Document Type and Number:
Japanese Patent JPS4857399
Kind Code:
A
Abstract:
A system and method for mounting an inertial instrument, such as a reference gyro, an accelerometer triad, or an inertial platform in an aircraft so that the instrument can be tested and calibrated on board the aircraft in its final mounting position without the necessity of test flying the aircraft for such calibration purposes. The inertial instrument is mounted for rotation about an axis angularly displaced with respect to reference axes of the aircraft so that the attitude of the instrument with respect to the reference axes of the aircraft can be changed by rotating the instrument about its mounting axis. The degree of angular movement of the instrument is detected and a theoretical output for the instrument is calculated by an onboard computer. This calculated output is then compared by the computer to the actual instrument output signal. The difference between the calculated signal and the actual signal can then be used to determine whether the instrument is suitable for use on the aircraft. In addition, the difference between the calculated signal and the actual output signal from the instrument can be used to calibrate the instrument and provide a correction signal thereto during normal operation of the instrument.
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Application Number:
JP11041872A
Publication Date:
August 11, 1973
Filing Date:
November 06, 1972
Export Citation:
International Classes:
B64F5/00; G01C21/16; G01C25/00; (IPC1-7): G01C25/00