The report presents the design of a helicopter stability and control augmentation system using optimal control techniques. The helicopter used as an example was the Sikorsky H-53, but the design procedure is applicable to other helicopters as well. Only the longitudinal dynamics are considered. A technique is described for the design of multivariable feedback controllers based upon results in optimal control theory. For a specified performance index the feedback controller is obtained by solving the matrix Riccati equation. A model is used in the forward controller such that the response of the model to pilot inputs approximates the desired helicopter response. A fixed gain controller is obtained which may be used over the entire helicopter flight envelope. The results show that optimal control theory can be used to design a helicopter stability and control augmentation system. Responses obtained may be classified as those which are desirable and yield good handling qualities. (Author)
Design of a Helicopter Stability and Control Augmentation System Using Optimal Control Theory
1971
103 pages
Report
Keine Angabe
Englisch
Aircraft , Helicopters , Flight control systems , Mathematical models , Airplane models , Helicopter rotors , Rotor blades(Rotary wings) , Stabilization systems , Feedback , Hovering , Optimization , Theses , Control theory , H-53 aircraft , Closed loop control systems , Computerized simulation , Computer aided design
Synthesis design method of helicopter stability and control augmentation system
British Library Online Contents | 1997
|Light helicopter stability augmentation system
Engineering Index Backfile | 1963
|