Compliant mount for aircraft, aircraft device assembly, folding wing for aircraft, folding wing tip aircraft, aircraft and method

Abstract

The invention provides a compliant mount for an aircraft, an aircraft device assembly, a folding wing for an aircraft, a folding wing tip aircraft, an aircraft, and a method. A compliant mount for attaching a device, such as for example a latch unit, to a structural member of an aircraft, and comprising: a mounting member for attaching to the structural member of the aircraft; a receiver for supporting the device and coupled to the mounting member along a longitudinal axis; and one or more spring elements arranged to resiliently bias the receptacle in alignment with the longitudinal axis and to allow angular movement of the receptacle away from the longitudinal axis. An aircraft device assembly includes such a compliant mount and an aircraft device supported by a receiver. An aircraft has one or more such device assemblies. The aircraft may be a folding wing tip aircraft, and the device assembly may be part of a folding wing tip actuation mechanism.

Description

TECHNICAL FIELD

[0001] The present invention relates to a compliant mount for attaching an aircraft device to a structural member of an aircraft. The invention is particularly suited, but by no means limited, to use in a folding wingtip aircraft for mounting a latch unit forming part of a folding wingtip actuation mechanism. BACKGROUND

[0002] Commercial passenger aircraft are being developed with folding wingtips to allow the aircraft to have a longer overall wingspan than can normally be accommodated at a passenger airport, for example due to wing span restrictions at the airport gate or along the taxiway. In turn, this can reduce aircraft fuel consumption (as a longer thinner wing can provide an improved lift-drag ratio) and can also enable larger passenger aircraft (carrying more passengers and thereby reducing carbon emissions per passenger) to be accommodated by the airport.

[0003] As shown for example in Figure 1a and Figure 1b Such a folding wingtip aircraft 10 has a pair of folding wings 12, with each folding wing 12 having a main wing portion 14 and a wingtip 16 which is foldable relative to the main wing portion 14 by means of an actuation mechanism 18. Figure 1a The wingtip 16 is shown in a folded (or raised) configuration, such that the effective wingspan of the aircraft (for example for the purpose of entering an airport gate) is determined by the wingspan of the main wing portion 14 rather than the wingtip 16. Figure 1b The wingtip 16 is shown in an unfolded (or lowered) configuration, such that the effective wingspan of the aircraft (for example for the purpose of take-off, flight and landing) is determined by the wingspan of the main wing portion 14 combined with the wingtip 16. Of course, the effective wingspan in the unfolded configuration is greater than the effective wingspan in the folded configuration, in order to provide sufficient lift for the aircraft during take-off, flight and landing. Typically, the transition from the folded configuration to the unfolded configuration will occur on the taxiway or at a stand after the aircraft has left the gate and is ready for take-off. Similarly, the transition from the unfolded configuration to the folded configuration typically occurs on the run-up area of the runway or taxiway after the aircraft has landed and is ready to approach the gate.

[0004] The actuation mechanism 18 of a folding wingtip aircraft typically includes a latching unit with a latching pin (also called a latch bolt) that can extend into an extended configuration to lock the angle of the wingtip 16 relative to the main wing portion 14 (i.e., locking the wingtip in a folded or extended configuration). Conversely, the latching pin can retract into a retracted configuration so that the angle of the wingtip 16 relative to the main wing portion 14 can be adjusted (i.e., changing the wing from a folded configuration to an extended configuration, or vice versa). The latching pin can be actuated between the extended and retracted configurations by, for example, an electrohydraulic piston or another actuating member. For example, as an alternative to an electrohydraulic piston, the latching pin can be electrically actuated or hydraulically actuated.

[0005] When the latch pin is driven into an extended configuration to lock the angle of the wingtip 16 relative to the main wing portion 14, the latch pin is typically driven through one or more (and usually more) lugs attached to the ends of the main wing portion 14 and the folding wingtip 16. In practice, these lugs may exhibit slight misalignment, which could impede the passage of the latch pin when it enters its extended configuration. Therefore, it is desirable to allow for some misalignment of the lugs when the latch unit is driven into its extended configuration.

[0006] It will be understood that such latching units with extendable and retractable latching pins can be used in applications other than folding-wing aircraft, and similar problems with misaligned components may apply. For example, a latching unit (with latching pins capable of extending through or into one or more receiving components) can be used to lock aircraft doors or to secure landing gear in a retracted or extended position. Furthermore, in addition to latching units, other aircraft parts intended to receive pins, bolts, or other inserting members may be slightly misaligned. Such inserting members can be actuated (e.g., in the case of latching pins) or non-actuated (e.g., pins or bolts inserted during aircraft assembly). In all these cases, it is desirable for the inserted member to allow for some misalignment of one or more parts through which it is inserted (or entered). Summary of the Invention

[0007] This specification sets forth various aspects and embodiments of the invention.

[0008] According to a first aspect of the invention, a compliant mount for an aircraft is provided for attaching a device (e.g., a latching unit) to a structural member of the aircraft. The compliant mount includes: a mounting member for attachment to the structural member of the aircraft; a receiving member for supporting the device, the receiving member being coupled to the mounting member along a longitudinal axis; and one or more spring elements arranged to elastically bias the receiving member to align with the longitudinal axis and allow angular movement of the receiving member away from the longitudinal axis.

[0009] The term “device” as used herein should be interpreted broadly to include actuated devices such as latching units, as well as non-actuated devices such as retaining pins or retaining bolts.

[0010] Because the angular movement of the receiver can be achieved by one or more spring elements, the device supported by the receiver can allow for a certain degree of misalignment of the device with the part that engages with it (such as a lug).

[0011] The aircraft can be a commercial passenger aircraft, such as an aircraft capable of carrying more than 50, for example, more than 100 passengers. For the purposes of this application, the term "commercial passenger aircraft" also includes aircraft of the same type configured for cargo transportation.

[0012] The mounting component may include a cavity in which a receiving element is mounted, and the cavity allows angular movement of the receiving element away from the longitudinal axis.

[0013] In the mounting member, the cavity may be defined by an annular wall surrounding a longitudinal axis and a support region projecting inward from the annular wall. The receiving member may have a cylindrical outer wall and an end region, and the end region of the receiving member may abut against the support region of the mounting member.

[0014] Advantageously, the end region of the receiving member may include an arched (curved or angled) region, and the support region of the mounting member may include a complementary arched (curved or angled) region, the end region of the receiving member being able to pivot about a longitudinal axis against the complementary arched region. This facilitates the pivoting motion of the receiving member relative to the mounting member.

[0015] Mounting components may have axial channels extending through the support area.

[0016] The receiving member may have a hollow core for supporting the device in use, and an axial channel extending from the hollow core through the end region.

[0017] Preferably, one or more spring elements include radial spring elements arranged around the receiver between the annular wall of the mounting member and the cylindrical outer wall of the receiver, for radially biasing the receiver and allowing radial movement of the receiver.

[0018] Preferably, the radial spring element comprises a wave spring.

[0019] Preferably, the wave spring of the radial spring element is in the form of peaks and valleys, which are oriented radially and orthogonal to the longitudinal axis.

[0020] Preferably, the annular wall of the mounting member is fitted with an annular recess (and optionally more than one such recess), in which the radial spring element is held.

[0021] The end region of the receiving member can project radially outward from the cylindrical outer wall of the receiving member. Therefore, the receiving member can be advantageously held constrained within the cavity by a radial spring element.

[0022] Preferably, one or more spring elements include axial spring elements arranged around the support region of the mounting member between the support region of the mounting member and the end region of the receiving member to provide axial pretension to the compliant mounting member.

[0023] Preferably, the axial spring element includes a wave spring.

[0024] Preferably, the wave spring of the axial spring element is in the form of peaks and valleys, with the peaks and valleys oriented axially about the longitudinal axis.

[0025] Preferably, the support area of ​​the mounting member incorporates an annular recess (and optionally more than one such recess), in which the axial spring element is held.

[0026] According to a second aspect of the invention, an aircraft device assembly is provided, comprising a compliant mounting member according to a first aspect of the invention and an aircraft device supported by a receiving member.

[0027] The device may include a movable member capable of extending along an axial channel through the end region of the receiver and through the support region of the mounting member, thereby changing from a retracted configuration to an extended configuration.

[0028] By way of example, the device can be a latching unit (e.g., for a folding wingtip actuation mechanism), and the movable component can be a latching pin (also known as a latch bolt).

[0029] According to a third aspect of the invention, a folding wing for an aircraft is provided, the folding wing having a main wing portion and a wingtip portion foldable relative to the main wing portion by means of an actuation mechanism, wherein the actuation mechanism includes a latching unit as provided by a second aspect of the invention, wherein a latching pin in an extended configuration locks the angle of the wingtip portion relative to the main wing portion, and wherein a latching pin in a retracted configuration allows the angle of the wingtip portion relative to the main wing portion to be adjusted.

[0030] According to a fourth aspect of the invention, a folding wingtip aircraft is provided, which has one or more folding wings according to a third aspect of the invention. Although typically both wings of such an aircraft are folded, depending on airport limitations, such as in order for the aircraft to approach the boarding gate, only one wing may need to be folded.

[0031] According to a fifth aspect of the invention, an aircraft having one or more device components according to a second aspect of the invention is provided.

[0032] Finally, according to a sixth aspect of the invention, a method is provided for attaching a device to a structural member of an aircraft using a compliant mount according to a first aspect of the invention, the method comprising (without a specific order): attaching a mounting member of the compliant mount to a structural member of the aircraft; and attaching the device to a receiving member of the compliant mount. Attached Figure Description

[0033] Embodiments of the invention will now be described by way of example only and with reference to the accompanying drawings, in which:

[0034] Figure 1a This is a schematic front view of an aircraft with folding wingtips, where the wingtips are in a folded configuration.

[0035] Figure 1b This shows the configuration with the wingtips in an extended position. Figure 1a Aircraft;

[0036] Figure 2 This is a schematic cross-sectional view of an example of a compliant mount for attaching a device, such as a latching unit, to a structural member of an aircraft. The compliant mount includes a mounting member, a receiver for supporting the device in use, and a spring element that allows angular movement of the receiver relative to the mounting member.

[0037] Figure 3 yes Figure 2 A three-dimensional view of the compliant mounting components;

[0038] Figure 4 yesFigure 2 A perspective view of the compliant mounting hardware, including the receiving parts and spring elements;

[0039] Figure 5 This applies when the latching unit is installed in the receiving part. Figure 4 A perspective view of the compliant mounting hardware, including the receiving parts and spring elements;

[0040] Figure 6 It supports the latch unit in its retracted configuration. Figure 2 A schematic diagram of the longitudinal cross-section of the compliant mounting component;

[0041] Figure 7a This is when the latching unit is in the extended configuration, such as Figure 6 A longitudinal cross-sectional schematic diagram of the compliant mounting member and latching unit, wherein the latching pin passes through a lug aligned with the longitudinal axis of the mounting member; and

[0042] Figure 7b and Figure 7a Correspondingly, however, it shows a certain degree of angular movement of the receiving part away from the longitudinal axis so that the latch pin can pass through the misaligned lug.

[0043] In the accompanying drawings, the same elements are always represented by the same reference numerals. Detailed Implementation

[0044] This embodiment represents the best mode known to the applicant for practicing the invention. However, this embodiment is not the only way to achieve this objective.

[0045] Figure 2 An example of a compliance mount 20 for an aircraft is shown. The compliance mount 20 is used to mount components such as latch units. Figure 5 , Figure 6 , Figure 7a and Figure 7b Devices such as those in the 80 and 90 series are attached to the structural components of the aircraft, while allowing the device a certain degree of angular movement or displacement, such as allowing the device to pass through (or enter) lugs. Figure 7a and Figure 7b Misalignment of components 110, 112, or others. In use, the structural component of the aircraft to which the mounting is attached may be, for example, a spar within the wing, or the first lug of a series of lugs forming part of the folding wingtip actuation mechanism.

[0046] The compliant mount 20 includes a mounting member 30, which is a separate component for attachment to a structural member of the aircraft, and a receiving member 70 for supporting the device. The mounting member 30 and the receiving member 70 are typically made of a metal with suitable strength and hardness. The receiving member 70 is coupled to the mounting member 30 along a longitudinal axis L. The compliant mount 20 also includes one or more spring elements arranged to elastically bias the receiving member 70 to alignment with the longitudinal axis L and to allow angular movement of the receiving member 70 away from the longitudinal axis L. In the illustrated example, the compliant mount 20 includes two such spring elements 50, 60, although in alternative examples only a single spring element may be provided. In other examples, more than two spring elements may be used.

[0047] The longitudinal axis L can be considered as the ideal orientation of the receiving member 70 and the device mounted therein, which corresponds to the case where the component through which the device is to pass is precisely aligned and therefore the device does not need to move away from the longitudinal axis L.

[0048] Also refer to Figure 3 and Figure 2 In the illustrated example, mounting member 30 includes a mounting ring 32 and three lugs 42, 44, and 46 projecting outward from the mounting ring 32. The underside of each lug 42, 44, and 46 is flush with the underside of the mounting ring 32. Each lug 42, 44, and 46 has corresponding holes 43, 45, and 47 through which mounting member 30 can be securely attached to structural members of the aircraft, for example, using bolts or other fasteners. It will be understood, of course, that alternative arrangements are possible for attaching mounting member 30 to structural members of the aircraft. For example, a different number of lugs (e.g., two or four lugs) could be provided instead of the three lugs illustrated. In other examples, alternative mounting configurations such as bayonet mounts, clamping elements, or keyways can be used.

[0049] Mounting component 30 can be manufactured as a single integral structure or produced as a component with parts.

[0050] Within the mounting ring 32, the mounting member 30 includes a cavity 40 in which a receiver 70 is mounted, and the cavity 40 allows angular movement of the receiver 70 away from the longitudinal axis L. In the illustrated example, the cavity 40 is primarily defined by an annular inner wall 34 surrounding the longitudinal axis L within the mounting ring 32 and a support region 36 projecting radially inward from the annular wall 34. In other words, the support region 36 can be considered as an inwardly projecting flange, the lower portion of which forms the lower portion of the mounting ring 32. The mounting member 30 has an axial channel 33 extending through the support region 36. Thus, the axial channel 33 communicates with the cavity 40 in which the receiver 70 is mounted. Both the axial channel 33 and the cavity 40 in which the receiver 70 is mounted are concentrically aligned with the longitudinal axis L. The axial channel 33 and the cavity 40 together extend axially through the entire mounting member 30.

[0051] In the illustrated example, the receiver 70 has a cylindrical outer wall 72 and an end region 76. The end region 76 projects radially outward and also has a portion extending radially inward at its distal end to form an inwardly projecting flange. Within the cylindrical outer wall 72, the receiver 70 has a hollow core 74 in which the device is supported during use, wherein the device abuts against the inwardly projecting flange portion of the end region 76. Furthermore, an axial channel 75 extends from the hollow core 74 through the inwardly projecting flange portion of the end region 76. The hollow core 74 and the axial channel 75 are both concentrically arranged about the longitudinal axis L when the receiver 70 has no angular displacement relative to the mounting member 30. The hollow core 74 and the axial channel 75 together extend axially through the entire receiver 70.

[0052] Within the compliant mount 20, the end region 76 of the receiver 70 abuts against the support region 36 of the mount member 30. In this respect, in the illustrated example, the inwardly projecting flange portion of the end region 76 includes an arched (curved or angled) region 78 on its underside. Similarly, the support region 36 of the mount member 30 includes a complementary arched (curved or angled) region 38 surrounding the edge of the channel 33, against which the arched region 78 of the receiver 70 is pivotable about the longitudinal axis L.

[0053] The surfaces of the mounting member 30 and / or the receiving member 70 that come into contact with each other may be coated with a suitable material to reduce friction between the mounting member 30 and the receiving member 70.

[0054] Now refer to Figure 4 and Figure 2In order to elastically bias the receiver 70 to align with the longitudinal axis L while allowing the receiver 70 to move away from the longitudinal axis L at an angle (i.e. radial), the illustrated example of the compliant mount 20 includes a radial spring element 60 arranged around the circumference of the receiver 70 between the annular wall 34 of the mount 30 and the cylindrical outer wall 72 of the receiver 70.

[0055] Preferably, as illustrated, the radial spring element 60 comprises a wave spring. Using terminology from wave physics, the wave spring of the radial spring element 60 takes the form of peaks (or crests) 62 and troughs 64, wherein the peaks 62 and troughs 64 are radially oriented and orthogonal to the longitudinal axis L. The peaks 62 press against the annular wall 34 of the mounting member 30, and the troughs 64 press against the cylindrical outer wall 72 of the receiver 70. In the illustrated example, the wave spring forming the radial spring element 60 has eight peaks and eight troughs, which provides a good, uniform bias to the receiver in all directions. However, in alternative examples, the number of peaks and troughs can vary beyond eight if desired.

[0056] Furthermore, in the illustrated example, the radial spring element 60 is a single continuous spring, although in alternative examples, the radial spring element 60 may be made instead of a series of shorter, separate spring members arranged circumferentially around the receiver 70.

[0057] like Figure 2 As shown in the illustrated example, the annular inner wall 34 of the mounting member 30 is fitted with an annular recess 35 in which the radial spring element 60 is held. In an alternative example, multiple separating recesses may be provided around the annular wall 34 of the mounting member 30 instead of a single continuous annular recess 35, wherein each separating recess is positioned to receive a corresponding peak 62 of the radial spring element 60.

[0058] As described above and as Figure 2 and Figure 4 As shown in the illustrated example, the end region 76 of the receiver 70 protrudes radially outward from the cylindrical outer wall 72 of the receiver 70. The length of the end region 76 along the longitudinal axis L is slightly less than the depth of the annular wall 34 below the annular recess 35 (i.e., the extent of the annular wall 34 between the annular recess 35 and the inwardly protruding support region 36). Therefore, the end region 76 of the receiver 70 is held and captured within the cavity 40 by the radial spring element 60. This function of the radial spring element 60 is to allow angular movement of the receiver 70 away from the longitudinal axis L, in addition to elastically biasing the receiver 70 to align with the longitudinal axis L.

[0059] To provide axial pretension of the receiving member 70 within the mounting member 30, the illustrated example of the compliant mounting member 20 also includes an axial spring element 50 arranged around the support region 36 of the mounting member 30 (i.e., around the circumference of the axial channel 33) between the support region 36 of the mounting member 30 and the end region 76 of the receiving member 70.

[0060] Preferably, as illustrated, the axial spring element 50 comprises a wave spring. The wave spring of the axial spring element 50 is in the form of peaks 52 and troughs 54, wherein the peaks 52 and troughs 54 are axially oriented about the longitudinal axis L (i.e., orthogonal to the orientation of the peaks 62 and troughs 64 of the radial spring element 60). The peaks 52 press against the underside of the end region 76 of the receiver 70, and the troughs 54 press against the support region 36 of the mounting member 30. In the illustrated example, the wave spring forming the axial spring element 50 has four peaks and four troughs, which provides a good, uniform degree of axial pretension to the receiver 70. However, in alternative examples, the number of peaks and troughs can vary beyond four if desired.

[0061] Furthermore, in the illustrated example, the axial spring element 50 is a single continuous spring, although in alternative examples, the axial spring element 50 may be made instead of a series of shorter, separate spring elements arranged around the support region 36 of the mounting member 30 (i.e., around the circumference of the axial channel 33).

[0062] like Figure 2 As shown in the illustrated example, the support region 36 of the mounting member 30 incorporates an annular recess 37 in which the axial spring element 50 is held. In an alternative example, multiple separating recesses may be provided around the support region 36 of the mounting member 30 instead of a single continuous annular recess 37, wherein each separating recess is positioned to receive a corresponding valley 54 of the axial spring element 50. Besides holding the axial spring element 50 in place, the annular recess 37 also helps to make the mounting member 30 more compact in the axial direction.

[0063] Figure 5 The illustration shows a receiving member 70 (in which spring elements 50 and 60 are held in place), which supports a device, namely latching units 80 and 90. See also... Figure 6 , Figure 7a and Figure 7b These figures illustrate latching units 80 and 90, which are mounted within compliant mount 20, thereby forming device assembly 120. In this specification, latching units 80 and 90, and indeed the entire device assembly 120, will be primarily described as being used, for example, for... Figure 1a and Figure 1bThe folding wingtip actuation mechanism 18 of the folding wingtip aircraft 10 shown is part of the folding wingtip actuation mechanism 18, wherein the actuation mechanism 18 controls the folding of the wingtip 16 relative to the main wing portion 14. However, in other examples, latching units 80, 90 and device assembly 120 may be used for different purposes, such as locking aircraft doors or securing landing gear in a retracted or extended position.

[0064] The latching unit includes an outer body portion 80 and a latching pin 90, the latching pin 90 being driven by an electro-hydraulic piston 100 or other driving member (such as... Figure 6 As shown and from Figure 7a and 7b (omitted) When driven, it can extend from the body part 80 and retract into the body part 80. The body part 80 and the latch pin 90 are basically in the form of hollow cylindrical members, wherein the latch pin 90 is concentrically and slidably mounted in the body part 80.

[0065] exist Figure 6 In the diagram, the latch pin 90 is shown in its retracted configuration, located within the body portion 80, while... Figure 5 , Figure 7a and Figure 7b In the diagram, the latch pin 90 is shown in its extended configuration. It can be noted that, in its extended configuration, the latch pin 90 extends from the body portion 80 to the opposite side of the compliant mount 20 relative to the body portion 80. In other words, the body portion 80 is mounted on one side of the compliant mount 20 (i.e., one side of the receiver 70), and the extension direction of the latch pin 90 extends through the compliant mount 20 towards the opposite side.

[0066] The outer diameter of the body portion 80 corresponds to the inner diameter of the receiving member 70, such that the body portion 80 is securely held within the receiving member 70. Mechanical fasteners and / or adhesives can be used to firmly secure the body portion 80 within the receiving member 70. For example, as can be obtained from... Figure 7a As seen in the diagram, the inner diameter of the body portion 80 is slightly smaller than the inner diameter of the axial channel 33 extending through the support region 36 of the mounting member 30. The outer diameter of the latch pin 90 is slightly smaller than the inner diameter of the body portion 80 to provide a sliding fit of the latch pin 90 within the body portion 80.

[0067] like Figure 6 As shown, the body portion 80 has a cover 82 through which the electro-hydraulic piston 100 can slide. Similarly, the latch pin 90 has a head 92 through which the piston 100 passes, wherein the piston 100 (e.g., at the front end of the latch pin 90) is fixedly connected within the latch pin 90.

[0068] When from Figure 6 The retraction configuration transformation toFigure 5 , Figure 7a and Figure 7b When the latch pin is extended, it is driven longitudinally along the axial channel 75 (along... Figure 7a and Figure 7b The direction of the drive (D) passes through the end region 76 of the receiving member 70 and is longitudinally driven through the support region 36 of the mounting member 30 along the axial channel 33.

[0069] Refer to the example of a folding wingtip actuation mechanism, and refer to Figure 1a , Figure 1b , Figure 7a and Figure 7b When the configuration is changed to the extended position, the latch pin 90 is driven in the direction D through one or more lugs 110, 112 attached to the ends of the main wing portion 14 and the folding wing tip 16, thereby locking the angle of the wing tip 16 relative to the main wing portion 14.

[0070] Figure 7a An ideal scenario is depicted in which lugs 110, 112 are correctly aligned with the longitudinal axis L of mounting member 30. In this case, latch pin 90 can be driven through lugs 110, 112 in direction D without any angular movement of receiver 70 relative to mounting member 30. Therefore, spring elements 50, 60 simply hold receiver 70 in an offset alignment with longitudinal axis L.

[0071] on the other hand, Figure 7b The scenario depicts lugs 110 and 112 not being properly aligned with the longitudinal axis L of the mounting member 30. Specifically, lug 112 is displaced relative to lug 110. In this case, the latch pin 90 can still be driven through the misaligned lugs 110 and 112 in the direction D because the spring elements 50 and 60 allow the receiving member 70 to move away from the longitudinal axis L to a certain degree of angular movement.

[0072] When the latch pin 90 is retracted to unlock the wingtip 16 from the main wing section 14 and thereby allow the wingtip 16 to rise or fall, the above process is performed in reverse. Similarly, when the latch pin 90 is retracted from the misaligned lugs 110, 112, it is advantageous for spring elements 50, 60 to allow the receiving member 70 to move angularly away from the longitudinal axis L to a certain extent, as in... Figure 7b In this case.

[0073] In this example, as implemented by the compliant mounting member 20, the range of angular movement of the receiver 70 away from the longitudinal axis L is typically less than 10°, and is generally expected to be about 5° or less. For example, the receiver 70 may move 1°, 2°, 3°, 4°, 5°, 6°, 7°, 8°, 9°, or 10° relative to the longitudinal axis L. The range of radial deflection of the receiver 70 relative to the longitudinal axis L may be about 1 mm.

[0074] Therefore, the compliant mount 20 described herein provides an acceptable but limited amount of compliance, allowing the device mounted in the receiver 70 to be arranged with a degree of misalignment with its mating parts (e.g., lugs 110, 112). Compared to other solutions for providing compliance, this mount 20 is relatively small compared to a typical mechanical universal joint and is less susceptible to the drawbacks of rubber mounts, such as degradation due to environmental conditions and aging.

[0075] Modification and replacement

[0076] Detailed implementation methods and some possible alternatives have been described above. As those skilled in the art will understand, many modifications and further substitutions can be made to the above implementation methods while still benefiting from the invention embodied therein.

[0077] For example, in the above example, the compliant latching units 80, 90, as part of the device assembly 120, are primarily described as part of a folding wingtip actuation mechanism. However, in other examples, the compliant mount 20 can be used to mount the latching units for different purposes, such as locking aircraft doors or securing landing gear in a retracted or extended position. In other examples, the compliant mount 20 of the present invention can be used to support non-actuated components, such as pins or bolts inserted or passing through parts during aircraft assembly, to allow for manufacturing tolerances in positioning or alignment of such parts.

[0078] In the above examples, spring elements 50 and 60 are wave springs, which are compact, provide proper biasing of the receiver 70, and allow sufficient angular movement of the receiver 70 away from the longitudinal axis L. However, in other examples, alternative types of springs can be used for spring elements 50 and 60, such as helical springs, rubber or elastomer springs, or coil springs. However, wave springs (made of metal) are generally superior to coil springs because even if wave springs crack, they can still perform their intended function, while a broken coil spring will lose its effectiveness considerably. Furthermore, rubber or elastomer springs may degrade and age easily, while metal wave springs will not. Therefore, metal wave springs are currently preferred for spring elements 50 and 60.

Claims

1. A compliant mount for an aircraft, the compliant mount being used to attach a device to a structural member of the aircraft, the compliant mount comprising: Mounting components are used to attach to the structural components of the aircraft; A receiving member for supporting the device, the receiving member being connected to the mounting member along a longitudinal axis; as well as One or more spring elements are arranged to elastically bias the receiver to align with the longitudinal axis and allow angular movement of the receiver away from the longitudinal axis.

2. The compliant mounting component according to claim 1, wherein, The mounting member includes a cavity in which the receiving member is mounted, and the cavity allows angular movement of the receiving member away from the longitudinal axis.

3. The compliant mounting component according to claim 2, wherein, In the mounting member, the cavity is defined by an annular wall surrounding the longitudinal axis and a support region projecting inward from the annular wall; The receiving member has a cylindrical outer wall and an end region; and The end region of the receiving member abuts against the support region of the mounting member.

4. The compliant mounting component according to claim 3, wherein, The end region of the receiving member includes an arched region, and the support region of the mounting member includes a complementary arched region, the end region of the receiving member being able to pivot about the longitudinal axis against the complementary arched region.

5. The compliant mounting component according to claim 4, wherein, The mounting component has an axial channel extending through the support region.

6. The compliant mounting component according to claim 5, wherein, The receiving member has a hollow core and an axial channel, the device being supported in the hollow core during use, and the axial channel extending from the hollow core through the end region.

7. The compliant mounting member according to any one of claims 3 to 6, wherein, The one or more spring elements include radial spring elements arranged around the receiver between the annular wall of the mounting member and the cylindrical outer wall of the receiver.

8. The compliant mounting component according to claim 7, wherein, The radial spring element includes a wave spring.

9. The compliant mounting member according to claim 8, wherein, The wave spring of the radial spring element is in the form of a peak and a trough, the peak and the trough being radially oriented and orthogonal to the longitudinal axis.

10. The compliant mount according to any one of claims 7 to 9, wherein, The annular wall of the mounting member is fitted with an annular recess, and the radial spring element is held in the annular recess.

11. The compliant mount according to any one of claims 7 to 10, wherein, The end region of the receiving member protrudes radially outward from the cylindrical outer wall of the receiving member.

12. The compliant mounting member according to claim 11, wherein, The end region of the receiving member is held constrained within the cavity by the radial spring element.

13. The compliant mount according to any one of claims 3 to 12, wherein, The one or more spring elements include axial spring elements arranged around the support region of the mounting member between the support region of the mounting member and the end region of the receiving member.

14. The compliant mounting member according to claim 13, wherein, The axial spring element includes a wave spring.

15. The compliant mounting member according to claim 14, wherein, The wave spring of the axial spring element is in the form of peaks and valleys, which are axially oriented about the longitudinal axis.

16. The compliant mount according to any one of claims 13 to 15, wherein, The support area of ​​the mounting member includes an annular recess, in which the axial spring element is held.

17. An aircraft device assembly comprising a compliant mount according to any of the preceding claims, and an aircraft device supported by the receiving member.

18. The aircraft device assembly according to claim 17 when dependent on claim 6, or claim 17 when dependent on any one of claims 7 to 16 when referencing claim 6, wherein, The device includes a movable member capable of extending longitudinally along the axial channel through the end region of the receiving member and through the support region of the mounting member, thereby changing from a retracted configuration to an extended configuration.

19. The aircraft device assembly according to claim 18, wherein, The device is a latching unit, and the movable member is a latching pin.

20. A folding wing for an aircraft, the folding wing having a main wing portion and a wingtip portion foldable relative to the main wing portion by means of an actuation mechanism, wherein, The actuation mechanism includes the aircraft device assembly according to claim 19. Wherein, the latch pin in the extended configuration locks the angle of the wingtip relative to the main wing portion, and The latch pin in the retracted configuration allows the angle of the wingtip relative to the main wing portion to be adjusted.

21. An aircraft having one or more folding wings as claimed in claim 20.

22. An aircraft having one or more aircraft device components according to any one of claims 17 to 19.

23. A method of attaching a device to a structural member of an aircraft using a compliant mount according to any one of claims 1 to 16, the method comprising: The mounting component of the compliant mount is attached to the structural component of the aircraft; as well as The device is attached to the receiving part of the compliant mount.

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