A slat trailing edge structure and wing
Patent Information
- Application Number
- CN202522296396.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-10-30
- Publication Date
- 2026-10-09
- Estimated Expiration
- 2035-10-30
AI Technical Summary
[0002]现有技术如图1，目前对于飞机缝翼尾缘结构，主要由上蒙皮1’、下蒙皮2’、后梁500等结构二次胶结而成，后梁500采用C型结构；如图2所示，具体的，下蒙皮2’采用搭接的连接形式，具体的下蒙皮2’包括尾缘下蒙皮200和缝翼下蒙皮400，二者采用搭接的连接形式；而上蒙皮1’采用蒙皮对接的连接形式，具体的上蒙皮1’包括尾缘上蒙皮100和缝翼上蒙皮300，进而将尾缘上蒙皮100、尾缘下蒙皮200、缝翼上蒙皮300、缝翼下蒙皮400、后梁500、上连接带板600等结构连接而成，因为后梁500通常单独设置且为C型结构，但是这种缝翼尾缘结构在安装时，需要考虑到尾缘上蒙皮100、尾缘下蒙皮200、缝翼上蒙皮300、缝翼下蒙皮400、后梁500、上连接带板600等结构的对接要求，受到翼型高度带来的连接及紧固件安装空间限制，同时尾缘上蒙皮100、尾缘下蒙皮200、缝翼上蒙皮300、缝翼下蒙皮400、后梁500、上连接带板600等结构相互独立设置，使得其零件数目较多、重量较大、装配时相互之间的安装间隙难以匹配协调
[0016]本实用新型提供的一种缝翼尾缘结构，包括缝翼蒙皮、尾缘蒙皮、支撑梁，缝翼蒙皮包括缝翼下蒙皮，尾缘蒙皮包括尾缘下蒙皮和尾缘上蒙皮；沿第一方向，尾缘下蒙皮与尾缘上蒙皮二者之间，一端设有间隔，另一端连接；尾缘下蒙皮与尾缘上蒙皮设有间隔的一端和缝翼下蒙皮的一端为一体化连接形成连体结构；支撑梁设于尾缘上蒙皮和连体结构之间；支撑梁包括相邻连接的第一梁和第二梁，第二梁一端与第一梁一体化连接，另一端与连体结构一体化连接，第一梁与尾缘上蒙皮连接，使得支撑梁与缝翼下蒙皮和尾缘下蒙皮呈一体化连接，相较于现有技术中，其无需使用连接带板，同时支撑梁与缝翼下蒙皮和尾缘下蒙皮呈一体化连接，可以减少装配零件数量，有效减轻缝翼结构重量，进而提高结构承载效率，减少了缝翼零件成型和结构装配的工作量，充分发挥一体化的优势，降低装配难度，有效降低结构制造成本。
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Figure CN224829598U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aircraft manufacturing technology, and in particular to a slat tail edge structure and wing. Background Technology
[0002] Existing technologies such as Figure 1 Currently, the tail edge structure of aircraft slats is mainly composed of upper skin 1', lower skin 2', and rear spars 500, which are bonded together in a secondary manner. The rear spars 500 adopts a C-shaped structure. Figure 2 As shown, specifically, the lower skin 2' adopts an overlapping connection form, specifically including the trailing edge lower skin 200 and the slat lower skin 400, which are connected by an overlapping connection; while the upper skin 1' adopts a butt-joint connection form, specifically including the trailing edge upper skin 100 and the slat upper skin 300, and then connecting the trailing edge upper skin 100, trailing edge lower skin 200, slat upper skin 300, slat lower skin 400, rear beam 500, upper connecting strip 600 and other structures to form a structure, because the rear beam 500 is usually set separately and is a C-shaped structure, but this When installing the slat trailing edge structure, the docking requirements of the upper trailing edge skin 100, lower trailing edge skin 200, upper slat skin 300, lower slat skin 400, rear beam 500, and upper connecting plate 600 need to be considered. Due to the limitations of connection and fastener installation space caused by the airfoil height, and the fact that the upper trailing edge skin 100, lower trailing edge skin 200, upper slat skin 300, lower slat skin 400, rear beam 500, and upper connecting plate 600 are set up independently, the number of parts is large, the weight is large, and the installation gaps between them are difficult to match and coordinate during assembly. Utility Model Content
[0003] The purpose of this invention is to provide a slat trailing edge structure and a wing that can improve the structural rationality of the slat trailing edge structure and the wing.
[0004] To achieve this objective, the present invention adopts the following technical solution:
[0005] A slat trailing edge structure includes: a slat skin, the slat skin including a lower slat skin; a trailing edge skin, the trailing edge skin including a lower trailing edge skin and an upper trailing edge skin; along a first direction, the lower trailing edge skin and the upper trailing edge skin are spaced apart at one end and connected at the other end; the spaced-apart end of the lower trailing edge skin and the upper trailing edge skin and the lower slat skin are integrally connected to form a continuous structure; a support beam is disposed between the upper trailing edge skin and the continuous structure; the support beam includes an adjacently connected first beam and a second beam, one end of the second beam is integrally connected to the first beam, and the other end is integrally connected to the continuous structure, and the first beam is connected to the upper trailing edge skin.
[0006] As an optional solution for the slat trailing edge structure provided by this utility model, the slat skin also includes an upper slat skin, which is connected to the side of the trailing edge upper skin away from the first beam.
[0007] As an optional solution for the slat tail edge structure provided by this utility model, an installation groove is provided on the side of the upper skin of the tail edge away from the first beam, and the upper skin of the slat is disposed in the installation groove.
[0008] As an optional solution for the slat trailing edge structure provided by this utility model, the depth of the mounting groove is consistent with the thickness of the skin on the slat.
[0009] As an optional solution to the slat trailing edge structure provided by this utility model, the slat trailing edge structure also includes a trailing edge pad, which is integrally connected to the side of the lower trailing edge skin facing the upper trailing edge skin.
[0010] As an optional solution for the slat trailing edge structure provided by this utility model, the support beam extends along the second direction, which is at an angle to the first direction. The trailing edge lower skin, the trailing edge pad on the trailing edge lower skin, the trailing edge upper skin, and the second beam surround to form a receiving cavity. The slat trailing edge structure also includes a full-height honeycomb core, which is installed in the receiving cavity.
[0011] As an optional solution to the slat trailing edge structure provided by this utility model, the slat trailing edge structure also includes sealing ribs located at both ends of the trailing edge skin along the second direction, and the sealing ribs at both ends are respectively connected to the inner surfaces of the lower trailing edge skin and the upper trailing edge skin.
[0012] As an optional solution to the slat trailing edge structure provided by this utility model, the sealing rib has the same shape as the two ends of the receiving cavity, and the sealing rib is used to seal the two ends of the receiving cavity.
[0013] As an optional solution to the slat trailing edge structure provided by this utility model, the sealing rib includes a first sealing rib and a second sealing rib arranged along a first direction, and the cross-section of the first sealing rib and / or the second sealing rib is quadrilateral.
[0014] Secondly, this utility model also provides a wing, including a wing box and a slat trailing edge structure disposed at the end of the wing box.
[0015] The beneficial effects of this utility model are:
[0016] This utility model provides a slat trailing edge structure, including a slat skin, a trailing edge skin, and a support beam. The slat skin includes a lower slat skin, and the trailing edge skin includes a lower trailing edge skin and an upper trailing edge skin. Along a first direction, the lower trailing edge skin and the upper trailing edge skin are spaced apart at one end and connected at the other end. The spaced-apart end of the lower trailing edge skin and the upper trailing edge skin and the end of the lower slat skin are integrally connected to form a continuous structure. The support beam is disposed between the upper trailing edge skin and the continuous structure. The support beam includes an adjacently connected first beam and a second beam, one end of the second beam being connected to the first beam. One end of the beam is integrated with the other end, and the other end is integrated with the main structure. The first beam is connected to the upper skin of the trailing edge, so that the support beam is integrated with the lower skin of the slat and the lower skin of the trailing edge. Compared with the existing technology, it does not require the use of connecting strip plates. At the same time, the integrated connection between the support beam and the lower skin of the slat and the lower skin of the trailing edge can reduce the number of assembly parts, effectively reduce the weight of the slat structure, thereby improving the structural load-bearing efficiency, reducing the workload of slat part forming and structural assembly, giving full play to the advantages of integration, reducing assembly difficulty, and effectively reducing structural manufacturing costs. Attached Figure Description
[0017] Figure 1 It is one of the existing structural forms for connecting the slat box section and the trailing edge;
[0018] Figure 2 It is one of the existing structural forms for connecting the slat box section and the trailing edge;
[0019] Figure 3 This is a structural side view of the slat trailing edge structure provided in a specific embodiment of this utility model;
[0020] Figure 4 This is one of the exploded schematic diagrams of the slat trailing edge structure provided in a specific embodiment of this utility model;
[0021] Figure 5 This is one of the exploded schematic diagrams of the slat trailing edge structure provided in a specific embodiment of this utility model.
[0022] In the picture:
[0023] 1' Upper skin; 2' Lower skin;
[0024] 100. Upper trailing edge skin; 200. Lower trailing edge skin; 300. Upper slat skin; 400. Lower slat skin; 500. Rear beam; 600. Upper connecting strip plate; 700. Full-height honeycomb core; 800. Trailing edge pad;
[0025] 1. Slatted skin; 2. Trailing edge skin; 3. Support beam; 4. Trailing edge pad; 5. Full-height honeycomb core; 6. Sealing rib;
[0026] 11. Lower skin of the slat; 12. Upper skin of the slat;
[0027] 21. Lower tail edge skin; 22. Upper tail edge skin; 221. Mounting groove;
[0028] 31. First beam; 32. Second beam;
[0029] 61. First sealing rib; 62. Second sealing rib;
[0030] X1, first direction; X2, second direction; X3, third direction. Detailed Implementation
[0031] To make the technical problems solved by this utility model, the technical solutions adopted, and the technical effects achieved clearer, the technical solutions of the embodiments of this utility model will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.
[0032] In the description of this utility model, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.
[0033] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.
[0034] like Figure 1 , Figure 2As shown, the current aircraft slat tail edge structure mainly consists of an upper tail edge skin 100, a lower tail edge skin 200, an upper slat skin 300, a lower slat skin 400, a rear sparsity 500, an upper connecting strip 600, a full-height honeycomb core 700, and a tail edge pad 800, all connected together. The rear sparsity 500 is usually a separate C-shaped structure. However, when installing this slat tail edge structure, it is necessary to consider the upper tail edge skin 100, the lower tail edge skin 200, the upper slat skin 300, and the lower slat skin 400. The docking requirements of structures such as the skin 400, rear beam 500, and upper connecting plate 600 are limited by the connection and fastener installation space caused by the airfoil height. At the same time, structures such as the trailing edge upper skin 100, trailing edge lower skin 200, slat upper skin 300, slat lower skin 400, rear beam 500, upper connecting plate 600, full-height honeycomb core 700, and trailing edge pad 800 are set up independently, resulting in a large number of parts, a large weight, and difficulty in matching and coordinating the installation gaps between them during assembly.
[0035] To avoid the problems of numerous parts, heavy weight, difficult connection, high precision requirements for parts manufacturing, and many assembly steps in traditional slat trailing edge structures, this embodiment provides a slat trailing edge structure that can reduce the number of assembly parts, effectively reduce the weight of the aircraft slat trailing edge structure, improve structural load-bearing efficiency, reduce the workload of slat part forming and structural assembly, give full play to the advantages of the integrated composite structure, improve the aerodynamic shape quality of the lower skin, reduce assembly difficulty, and effectively reduce structural manufacturing costs.
[0036] Specifically, such as Figures 3 to 5 As shown, a slat trailing edge structure includes a slat skin 1, a trailing edge skin 2, and a support beam 3. The slat skin 1 includes a lower slat skin 11; the trailing edge skin 2 includes a lower trailing edge skin 21 and an upper trailing edge skin 22; along a first direction X1, the lower trailing edge skin 21 and the upper trailing edge skin 22 are separated at one end and connected at the other end; the separated end of the lower trailing edge skin 21 and the upper trailing edge skin 22 and the lower slat skin 11 are integrally connected to form a continuous structure; the support beam 3 is located between the upper trailing edge skin 22 and the continuous structure; the support beam 3 includes an adjacent first beam 31 and a second beam 32, one end of the second beam 32 is integrally connected to the first beam 31, and the other end is integrally connected to the continuous structure, and the first beam 31 is connected to the upper trailing edge skin 22.
[0037] It is understood that the slat skin 1 includes a lower slat skin 11. Along the first direction X1, there is a gap at one end between the lower trailing edge skin 21 and the upper trailing edge skin 22, and the other end is connected, so that the gapped end of the lower trailing edge skin 21 and the upper trailing edge skin 22 is an open structure. At the same time, the gapped end of the lower trailing edge skin 21 and the upper trailing edge skin 22 and the end of the lower slat skin 11 are integrally connected to form a connected structure. That is, one end of the lower trailing edge skin 21 and the lower slat skin 11 is an integral connected structure. Meanwhile, the support beam 3 is located between the upper trailing edge skin 22 and the connected structure, and the support beam 3 includes an adjacently connected first beam 31 and a second beam 32. One end of the second beam 32 is integrally connected to the first beam 31, and the other end is integrally connected to the connected structure. The first beam 31 and the upper trailing edge skin 22 are integrally connected to the upper trailing edge skin 11. The skin 22 connection integrates the first beam 31, the second beam 32, the lower skin 11 of the slat, and the lower skin 21 of the trailing edge into a single unit, forming a continuous structure. This is equivalent to eliminating one upper connecting plate component compared to existing technologies, thereby reducing the weight of the aircraft structure, lowering the manufacturing cost of parts, reducing the number of assembly parts, effectively reducing the weight of the slat structure, and improving the structural load-bearing efficiency. Compared to existing technologies, it also reduces the assembly steps of the lower skin of the slat and the trailing edge assembly, thereby reducing the number of fasteners required, reducing the weight of the aircraft structure, simplifying the component assembly process, reducing assembly difficulty, improving the shape quality of the component after molding, reducing the workload of slat component molding and structural assembly, fully leveraging the advantages of integration, reducing assembly difficulty, and effectively reducing structural manufacturing costs.
[0038] It should be noted that in this embodiment, the first beam 31, the second beam 32, the lower skin of the slat 11, and the lower skin of the trailing edge 21 are all integrally connected, thus presenting a one-piece structure. This is equivalent to eliminating the conventional connection structure where fasteners are present at the rear beam 500, the lower skin of the trailing edge 200, and the lower skin of the slat 400. As a result, the force transmission does not need to go through the process of the rear beam 500, the lower skin of the trailing edge 200, and the lower skin of the slat 400, because the first beam 31, the second beam 32, the lower skin of the slat 11, and the lower skin of the trailing edge 21 are already an integral structure, which can effectively reduce the stress concentration phenomenon in the fastener connection area.
[0039] Alternatively, in this embodiment, such as Figure 5 As shown, the first direction X1 is the airflow direction of the slat trailing edge structure, the second direction X2 is the spanwise direction of the slat trailing edge structure, and the third direction X3 is the thickness direction of the slat trailing edge structure. The first direction X1, the second direction X2, and the third direction X3 are set at an angle to each other.
[0040] Understandably, with Figure 5For example, the first direction X1 is the airflow direction on the surface of the slat trailing edge structure, which can be understood as the length direction of the slat trailing edge structure. The second direction X2 is the spanwise direction of the slat trailing edge structure, which can be understood as the width direction of the slat trailing edge structure. The third direction X3 is the thickness direction of the slat trailing edge structure. At the same time, the first direction X1, the second direction X2 and the third direction X3 are set at an angle to each other, for example, 90°.
[0041] Alternatively, in this embodiment, such as Figure 3 , Figure 4 , Figure 5 As shown, the slat skin 1 also includes a slat upper skin 12, which is connected to the trailing edge upper skin 22 on the side opposite to the first beam 31.
[0042] Understandably, the slat skin 1 also includes a slat upper skin 12, which is connected to the trailing edge upper skin 22. Specifically, the connection point is on the side of the trailing edge upper skin 22 away from the first beam 31. This arrangement ensures the installation of the slat upper skin 12. However, the slat upper skin 12 is not directly on the first beam 31, but is connected to the trailing edge upper skin 22, thereby ensuring the layup effect of the slat upper skin 12, reducing the manufacturing process of the individual structure, thus reducing the difficulty of structural manufacturing, and improving the structural rationality of the slat trailing edge structure.
[0043] Alternatively, in this embodiment, such as Figure 3 , Figure 4 , Figure 5 As shown, the upper skin 22 of the trailing edge is provided with a mounting groove 221 on the side opposite to the first beam 31, and the upper skin 12 of the slat is disposed in the mounting groove 221.
[0044] It is understandable that the upper skin 22 of the trailing edge is provided with a mounting groove 221 on the side away from the first beam 31, so that the side of the upper skin 22 of the trailing edge away from the first beam 31 forms a "lower limit structure", thereby effectively ensuring the connection effect between the upper skin 12 of the slat and the upper skin 22 of the trailing edge, and thus improving the structural rationality of the trailing edge structure of the slat.
[0045] It should be noted that the upper skin 12 of the slat is connected to the mounting groove 221 of the upper skin 12 of the slat, which is equivalent to forming an overlapping connection. In contrast, the existing technology usually uses a connecting strip plate for connection. However, the connecting strip plate may not be aligned with the axis of the component, or when the direction of the external force does not pass through the centroid of the component, an eccentric effect will occur, resulting in additional bending moment or torque, which will affect the overall stiffness of the structure. In this embodiment, the upper skin 12 of the slat overlaps with the mounting groove 221 of the upper skin 12 of the slat, which can eliminate the eccentric effect of the force transmission of the connecting strip plate, improve the structural efficiency, and thus improve the structural rationality and actual use effect of the slat trailing edge structure.
[0046] Alternatively, in this embodiment, such as Figure 3 , Figure 4 , Figure 5 As shown, the depth of the mounting groove 221 is consistent with the thickness of the skin 12 on the slat.
[0047] Understandably, by setting the upper skin 12 of the slat to be set within the mounting groove 221, and by ensuring that the depth of the mounting groove 221 matches the thickness of the upper skin 12 of the slat, the connection between the upper skin 12 of the slat and the upper skin 22 of the trailing edge can be guaranteed while minimizing any height difference between their surfaces. This smooth connection ensures the forming effect of the upper skin 12 of the slat and the upper skin 22 of the trailing edge, thereby guaranteeing the aerodynamic shape quality of the slat trailing edge structure. In other words, it improves the structural rationality and practical performance of the slat trailing edge structure.
[0048] Alternatively, in this embodiment, such as Figure 3 , Figure 4 , Figure 5 As shown, the slat trailing edge structure also includes a trailing edge pad 4, which is integrally connected to the side of the lower trailing edge skin 21 facing the upper trailing edge skin 22.
[0049] Understandably, with Figure 1 , Figure 2 For example, the current aircraft slat trailing edge structure is mainly composed of upper skin 1', lower skin 2', rear spars 3', and trailing edge pad 800, which are bonded together in a secondary manner. The trailing edge pad 800 is usually set independently, which leads to problems such as a large number of parts, heavy weight, and difficulty in matching and coordinating the installation gaps between them during assembly. In this embodiment, the trailing edge pad 4 aims to further optimize the installation effect of the full-height honeycomb core 5. Specifically, the trailing edge pad 4 is integrated and connected to the side of the lower trailing edge skin 21 facing the upper trailing edge skin 22, so that the trailing edge pad 4 and the trailing edge skin 2 are integrated into one structure. This reduces the number of parts and the separate structural manufacturing process of the pad structure, thereby reducing the difficulty of structural manufacturing, reducing the workload of structural assembly, and reducing the structural manufacturing cost. At the same time, it improves the structural rationality and actual use effect of the slat trailing edge structure.
[0050] Alternatively, in this embodiment, the slat lower skin 11, support beam 3, trailing edge lower skin 21, and trailing edge pad 4 are integrated by a bonding process.
[0051] It is understandable that by setting up multiple film-coating surfaces and corresponding tooling, the shape of the composite material is fixed before laying and curing, thereby ensuring the integrated structure forming effect.
[0052] Alternatively, in this embodiment, such as Figure 3 , Figure 4 , Figure 5 As shown, the support beam 3 extends along the second direction X2, which is at an angle to the first direction X1. The trailing edge lower skin 21, the trailing edge pad 4 on the trailing edge lower skin 21, the trailing edge upper skin 22, and the second beam 32 form a receiving cavity. The slat trailing edge structure also includes a full-height honeycomb core 5, which is installed in the receiving cavity.
[0053] Understandably, the lower trailing edge skin 21, the trailing edge pad 4 on the lower trailing edge skin 21, the upper trailing edge skin 22, and the second beam 32 together form a receiving cavity, which can then accommodate the full-height honeycomb core 5. Existing technologies typically form the full-height honeycomb core 5 and other structures through secondary bonding, resulting in a large number of parts, significant weight, and difficulty in matching and coordinating installation gaps during assembly. In this embodiment, the integrated trailing edge pad 4 connected to the lower trailing edge skin 21 reduces the individual manufacturing process of the pad and other structures, thereby reducing the difficulty of structural manufacturing, the workload of structural assembly, and the cost of structural manufacturing.
[0054] Alternatively, in this embodiment, such as Figure 4 , Figure 5 As shown, the slat trailing edge structure also includes sealing ribs 6 located at both ends of the trailing edge skin 2 along the second direction X2, with the sealing ribs 6 at both ends connected to the inner surfaces of the lower trailing edge skin 21 and the upper trailing edge skin 22, respectively.
[0055] It is understandable that the sealing ribs 6 at both ends along the second direction X2 are connected to the inner surfaces of the lower tail edge skin 21 and the upper tail edge skin 22 respectively, so that the openings of the receiving cavity at both ends in the second direction X2 are blocked, thereby ensuring that the full-height honeycomb core 5 inside the receiving cavity is stably installed therein.
[0056] Alternatively, in this embodiment, such as Figure 4 , Figure 5 As shown, the sealing rib 6 has the same shape as the two ends of the receiving cavity, and the sealing rib 6 is used to seal the two ends of the receiving cavity.
[0057] Understandably, the sealing rib 6 has the same shape as the two ends of the receiving cavity and is used to seal the two ends of the receiving cavity. This ensures that the sealing rib 6 does not affect the shape of the slat trailing edge structure, preventing any protrusions or depressions, thus ensuring the rationality of the structure. In other words, it ensures the forming effect of the upper skin 12 and the upper skin 22 of the trailing edge, thereby ensuring the aerodynamic shape quality of the slat trailing edge structure and improving the structural rationality and actual use effect of the slat trailing edge structure.
[0058] Alternatively, in this embodiment, such as Figure 4 , Figure 5As shown, the sealing rib 6 includes a first sealing rib 61 and a second sealing rib 62 arranged along the first direction X1, and the cross-section of the first sealing rib 61 and / or the second sealing rib 62 is quadrilateral.
[0059] It is understood that the sealing rib 6 includes a first sealing rib 61 and a second sealing rib 62 arranged along the first direction X1, wherein the cross-section of the first sealing rib 61 and / or the second sealing rib 62 along the plane containing the third direction X3 and the second direction X2 is quadrilateral. Figure 4 , Figure 5 Taking this as an example, the first sealing rib 61 has a quadrilateral cross-section along the plane containing the third direction X3 and the second direction X2, while the second sealing rib 62 does not have a quadrilateral cross-section along the plane containing the third direction X3 and the second direction X2; it is just a conventional sealing rib structure. The first sealing rib 61, with its quadrilateral cross-section along the plane containing the third direction X3 and the second direction X2, can provide better structural strength, further improving the structural strength of the slat trailing edge structure, and thus improving the structural stability of the slat trailing edge structure, enabling it to cope with high-altitude and strong airflow application scenarios. Of course, it is also possible that the first sealing rib 61 does not have a quadrilateral cross-section along the third direction X3, while the second sealing rib 62 does; or, both the first sealing rib 61 and the second sealing rib 62 have quadrilateral cross-sections along the third direction X3. This setting can further improve the structural stability of the slat trailing edge structure, thereby improving the actual use effect of the slat trailing edge structure.
[0060] Alternatively, in this embodiment, such as Figure 4 , Figure 5 As shown, as a preferred embodiment, only the cross-section of the first sealing rib 61 along the plane containing the third direction X3 and the second direction X2 is quadrilateral.
[0061] Understandably, only the first sealing rib 61 has a quadrilateral cross-section along the plane containing the third direction X3 and the second direction X2, while the second sealing rib 62 is not a quadrilateral structure along the plane containing the third direction X3 and the second direction X2. It is just a conventional sealing rib structure. This setting can ensure that the end of the slat trailing edge structure is reinforced by the first sealing rib 61. Since the second sealing rib 62 is not a quadrilateral structure along the plane containing the third direction X3 and the second direction X2, it can further reduce the weight of the sealing rib 6, thereby reducing the weight of the overall slat trailing edge structure. This maximizes the performance of the slat trailing edge structure, improves the structural rationality and actual performance of the slat trailing edge structure, and also reduces the manufacturing cost of the slat trailing edge structure.
[0062] As an option, such as Figure 3 , Figure 4 , Figure 5 As shown, this embodiment also includes a method for installing a slat trailing edge structure, specifically comprising the following steps:
[0063] S1, the lower slat skin 11, support beam 3, lower tail edge skin 21, upper tail edge skin 22, full-height honeycomb core 5, and sealing ribs at both ends are integrated into one piece through a laying process.
[0064] S2: Connect one end of the upper trailing edge skin 22 away from the slat skin 1 to one end of the lower trailing edge skin 21 away from the slat skin 1 using fasteners, and connect the upper trailing edge skin 22 to the first beam 31 of the support beam 3 using fasteners.
[0065] S3: Connect the upper skin 12 of the slat to the mounting groove 221 on the side of the upper skin 22 of the trailing edge away from the first beam 31 using fasteners, thus completing the installation of the trailing edge structure of the slat.
[0066] In step S1, the upper skin 22 of the trailing edge and the sealing ribs 6 at both ends need to be laid separately. After the laying is completed, the full-height honeycomb core 5 is fixed and cured, that is, the co-curing process is used for connection. Then, the lower skin 11 of the slat, the support beam 3, the lower skin 21 of the trailing edge, the upper skin 22 of the trailing edge, the full-height honeycomb core 5, the sealing ribs 6 at both ends and the trailing edge pad 4 are formed into one piece through the laying process.
[0067] This embodiment provides a method for installing a slat trailing edge structure. Since the lower trailing edge skin 21 and the lower slat skin 11 are integrated into a single structure at one end, and a support beam 3 is located between the upper trailing edge skin 22 and the integrated structure, the support beam 3 includes an adjacent first beam 31 and a second beam 32. One end of the second beam 32 is integratedly connected to the first beam 31, and the other end is integratedly connected to the integrated structure. The first beam 31 is connected to the upper trailing edge skin 22, making the first beam 31, the second beam 32, the lower slat skin 11, and the lower trailing edge skin 21 all integrally connected, thus presenting a single structure. This is equivalent to reducing one upper connecting plate component compared to existing technologies, thereby reducing the aircraft's structural weight and lowering costs. The reduced component manufacturing cost allows for a decrease in the number of assembly parts, effectively reducing the weight of the slat structure and improving structural load-bearing efficiency. Compared to existing technologies, it reduces the assembly steps of the lower skin and trailing edge components of the slat, thereby reducing the number of fasteners, reducing the weight of the aircraft structure, simplifying the component assembly process, reducing assembly difficulty, improving the shape quality of the component after molding, reducing the workload of slat component molding and structural assembly, fully leveraging the advantages of integration, reducing assembly difficulty, effectively reducing structural manufacturing costs, and most importantly, improving the installation efficiency of the slat trailing edge structure and the final structural stability of the slat trailing edge structure. In addition, it effectively reduces the production and manufacturing costs of the slat trailing edge structure.
[0068] This utility model also provides a wing that improves the structural rationality of the wing by adopting the above-mentioned slat trailing edge structure.
[0069] Specifically, such as Figures 3 to 5 As shown, an airfoil includes a wing box and a slat trailing edge structure disposed at the end of the wing box.
[0070] It is understandable that, since the slat skin 1 includes the lower slat skin 11, along the first direction X1, the lower trailing edge skin 21 and the upper trailing edge skin 22 are separated at one end and connected at the other end, making the separated end of the lower trailing edge skin 21 and the upper trailing edge skin 22 an open structure. At the same time, the separated end of the lower trailing edge skin 21 and the upper trailing edge skin 22 and one end of the lower slat skin 11 are integrally connected to form a connected structure, that is, one end of the lower trailing edge skin 21 and the lower slat skin 11 is an open structure. The integrated, one-piece structure features a support beam 3 positioned between the trailing edge upper skin 22 and the integrated structure. The support beam 3 includes an adjacent, connected first beam 31 and second beam 32. One end of the second beam 32 is integrally connected to the first beam 31, and the other end is integrally connected to the integrated structure. The first beam 31 is connected to the trailing edge upper skin 22, making the first beam 31, second beam 32, lower slat skin 11, and lower trailing edge skin 21 all integrally connected, thus presenting a one-piece structure. This is essentially a significant improvement over existing technologies. The invention reduces the number of upper connecting plate components, thereby reducing the aircraft's structural weight, lowering component manufacturing costs, and consequently reducing the number of assembly parts. This effectively reduces the weight of the slat structure, thereby improving structural load-bearing efficiency. Compared to existing technologies, it reduces the assembly steps of the slat lower skin and trailing edge assembly, thus reducing the number of fasteners required, further reducing the aircraft's structural weight, simplifying component assembly processes, reducing assembly difficulty, improving the overall shape quality of the assembled components, and reducing the workload of slat component forming and structural assembly. It fully leverages the advantages of integration, reduces assembly difficulty, and effectively lowers structural manufacturing costs. Specifically, the slat trailing edge structure allows the support beam 3 to be integrally connected with the slat lower skin 11 and trailing edge lower skin 21, which reduces the number of assembly parts on the wing, effectively reduces the weight of the slat structure, thereby improving the wing's structural load-bearing efficiency, and reduces the workload of slat component forming and structural assembly. It fully leverages the advantages of integration, reduces assembly difficulty, and effectively lowers structural manufacturing costs.
[0071] Obviously, the above embodiments of this utility model are merely examples for clearly illustrating the present utility model, and are not intended to limit the implementation of the present utility model. Those skilled in the art can make other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this utility model should be included within the protection scope of the claims of this utility model.
Claims
1. A slat trailing edge structure, characterized in that, include: Slat skin (1), the slat skin (1) includes slat underskin (11); The trailing edge skin (2) includes a lower trailing edge skin (21) and an upper trailing edge skin (22); along the first direction (X1), the lower trailing edge skin (21) and the upper trailing edge skin (22) are separated at one end and connected at the other end; the end of the lower trailing edge skin (21) and the upper trailing edge skin (22) that are separated and the end of the slat lower skin (11) are integrally connected to form a connected structure; Support beam (3), the support beam (3) is located between the tail edge upper skin (22) and the connecting structure; the support beam (3) includes a first beam (31) and a second beam (32) connected adjacent to each other, one end of the second beam (32) is integrally connected to the first beam (31), and the other end is integrally connected to the connecting structure, and the first beam (31) is connected to the tail edge upper skin (22).
2. The slat trailing edge structure according to claim 1, characterized in that, The slat skin (1) also includes a slat upper skin (12), which is connected to the side of the trailing edge upper skin (22) away from the first beam (31).
3. The slat trailing edge structure according to claim 2, characterized in that, The upper skin (22) of the trailing edge is provided with a mounting groove (221) on the side opposite to the first beam (31), and the upper skin (12) of the slat is disposed in the mounting groove (221).
4. The slat trailing edge structure according to claim 3, characterized in that, The depth of the mounting groove (221) is the same as the thickness of the skin (12) on the slat.
5. The slat trailing edge structure according to claim 1, characterized in that, The slat trailing edge structure also includes a trailing edge pad (4), which is integrally connected to the side of the lower trailing edge skin (21) facing the upper trailing edge skin (22).
6. The slat trailing edge structure according to claim 5, characterized in that, The support beam (3) extends along the second direction (X2), which is at an angle to the first direction (X1). The trailing edge lower skin (21), the trailing edge pad (4) on the trailing edge lower skin (21), the trailing edge upper skin (22), and the second beam (32) form a receiving cavity. The slat trailing edge structure also includes a full-height honeycomb core (5), which is installed in the receiving cavity.
7. The slat trailing edge structure according to claim 6, characterized in that, The slat trailing edge structure also includes sealing ribs (6) located at both ends of the trailing edge skin (2) along the second direction (X2), and the sealing ribs (6) at both ends are respectively connected to the inner surfaces of the lower trailing edge skin (21) and the upper trailing edge skin (22).
8. The slat trailing edge structure according to claim 7, characterized in that, The sealing rib (6) has the same shape as the two ends of the receiving cavity, and the sealing rib (6) is used to seal the two ends of the receiving cavity.
9. The slat trailing edge structure according to claim 7, characterized in that, The sealing rib (6) includes a first sealing rib (61) and a second sealing rib (62) arranged along the first direction (X1), wherein the cross-section of the first sealing rib (61) and / or the second sealing rib (62) is quadrilateral.
10. A wing, characterized in that, It includes a wing box and a slat trailing edge structure as described in any one of claims 1-9 disposed at the end of the wing box.