Landing gear load sensing apparatus and methods
A sensor carrier for sensing forces acting upon an axle of an aircraft landing gear assembly is disclosed being arranged to fit within the axle and includes an end coupling for fixing to one end of the axle, and a central coupling for fixing to a central portion of the axle where the axle attaches to a main leg of the assembly. The sensor carrier includes a sensor arrangement arranged to detect strain occurring between the end coupling and the central coupling so that in use, the sensor arrangement indicates strain occurring between the end of the axle and the main leg of the aircraft.
1 . A sensor carrier, comprising:
an elongate carrier body configured to be disposed within an axle of an aircraft landing gear assembly;
a first coupling for coupling the elongate carrier body to a first location of the axle;
a second coupling for coupling the elongate carrier body to a second location of the axle axially spaced apart from the first location of the axle; and
at least one sensor disposed on the elongate carrier body and configured to detect strain between the first coupling and the second coupling,
wherein said at least one sensor is configured such that when the sensor carrier is within the axle and coupled to the axle by the first and second couplings respectively, strain occurring between the first location and the second location of the axle is detected by said at least one sensor.
2 . The sensor carrier of claim 1 , wherein said at least one sensor comprises a plurality of sensors arranged within the sensor carrier between the first coupling and second coupling.
3 . The sensor carrier of claim 1 , further comprising:
a third coupling for coupling the sensor carrier to a third location of the axle axially spaced apart from the first and second locations; and
at least one further sensor arranged to detect strain occurring between the second location and the third location of the axle,
wherein said at least one further sensor is configured such that when the sensor carrier is coupled to the axle, strain occurring between the second location and the third location of the axle is detected by said at least one further sensor.
4 . The sensor carrier of claim 3 , wherein the first and third locations are disposed in opposite axial directions away from the second coupling.
5 . The sensor carrier of claim 3 , wherein said at least one further sensor comprises a plurality of further sensors arranged within the sensor carrier between the second coupling and the third coupling.
6 . The sensor carrier of claim 1 , wherein the second location of the axle corresponds to a connection between the axle and a landing gear leg.
7 . The sensor carrier of claim 6 , further comprising at least one central sensor disposed within the sensor carrier proximate to the second coupling, said at least one central sensor being arranged to cooperate with said at least one sensor.
8 . The sensor carrier of claim 7 , wherein said at least one central sensor comprises a plurality of central sensors arranged within the sensor carrier proximate the second coupling.
9 . The sensor carrier of claim 1 , wherein the strain detected by the sensor carrier includes torsional strain relating to the braking action of wheels attached to the axle.
10 . The sensor carrier of claim 1 , wherein the strain detected by the sensor carrier includes vertical strain caused by forces acting on the axle during landing and take-off of the aircraft.
11 . The sensor carrier of claim 1 , further comprising a plurality of further sensors arranged within the sensor carrier which, together with said at least one sensor, are arranged (a) to detect strain between the first coupling and the second coupling, (b) to detect torsional strain relating to the braking action of wheels attached to the axle and (c) to detect vertical strain caused by forces acting on the axle during landing and/or take-off of the aircraft.
12 . The sensor carrier of claim 1 , wherein the sensor carrier also includes at least one of: a wheel speed tachometer; a brake cooling fan motor; and a tire pressure indicating system.
13 . The sensor carrier of claim 1 , wherein the sensor carrier is made of composite material.
14 . A landing gear assembly comprising the sensor carrier of claim 1 .
15 . An aircraft comprising the landing gear assembly according to claim 14 .
16 . A method for determining forces acting on an axle of an aircraft landing gear assembly, the method comprising:
an elongate carrier body configured to be disposed within the axle of an aircraft landing gear assembly;
sensing strain occurring at a sensor pack disposed on the elongate carrier body,
the sensor pack being coupled between two axially spaced apart locations of the axle,
wherein the sensed strain at the sensor pack provides an indication of strain occurring between the two axially spaced apart locations of the axle.
17 . The method of claim 16 , including a step of a processor using an input representative of the sensed strain at the sensor pack to provide an output of a braking torque and/or vertical loads at the axle, with the use of a relationship that relates the strains directly sustained by structure of the sensor pack, and sensed by the sensors of the sensor pack, to said braking torque and/or vertical loads.
18 . The method of claim 17 , wherein the inputs used by the processor include inputs from at least three strain sensors distributed internally within the sensor pack and mounted on structure of the sensor pack to measure strain directly sustained by said structure of the sensor pack.
19 . A method for replacing a sensor pack, the sensor pack being in form of an elongate carrier body disposed within an axle of an aircraft landing gear assembly, wherein the sensor pack is coupled between two axially spaced apart locations of the axle, the method comprising:
decoupling the sensor pack from the two axially spaced apart locations of the axle;
removing the sensor pack from the axle;
inserting a replacement sensor pack in the axle; and
coupling the replacement sensor pack to the two axially spaced apart locations of the axle.
20 . The method of claim 19 , further comprising the step of, prior to step of inserting, calibrating the replacement sensor pack.