05.1 - Flight Dynamics and Control (Control & Modelling)

MISSILE AUTOPILOT DESIGN USING CONTRACTION THEORY-BASED OUTPUT FEEDBACK CONTROL

H.-H. Kwon¹, H.-L. Choi¹; ¹KAIST, South Korea

Many approaches for nonlinear autopilot design are applied to control angle-of-attack or sideslip angle and need to design additional nonlinear observer. However, state-feedback controller and stable observer just don’t guarantee the stability of combined system. We proposed nonlinear autopilot design using control contraction metrics where separation principle holds for controllers and observers

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