A hybrid strapdown inertial navigation system intended for use on spin stabilized flight test vehicles is described. The configuration of the navigator which is briefly described consists of three floated rate integrating gyros, one of which is used in conjunction with the gimbal with the remaining two operated in a rate gyro mode. Outputs from the two strapdown gyros and three accelerometers are digitized and processed by a high performance computer. The navigation algorithms utilize a direction cosine matrix formulation for the attitude computation implemented in the digital computer. The implementation of this algorithm for the single gimbal configuration is described. An accuracy model and results for a reentry vehicle flight test trajectory are presented. The flight test performance from launch to reentry is presented. (ERA citation 06:002725)


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    Title :

    Single Gimbal/Strapdown Inertial Navigation System for Use on Spin Stabilized Flight Test Vehicles


    Contributors:
    A. C. Watts (author) / R. D. Andreas (author)

    Publication date :

    1980


    Size :

    7 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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