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.


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    Titel :

    Analysis and testing of aeroelastic model stability augmentation systems


    Beteiligte:
    Sevart, F. D. (Autor:in) / Patel, S. M. (Autor:in)

    Erscheinungsdatum :

    15.10.1973


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



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