Testing and evaluation of a stability augmentation system for aircraft flight control were performed. The flutter suppression system and synthesis conducted on a scale model of a supersonic wing for a transport aircraft are discussed. Mechanization and testing of the leading and trailing edge surface actuation systems are described. The ride control system analyses for a 375,000 pound gross weight B-52E aircraft are presented. Analyses of the B-52E aircraft maneuver load control system are included. (Author)


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    Title :

    Analysis and Testing of Aeroelastic Model Stability Augmentation Systems


    Contributors:
    F. D. Sevart (author) / S. M. Patel (author)

    Publication date :

    1973


    Size :

    167 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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