional navigation, missile control, robust control, linear quadratic regulator, Monte Carlo simulations.
Modeling and control of a spinning missile is investigated. A new frame called non-rolling frame is proposed to carry out proportional navigation guidance laws and control. It is shown that the missile equations of motion written in this new frame are simpler, and trim conditions may also be defined in this frame without neglecting gravity contributions. Linear quadratic regulators are designed using the linearized non-rolling frame equations. The effectiveness of the designs under changing flight conditions is demonstrated through nonlinear simulations. The effectiveness of the design for target engagement in spite of parameter uncertainty is also demonstrated through Monte Carlo simulations.
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