Results are presented for the first flight demonstration test of a strapdown laser inertial navigation system in a helicopter environment. It is noted that acceptable navigation accuracies were obtained with system alignment times as short as 5 min or less, and that the use of all four available sensors in the navigation algorithm did not significantly improve performance over that achievable by means of only three orthogonal sensors. Failure detection by means of the parity residual from four axes proved successful for failure levels far below the noise threshold of flight control sensing requirements. Summing the gyro parity residual for a period of 13-20 min can yield step-shifted laser gyro sensor bias error detection comparable to the gyro random shift specification.


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    Titel :

    Performance of a Strapdown Ring Laser Gyro Tetrad Inertial Navigation System in a helicopter flight environment


    Beteiligte:
    Carestia, R. A. (Autor:in) / Hruby, R. J. (Autor:in) / Bjorkman, W. S. (Autor:in)

    Kongress:

    National Aerospace Meeting ; 1982 ; Moffett Field, CA


    Erscheinungsdatum :

    01.01.1982


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch