LANDING GEAR ASSEMBLEY |
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申请号 | EP04726216.7 | 申请日 | 2004-04-07 | 公开(公告)号 | EP1613532B1 | 公开(公告)日 | 2008-12-10 |
申请人 | Airbus UK Limited; | 发明人 | CHOW, Leung Choi; WOOD, Christopher Neil; | ||||
摘要 | An aircraft landing gear (9) includes a wheel (1) having a wheel rim (3) on which a tyre (4) is held. The gap (6) between the rim (3) and tyre (4) is bridged and covered by a sealing element (7), which thereby presents a smooth surface to the air flowing over the wheel during flight of the aircraft (8). Thus, noise that would otherwise be generated by the interaction of air and the parts of the wheel (1) and/or tyre (4) defining the gap (6) is reduced. Such noise reduction benefits may also be achieved by providing a tyre (4) and wheel (1) so shaped that there is no gap (6) between the tyre (4) and wheel rim (3). | ||||||
权利要求 | |||||||
说明书全文 | The present invention relates to reducing noise caused by an aircraft landing gear. In particular, the invention relates to landing gear designed to reduce the noise generated by the interaction of the wheel of a landing gear and the air flowing past it during the approach of the aircraft when landing. It is desirous to reduce the noise generated by aircraft, for example, to lessen disruption or inconvenience, resulting from aircraft noise, caused to the public on the ground near airports. A significant amount of noise is generated by the interaction of the aircraft and the air flowing past it, which results in turbulent flows and consequently noise. It is particularly important to reduce noise created during approach of the aircraft on landing. During approach, a significant contribution to the amount of noise that the aircraft makes is made by the landing gear, which is typically deployed early for landing for safety reasons. The deployment of landing gear will increase drag and assist deceleration of the aircraft. One source of noise is the wheel of the landing gear. During take-off, noise from the landing gear is a less significant factor because engine noise is generally greater and because the landing gear is generally stowed at the earliest opportunity to reduce drag and aid take-off. During normal flight, the landing gear of an aircraft is typically stowed in a landing gear bay, the bay being closed off by doors so that no part of the landing gear is subjected to the air flow. It is an aim of the present invention to provide a landing gear that generates less noise compared to a landing gear of the same size that has not been adapted, designed or manufactured in accordance with the present invention. According to the invention there is provided an aircraft landing gear including a wheel having a rim around which there is mounted a tyre, and a part located at the junction between the tyre and the rim, the part being shaped such that on one side of the wheel, during use of the landing gear on an aircraft when airborne and the landing gear is in a position ready for landing of the aircraft, the surface of said part interfaces smoothly with the surfaces, presented to the airflow, of both the tyre and the wheel, whereby noise resulting from the interaction of the landing gear and the airflow during approach of the aircraft on landing may be reduced as a result of the gap, which would otherwise exist between the tyre and the rim, being closed, characterised in that said part is configured to be movable so that the tyre may be inspected, whilst the aircraft is on the ground and the tyre is mounted on the rim, without requiring said part to be separated from the wheel. It has previously been proposed to provide a landing gear including a wheel comprising a wheel rim, a tyre, and a hub cap that covers various voids. However, in that proposal the hub cap has not covered all such voids and in particular there may be a significant gap defined between the wheel rim and tyre. Such a landing gear could create significant noise as a result of the interaction of the parts of the wheel defining that gap and the air flowing past the wheel. Thus the noise caused by the interaction of the air and the wheel, caused during the approach when landing, may be reduced by means of providing a wheel according to the present invention. British Patent Application published under number Other tyre wheel assemblies are disclosed in the prior art. It will be appreciated that the noise generated by an aircraft wheel during approach on landing is generally as a result of the airflow interacting with the wheel and that the wheel will typically not be rotating during approach on landing. Advantageously, the wheel including the rim, tyre and said part, is designed, modified and/or configured to reduce, in use, the amount of turbulent air flow generated in the region of the junction between the tyre and the rim. Advantageously, the wheel including the rim, tyre and said part, is designed, modified and/or configured to streamline, in use, the flow of air past the wheel. Said part is preferably so shaped that it does not include any substantial portion that is concave (when viewed from outside of the wheel) when the aircraft is airborne. Said part is preferably so shaped that it is substantially flat and/or convex (when viewed from outside of the wheel) when the aircraft is airborne. Thus, there need be no gap between the wheel rim and the tyre, when the part is shaped in accordance with these preferred features of the invention. Having no such gap reduces the noise created by the wheel when compared with otherwise identical wheels having such gaps. Such gaps are generally concave in shape and have edges where different surfaces meet, such edges also contributing to unwanted noise. Said part may be defined by a separate component part of the wheel. Said part may be defined by a sealing element, which bridges a gap between the wheel rim and the tyre. The sealing element may for example be provided in the form of a separate component. The sealing element may for example be in the form of a soft rubber pad. The sealing element may be formed from liquid sealant material that has been solidified. The term liquid is intended to cover sealant in a plastic and/or malleable state as well as sealant in a less viscous state. The sealing element may comprise an adhesive, a silicone based material or similar sealing material. The sealing element may be moulded before being assembled. Alternatively, the sealing element may be moulded into shape in situ. For example, a liquid sealant material may be deposited into a gap between the wheel rim and the tyre and then allowed to solidify (or set). The sealing element may be in the form of an elastomeric element, such as, for example, a rubber seal. The sealing element may be generally annular in shape and tapering in cross-section so that the thickness of the element reduces with radial distance from its centre. Preferably, said part (the part that interfaces smoothly between the tyre and the wheel) is defined by a multiplicity of flexible elements extending radially across the junction between the tyre and the rim. For example, brushes may be provided, which bridge a gap between the wheel rim and the tyre. Said part may be defined by such brushes. The shape of said part (the part that interfaces smoothly between the tyre and the wheel) is advantageously maintained throughout the approach of the aircraft when landing. On touching down, the aircraft generates a significant amount of noise and reducing the noise generated by air flowing past the wheels may no longer be important. Thus, the part between the wheel rim and the tyre may change shape significantly after touchdown. The part is preferably stiff enough not to change shape significantly during normal flight, but flexible enough that the shape of the part changes on touchdown (and preferably so flexible that the shape of the part when the aircraft is at a standstill on the ground is significantly different from when the aircraft is airborne). The tyre and the wheel rim may for example be so shaped that there is a need for a gap to be present between the tyre and the wheel rim when landing to allow for deformation of the tyre without causing undesirable local wear of the tyre at a position between the wheel rim and the periphery of the tyre. It may for that reason be advantageous for at least a portion of said part to be so configured to be deflected from, or otherwise forced out of, a gap that said part bridges when the aircraft lands. The part if configured to be so movable in that way, is advantageously also configured such that once the aircraft is airborne again said at least a portion moves back to the position in which it bridges the gap. At least a portion of said part may be so configured that, once the force between the wheels and the ground exceeds a given threshold force, for example on touchdown, it moves out of a gap that said part bridges when the aircraft is airborne. The threshold force may be less than or equal to the weight supported by the wheel when the aircraft is unloaded and stationary on the ground. Said at least a portion of said part may also be so configured that, once the force between the wheels and the ground drops to or below a given threshold force, for example after the aircraft has lifted off the ground during take-off, said at least a portion of said part moves back to the position in which it bridges the gap. Said threshold force may be the same as the threshold force first mentioned above. The threshold force is preferably greater than zero, but could be close to or equal to zero. The threshold force may be between 0.01 and 0.5 times the weight supported by the wheel when the aircraft is unloaded and stationary on the ground. Said part is preferably defined at least partly by an elastically deformable material. The material is preferably chosen such that the deforming of such material during normal usage is reversible (i.e. substantially elastic deformation) so that the part does not deteriorate after only a few series of take-offs and landings. As mentioned above, said part is so arranged and configured that the tyre may be inspected whilst the aircraft is on the ground and the tyre is mounted on the wheel. It is particularly important, insofar as this feature is concerned, that the side wall portion of the tyre immediately adjacent to the wheel rim may be inspected for wear and/or damage. Only a portion of said part may be configured to be movable for this purpose. For example, a portion of the part bridging a gap between the wheel rim and the tyre, thereby hiding the portion of the wheel behind said part, is advantageously flexible, and preferably resiliently flexible, and is so arranged that said part may be moved manually to reveal the portion of the tyre that is otherwise hidden from view. Said part may be moved by lifting the periphery of the part thereby bending the part. Such an action may for example be considered as peeling back the part to reveal the tyre underneath. The wheel may include a hub cap. The hub cap may extend to the junction between the wheel rim and the tyre. The surface, presented to the airflow, of the rim may be defined by the hub cap. Said part may be defined at least in part by a part of the hub cap. For example the hub cap may have an outer portion in the form of a flexible sealing member that extends radially outwardly from the periphery of an inner portion of the hub cap. Said part may extend significantly beyond the immediate vicinity of the junction between the tyre and the rim. For example, said part may cover an area of greater than 5% of the wheel area (equal to πR2 where R is the radius of the tyre when in the air). Preferably, said part covers more than 10% of the wheel area and more preferably more than 20% of the wheel area and yet more preferably more than 40% of the wheel area. It is stated above that at least one side of the wheel includes said part. Preferably, said at least one side is the side of the wheel opposite to the side which is configured to receive the axle. Both sides of the wheel may be arranged in accordance with the present invention. Thus, the wheel may include a further part shaped such that on the other side of the wheel, during use of the landing gear on an aircraft when airborne and the landing gear is in a position ready for landing of the aircraft, the surface of said further part interfaces smoothly with the surfaces, presented to the airflow, of both the tyre and the wheel, whereby noise resulting from the interaction of the landing gear and the airflow during approach of the aircraft on landing may be reduced as a result of the gap, which would otherwise exist between the tyre and the rim, being closed. According to a further aspect of the invention there is provided an aircraft including an aircraft landing gear according to the present invention. The aircraft landing gear of the aircraft may be fixed in position. Alternatively, the landing gear is movable from a stored position to an operative position. The present invention has particular application to aircraft wherein the landing gear is moveable between a stowed (stored) position and a deployed (operative) position. Aircraft having landing gear that are fixed in position are generally not designed with noise reduction in mind. The invention is of greater application to larger aircraft, particularly passenger-carrying aircraft, where noise reduction on landing of the aircraft is of greater relevance. The landing gear is preferably of a size suitable for use on an aircraft designed to carry more than 50 passengers, and more preferably more than 100 passengers. Such aircraft generally have retractable landing gear assemblies. Other features of the invention described herein may of course be incorporated into this aspect of the present invention. The present invention also provides a method of reducing noise caused by landing gear on an aircraft, for example during approach of the aircraft on landing, including a step of manufacturing an aircraft according to any aspect of the above-described invention. Such a method advantageously includes a step of modifying an existing design in order to reduce noise caused by the landing gear. There is further provided a component, such as a sealing element for example, for use in the landing gear according to the present invention, the component advantageously being in the form of a separate component as described herein. Embodiments of the present invention will now be described by way of example with reference to the following schematic drawings of which:
The wheel 1 includes a hub cap 2a (seen most clearly in It will be appreciated that various modifications may be made to the above-described embodiments of the invention. For example, the function of the sealing element 7 of the first embodiment (or of the sealing member 13 of the second embodiment) could be achieved by means of brushes having resiliently deformable bristles aligned radially with respect to the axis of the tyre 1 (i.e. in a radial direction from the axis). The rubber sealing element 7 of the first embodiment could alternatively be replaced with flexible adhesive or gel or other suitable sealing material. Whilst the side 1a of the wheel 1 in the embodiments described above has substantially no discontinuities, the wheel 1 may include certain features requiring such discontinuities to be provided, for example in the form of small apertures or protrusions. Such discontinuities may contribute to the noise generated by the wheel 1 travelling through the air, but the reasons for providing such features may outweigh the benefits of the greater reduction in noise that might be achieved if such features were not provided. It is however envisaged that the provision of such features would not interfere with the benefits provided by the above-described embodiment in terms of noise reduction gained by the provision of the sealing element (or by means of the smoothing of the junction between the wheel rim and the tyre). |