Aircraft brake assembly sensing device
The present invention relates to a sensing device for monitoring aircraft brake assemblies, in particular the sensing device is for monitoring wear and/or temperature of the aircraft brake assembly. The device comprises a housing rigidly connected to the chassis of the aircraft brake assembly, wherein the housing comprises a displacement sensor. The device further comprises a pin extending through the housing with a first end configured to move with a pressure plate of the aircraft brake assembly such that, in use, the pin is configured to move relative to the housing in a longitudinal direction of the pin. The pin comprises a detectable element positioned within the housing, and the displacement sensor is configured to monitor the position of the detectable element within the housing.
1 . A sensing device for monitoring an aircraft brake assembly, the sensing device comprising:
a housing configured to be rigidly connected to the chassis of the aircraft brake assembly, the housing comprising a displacement sensor; and
a pin extending through the housing and comprising a first end configured to move with a pressure plate of the aircraft brake assembly such that, in use, the pin is configured to move relative to the housing in a longitudinal direction of the pin;
wherein the pin comprises a detectable element portion positioned within the housing and comprising a first end and a second end and wherein the displacement sensor is configured to monitor the position of the detectable element portion within the housing,
wherein the pin comprises a temperature sensing portion located between the first end of the detectable element portion and the pressure plate and configured to monitor a temperature of the pressure plate, and
wherein the pin comprises a visual wear detection portion located proximate the second end of the detectable element portion and extending from the housing in a direction away from the pressure plate and configured to indicate wear of brake discs in the aircraft brake assembly.
2 . The sensing device of claim 1 , wherein the housing comprises a transmitter configured to receive sensor data from the displacement sensor, and configured to transmit the sensor data to a central receiver.
3 . The sensing device of claim 1 , wherein the sensing surface of the temperature sensing portion is configured to be in direct contact with the pressure plate.
4 . The sensing device of claim 2 , wherein the transmitter is configured to receive sensor data from the temperature sensor, and configured to transmit the sensor data to a central receiver.
5 . The sensing device of claim 4 , wherein the transmitter is connected to the displacement sensor and to the temperature sensor by a wired connection.
6 . The sensing device of claim 1 , wherein the displacement sensor comprises a linear variable differential transformer (LVDT) sensor.
7 . The sensing device of claim 1 , wherein the first end of the pin is configured to be rigidly connected to the pressure plate.
8 . The sensing device of claim 1 wherein the first end of the pin is biased towards the pressure plate, optionally using a spring.
9 . The sensing device of claim 1 , comprising a protective shield configured to extend from the housing to the pressure plate to enclose a portion of the pin extending from the housing to the pressure plate, wherein the protective shield is configured to move with the pressure plate so that, in use, the protective shield moves relative to the housing.
10 . The sensing device of claim 9 , wherein the protective shield is rigidly connected to the pressure plate proximate the first end of the pin, and/or is rigidly connected to the pin at a point along the length of the pin.
11 . An aircraft brake assembly comprising:
a plurality of brake discs including one or more stators and one or more rotors;
a pressure plate located at a first side of the brake assembly;
a chassis comprising one or more pistons configured to actuate the pressure plate to urge the plurality of brake discs together in use; and
the sensing device according to claim 1 , wherein the housing is rigidly connected to the chassis of the aircraft brake assembly, and wherein the pin is configured to move with one of the first or second pressure plates.
12 . The sensing device of claim 1 , wherein the detectable element portion, the temperature sensing portion, and the visual wear detection portion are joined together to form the pin.
13 . The sensing device of claim 1 , wherein the detectable element portion, the temperature sensing portion, and the visual wear detection portion form one integral pin.
14 . A method of monitoring an aircraft brake assembly comprising:
providing a housing rigidly attached to the chassis of an aircraft brake assembly, wherein the housing comprises a displacement sensor;
providing a pin which extends through the housing to a first end which moves with a pressure plate of the aircraft brake assembly so that the pin moves relative to the housing; wherein the pin comprises a detectable element portion positioned within the housing and comprising a first end and a second end, wherein the pin comprises a temperature sensing portion located between the first end of the detectable element portion and the pressure plate, and wherein the pin comprises a visual wear detection portion located proximate the second end of the detectable element portion and extending from the housing in a direction away from the pressure plate;
monitoring a position of the detectable element within the housing using the displacement sensor;
monitoring a temperature of the pressure plate via the temperature sensing portion; and
monitoring wear of brake discs in the aircraft brake assembly via the visual wear detection portion.
15 . A sensing device for monitoring an aircraft brake assembly, the sensing device comprising:
a housing configured to be rigidly connected to the chassis of the aircraft brake assembly, the housing comprising a transmitter; and
a pin extending through the housing and comprising a first end configured to contact a pressure plate of the aircraft, wherein in use the pin is configured to move with the pressure plate relative to the housing in a longitudinal direction of the pin;
wherein the pin comprises a detectable element portion positioned within the housing and comprising a first end and a second end and wherein the displacement sensor is configured to monitor the position of the detectable element portion within the housing,
wherein the pin comprises a temperature sensor portion located between the first end of the detectable element portion and the pressure plate and configured to monitor a temperature of the pressure plate and wherein the transmitter is configured to receive sensor data from the temperature sensor via a wired connection and to transmit the sensor data to a receiver external to the housing, and
wherein the pin comprises a visual wear detection portion located proximate the second end of the detectable element portion and extending from the housing in a direction away from the pressure plate and configured to indicate wear of brake discs in the aircraft brake assembly.