This paper presents the mathematical development and flight test results of an angle of attack estimation system based on inertial navigation system inputs. The estimator uses these inputs to determine the coefficient of lift required at any instant inflight. Angle of attack is then modeled through a regression analysis based on coefficient of lift, altitude and Mach. Overall correlation of the estimator as tested was generally within 0.5 degrees through 17 degrees angle of attack on an F-15A aircraft. A robustness analysis indicates that the system can be used adequately in maneuvering flight.


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    Title :

    Angle of attack estimation using an inertial reference platform


    Contributors:

    Conference:

    AIAA Atmospheric Flight Mechanics Conference ; 1988 ; Minneapolis, MN, United States


    Publication date :

    1988-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Angle of attack estimation using an inertial reference platform

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