Fault detection based on brake torque and temperature
A fault detection and brake technology, applied in the direction of brakes, brake components, aircraft braking arrangements, etc., can solve problems such as undetectable deviations, faults that cannot be detected by monitoring systems, etc.
Active Publication Date: 2022-01-28
AIRBUS OPERATIONS LTD
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Problems solved by technology
Where such active controls are operating to alter the behavior of a given aircraft component, any deviation from the normal behavior of the component may not be detectable based on sensor data pertaining to the performance of that component because the active control system can Automatically compensates for deviations
Therefore, as a result of the introduction of active controls, various faults may not be detected by current monitoring systems
Method used
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Embodiment Construction
[0030] Many aircraft, particularly those of airlines, are equipped with one or more monitoring systems for monitoring the condition and / or performance of aircraft components. An example of such a monitoring system is a Brake Temperature Monitoring System (BTMS) for measuring and monitoring the temperature of wheel brakes. The BTMS includes a temperature sensor for each wheel brake of each set of wheels that can be braked. Each of the temperature sensors communicates with a central computer, usually located in the avionics bay of the aircraft. The BTMS computer monitors the measured brake temperature and may generate an alarm in certain circumstances, for example if the brakes are too hot for the aircraft to take off. Similarly, a tire pressure monitoring system may include a pressure sensor for each tire that provides data to a central computer. Other monitoring systems such as brake wear pins rely on visual inspection of sensors or measuring equipment by ground personnel. ...
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The present invention relates to fault detection based on brake torque and temperature. A fault detection system for detecting faults associated with an aircraft braking system including brakes. The detection system includes a controller configured to receive brake demand information, torque information, wear information, wheel speed information, and brake temperature information. The controller calculates the expected maximum temperature of the brakes based on the torque information, wear information and wheel speed information; determines whether there is a significant temperature difference between the expected maximum temperature and the brake temperature information; determines whether there is significant torque based on the brake demand information and the torque information related differences. The controller generates a first alarm if there is a significant torque related difference and no significant temperature difference; a second alarm if there is a significant temperature difference and no significant torque related difference; and if there is a significant temperature difference difference and there is a significant torque-related difference, a third alarm is generated.
Description
technical field [0001] The invention relates to a fault detection system for detecting a fault related to an aircraft braking system comprising at least one brake and a method for detecting and diagnosing a fault related to an aircraft braking system. Background technique [0002] Modern aircraft, especially passenger aircraft, have various sensors for monitoring the condition and performance of aircraft components including brakes, wheels and tires. Typically, each monitored parameter (eg, brake temperature, tire pressure, wheel speed, etc.) may be measured by a separate sensor, and the sensor data provided to a dedicated monitoring system for that parameter. An associated monitoring system can generate an alarm if the monitored parameter deviates from the normal operating range. [0003] Deviation of a single parameter from normal does not provide much information about the root cause of the deviation. Therefore, in response to such an alert, maintenance personnel must c...
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IPC IPC(8): B60T17/22B64C25/42
CPCB60T17/22B64C25/42B60T8/885B60T2270/406B60T8/1703B64F5/60B60T17/221B64D2045/0085G07C5/006G07C5/0808B64C25/44G07C5/0816
Inventor 安德鲁·比尔戴维·克拉克
Owner AIRBUS OPERATIONS LTD