Shape preserving device for aircraft skin

Abstract

The invention provides a shape maintaining device for an aircraft skin, and the shape maintaining device comprises a spring assembly, one end of the spring assembly is connected to a fixed frame used for connecting the aircraft skin; the plate-shaped assembly is connected to the edge of the other end of the spring assembly and the opposite edge consistent with the curvature of the aircraft skin; one end of the pull rod assembly is connected to the opposite edge of the plate-shaped assembly, the other end of the pull rod assembly is connected to the aircraft skin, and when the aircraft skin is connected to the fixing frame through the shape maintaining device, the pull rod assembly is connected to the plate-shaped assembly through the spring assembly. The spring assembly can elastically deform at least under the gravity of the shape maintaining device and the aircraft skin. The pull rod assembly comprises a knuckle bearing, and the knuckle bearing is constructed to be capable of adjusting the axis direction of the pull rod assembly so that the axis of the pull rod assembly can be perpendicular to the outer surface of the aircraft skin.

Description

Technical Field

[0001] The present invention discloses a shape retention device, specifically, a shape retention device for an aircraft skin, which is used for shape retention of the skin during aircraft maintenance, that is, to prevent the skin from deforming due to external forces during the maintenance process. Background Art

[0002] During aircraft maintenance, due to the replacement of the main structural components of the aircraft, the skin assembly loses its supporting members and thus deforms. Therefore, it is necessary to provide a shape retention device outside the aircraft skin assembly to prevent the skin from deforming.

[0003] The existing shape retention of the aircraft skin is achieved by sleeving an external structural frame outside the aircraft skin assembly. This external structural frame lacks flexible support for the skin assembly that has lost its supporting members, and often causes the skin assembly to deform. In addition, this external structural frame cannot monitor the force on the skin assembly, and due to its shape matching a specific skin assembly, the external structural frame lacks universality. Summary of the Invention

[0004] In view of the above problems in the prior art, the present invention provides a shape retention device for an aircraft skin. The aircraft skin assembly is connected to a gantry frame outside the aircraft skin assembly through this shape retention device to achieve the purpose of shape retention.

[0005] The present invention provides a shape retention device for an aircraft skin, including:

[0006] A spring assembly, one end of the spring assembly is connected to a fixed frame for connecting the aircraft skin;

[0007] A plate-like assembly, the plate-like assembly is connected to the edge of the other end of the spring assembly and the opposite edge that is consistent with the curvature of the aircraft skin;

[0008] A tie rod assembly, one end of the tie rod assembly is connected to the opposite edge of the plate-like assembly, and the other end of the tie rod assembly is connected to the aircraft skin.

[0009] Wherein, the spring assembly is configured such that when the aircraft skin is connected to the fixed frame through the shape retention device, the spring assembly can elastically deform at least under the gravity of the shape retention device and the aircraft skin;

[0010] Wherein, the tie rod assembly includes a spherical plain bearing, and the spherical plain bearing is configured to be able to adjust the axial direction of the tie rod assembly so that the axis of the tie rod assembly is perpendicular to the outer surface of the aircraft skin.

[0011] According to one embodiment, at least one end of the tie rod assembly is provided with the spherical plain bearing.

[0012] According to one embodiment, the spherical plain bearing is configured to be able to adjust the axial direction of the tie rod assembly within a conical angle of 30 degrees.

[0013] According to one embodiment, the tie rod assembly further includes a tension sensor connected to the spherical plain bearing for monitoring the force on the aircraft skin.

[0014] According to one embodiment, the tie rod assembly further includes a nut sleeve screw assembly connected to the tension sensor.

[0015] According to one embodiment, the tension sensor includes a bearing so that the nut sleeve screw assembly can rotate around the axis of the tie rod assembly.

[0016] According to one embodiment, at one end of the tie rod assembly connected to the plate-like assembly, a support is provided. The support includes a cross groove for accommodating the spherical plain bearing, and the cross groove is configured such that the spherical plain bearing can move within the cross groove to adjust the position of the tie rod assembly relative to the plate-like assembly.

[0017] According to one embodiment, at the other end of the tie rod assembly connected to the aircraft skin, it includes a connecting support, and the connecting support is connected to the aircraft skin through a connecting nut.

[0018] According to one embodiment, the support has a T-shaped configuration.

[0019] According to one embodiment, the connecting support has a C-shaped configuration.

[0020] According to one embodiment, the other side of the plate-like assembly has a shape consistent with the shape of the aircraft skin. s

[0021] According to another aspect of the present invention, there is also provided a shape-preserving device for an aircraft skin. The shape-preserving device includes a plurality of shape-preserving devices, and the plurality of shape-preserving devices are installed at different positions of the aircraft skin to ensure uniform force on the aircraft skin.

[0022] The shape-preserving device of the present invention can flexibly cooperate with the hole axis of the aircraft skin assembly. Under the condition of ensuring a certain tensile force, it can avoid damage to the skin assembly caused by the tensile force (for example, the loading force applied by maintenance personnel inside the aircraft during the maintenance process). The shape-preserving device of the present invention can freely adjust the position and direction of the skin assembly within a certain distance and angle range. The shape-preserving device of the present invention has an alarm function to prevent overloading of the tensile force. Description of the Drawings

[0023] When combined with the accompanying drawings, the above objects, as well as other objects, features, and advantages of the present disclosure, will be more fully understood by referring to the following illustrative and non - limiting detailed description of exemplary embodiments of the present disclosure.

[0024] Figure 1 A perspective view of a conformal device for an aircraft skin assembled with the aircraft skin according to an embodiment of the present invention is shown;

[0025] Figure 2 A perspective view of a spring assembly of a conformal device for an aircraft skin according to an embodiment of the present invention is shown;

[0026] Figure 3 A schematic diagram showing the aircraft skin assembly and the spring deforming together under an external force is shown;

[0027] Figure 4 A perspective view of a gantry clamping plate of a conformal device for an aircraft skin according to an embodiment of the present invention is shown;

[0028] Figure 5 A perspective view of a tie - rod assembly of a conformal device for an aircraft skin according to an embodiment of the present invention is shown;

[0029] Figure 6 A cross - sectional view of a tension sensor of a conformal device for an aircraft skin according to an embodiment of the present invention is shown;

[0030] Figure 7 A cross - sectional view of a tie - rod assembly of a conformal device for an aircraft skin according to an embodiment of the present invention is shown, and specifically shows the end nut and the connecting nut;

[0031] Figure 8 An axonometric view of a tie - rod assembly of a conformal device for an aircraft skin according to an embodiment of the present invention is shown, and specifically shows the support and the connecting support. Detailed implementation manners

[0032] The present invention will now be described with reference to the accompanying drawings, in which preferred exemplary embodiments of the present invention are shown. However, the present invention may be implemented in other forms and should not be construed as being limited to the embodiments disclosed herein. The disclosed embodiments are provided to fully convey the scope of the present invention to those skilled in the art. Thus, those skilled in the art understand that changes and modifications can be made within the scope of the present invention according to the guidance in the following detailed description.

[0033] Therefore, it should be understood that the disclosure of the present invention is not limited to the steps of specific components of the described device, as such a device can be changed. It should also be understood that the terms used herein are only for describing specific embodiments and are not intended to be limiting. It should be noted that when used in the specification and the appended claims, the expressions "a", "an", "the", and "said" are intended to mean the presence of one or more elements, unless the context clearly indicates otherwise. Thus, for example, a reference to "a unit" or "the unit" may include several devices and the like. In addition, the words "comprising", "including", "containing", and similar expressions do not exclude other elements or steps.

[0034] Figure 1 A perspective view of the conformal device 1 for an aircraft skin assembled with the aircraft skin according to an embodiment of the present invention is shown. As Figure 1 shown, the skin assembly 2 of the aircraft is connected to the gantry frame 3 through the conformal device 1 described in the present invention. Preferably, the skin assembly 2 is a certain fuselage section of the aircraft. However, the present invention is not limited thereto. According to the structure of the skin assembly to be hoisted, a plurality of conformal devices 1 form a set of conformal equipment and are connected to the gantry frame 3, so that the tensile forces on each part of the skin assembly 2 are balanced. Optionally, the gantry frame 3 is fixed to the ground 4.

[0035] Figure 2 A perspective view of the spring assembly 100 of the conformal device 1 for an aircraft skin according to an embodiment of the present invention is shown. As shown in the figure, one end of the spring assembly 100 is connected to the gantry frame 3, and the other end is connected to the gantry clamping plate 200. Generally, a plurality of identical spring assemblies 100 are connected to the gantry frame 3 and the gantry clamping plate 200. The spring assembly 100 is configured such that when the skin assembly 2 is connected to the gantry frame 3 through the conformal device 1, the spring assembly 100 can bear the gravity of the conformal device 1 and the skin assembly 2 and elastically deform at least under this gravity. Through the spring assembly 100, the skin assembly 2 is elastically connected to the gantry frame 3, that is, within a certain vertical height range, the skin assembly 2 is in a floating state, so that significant deformation of the skin assembly 2 can be avoided when subjected to an external force.

[0036] According to one embodiment, 6 spring assemblies 100 of the same specification are connected to the gantry clamping plate 200, and the specific parameters of the spring assembly 100 are as follows:

[0037]

[0038] Figure 3 A schematic diagram showing the aircraft skin assembly and the spring deforming together under an external force is shown. As Figure 3As shown, the skin assembly 2 is suspended and fixed via the spring assembly 100. Under the action of vertical tension, the skin assembly 2 and the spring assembly 100 elastically deform together, and the deformation of the skin assembly 2 is lower than the acceptable deformation threshold of 1 mm.

[0039] Specifically, assuming that the elastic coefficient of the aircraft skin assembly 2 is k2=2024N / mm, the overall elastic coefficient k of the spring assembly 100 and the skin assembly 2 is:

[0040] k=6*k1*k2 / (6*k1+k2)≈538.9N / mm

[0041] The overall deformation of the spring assembly 100 and the skin assembly 2 is ΔL 总 for:

[0042] ΔL 总 =F / k,

[0043] Where F is the vertical tension.

[0044] Deformation ΔL of skin component 2 蒙皮组件 for:

[0045] ΔL 蒙皮组件 =ΔL 总 -ΔL

[0046] Wherein, ΔL is the elastic deformation of the spring assembly 100 .

[0047] For example, when the vertical tension F is 2000N,

[0048] ΔL=F / (6*k1)=2000 / (6×122.4)=2.72mm

[0049] ΔL 总 =F / k=2000 / 538.9=3.71mm

[0050] ΔL 蒙皮组件 =ΔL 总 -ΔL=0.99mm

[0051] In fact, the elastic coefficient k2 of the aircraft skin assembly 2 is>>2024 N / mm. Therefore, suspending the aircraft skin assembly 2 via the spring assembly 100 can significantly reduce and / or avoid deformation of the aircraft skin assembly 2 under tension.

[0052] Figure 4 FIG. 2 shows a perspective view of a gantry plate 200 of a conformal device 1 for aircraft skin according to an embodiment of the present invention. Figure 4As shown, the gantry clamping plate 200 is plate-shaped, and the curvature of the edge near the skin assembly 2 of the aircraft is consistent with the curvature of the cross-section of the skin assembly 2. The curved edge of the gantry clamping plate 200 is connected to a plurality of tie rod assemblies 300. The gantry clamping plate 200 also has an edge opposite to the curved edge and connected to the spring assembly 100, and is further connected to the gantry frame 3 via the spring assembly 100.

[0053] Figure 5 A perspective view of the tie rod assembly 300 of the conformal device 1 for the aircraft skin according to an embodiment of the present invention is shown. One end of the tie rod assembly 300 is connected to the curved edge of the gantry clamping plate 200, and the other end is connected to the aircraft skin assembly 2. As Figure 5 shown, the tie rod assembly 300 includes a support 301, a spherical plain bearing 302, a tension sensor 303, a nut sleeve screw assembly 304, a connecting support 305, etc.

[0054] According to one embodiment, the spherical plain bearing 302 is configured to be able to adjust the axial direction of the tie rod assembly 300 such that the axis of the tie rod assembly 300 is perpendicular to the outer surface of the aircraft skin. Preferably, the spherical plain bearing 302 has an adjustable cone angle of 30 degrees. The spherical plain bearing 302 can adjust the axial direction of the tie rod assembly 300 within the range of its cone angle to be perpendicular to the outer surface of the skin assembly 2. The spherical plain bearing 302 is provided at at least one end of the tie rod assembly 300. Preferably, spherical plain bearings 302 are provided at both ends of the tie rod assembly 300. The spherical plain bearing 302 has a maximum load. When the vertical tension on the skin assembly 2 is too large, for example, the vertical tension is greater than 2000 N, the spherical plain bearing 302 can automatically disconnect, thereby protecting the skin assembly 2.

[0055] Figure 6 A cross-sectional view of the tension sensor 303 of the conformal device 1 for the aircraft skin according to an embodiment of the present invention is shown. As shown, one end of the tension sensor 303 is connected to the spherical plain bearing 302 by thread, and the other end is connected to the nut sleeve 306 via a bearing end cover, a bearing, and a bearing lock nut. The tension sensor 303 can monitor the force condition of the aircraft skin assembly 2 in real time. If the tension exceeds a certain value, the tension sensor 303 alarms to indicate tension overload.

[0056] Figure 7 A cross-sectional view of the tie rod assembly 300 of the conformal device 1 for the aircraft skin according to an embodiment of the present invention is shown. As Figure 7As shown, the tie rod assembly 300 includes a nut sleeve screw assembly 304 connected to a spherical plain bearing 302, wherein one end of the nut sleeve 306 is threadedly connected to the screw 307, and the other end is connected to the tension sensor 303. The nut sleeve 306 can rotate around the screw 307 to adjust the telescopic length of the screw 307, and thus can adjust the axial distance between the two spherical plain bearings 302 according to the actual situation. One end of the screw 307 is connected to the nut sleeve 306, and the other end is connected to the spherical plain bearing 302 or the connecting support 305. Figure 7 It is further shown that the spherical plain bearing 302 is connected to the support 301 or the connecting support 305 through an end nut, the support 301 is connected to the gantry card plate 200 by threaded connection or other means, and the connecting support 305 is connected to the corresponding hole in the skin assembly 2 via screws, connecting nuts and their gaskets.

[0057] Figure 8 An axonometric view of the tie rod assembly 300 of the conformal device 1 for an aircraft skin according to an embodiment of the present invention is shown, and the support 301 and the connecting support 305 are specifically shown. As Figure 8 shown, the support 301 is in a T shape and includes a cross groove for accommodating the spherical plain bearing, so that the position of the spherical plain bearing in the cross groove can be moved as needed, and thus the position of the tie rod assembly 300 relative to the gantry card plate 200 can be adjusted. The connecting support 305 is in a C shape, one side of which is connected to the spherical plain bearing 302 through an end nut, and the other side is connected to the aircraft skin assembly 2 through bolts, connecting nuts and their gaskets.

[0058] During the use of the conformal device 1 for an aircraft skin, first, one end of a plurality of spring assemblies 100 is connected to the gantry frame 3. Then, one side of the gantry card plate 200 is connected to the other ends of the plurality of spring assemblies 100. Finally, the supports 301 of the plurality of tie rod assemblies 300 are connected to the gantry card plate 200, and the connecting supports 305 of the plurality of tie rod assemblies 300 are connected to the aircraft skin assembly 2, and the direction of the tie rod assembly 300 is adjusted so that the axis of each tie rod assembly 300 is perpendicular to the outer surface of the aircraft skin assembly 2.

[0059] The conformal device 1 for an aircraft skin of the present invention can freely adjust the position and direction of the aircraft skin assembly 2 relative to the gantry frame 3 within a certain distance and angle range, so that the aircraft skin assembly 2 can be hoisted flexibly, and under a certain tensile force, damage and deformation of the aircraft skin assembly 2 caused by external force are avoided. Through the tension sensor 303, the conformal device 1 of the present invention can monitor the stress state of the skin assembly 2 in real time and alarm when the stress is abnormal. In addition, when the tensile force on the aircraft skin assembly 2 is too large, the conformal device 1 of the present invention automatically disconnects the connection with the aircraft skin assembly 2 to avoid damage and deformation of the aircraft skin assembly 2.

[0060] Those skilled in the art will recognize that the present disclosure is not limited to the above preferred embodiments. Those skilled in the art will also recognize that modifications and variations are possible within the scope of the appended claims. In addition, by studying the drawings, the disclosure, and the appended claims, those skilled in the art of implementing the claimed disclosure will be able to understand and implement variations of the disclosed embodiments.

Claims

1. A conformal device for an aircraft skin, comprising: A spring assembly, one end of the spring assembly being connected to a fixed frame for connecting the aircraft skin; A plate-like assembly, the plate-like assembly being connected to the edge of the other end of the spring assembly and the opposite edge conforming to the curvature of the aircraft skin; A tie rod assembly, one end of the tie rod assembly being connected to the opposite edge of the plate-like assembly, and the other end of the tie rod assembly being connected to the aircraft skin, wherein the spring assembly is configured such that when the aircraft skin is connected to the fixed frame through the conformal device, the spring assembly can elastically deform at least under the gravity of the conformal device and the aircraft skin; wherein the tie rod assembly includes a spherical plain bearing, and the spherical plain bearing is configured to be able to adjust the axial direction of the tie rod assembly such that the axis of the tie rod assembly is perpendicular to the outer surface of the aircraft skin.

2. The conformal device according to claim 1, wherein, At least one end of the tie rod assembly is provided with the spherical plain bearing.

3. The conformal device according to claim 1, wherein, The spherical plain bearing is configured to be able to adjust the axial direction of the tie rod assembly within a conical angle of 30 degrees.

4. The conformal device according to claim 1, wherein, The tie rod assembly further includes a tension sensor connected to the spherical plain bearing for monitoring the force on the aircraft skin.

5. The conformal device according to claim 4, wherein, The tie rod assembly further includes a nut-sleeve-screw assembly connected to the tension sensor.

6. The conformal device according to claim 5, wherein, The tension sensor includes a bearing so that the nut-sleeve-screw assembly can rotate around the axis of the tie rod assembly.

7. The conformal device according to claim 1, wherein, The tie rod assembly is provided with a support at the end connected to the plate-like assembly, and the support includes a cross slot for accommodating the spherical plain bearing, and the cross slot is configured such that the spherical plain bearing can move within the cross slot to adjust the position of the tie rod assembly relative to the plate-like assembly.

8. The conformal device according to claim 1, wherein, The other end of the tie rod assembly connected to the aircraft skin includes a connection support, and the connection support is connected to the aircraft skin through a connection nut.

9. The conformal device according to claim 7, wherein The support has a T-shaped configuration.

10. The conformal device according to claim 8, wherein, The connection support has a C-shaped configuration.

11. A conformal device for an aircraft skin, the conformal device comprising a plurality of conformal devices as claimed in any one of claims 1-10, and the plurality of conformal devices being installed at different positions of the aircraft skin to ensure uniform force on the aircraft skin.

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