| 摘要 |
The performance of a dual platform inertial navigation system of the type wherein each platform is stabilized by two, two degree-of-freedom gyros is monitored by utilizing the redundant axis gyro output of each platform to produce an attitude error indication of the GO/NO GO operating condition of the platform about the redundant axis of the platform. The redundant gyro axes of the two platforms are aligned with two, mutually-perpendicular inertial reference axes and the rate output of each redundant axis gyro is sensed, compared with a computed rate output for the corresponding navigation gyro axis, and integrated to provide an attitude error indication for each platform about the redundant axis for that platform. Signals from the roll and pitch synchros of each platform are compared and the difference signals resolved into two attitude error signals representing the attitude error about each of the two inertial reference axes, so that the two redundant axis error signals may be logically compared with the two attitude error signals derived from the synchros to provide a GO/NO GO fault warning signal for each platform.
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