This paper presents a summary of results obtained to date in an ongoing cooperative research program between NASA and the U.S. Navy to develop design criteria for high-angle-of-attack nose- down pitch control for combat aircraft. A fundamental design consideration for aircraft incorporating relaxed static stability in pitch is the level of stability which achieves a proper balance between high- speed performance considerations and low-speed requirements for maneuvering at high angles of attack. A comprehensive data base of piloted simulation results was generated for parametric variations of critical parameters affecting nose-down control capability. The results showed a strong correlation of pilot rating to the short-term pitch response for nose-down commands applied at high- angle-of-attack conditions. Using these data, candidate design guidelines and flight demonstration requirements were defined. Full- scale flight testing to validate the research methodology and proposed guidelines is in progress, some preliminary results of which are reviewed.


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    Title :

    Status of the Validation of High-Angle-Of-Attack Nose-Down Pitch Control Margin Design Guidelines


    Contributors:

    Publication date :

    1992-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    Status of the validation of high-angle-of-attack nose-down pitch control margin design guidelines

    OGBURN, MARILYN / FOSTER, JOHN / PAHLE, JOSEPH et al. | AIAA | 1993



    Status of the Validation of High-Angle-of-Attack Nose-Down Pitch Control Margin Design Guidelines

    Ogburn, M. / Foster, J. / Pahle, J. et al. | British Library Conference Proceedings | 1993



    Development of High-Angle-of-Attack Nose-Down Pitch Control Margin Design Guidelines for Combat Aircraft

    Ogburn, M. E. / United States / National Aeronautics and Space Administration| Langley Research Center | British Library Conference Proceedings | 1994