Application and flight test of linearizing transformations using measurement feedback to the nonlinear control problem
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A NEW APPROACH TO THE NONLINEAR CONTROL PROBLEM
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accelerometer output aerodynamic models aircraft altitude commanded altitude rate angle of attack angle-of-attack command apparent linear system approach body axis command equation commanded incremental load commanded roll Control Inverse Transformation control law computer control loop deg/sec derived eliminate Euler angles excess-thrust windup turn f>com flight data flight system flight-test data Flight-Test Results flight-test trajectory control ft/sec FTTC functions guidance law hcom incremental load factor inertial integral inverse linearizing transformation Inverse Transformation Equations kinematic acceleration level acceleration linear control law linearizing transformation equation Mach Number Command measurement equation measurement feedback Meyer noise nonlinear system Operator terminal outer-loop control Pcom Pitch Control PLAcom pseudocontrol pushover-pullup maneuver Qcom ramp RAV system real nonlinear control roll control roll ratcheting roll rate shown in equation shown in figure simulated maneuver techniques throttle command thrust model time-scale separation tracking trajectory control problem vector Vref W-map WT-map z-body