SYSTEMS AND METHODS FOR ATTITUDE FAULT DETECTION IN ONE OR MORE INERTIAL MEASUREMENT UNITS
First Claim
1. An avionics system comprising:
- at least one inertial measurement unit configured to produce a calculated pitch solution, a calculated roll solution, or both;
at least one monitor coupled to the at least one inertial measurement unit and configured to produce an estimated pitch solution, an estimated roll solution, or both,wherein the at least one monitor produces the estimated pitch solution by adding angle of attack data to flight path angle data, andwherein the at least one monitor produces the estimated roll solution by calculating a double-differencing solution using data from transversely mounted dual global navigation satellite system antennas;
a comparator, wherein the comparator determines the difference between the calculated pitch solution and the estimated pitch solution, the difference between the calculated roll solution and the estimated roll solution, or both; and
at least one display device communicatively coupled to the comparator;
wherein the at least one display device receives a warning message from the comparator when the difference between the calculated pitch solution and the estimated pitch solution is greater than a pitch threshold, or when the difference between the calculated roll solution and the estimated roll solution is greater than a roll threshold, or both.
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Abstract
Systems and methods for attitude fault detection in an inertial measurement unit (IMU) are disclosed. In one embodiment, an avionics system comprises: an IMU configured to produce a calculated pitch solution, a calculated roll solution, or both; a monitor coupled to the IMU and configured to produce an estimated pitch solution, an estimated roll solution, or both; a comparator, wherein the comparator determines the difference between the calculated pitch solution and the estimated pitch solution, the difference between the calculated roll solution and the estimated roll solution, or both; and a display device communicatively coupled to the comparator; wherein the display device receives a warning message from the comparator when the difference between the calculated pitch solution and the estimated pitch solution is greater than a pitch threshold, or when the difference between the calculated roll solution and the estimated roll solution is greater than a roll threshold, or both.
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Citations
20 Claims
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1. An avionics system comprising:
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at least one inertial measurement unit configured to produce a calculated pitch solution, a calculated roll solution, or both; at least one monitor coupled to the at least one inertial measurement unit and configured to produce an estimated pitch solution, an estimated roll solution, or both, wherein the at least one monitor produces the estimated pitch solution by adding angle of attack data to flight path angle data, and wherein the at least one monitor produces the estimated roll solution by calculating a double-differencing solution using data from transversely mounted dual global navigation satellite system antennas; a comparator, wherein the comparator determines the difference between the calculated pitch solution and the estimated pitch solution, the difference between the calculated roll solution and the estimated roll solution, or both; and at least one display device communicatively coupled to the comparator; wherein the at least one display device receives a warning message from the comparator when the difference between the calculated pitch solution and the estimated pitch solution is greater than a pitch threshold, or when the difference between the calculated roll solution and the estimated roll solution is greater than a roll threshold, or both. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A non-transitory computer-readable medium having computer-executable instructions stored thereon which, when executed by one or more processors, cause the one or more processors to perform the steps of:
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producing a pitch estimate solution by adding angle of attack data to flight path angle data of an aircraft; and producing a roll estimate solution by calculating a double-differencing solution using data from transversely mounted dual global navigation satellite system antennas. - View Dependent Claims (11, 12, 13, 14, 15)
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16. A method for attitude fault detection in one or more inertial measurement units, comprising:
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determining an estimated pitch solution, an estimated roll solution, or both, wherein the estimated pitch solution is determined by adding angle of attack data to flight path angle data and wherein the estimated roll solution is determined by calculating a double-differencing solution using data from transversely mounted dual global navigation satellite system antennas; and determining a difference between the estimated pitch solution and a calculated pitch solution, the estimated roll solution and a calculated roll solution, or both; and sending a warning message to a display device when the difference between the estimated pitch solution and the calculated pitch solution is greater than a pitch threshold, the difference between the estimated roll solution and the calculated roll solution is greater than a roll threshold, or both. - View Dependent Claims (17, 18, 19, 20)
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Specification