The main objective of the study is to assess the effects of incorporating higher order dynamics such as rotor and inflow dynamics when designing a flight control system to satisfy handling qualities specifications such as ADS-33C. The control methodologies examined are Linear Quadratic Gaussian (LQG), Eigenstructure Assignment (EA), and Hinfinite. The UH-60 in hover is used as a test case to which a representative subset of the ADS-33C requirements, for a Rate Command Attitude Hold response type, is applied. The results indicate that acceptable controllers can be designed using EA with a rigid body model of the helicopter; however the control activity is high and the controller is not robust. An Hinfinite design requires the modeling of higher order dynamics; the resulting controller is higher order but more robust, and the control activity is lower. It was not possible to determine a suitable LQG based controller that would satisfy all the requirements.
Effects of higher order dynamics on helicopter flight control law design
Einfluß der Dynamik höherer Ordnung auf die Helikopter-Flugregelungsauslegung
Journal of the American Helicopter Society ; 39 , 3 ; 12-23
1994
12 Seiten, 17 Bilder, 23 Quellen
Aufsatz (Zeitschrift)
Englisch
Implementierung , Hubschrauber , Aerodynamik , Flugregelung , Stabilität von Regelungssystemen , Blockdiagramm , Rechenmodell , Flugverhalten , Bewertung , Betriebsparameter , Auslegung (Dimension) , quadratische Funktion , lineare Gleichung , Test (Prüfung) , Matrix (Zahlenschema) , Frequenzbereich
Effects of Higher Order Dynamics on Helicopter Flight Control Law Design
Online Contents | 1994
|TIBKAT | 1975
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