## On the design of a high-gain saturating control system for use as an adaptive autopilot |

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adaptive autopilot aerodynamic gain aircraft poles airframe analog computer assumed block diagram chatter amplitude control closed-loop poles closed-loop transfer function compensating loop considered constant control-surface deflection damping ratio derived determined dither equation equivalent gain equivalent limiter gain equivalent linear system feedback zeros filter Fixed zeros flight envelope function of equivalent heavy dots high-gain saturating control high-gain saturating system input magnitude lags Laplace transform large inputs lead network limit cycle limit level controller loci locus low dynamic pressures low-frequency missile example Moving zeros natural frequency nonlinear normal acceleration Normal accelerometer normal-acceleration autopilot obtained open-loop gain output phase shift presented in sketch reduce the chatter result root root-locus technique saturating control system sec Flight condition shown in sketch signal simulation sine wave sketch g small inputs static margin step input step response step-input magnitude structural load system response unstable WADC worst flight condition zero positions