A multiple input-multiple output flight control design on the KC-135 aircraft is completed using Quantitative Feedback Theory (QFT). The three degrees-of-freedom model for the lateral mode is reduced to a two degrees-of-freedom model. From this model a robust controller is developed to perform two maneuvers over a wide range of the aircraft flight envelope. The three degrees-of-freedom for the longitudinal mode is then used to develop a robust controller to perform one maneuver. The first and second body bending modes are then added to remove the rigid bosy constraint and a robust control is developed for the non-rigid aircraft. The robust controllers developed for the lateral and longitudinal modes are simulated over a large range of the aircraft's flight envelope. The conclusion drawn from the research is that this method is very effective in designing multiple input-multiple output systems with plant uncertainty.
Design of Robust Controllers for a Multiple Input-Multiple Output Control System with Uncertain Parameters Application to the Lateral and Longitudinal Modes of the KC-135 Transport Aircraft
1984
380 pages
Report
Keine Angabe
Englisch
Avionics , Attitude control systems , Input output models , Tanker aircraft , Flight maneuvers , Bending , Computer aided design , Pitch(Motion) , Roll , Multiple operation , Mathematical models , Control theory , Flight envelope , Flight control systems , Feedback , Degrees of freedom , Multivariate analysis , Theses , Robust controllers , Multivariate control , QFT(Quantitative Feedback Theory) , KC-135 aircraft , C-135 aircraft , Nonrigid aircraft
A MULTIPLE-INPUT MULTIPLE-OUTPUT SMOOTHING TECHNIQUE: THEORY AND APPLICATION TO AIRCRAFT DATA
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