Abstract: An aircraft brake temperature control system (BTCS) 100 for controlling a temperature of a brake 220 of a landing gear 201 of the aircraft 200. The BTCS 100 includes a controller 110 configured to cause at least one fluid moving device 230, 231, 232 to drive a flow of fluid onto the brake 220, selectively in one of a plurality of modes, to control the temperature of the brake 220. The BTCS 100 may be incorporated into an aircraft system 1000 with at least one fluid moving device 230, 231, 232, wherein the aircraft system is on an aircraft 200.

Abstract: A sensor network for use in an aircraft, including a plurality of wireless nodes. A first wireless node of the plurality of wireless nodes is arranged to communicate with at least one other wireless node of the plurality of wireless nodes. The communication is via a secure communications channel and is on the basis of a control message received at the first wireless node. The at least one other wireless node is arranged to perform an operation on the basis of the control message.

Abstract: A temperature sensing device to sense aircraft wheel brake temperature is disclosed including a sensing device substrate; and one or more package layers attached to the sensing device substrate, wherein: the sensing device substrate carries one or more electronic components for sensing temperature. Also disclosed is a wireless relay device to wirelessly transmit an interrogation signal to a temperature sensing device and wirelessly receive an output signal from the temperature sensing device, the temperature sensing device to sense aircraft wheel brake temperature, the wireless relay device comprising: a relay substrate; and one or more package layers attached to the relay substrate, wherein: the relay substrate carries one or more electronic components of the wireless relay device. Also disclosed is a method of manufacturing a temperature sensing device to sense aircraft wheel brake temperature.

Abstract: A brake disc for an aircraft wheel brake including: a temperature sensing device comprising a surface acoustic wave (SAW) sensor element and a sensor antenna, wherein the temperature sensing device is attached to the brake disc by means of a ceramic adhesive and one or more ceramic bolts. A method of attaching a temperature sensing device to a brake disc of an aircraft wheel brake.

Abstract: A holder for a wireless relay device is disclosed including a rigid hollow arm member to be received in a groove in a torque tube spline of an aircraft wheel brake; and a support member to support the wireless relay device, the support member mechanically coupled to the rigid hollow arm member towards a first end of the rigid hollow arm member, wherein: the rigid hollow arm member provides a conduit for a communications cable to couple to the wireless relay device. Also disclosed is an aircraft wheel brake comprising the holder and an aircraft comprising the aircraft wheel brake.

Abstract: A temperature sensing device for sensing aircraft wheel brake temperature, the temperature sensing device including a surface acoustic wave, SAW, sensor element with a resonant frequency within a frequency range between 175 megahertz and 190 megahertz at a predetermined temperature. The temperature sensing system also includes a wireless relay device, a method for sensing temperature of a wheel brake of an aircraft.

Abstract: A cable structure to carry signals to and from a component of a temperature sensing arrangement in an aircraft wheel brake is disclosed including elongate elements including a plurality of cables and/or wires, one or more ceramic spacer layers, a ceramic cover layer and a metallic layer surrounding the one or more ceramic spacer layers and the ceramic cover layer. Also disclosed is an aircraft wheel brake comprising the cable structure and an aircraft comprising the aircraft wheel brake.

Abstract: A temperature sensing device for sensing aircraft wheel brake temperature is disclosed including a sensor antenna electrically coupled to a surface acoustic wave, SAW, sensor element, wherein: the sensor antenna comprises a conductive loop disposed on a surface of a substrate, the conductive loop surrounding an attachment region of the substrate, the attachment region having substantially no conductor material thereon. Also disclosed is a brake disc for an aircraft wheel brake comprising the temperature sensing device, and aircraft comprising the brake disc and a method of manufacturing a temperature sensing device.

Abstract: A temperature sensing device for sensing aircraft wheel brake temperature, the temperature sensing device including: a surface acoustic wave (SAW) sensor element having an interdigital transducer that has electrodes disposed along the surface of a substrate forming a periodic structure. The electrodes having a thickness, in a direction perpendicular to the surface, of between 120 and 190 nanometres.

Abstract: An apparatus for an aircraft having one or more aircraft wheel brakes, and a brake wear sensor configured to measure a wear state of a brake of the one or more aircraft wheel brakes, is disclosed. The apparatus includes a processor configured to determine a wear relationship between a wear state of the brake and a number of use cycles of the brake, determine a predicted wear state of the brake based on the wear relationship; determine a number of future use cycles of the brake based on a predicted condition of the brake, the predicted condition comprising the predicted wear state of the brake; and provide an indication of the determined number of the future use cycles to ground crew and/or a pilot of the aircraft, wherein the number of future use cycles is the number of use cycles for which the brake is allowed to be used, and a use cycle comprises all uses of the brake relating to a flight undertaken by the aircraft.

Abstract: An aircraft brake temperature control system (BTCS) 100 for controlling a temperature of a brake 220 of a landing gear 201 of the aircraft 200. The BTCS 100 includes a controller 110 configured to cause at least one fluid moving device 230, 231, 232 to drive a flow of fluid onto the brake 220, selectively in one of a plurality of modes, to control the temperature of the brake 220. The BTCS 100 may be incorporated into an aircraft system 1000 with at least one fluid moving device 230, 231, 232, wherein the aircraft system is on an aircraft 200.

Abstract: An aircraft brake temperature control system (BTCS) 100 for controlling a temperature of a brake 220 of a landing gear 201 of the aircraft 200. The BTCS 100 includes a controller 110 configured to cause a thermal management system 2000 to regulate the temperature of the brake 220, on the basis of a selection of an objective for regulating the temperature of brake from a plurality of objectives 121, 122 for regulating the temperature of the brake. An aircraft 200 includes the BTCS; and a method 300 controls a temperature of a brake of a landing gear of an aircraft.

Abstract: A brake temperature sensing system for an aircraft including a sensor apparatus and an interrogation apparatus. The sensor apparatus includes a temperature sensor for attachment to a brake disc of an aircraft brake, and a relay for attachment to the brake. The temperature sensor is configured to wirelessly transmit a measurement signal containing information relating to a temperature of the brake disc, responsive to receiving a wireless interrogation signal. The relay is configured to receive an interrogation signal from the interrogation apparatus; wirelessly transmit the interrogation signal to the temperature sensor; receive the wireless measurement signal from the temperature sensor; and transmit the received measurement signal. The interrogation apparatus comprises a controller configured to generate an interrogation signal; and a transceiver configured to transmit the generated interrogation signal to the sensor apparatus; and receive the measurement signal transmitted by the sensor apparatus.

Abstract: An apparatus for reducing brake wear having a brake de-selection function for selectively disabling at least one brake on a vehicle; and a controller. The controller is configured to receive torque information which relates to torque reacted by a brake on the vehicle during a braking event and wheel speed information which relates to a speed of a wheel associated with the brake during the braking event; calculate an energy input into the brake during the braking event, based on the received torque information and the received wheel speed information; determine whether the calculated energy input meets at least one predefined energy input criterion; and activate the brake de-selection function if the calculated energy input meets the at least one predefined energy input criterion.

Abstract: A sensor network for use in an aircraft, including a plurality of wireless nodes. A first wireless node of the plurality of wireless nodes is arranged to communicate with at least one other wireless node of the plurality of wireless nodes. The communication is via a secure communications channel and is on the basis of a control message received at the first wireless node. The at least one other wireless node is arranged to perform an operation on the basis of the control message.

Abstract: An apparatus for reducing brake wear having a brake de-selection function for selectively disabling at least one brake on a vehicle; and a controller. The controller is configured to receive torque information which relates to torque reacted by a brake on the vehicle during a braking event and wheel speed information which relates to a speed of a wheel associated with the brake during the braking event; calculate an energy input into the brake during the braking event, based on the received torque information and the received wheel speed information; determine whether the calculated energy input meets at least one predefined energy input criterion; and activate the brake de-selection function if the calculated energy input meets the at least one predefined energy input criterion.

Abstract: A sensor network for use in an aircraft, including a plurality of wireless nodes. A first wireless node of the plurality of wireless nodes is arranged to communicate with at least one other wireless node of the plurality of wireless nodes. The communication is via a secure communications channel and is on the basis of a control message received at the first wireless node. The at least one other wireless node is arranged to perform an operation on the basis of the control message.

Abstract: A system including a sensor, a computing device and a Wireless Access Point (WAP). The sensor in response to receipt of an initiation signal, via a first communication channel, from a relatively proximal computing device, is arranged to generate and store first security information and to transmit, wirelessly via a second communications channel, a first message comprising information representing at least a part of the first security information. The WAP, which is remote from the sensor is arranged to receive and store the first message. The WAP is arranged to generate second security information and to transmit wirelessly to the computing device, via a third communications channel when the computing device is within range of the WAP, a second message comprising information representing at least a part of the second security information. The sensor is arranged to receive at least the second message via only the first communications channel.

Abstract: A brake temperature sensing system for an aircraft including a sensor apparatus and an interrogation apparatus. The sensor apparatus includes a temperature sensor for attachment to a brake disc of an aircraft brake, and a relay for attachment to the brake. The temperature sensor is configured to wirelessly transmit a measurement signal containing information relating to a temperature of the brake disc, responsive to receiving a wireless interrogation signal. The relay is configured to receive an interrogation signal from the interrogation apparatus; wirelessly transmit the interrogation signal to the temperature sensor; receive the wireless measurement signal from the temperature sensor; and transmit the received measurement signal. The interrogation apparatus comprises a controller configured to generate an interrogation signal; and a transceiver configured to transmit the generated interrogation signal to the sensor apparatus; and receive the measurement signal transmitted by the sensor apparatus.

Abstract: A brake temperature sensing system for an aircraft including a sensor apparatus and an interrogation apparatus. The sensor apparatus includes a temperature sensor for attachment to a brake disc of an aircraft brake, and a relay for attachment to the brake. The temperature sensor is configured to wirelessly transmit a measurement signal containing information relating to a temperature of the brake disc, responsive to receiving a wireless interrogation signal. The relay is configured to receive an interrogation signal from the interrogation apparatus; wirelessly transmit the interrogation signal to the temperature sensor; receive the wireless measurement signal from the temperature sensor; and transmit the received measurement signal. The interrogation apparatus comprises a controller configured to generate an interrogation signal; and a transceiver configured to transmit the generated interrogation signal to the sensor apparatus; and receive the measurement signal transmitted by the sensor apparatus.