A Nonlinear Roll Autopilot based on 5-DOF Models of Missiles
نویسندگان
چکیده
This paper suggests a nonlinear control law to stabilize the rolling motion of missiles. Based on the analysis of rolling moment characteristics due to pitch/yaw control cross-coupling, we propose a conjecture that the moment is described by the bilinear form of pitch/yaw acceleration and yaw/pitch control. The conjecture fits a set of wind tunnel test data and leads to a bilinear control law. An important point is that the control law is implemented by using pitch/yaw accelerations and control signals. Simulations show that the new control law stabilizes rolling motions which cannot be stabilized by linear feedback control laws.
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