Landing gear for an aircraft

Abstract

Landing gear for an aircraft, in particular for a helicopter, with at least one device for detecting the load on the landing gear, wherein the device is arranged within one or more wheel axles of the landing gear, and wherein the landing gear comprises a support which is angled to the wheel axle, wherein the device comprises at least one auxiliary element arranged within the wheel axle which is designed to deform or move depending on the load on the landing gear, and wherein at least one sensor is provided for detecting the deformation or movement of the auxiliary element, characterized in that the sensor comprises at least one pressure sensor.

Description

[0001] The invention relates to a landing gear for an aircraft, in particular for a helicopter, comprising at least one device for detecting the load on the landing gear, wherein the device is arranged within a wheel axle of the landing gear, and wherein the landing gear includes a support that is angled to the wheel axle. The invention further relates to a corresponding device for a landing gear of an aircraft.

[0002] It is known from the prior art to perform load measurements on the landing gear of aircraft. The loads on the landing gear thus recorded can be used for the control of the aircraft, for monitoring the wear of the landing gear, and / or for the detection and / or indication of malfunctions.

[0003] The load on the landing gear results, for example, from the weight of the aircraft resting on a surface. The aircraft's weight is transferred to the ground via the landing gear, thus subjecting it to a corresponding load. This load can cause deformation of the landing gear.

[0004] For chassis of this type, for example, eddy current sensors or optical sensors can be used to detect deformations of the chassis.

[0005] The sensors used are typically protected from environmental influences, contamination, and other damage by an encapsulation. This is necessary because the load measurement, or the values ​​recorded by the sensors, are taken into account by the aircraft's flight control system during landing, and the load measurement can therefore directly influence the landing procedure. Consequently, the required availability and reliability of such devices are considered very high.

[0006] A disadvantage of the systems known from the prior art is that the encapsulation used adds weight and cost to the entire aircraft.

[0007] US patent 2006 / 0283239A1 discloses a chassis with the features of the preamble of claim 1.

[0008] The object of the invention is therefore to provide an improved chassis or an improved device for detecting the load on the chassis, in which a special encapsulation of the measuring technology or the components used in the wheel axle is not required.

[0009] This problem is solved by a chassis with the features of claim 1. Advantageous embodiments are the subject of the dependent claims.

[0010] Accordingly, a landing gear is provided for an aircraft, which may in particular be a helicopter. The landing gear includes at least one device for detecting the load on the landing gear, wherein the device is arranged within a wheel axle of the landing gear. The wheel axle may be designed as, for example, a hollow cylindrical profile element, or it may include such a profile element. The load in this case refers to the forces introduced into or absorbed by the landing gear, which depend primarily on the weight of the aircraft.

[0011] The landing gear comprises a wheel axle angled towards the support. The support is the part of the landing gear through which the wheel axle connects to the aircraft and through which the aircraft's weight is transferred to the wheel axle or the ground beneath it. The support can be designed as a shock absorber, be part of a shock absorber, or comprise a shock absorber.

[0012] According to the invention, the device comprises at least one auxiliary element arranged within the wheel axle, which is designed to deform or move depending on the load on the chassis. Furthermore, the device comprises at least one sensor for detecting the deformation or movement of the auxiliary element. The sensor can be arranged directly on the auxiliary element. In particular, the sensor and the auxiliary element can be bonded and / or screwed together.

[0013] In a preferred embodiment of the invention, it is conceivable that the auxiliary element extends from a transition area where the support merges into the wheel axle to a wheel area where a wheel can be arranged on the wheel axle. The auxiliary element can also extend beyond these areas or only in a partial section between them.

[0014] In a further preferred embodiment, it is conceivable that the auxiliary element is arranged along or offset from the central axis of the wheel axle and / or is formed in one piece. The auxiliary element can be aligned exactly parallel and / or concentric to the wheel axle.

[0015] In a further preferred embodiment, it is conceivable that the auxiliary element is designed at least partially or along its entire length as a solid component without a cavity, and in particular as cylindrical or with a rectangular cross-section, or as a stepped component, or that the auxiliary element is designed as a hollow body. A combined embodiment of the auxiliary element is also conceivable, in which at least one part of it is designed as a hollow body and at least one other part as a solid component. It is also conceivable that one part of the auxiliary element is cylindrical, while another part has a rectangular or other cross-section. The auxiliary element can be made of an aluminum or steel alloy and / or be designed as a bending beam.

[0016] In a further preferred embodiment, it is conceivable that the auxiliary element is coupled to the wheel axle by means of two coupling bodies, in particular arranged on opposite sections of the auxiliary element. The coupling bodies can be hollow cylindrical, at least in part. It is conceivable that one of the coupling bodies is arranged in the transition area, while the other coupling body is arranged in the wheel area. The coupling body arranged in the wheel area can have a smaller axial extent than the coupling body arranged in the transition area.

[0017] In a further preferred embodiment, it is conceivable that the coupling bodies include, in particular, centrally or eccentrically arranged recesses and / or through-holes for receiving the auxiliary body. The recesses and / or through-holes can be formed centrally to the wheel axle. It is also conceivable to manufacture the auxiliary body and at least one of the coupling bodies as a single piece.

[0018] According to the invention, the sensor comprises at least one pressure sensor. A combination of different sensors, such as strain gauges and / or piezoelectric sensors, can also be used. The sensor can be mounted on or integrated into the auxiliary element. The auxiliary element can, for example, include a groove or other recess or passage for receiving the sensor. The sensor can be coupled to the groove or groove area by force-fit and / or positive-fit.

[0019] In a further preferred embodiment, it is conceivable that the sensor is arranged along the auxiliary element and / or at an end section of the auxiliary element. For easier mounting of the sensor, the auxiliary body may have a cross-section with at least one flattened side.

[0020] In another preferred embodiment, the sensor is conceivable to be arranged between the coupling bodies or outside the area bounded by the coupling bodies. The sensor can also be arranged on one of the coupling bodies itself.

[0021] In a further preferred embodiment, it is conceivable that the support and the wheel axle are manufactured in two parts or that the support and the wheel axle are manufactured in one part, wherein the support and the wheel axle are manufactured in particular as forgings or as forgings. The one-piece or two-piece manufacturing refers in the present case to components manufactured in one or two parts, or even in multiple parts.

[0022] The invention further relates to a device for detecting the load on the landing gear of an aircraft. The device may comprise at least one of the features mentioned in claims 1 to 9.

[0023] Further details and advantages of the invention will become apparent from the illustrations shown in the figures. These show: Fig. 1: Schematic view of a first embodiment, Fig. 2: Schematic view of a second embodiment, and Fig. 3: Schematic view of a third embodiment.

[0024] Fig. Figure 1 shows a schematic view of a first embodiment of the landing gear 1 according to the invention. The landing gear 1 is a landing gear 1 of an aircraft, such as a helicopter. The landing gear 1 comprises at least one device 2 for detecting the load on the landing gear 1. Landing gears 1 of this type are subjected to particularly high stress during landing procedures of aircraft, and the current load on the landing gear 1 can be used for improved flight control of the aircraft.

[0025] The load-sensing device 2 is arranged at least partially or largely within a wheel axle 3 of the chassis 1, on which a chassis wheel (not shown) can also be arranged. The wheel axle 3 can typically be coupled to a support 4 angled towards it. The support 4 and the wheel axle 3 are connected to each other via a transition area 5. This connection can, for example, be a welded joint.

[0026] The device 2 comprises at least one auxiliary element 6 arranged within the wheel axle 3, which is designed to deform or move depending on the load on the chassis 1. The auxiliary element 6 can be selected and / or arranged such that its deformation or movement is at least partially proportional to the load on the chassis 1.

[0027] According to the invention, at least one sensor 7 is provided for detecting this deformation or movement of the auxiliary element 6.

[0028] As can be seen from the figures, the auxiliary element 6 can extend from the transition area 5 to the wheel area 8, in which a wheel (not shown) can be arranged on the wheel axle 3.

[0029] The auxiliary element 6 can be arranged along the central axis of the wheel axle 3. The wheel axle 3 itself can be designed as an elongated hollow body with a corresponding central axis. The auxiliary element 6 can be formed in one piece.

[0030] In the exemplary embodiment of the Fig. 1. The auxiliary element 6 is designed, at least in sections, as a solid component that has no cavity. The auxiliary element 6 can, for example, be cylindrical. However, it is also possible for the auxiliary element 6 to be designed as a hollow body.

[0031] The auxiliary element 6 can be coupled to the wheel axle 3 by means of two coupling bodies 9, 9' arranged on opposite sections of the auxiliary element 6. It is also conceivable that the auxiliary element 6 is manufactured in one piece with at least one of the coupling bodies 9, 9'.

[0032] The coupling bodies 9, 9' may include recesses and / or through-holes for receiving the auxiliary body. These may, for example, be bores in the coupling bodies 9, 9'. The recesses and / or through-holes may be arranged centrally, i.e., radially centrally, or along the central axis of the wheel axle 3 on the coupling bodies 9, 9'.

[0033] Sensor 7 includes at least one pressure sensor. A combination of different sensor types is also conceivable.

[0034] As from Fig. As can be seen from Figure 1, the sensor 7 can be arranged along the auxiliary element 6, for example, near one of the coupling bodies 9, 9'. However, a central arrangement of the sensor 7 between the two coupling bodies 9, 9' is also conceivable. In this case, the sensor 7 can be positioned between the coupling bodies 9, 9' and in a central section of the auxiliary element 6.

[0035] As from Fig. As can be seen from Figure 2, the sensor 7 can also be arranged at an end section of the auxiliary element 6 and thus outside the area bounded by the coupling bodies 9, 9'. In an embodiment with a hollow auxiliary element 6, the sensor 7, in particular as a pressure sensor, can be arranged at least partially inside the auxiliary element 6. Such a sensor mounted inside the auxiliary element 6 can extend along a large part, the entire length, or almost the entire length of the auxiliary element 6.

[0036] The sensor 7 can also be positioned in extension of the auxiliary element 6.

[0037] At least one of the coupling bodies 9 can be provided in the transition area 5, while the other coupling body 9' can be provided in the wheel area 8. As can be seen from the figures, the coupling body 9' provided in the wheel area 8 can be shorter in the axial direction than the coupling body 9 provided in the transition area 5.

[0038] A cable gland can be provided in the coupling body 9 of the transition area 5, through which a cable leading to sensor 7 can run. This cable can then run further through the wheel axle 3 and the support 4 to a computer or on-board computer.

[0039] The invention enables direct load measurement at the wheel axle 3, whereby the measuring technology used requires no special encapsulation. The positioning of the device 2 for detecting the load on the chassis 1 within the wheel axle 3 makes the invention insensitive to environmental influences.

[0040] The landing gear 1 according to the invention, or the device 2 for detecting the load on the landing gear 1, can be used universally, for example, for flight control of an aircraft such as a helicopter. A value is determined via force measurement, deformation measurement, or pressure measurement, which allows conclusions to be drawn about the load on the landing gear 1.

[0041] The landing gear 1 or the device 2 can also be used in connection with an unmanned aircraft or a UAV and generally in connection with a fixed-wing aircraft or a helicopter.

[0042] Particularly in connection with fixed-wing aircraft, the invention can be used in conjunction with a weight-on-wheel system, where the recorded measurements can be used to measure the load of the aircraft, to measure the load distribution and / or to record the landing gear load.

[0043] Fig. Figure 3 shows an embodiment of the invention in which the auxiliary element 6 is slidably mounted within the wheel axle 3. Depending on the load on the wheel axle 3, the auxiliary element 6 can be moved to a different position.

[0044] A pressure fluid P can be present on at least one first side of the auxiliary element 6, which exerts a different pressure on the auxiliary element 6 depending on the load and thus deformation of the wheel axle 3.

[0045] A spring 10 can be arranged on a second side opposite the first side, configured to exert a force on the auxiliary element 6 depending on its position. The spring 10 can thus return the auxiliary element 6 to a neutral position when the chassis 1 is unloaded.

[0046] The auxiliary element 6 can comprise a rod section 61, via which the auxiliary element 6 is slidably mounted on the wheel axle 3.

[0047] The sensor 7 can detect the position of the auxiliary element 6 relative to the wheel axle 3 and / or the pressure of the pressure fluid P.

Claims

[1] Landing gear for an aircraft, in particular for a helicopter, comprising at least one device for detecting the load on the landing gear, wherein the device is arranged within one or more wheel axles of the landing gear, and wherein the landing gear comprises a support which is angled to the wheel axle, wherein the device comprises at least one auxiliary element arranged within the wheel axle which is configured to deform or move depending on the load on the landing gear, and wherein at least one sensor is provided for detecting the deformation or movement of the auxiliary element, characterized by that the sensor includes at least one pressure sensor. [2] Chassis according to claim 1, characterized by , that the auxiliary element extends from a transition area where the support merges into the wheel axle to a wheel area where a wheel can be arranged on the wheel axle. [3] Chassis according to claim 1 or 2, characterized by that the auxiliary element is arranged along or offset from the central axis of the wheel axle and / or is formed in one piece. [4] Chassis according to any one of the preceding claims, characterized by that the auxiliary element is designed at least in sections or along its entire length as a solid component without a cavity and in particular cylindrical or with a rectangular cross-section or offset, or that the auxiliary element is designed as a hollow body. [5] Chassis according to any one of the preceding claims, characterized by , that the auxiliary element is coupled to the wheel axle by means of two coupling bodies, in particular arranged on opposite sections of the auxiliary element. [6] Chassis according to claim 5, characterized by that the coupling bodies include, in particular, centrally or eccentrically arranged recesses and / or feedthroughs for receiving the auxiliary body. [7] Chassis according to any one of the preceding claims, characterized by that the sensor is arranged along the auxiliary element and / or at an end section of the auxiliary element. [8] Chassis at least according to claim 5, characterized by that the sensor is located between the coupling bodies or outside the area bounded by the coupling bodies. [9] Chassis according to any one of the preceding claims, characterized by that the support and the wheel axle are manufactured in two parts or that the support and the wheel axle are manufactured in one part, wherein the support and the wheel axle are manufactured in particular as forged parts or as a forged part. [10] Device for measuring the load on the landing gear of an aircraft, characterized by that the device comprises at least one of the features mentioned in claims 1 to 9.

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