A Method for obtaining reduced-order control laws for high-order systems using optimization techniques
Vivek Mukhopadhyay, Jerry R. Newsom, Irving Abel, Langley Research Center, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1981 - Mathematics - 64 pages
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25th-order plant accelerometer actuator dynamics aerodynamic lag terms aeroelastic APPENDIX augmented components of partitioned conjugate gradient algorithm control input control law designed control surface deflection controller design coordinate vector covariance matrix dB at 60 defined in equations design dynamic pressure dynamic-pressure root locus dynamics matrix equa equations B7 estimation error feedback control law flexible modes flutter dynamic pressure flutter-suppression control law fourth-order control law free design full-order control law full-state feedback gain gust velocity initial values input-noise adjustment procedure Kalman estimator gain Lagrange multiplier LQG solution Lyapunov equation NASA noise vector nonlinear programing Nyquist diagrams obtained Optimal Control optimal full-state feedback output matrix partitioned matrix phase and gain plant noise Point Phase margin presented in figure rad/sec Gain margin reduced-order control law reoptimization residualization methods root-mean-square s-plane state-space steady-state responses transfer function truncation and residualization truncation method white noise