A Practical Optimization Design Procedure for Stability Augmentation Systems.

摘要

A systematic procedure for the design of aircraft stability augmentation systems is presented. The key features of this procedure are the selection of essential feedbacks from an examination of several handling quality metrics and the use of parameter optimization techniques to determine the numerical values of the SAS parameters. The optimization problem is structured to include both manual and SAS feedbacks. The cost function includes pilot tracking errors and SAS control deflections. A method of selecting the relative weighting is presented. The feasibility of this procedure is demonstrated by applying it to the longitudinal axis of the F-4aircraft. Three widely different flight conditions are selected. For all three,the same SAS form (pitch rate and normal acceleration feedbacks to the elevator),the identical problem formulation,and the same method of selecting the cost function weights are used. The resulting systems are judged quite satisfactory and well within the short-period requirements of the current military handling qualities specification. (Author)