Aircraft landing gear assembly
AssigneesSafran Landing Systems UK LTD, Safran Landing Systems
InventorsNeil Price, Marie Coq
Life of this patent
Estimating the term…
Abstract
An aircraft landing gear assembly comprising: an axle having an axis, a wheel rotatably mounted on the axle to rotate about the axis, a brake arranged to selectively exert a braking torque on the wheel about the axis, a brake anchor structure having a substantially fixed position relative to the axle, a brake reaction linkage that mechanically couples the brake to the brake anchor structure, and a sensor comprising a sensor element arranged to detect a change in one or more physical properties of a component of the brake reaction linkage in order to determine a stress in the component due to the braking torque, wherein the sensor element does not contact the component.
Claims17
An aircraft landing gear assembly comprising:
- an axle having an axis;
- a wheel rotatably mounted on the axle to rotate about the axis;
- a brake arranged to selectively exert a braking torque on the wheel about the axis;
- a brake anchor structure comprising a first structural component of the aircraft landing gear assembly which is arranged so as to have a substantially fixed position relative to the axle;
- a brake reaction linkage comprising one or more second structural components of the aircraft landing gear assembly that mechanically couple the brake to the brake anchor structure such that the one or more second structural components react the braking torque;
- and
- a sensor comprising a sensor element arranged and configured to detect a change in one or more physical properties of at least one of the second structural components of the brake reaction linkage in order to determine a stress in the at least one of the second structural components due to the braking torque, wherein the sensor element does not contact the component, and wherein the sensor element is arranged and configured to directly observe the at least one of the second structural components of the brake reaction linkage in order to detect the change in one or more physical properties of the at least one of the second structural components of the brake reaction linkage.
An aircraft including one or more landing gear assemblies, each landing gear assembly comprising:
- an axle having an axis,
- a wheel rotatably mounted on the axle to rotate about the axis,
- a brake arranged to selectively exert a braking torque on the wheel about the axis,
- a brake anchor structure comprising a first structural component of the aircraft landing gear assembly which is arranged so as to have a substantially fixed position relative to the axle,
- a brake reaction linkage comprising one or more second structural components of the aircraft landing gear assembly that mechanically couple the brake to the brake anchor structure such that the one or more second structural components react the braking torque, and
- a sensor comprising a sensor element arranged and configured to detect a change in one or more physical properties of at least one of the second structural components of the brake reaction linkage in order to determine a stress in the at least one of the second structural components due to the braking torque, wherein the sensor element does not contact the component, and wherein the sensor element is arranged and configured to directly observe the at least one of the second structural components of the brake reaction linkage in order to detect the change in one or more physical properties of the at least one of the second structural components of the brake reaction linkage.
Dependencies are inferred from the claim text.