Positioning device and positioning method for a wing support rib

Abstract

This application provides a positioning device and method for a wing support rib, relating to the technical field of aircraft. The positioning device for the wing support rib includes a support assembly and a positioning assembly. The support assembly is disposed within the lower skin, and the positioning assembly is movably connected to the support assembly, used to abut against the support rib to determine its installation position within the lower skin. The position of the positioning assembly on the support assembly can be adjusted according to the design dimensions of the support rib, enabling the determination of the support rib's installation position within the lower skin by abutting against the positioning assembly. This allows for rapid positioning and installation of the support rib, improving installation accuracy and accelerating wing modification work.

Description

Technical Field

[0001] This application relates to the technical field of aircraft, and in particular to a wing support rib positioning device and positioning method. Background Technology

[0002] An aircraft wing is generally composed of a lower skin, an upper skin, a spars, and multiple support ribs. The multiple support ribs are spaced apart on the spars and are arranged together with the spars between the upper and lower skins to support the structural shape of the upper and lower skins.

[0003] During the aircraft development phase, in order to design the performance of the wing under different structures, modifications are made to the basic type of wing by adding or changing the number or position of loads at the lower skin position. This requires changing the number or position of the support ribs.

[0004] Currently, when changing the installation position of the support beam, the R&D personnel directly install each support rib at the designed position of the wing beam or lower skin based on the installation data. This method cannot control the accuracy of the dimensional installation and is inefficient. Summary of the Invention

[0005] This application provides a positioning device and method for wing support ribs, which can more accurately locate the installation position of each support rib and improve the efficiency of wing modification.

[0006] In a first aspect, this application provides a positioning device for a wing support rib, comprising:

[0007] Support components are used to set in the lower skin;

[0008] A positioning component, movably connected to a support component, is used to abut against the support rib to determine the mounting position of the support rib in the lower skin.

[0009] In some embodiments, the positioning component includes:

[0010] The first fixed beam is movably connected to the support assembly;

[0011] A second fixing beam is disposed on the first fixing beam and is used to extend toward the lower skin;

[0012] A positioning plate is disposed on the second fixed beam and has a positioning surface for abutting against the support rib.

[0013] In some embodiments, the positioning component further includes a movable connector, comprising:

[0014] A first connecting part is slidably disposed on the support assembly and is provided with a first fastener for fixing the position of the first connecting part;

[0015] The second connecting part is provided with a second fastener and is fixed to the first fixed beam through the second connecting part.

[0016] In some embodiments, the support component is provided with a mounting groove, and the first connecting portion is slidably embedded in the mounting groove so that the first connecting portion can slide along the extension direction of the mounting groove.

[0017] In some embodiments, the positioning component further includes a reinforcing beam, which is inclined and connected at both ends to the first fixing beam and the support component, respectively.

[0018] In some embodiments, a connecting plate is provided between the first fixed beam or at least one of the support components and the reinforcing beam.

[0019] In some embodiments, the support assembly includes a first support beam and a second support beam, wherein there are two first support beams spaced apart, and the extension direction of the second support beam is not parallel to the extension direction of the first support beam, and the second support beam is connected between at least two of the first support beams.

[0020] The positioning component is disposed on the first support beam.

[0021] In some embodiments, the support assembly further includes a limiting member disposed on the first support beam;

[0022] The limiting member is used to abut against the wing beam to determine the placement position of the support assembly in the lower skin.

[0023] In some embodiments, the limiting member includes at least two limiting beams spaced apart along the extension direction of the first support beam.

[0024] On the other hand, this application provides a method for positioning wing support ribs, including:

[0025] The positioning device for the wing support rib described in the first aspect and any of its embodiments is placed in the lower skin;

[0026] Obtain the installation data of the support rib;

[0027] Adjust the positioning component to the positioning position according to the installation data;

[0028] The support rib is abutted against the positioning component to determine the installation position of the support rib in the lower skin;

[0029] A position mark is set on the support component according to the positioning position of the positioning component on the support component.

[0030] In some implementations, the operation from acquiring the installation data to setting the position mark on the support component is repeated at least once;

[0031] Each set of installation data corresponds to a different modification scheme for the wing.

[0032] The wing support rib positioning device and positioning method provided in this application place the positioning device in the lower skin of the wing during wing rib installation. Based on the installation data of the support rib, the relative position of the positioning component on the support component is adjusted. The installation position of the support rib in the lower skin is determined by making the support rib abut against the positioning component. This enables the positioning and installation of the support rib to be completed quickly, improves the installation accuracy of the support rib, and speeds up the modification work of the wing. Attached Figure Description

[0033] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0034] Figure 1 This is a schematic diagram of the positioning device for the wing support rib in an embodiment of this application;

[0035] Figure 2 This is a schematic diagram of the supporting components in the embodiments of this application;

[0036] Figure 3 This is a partial view of the positioning device for the wing support rib in an embodiment of this application;

[0037] Figure 4 This is another partial view of the positioning device for the wing support rib in an embodiment of this application;

[0038] Figure 5 This is a flowchart of the positioning method for the wing support beam in the embodiments of this application.

[0039] Explanation of reference numerals in the attached figures:

[0040] 100. Support component; 110. First support beam; 111. Mounting slot; 120. Second support beam; 130. Limiting beam;

[0041] 200. Positioning assembly; 210. First fixed beam; 220. Second fixed beam; 230. Positioning plate; 240. Reinforcing beam; 250. Connecting plate; 260. Movable connector; 261. First connecting part; 262. Second connecting part; 263. Set screw;

[0042] 300. Supporting ribs.

[0043] The accompanying drawings illustrate specific embodiments of this application, which will be described in more detail below. These drawings and descriptions are not intended to limit the scope of the concept in any way, but rather to illustrate the concept of this application to those skilled in the art through reference to particular embodiments. Detailed Implementation

[0044] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this application as detailed in the appended claims.

[0045] Figure 1 This is a schematic diagram of the positioning device for the wing support rib in the embodiments of this application.

[0046] Reference Figure 1 This application provides a positioning device for a wing support rib, including a support assembly 100 and a positioning assembly 200. The support assembly 100 is disposed in the lower skin of the wing, and the positioning assembly 200 is movably connected to the support assembly 100 to position the support rib 300 against the support assembly 100 to determine the installation position of the support rib 300 in the lower skin.

[0047] When installing the support rib 300 in the lower skin of the wing, the support assembly 100 is set in the lower skin. Then, according to the installation dimensions of the support rib 300 in the lower skin, the relative position of the positioning assembly 200 on the support assembly 100 is adjusted. After the support beam is set in the lower skin, the installation position of the support rib 300 is determined by abutting against the positioning assembly 200. Then, the support rib 300 is fixed relative to the wing spars or the lower skin, so as to achieve quick and accurate installation of the support rib 300.

[0048] The structure of the support component 100 can be adapted to the structure of the lower skin or wing spars, and it can be stably supported on the lower skin or wing spars.

[0049] Figure 2 This is a schematic diagram of the structure of the support component in the embodiments of this application.

[0050] Reference Figure 2 In some embodiments, the support assembly 100 may include a first support beam 110 and a second support beam 120. There are two first support beams 110 spaced apart. The extension direction of the second support beam 120 is not parallel to the extension direction of the first support beams 110, and it is connected between at least two first support beams 110. A positioning assembly 200 is disposed on the first support beam 110.

[0051] For example, two first support beams 110 are parallel to each other, and a second support beam 120 is vertically disposed between the two first support beams 110. Multiple second support beams 120 are provided and distributed at intervals along the extension direction of the first support beams 110 to form a stable frame structure, providing more stable support for the positioning component 200.

[0052] In use, after the support assembly 100 is placed inside the lower skin, the extension direction of the first support beam 110 can be parallel to the extension direction of the wing spars. By adjusting the relative position of the positioning assembly 200 on the first support beam 110, the positioning assembly 200 is changed to the installation position of the support rib 300 in the lower skin.

[0053] Optionally, both the first support beam 110 and the second support beam 120 are industrial aluminum profiles with T-slots and are connected and fixed by 90° angle brackets.

[0054] Since the wing has multiple support ribs 300, the number of positioning components 200 can be adapted to the number of support ribs 300 to be installed. A support rib 300 can be positioned by one or more positioning components 200. This embodiment does not impose a specific limitation on this.

[0055] Reference Figure 1 The placement of each positioning component 200 on the support component 100 can be determined according to the design position of each support rib 300. For example, in a wing with two spars, some support ribs 300 are located on the outer sides of the two spars facing away from each other, and some support ribs 300 are located on the inner sides of the two spars. Therefore, some positioning components 200 can be installed on the outer side of the first support beam 110 to position the support ribs 300 that need to be installed on the outer side of the two spars, and some positioning components 200 can be installed on the inner side of the two first support beams 110 to position the support ribs 300 that need to be installed on the inner side of the two spars.

[0056] Figure 3 This is a partial view of the positioning device for the wing support rib in an embodiment of this application.

[0057] Combination Figure 1 and Figure 3 In some embodiments, the positioning assembly 200 may include a first fixing beam 210, a second fixing beam 220, and a positioning plate 230. The first fixing beam 210 is movably connected to the support assembly 100. The second fixing beam 220 is disposed on the first fixing beam 210 and extends downward in the direction of the skin. The positioning plate 230 is disposed on the second fixing beam 220 and has a positioning surface for abutting against the support rib 300.

[0058] The first fixed beam 210 is parallel to the extension direction of the second support beam 120 and is connected to the first support beam 110. For the positioning component 200 located outside the first support beam 110, one end of the first fixed beam 210 is movably connected to the outer sidewall of the first support beam 110; for the positioning component 200 located inside the two first support beams 110, both ends of the first fixed beam 210 are movably connected to the two first support beams 110 respectively.

[0059] The second fixed beam 220 can be set vertically, and the top end of the second fixed beam 220 is connected to the first fixed beam 210. At least two second fixed beams 220 can be set, and the positioning plate 230 is fixed on at least two second fixed beams 220. The positioning plate 230 is set on the upper side of the lower skin, and the surface of the positioning plate 230 facing away from the second fixed beam 220 can serve as a positioning surface for supporting the abutment of the rib 300.

[0060] Optionally, the first fixed beam 210 and the second fixed beam 220 are also industrial aluminum profiles with T-slots. They can also be connected and fixed by corner brackets, and the positioning plate 230 can be fixed to one side of the second fixed beam 220 by hexagonal bolts.

[0061] Figure 4 This is another partial view of the positioning device for the wing support rib in an embodiment of this application.

[0062] Reference Figure 4 In some embodiments, the positioning component 200 further includes a movable connector 260, comprising a first connecting portion 261 and a second connecting portion 262. The first connecting portion 261 is slidably disposed on the support component 100 and is provided with a first fastener for fixing the position of the first connecting portion 261. The second connecting portion 262 is provided with a second fastener and is fixed to the first fixed beam 210 by the second fastener.

[0063] The first connecting portion 261 is disposed on the side of the first support beam 110 and can slide along the extending direction of the first support beam 110, so that the first fixing beam 210 can move along the extending direction of the first support beam 110, thereby changing the installation position of the positioning component 200 on the first support beam 110. For example, the first support beam 110 may be provided with a mounting groove 111, and the first connecting portion 261 is slidably embedded in the mounting groove 111.

[0064] When an industrial aluminum profile with a T-slot is used as the first support beam 110 and the first fixed beam 210, the T-slot can be used as the mounting groove 111. The cross-sectional shape of the first connecting part 261 and the second connecting part 262 can both be T-shaped, and the first fastener and the second fastener can both be set screws 263.

[0065] In some embodiments, the fixed beam may further include a reinforcing beam 240, which is inclined and connected at both ends to the first fixed beam 210 and the first support beam 110, respectively.

[0066] Combination Figure 1 As shown, the first fixed beam 210 is located outside the first support beam 110, with one end connected to the first support beam 110. The first fixed beam 210 located between the two first support beams 110 is connected to the two first support beams 110 at both ends. As a result, the connection strength of the first fixed beam 210 connected to the outside of the first support beam 110 is low. Furthermore, the position of the first fixed beam 210 is fixed only by the movable connector 260. During use, the position of the first fixed beam 210 is easily loosened due to shaking and other problems, which causes the corresponding positioning plate 230 to shift and affects the positioning accuracy of the support rib 300.

[0067] Therefore, by setting the reinforcing beam 240, the connection strength between the first fixed beam 210 and the first support beam 110 can be increased, thereby improving the stability of the positioning assembly 200. Optionally, the reinforcing beam 240 can also be an industrial aluminum profile with a T-slot.

[0068] In some embodiments, a connecting plate 250 is provided between at least one of the first fixed beam 210 or the support assembly 100 and the reinforcing beam 240. This can further improve the connection strength between the reinforcing beam 240 and the first fixed beam 210 and the first support beam 110.

[0069] For example, refer to Figure 1 A connecting plate 250 is provided at the connection between the reinforcing beam 240 and the first supporting beam 110, and at the connection between the reinforcing beam 240 and the first fixed beam 210. The connecting plate 250 can be connected and fixed with fasteners such as bolts, so that when the position of the positioning component 200 is adjusted, both the reinforcing beam 240 and the first fixed beam 210 can slide relative to the first supporting beam 110.

[0070] In some embodiments, the support assembly 100 further includes a limiting member disposed on the first support beam 110. The limiting member is used to abut against the wing beam to determine the placement position of the support assembly 100 in the lower skin.

[0071] When placing the support assembly 100, the positioning of the support assembly 100 in the lower skin can be determined by the cooperation of the limiting component and the wing spars, so that the setting position of each positioning component 200 relative to the lower skin is accurate, and the installation accuracy of each support rib 300 is further improved.

[0072] The number of limiting components can be set according to the number of wing spars in the wing. For example, when the wing includes two wing spars, a limiting component can be provided at the bottom of each first support beam 110. The two limiting components abut against the two wing spars respectively to limit the placement position of the support assembly 100.

[0073] In some embodiments, the limiting member may include at least two limiting beams 130 spaced apart along the extension direction of the first support beam 110.

[0074] In use, the bottom end of the limiting beam 130 abuts against the lower skin to support the support assembly 100 within the lower skin. The sidewall of the limiting beam 130 can abut against the outer side of the wing beam to limit the position of the support assembly 100. Optionally, the limiting beam 130 can also be an industrial aluminum profile with a T-slot.

[0075] In addition, a second support beam 120 can be provided at the location of each limiting beam 130, and corner brackets are provided between the first support beam 110 and the limiting beam 130, between the first support beam 110 and the second support beam 120, and between the second support beam 120 and the limiting beam 130, in order to strengthen the connection strength of the limiting beam 130 and improve the structural stability of the entire support assembly 100.

[0076] The positioning device provided in this application embodiment first uses a limiting member to position the support assembly 100 in the lower skin when installing the support rib 300 into the lower skin. Then, according to the design data of the support rib 300, the relative positions of each positioning component 200 on the support assembly 100 are adjusted, and each support rib 300 is positioned to the installation position using each positioning component 200, thereby improving the installation accuracy and efficiency of the support rib 300.

[0077] Figure 5 This is a flowchart of the positioning method for the wing support beam in the embodiments of this application.

[0078] Reference Figure 5 Based on the above-mentioned positioning device, this embodiment also provides a positioning method for wing support ribs, including steps 501 to 506.

[0079] In step 501, the positioning component 200 is placed in the lower skin.

[0080] Specifically, by having the limiting member cooperate with the lower skin and the wing beam, the placement position of the support assembly 100 is limited, thereby determining the placement position of the support assembly 100.

[0081] In step 502, the installation data of the support rib 300 is obtained.

[0082] The installation data includes the number of support ribs 300 and the specific installation position of each support rib 300, which can be calculated by the R&D personnel based on the wing modification plan, such as by changing the number or position of the loads in the lower skin.

[0083] In step 503, the positioning is adjusted to the designated location based on the installation data.

[0084] After obtaining the installation data for the modification plan, based on the number of support ribs 300 and the installation position of each support rib 300, select a corresponding number of positioning components 200 and install them on the support component 100, and adjust each positioning component 200 to the positioning position so that each positioning plate 230 can determine the installation position of the support rib 300.

[0085] In step 504, the support rib 300 is abutted against the positioning component 200 to determine the installation position of the support rib 300 in the lower skin.

[0086] The support rib 300 directly abuts against the surface of the corresponding positioning plate 230, and the support rib 300 is connected and fixed to the wing beam or lower skin. Furthermore, after all the support ribs 300 are installed, the positioning device can be removed, and the installation position of each support rib 300 can be measured and verified to ensure that it matches the requirements of the installation data, thus guaranteeing the installation accuracy of the support ribs 300.

[0087] In step 505, a position mark is set on the support component 100 according to the positioning position of the positioning component 200 on the support component 100.

[0088] Position marks can be set on the first support beam 110 of the support component 100 according to the position of the first fixed beam 210 in the positioning component 200. The position of each first fixed beam 210 can be marked on the surface of the first support beam 110 by means of graphics or colors using a marker pen, or by means of engraving marks on the surface of the first support beam 110 using a carving knife.

[0089] In some embodiments, the operation from acquiring the installation data to setting the position mark on the support assembly is repeated at least once. Each acquisition of installation data corresponds to a different modification scheme for the wing.

[0090] When modifying the wing, different modification schemes need to be proposed and tested separately. The scheme with the best performance is then selected for further testing. Therefore, multiple sets of installation data for the support rib 300 need to be calculated for different modification schemes, and these sets of installation data are tested sequentially. After selecting the set of installation data with the best performance, the support rib 300 with the optimal installation data is reinstalled in the wing for subsequent testing.

[0091] After testing all installation data, the positioning component 200 has different positioning positions on the support component 100 for different installation data, and different position marks are set on the support component 100. This allows R&D personnel to quickly set each positioning component 200 to the corresponding positioning position according to the corresponding position marks, facilitating repeated installation operations of the support rib 300 and improving the efficiency of wing modification. In actual operation, the position marks of the same positioning component under different installation data can be distinguished by changing the color, shape, etc., and this embodiment does not impose too many restrictions on this.

[0092] The embodiments of this application have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are only for the purpose of helping to understand the method and core ideas of this application. Furthermore, any changes or modifications made by those skilled in the art based on the ideas of this application, and on the specific implementation methods and application scope of this application, are all within the scope of protection of this application. Therefore, the content of this specification should not be construed as a limitation of this application.

Claims

1. A positioning device for a wing support rib, characterized by, include: A support assembly is provided in the lower skin, and the support assembly is provided with a mounting groove; A positioning component, movably connected to a support component, is used to abut against the support rib to determine the mounting position of the support rib in the lower skin, the positioning component comprising: The first fixed beam is movably connected to the support assembly; A second fixing beam is disposed on the first fixing beam and is used to extend toward the lower skin; A positioning plate is disposed on the second fixed beam and has a positioning surface for abutting against the support rib; Active connectors include: A first connecting part is slidably disposed on the support assembly and is provided with a first fastener for fixing the position of the first connecting part; The second connecting part is provided with a second fastener and is fixed to the first fixed beam through the second connecting part; The first connecting part is slidably embedded in the mounting groove so that the first connecting part can slide along the extension direction of the mounting groove.

2. The wing support rib positioning device of claim 1, wherein, The positioning component also includes a reinforcing beam, which is inclined and connected at both ends to the first fixing beam and the support component, respectively.

3. The positioning device for the wing support rib according to claim 2, characterized in that, A connecting plate is provided between the first fixed beam or at least one of the supporting components and the reinforcing beam.

4. The positioning device for the wing support rib according to any one of claims 1-3, characterized in that, The support assembly includes a first support beam and a second support beam. There are two first support beams that are spaced apart. The extension direction of the second support beam is not parallel to the extension direction of the first support beam, and it is connected between at least two of the first support beams. The positioning component is disposed on the first support beam.

5. The positioning device for the wing support rib according to claim 4, characterized in that, The support assembly also includes a limiting member disposed on the first support beam; The limiting member is used to abut against the wing beam to determine the placement position of the support assembly in the lower skin.

6. The positioning device for the wing support rib according to claim 5, characterized in that, The limiting component includes at least two limiting beams arranged at intervals along the extension direction of the first support beam.

7. A method for positioning wing support ribs, characterized in that, include: The positioning device for the wing support rib as described in any one of claims 1-6 is placed in the lower skin; Obtain the installation data of the support rib; Adjust the positioning component to the positioning position according to the installation data; The support rib is abutted against the positioning component to determine the installation position of the support rib in the lower skin; A position mark is set on the support component according to the positioning position of the positioning component on the support component.

8. The method for positioning wing support ribs according to claim 7, characterized in that, The operation from acquiring the installation data to setting the position mark on the support component is repeated at least once; Each set of installation data corresponds to a different modification scheme for the wing.

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