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US 2006/0217852 A1Published application
Method for determining roll rate gyro bias in an attitude heading reference system
OwnerRicardo Priceinventor
Life of this patent
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Abstract
A method and computer program product for determining the roll rate gyro bias of an attitude and heading reference system from true air speed, heading rate and body accelerations using centripetal force equations.
Claims10
A method for correcting a bias of a roll rate gyro utilized in an Attitude and Heading Reference System, said method comprising:
- (a) monitoring the heading rate of an aircraft;
- (b) monitoring at least the lateral and vertical body accelerations of the aircraft;
- (c) monitoring the true airspeed of the aircraft;
- (d) calculating a bank angle from the above using centripetal force equations;
- (e) comparing said calculated bank angle with the bank angle derived from integrating the output of said roll rate gyro;
- and
- (f) when the aircraft is in a low-dynamic state, adjusting said bias so that the bank angle derived from integrating the output of said roll rate gyro converges with the bank angle calculated from the centripetal force equations.
4 more elements
A computer program product for correcting a bias of a roll rate gyro utilized in an Attitude and Heading Reference System, said program product comprising:
- a computer readable storage medium having a computer readable program embodied in said medium, said computer readable program having:
- first computer instructions for monitoring the heading rate of an aircraft;
- second computer instructions for monitoring at least the lateral and vertical body accelerations of the aircraft;
- third computer instructions for monitoring the true airspeed of the aircraft;
- fourth computer instructions for calculating a bank angle from the above using centripetal force equations;
- fifth computer instructions for comparing said calculated bank angle with the bank angle derived from integrating the output of said roll rate gyro;
- and
- sixth computer instructions for, when the aircraft is in a low-dynamic state, adjusting said bias so that the bank angle derived from integrating the output of said roll rate gyro converges with the bank angle calculated from the centripetal force equations.
5 more elements
Dependencies are inferred from the claim text.