Strapped down attitude and heading reference system for aircraft

Details Strapped down attitude and heading reference system for aircraft Strapped down attitude and heading reference system for aircraft

1978-05-18

1980-07-15

Eisenzopf, Reinhard J.

Aeronautics and astronautics

Aircraft control

Automatic

33321, 73178R, 73504, 244 79, 244165, 364453, G05D 110

Patent

active

042124433

ABSTRACT:
A set of two two-degrees-of-freedom rate gyroscopes and three linear accelerometers are assembled in a single module adapted to be mounted within a single aircraft electronics control unit, the unit comprising a strapped-down attitude and heading reference system. The module base provides a common keyed support for the two pre-calibrated gyros and three accelerometers in intimate mechanical and thermal association. The two gyros are oriented in the base and the base oriented in the aircraft so that the spin axis of one gyro is oriented parallel to the aircraft Z axis and that of the other gyro parallel to the aircraft Y axis while the gyro pickoffs and torquers (input and output axes, respectively) are rotated or skewed forty-five degrees about the spin axes to positions such that the input and output axes lie along the slant heights of a forty-five degree half angle right circular cone, the axis of which lies along the aircraft X axis. Thus a single module provides greatly simplified rate sensing about the aircraft primary axes with correspondingly simplified fault detection of the rate sensors.

REFERENCES:
patent: 3463909 (1969-08-01), Weiss
patent: 3483746 (1969-12-01), Bers
patent: 3489004 (1970-01-01), Barnhill et al.
patent: 3492465 (1970-01-01), Buscher et al.
patent: 3790766 (1974-02-01), Brown
patent: 4106094 (1978-08-01), Land
patent: 4125017 (1978-11-01), Dhuyvetter et al.

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