Reduced error sensor fault detection
AssigneeHamilton Sundstrand Corporation
InventorsGary M. McBrien, James A. Gosse
Life of this patent
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Abstract
Disclosed is an aircraft sensor fault detection system. The system includes a sensor system having a sensing apparatus to measure a parameter of an environment and a measurement circuit coupled to the sensing apparatus. The system includes a source of alternating current connected to the sensor system. The system further includes an alternating current measurement system that measures alternating current passing through the sensor system and indicates an error when a threshold based on a change in impedance of the sensing apparatus is exceeded.
Claims20
An aircraft sensor fault detection system, the system comprising:
- a sensor system including a sensing apparatus to measure a parameter of an environment and a measurement circuit coupled to the sensing apparatus;
- a first source of alternating current connected to a first conductor of the sensor system;
- a second source of alternating current connected to a second conductor of the sensor system, the second source of alternating current being 180 degrees out of phase with the first source of alternating current;
- and
- an alternating current measurement system arranged to measure alternating current from the first source and the second source passing through the sensor system, the alternating current being changed by a change in impedance of the first conductor or the second conductor, and to indicate an error based on the change in impedance, indicated by the alternating current, exceeding a threshold.
An aircraft sensor fault detection system, the system comprising:
- a sensor system including a thermocouple to measure a temperature of an environment and a measurement circuit coupled to the thermocouple to measure a direct voltage generated by the thermocouple;
- a first source of alternating current connected to a first conductor of the sensor system;
- a second source, 180 degrees out of phase with the first source, connected to a second conductor of the sensor system;
- and
- an alternating current measurement system arranged to measure alternating current from the first source and the second source passing through the sensor system as a rectified and smoothed direct current isolated from the direct voltage generated by the thermocouple, and to indicate an error when a threshold based on a change in impedance of the sensor system is exceeded.
A method of detecting a fault in an aircraft sensor system, the method comprising:
- driving an alternating current through a sensing system including a sensing apparatus from a first source connected to a first conductor of the sensing apparatus and from a second source, 180 degrees out of phase with the first source, connected to a second conductor of the sensing apparatus, the sensing apparatus measuring a parameter of an environment and a measurement circuit coupled to the sensing apparatus;
- separating a direct current associated with the sensing system from the alternating current;
- rectifying the alternating current;
- comparing a feature of the rectified alternating current with a predetermined threshold based on the alternating current;
- outputting an error based on the comparison;
- and
- operating an aircraft according to the error.
Dependencies are inferred from the claim text.