초록 ▼

The load on an aircraft component, such as the load on a landing gear leg during braking, is measured with a contactless, all-weather displacement measuring system. The system includes a control unit a controllable microwave emitter of electromagnetic radiation and a microwave detector comprising a

The load on an aircraft component, such as the load on a landing gear leg during braking, is measured with a contactless, all-weather displacement measuring system. The system includes a control unit a controllable microwave emitter of electromagnetic radiation and a microwave detector comprising a plurality of antennae. When the aircraft component is subjected to a load relative movement of the emitter and detector is caused. The detector generates in response to microwave radiation received from the focused beam of radiation emitted by the emitter a signal that is received by a signal processor of the control unit. The signal received by the control unit depends on the relative positions of the emitter and detector. The control unit is arranged to provide an output signal representative of the load sustained by the aircraft component. The system may be used to control braking in dependence on the output signal so as to maximize braking efficiency without overloading the landing gear leg.

대표청구항 ▼

The invention claimed is: 1. An aircraft including apparatus for measuring a current load on a component of the aircraft, the apparatus including a control unit, a controllable emitter of microwave radiation, and a detector able to detect radiation from said emitter, wherein the apparatus is arrang

The invention claimed is: 1. An aircraft including apparatus for measuring a current load on a component of the aircraft, the apparatus including a control unit, a controllable emitter of microwave radiation, and a detector able to detect radiation from said emitter, wherein the apparatus is arranged so that, in use when the aircraft component is subjected to a current load of the type to be measured, relative movement of the detector and the position of the radiation from the emitter in the region of the detector is caused, the detector in use generates in response to microwave radiation received from the emitter a signal that is received by the control unit, the signal being dependent on the relative positions of the detector and the radiation from the emitter in the region of the detector, and the control unit is arranged to provide an output signal dependent on the current load sustained by the aircraft component. 2. An aircraft according to claim 1, wherein the signal that is generated by the detector in response to radiation received from the emitter is dependent on the relative positions of the emitter and detector. 3. An aircraft according to claim 1, wherein one of the emitter and detector is fixed at a first position local to the aircraft component, and the other of the emitter and detector is fixed at a second position remote from the aircraft component. 4. An aircraft according to claim 1, wherein the detector comprises a plurality of spaced apart antennae, which in use generate in response to microwave radiation received from said emitter a signal or signals that in use are received by the control unit, which signal or signals being dependent on the relative positions of the detector and the radiation from the emitter in the region of the detector. 5. An aircraft according to claim 1, wherein the apparatus is so arranged that the signal generated by the detector in dependence on the relative positions of the detector and the radiation from the emitter in the region of the detector depends on the relative levels of intensity of radiation received by the antennae. 6. An aircraft according to claim 1, wherein the controllable emitter emits a focused beam of microwave radiation and each antenna produces a signal that is dependent on the area of each antenna within the beam of radiation. 7. An aircraft according to claim 1, wherein the apparatus is so arranged that the signals from a pair of antennae are used to produce a signal representative of the position of the detector relative to the position of the radiation from the emitter in the region of the detector, in a single given direction. 8. An aircraft according to claim 1, wherein the signal generated by the detector in use in response to microwave radiation received from the emitter is representative of the position of the detector relative to the position of the radiation from the emitter in the region of the detector having two degrees of freedom. 9. An aircraft according to claim 1, wherein the apparatus includes a pair of detectors arranged to enable a torque sustained by the component to be measured. 10. An aircraft according to claim 1, wherein the apparatus is arranged to provide an output that is representative of the load sustained by the component. 11. An aircraft according to claim 1, wherein the aircraft component is a leg of an aircraft landing gear. 12. An aircraft according to claim 11 and further including a load control system, wherein the load control system is arranged to monitor a measurement of the load sustained by the aircraft component, the measurement being ascertained from the output signal from the control unit, and to control a part of the aircraft in dependence on the measurements so monitored. 13. An aircraft according to claim 12, wherein the load control system is a braking control system, and the aircraft component is a leg of an aircraft landing gear, wherein the braking control system is arranged to control the braking in dependence on the loads monitored by the braking control system. 14. An apparatus for measuring a load on a component of an aircraft, the apparatus including a control unit, a controllable emitter of microwave radiation, and a detector able to detect radiation from said emitter, the apparatus being configured to be suitable for use as the apparatus of the aircraft as claimed in claim 1. 15. A method of measuring a load on an aircraft component, the method including the following steps: causing microwave radiation to be emitted from an emitter, measuring the radiation received by a detector from the emitter, the radiation measurement being dependent on the relative movement of the detector and the position of the radiation from the emitter in the region of the detector caused by a load on the aircraft component, and calculating an indication of the load sustained by the aircraft component from the radiation measurement together with data concerning the relationship between the radiation measurement and the load sustained by the component. 16. A method according to claim 15, wherein the radiation measurement is dependent on the relative movement of the emitter and detector. 17. A method according to claim 15, wherein the detector comprises a plurality of antennae and an indication of relative movement of the detector and the position of the radiation from the emitter in the region of the detector is calculated from measurements of the relative amounts of radiation received by the antennae. 18. A method according to claim 15, wherein the indication of the relative movement of the detector and the position of the radiation from the emitter in the region of the detector, comprises an indication of movement in at least two dimensions and the indication of the load sustained by the aircraft component comprises an indication of the load in at least two dimensions. 19. A method according to claim 15, when performed as part of a method of controlling the loads sustained by an aircraft component including monitoring the loads sustained by the aircraft component, the method further including a step of controlling a part of the aircraft in dependence on the results of the monitoring of the loads. 20. A method according to claim 19, when performed as part of a method of maneuvering an aircraft on the ground, the method further including a step of controlling the loads sustained by the aircraft during the maneuvers by means of monitoring the loads on the leg of the landing gear of the aircraft and controlling the braking and/or steering of the aircraft in dependence on the loads so monitored. 21. A method according to claim 15 wherein the step of measuring a load on an aircraft component includes performing a real-time calculation so as to provide a measurement on a current load.