Bluff body for the wing root and method for manufacturing the same

Abstract

The application belongs to the technical field of aircraft manufacturing, and discloses a wing root fairing cover body and a manufacturing method thereof. The wing root fairing cover body comprises a core material, a pouring sealant and a skin. The core material comprises a first part and a second part, both of which are plate-shaped and connected with each other to form the core material with an "L" shaped cross section. The first part is provided with a pouring sealant mounting groove, and the pouring sealant is arranged in the pouring sealant mounting groove. The skin is wrapped and packaged on the outer surface of the core material. The wing root fairing cover body has a relatively simple manufacturing method, low processing difficulty, short production cycle and relatively low processing cost.

Description

Technical Field

[0001] This invention relates to the field of aircraft manufacturing technology, and in particular to a wing root fairing housing and its manufacturing method. Background Technology

[0002] The wing root fairing is a fairing installed at the junction of the aircraft wing and fuselage, mainly used to optimize airflow and protect the internal structure.

[0003] Civilian passenger aircraft are a type of aircraft. The horizontal tail of a civil passenger aircraft mainly functions to stabilize flight attitude and control ascent and descent. The wing root fairing in the horizontal tail assembly mainly plays a role in shaping the connection between the horizontal tail and the fuselage, thereby reducing flight drag.

[0004] In existing technologies, when manufacturing the wing root fairing, since the wing root fairing is generally a long strip structure with an L-shaped cross-section, the internal core material is typically formed using a heat-setting process. This involves first heating the plate-like core material to a specific temperature to relax its molecular structure; then, while still heated, fixing the core material into an L-shaped strip structure; and finally, cooling the core material to stabilize its molecular structure in the new shape.

[0005] The core material for forming the wing root fairing body using a heat-setting process is difficult to process, has a long production cycle, and ultimately leads to increased processing costs. Summary of the Invention

[0006] The purpose of this invention is to provide a wing root fairing housing and its manufacturing method, which is relatively simple to manufacture, easy to process, and has a short production cycle, thus avoiding excessive processing costs for the wing root fairing housing.

[0007] To achieve this objective, the present invention adopts the following technical solution:

[0008] The wing root fairing housing includes:

[0009] The core material includes a first part and a second part, both of which are plate-shaped and connected to each other to form the core material with an "L" shaped cross section.

[0010] A potting compound, wherein the first split body is provided with a potting compound mounting groove, and the potting compound is disposed in the potting compound mounting groove;

[0011] The skin is used to cover and encapsulate the outer surface of the core material.

[0012] Optionally, one of the first and second parts is provided with a plug tooth, and the other is provided with a plug groove that engages with the plug tooth.

[0013] Optionally, the insertion teeth are inserted into the insertion slots and adhesive is provided between them.

[0014] Optionally, an adhesive film is applied to both sides of the core material at the joint of the insertion teeth and the insertion groove.

[0015] Optionally, the first split body is provided with a plurality of potting component mounting slots, and each potting component mounting slot is provided with a potting component.

[0016] Optionally, the edge of the core material is chamfered, and the size of the chamfer is not less than a set angle.

[0017] A method for manufacturing a wing root fairing housing, used to process and form the aforementioned wing root fairing housing, includes the following steps:

[0018] S1. Process to form a first part and a second part, and simultaneously manufacture a potting component mounting groove on the first part;

[0019] S2. Connect the first component and the second component together to form the core material;

[0020] S3. The potting compound is installed in the potting compound mounting groove using expanding foam, and the skin is wrapped and encapsulated on the outer surface of the core material.

[0021] Optionally, in step S3, the skin includes a first skin and a second skin, wherein the first skin and the second skin are respectively cured and formed on opposite sides of the core material.

[0022] Optionally, the manufacturing method of the wing root fairing further includes the following steps:

[0023] S4. Fill and cure the sealing area of ​​the wing root fairing.

[0024] Optionally, step S4 includes:

[0025] S41. Remove material from the edge of the wing root fairing body inward by a set dimension;

[0026] S42. Use a protective film to cover and protect the first skin and the second skin;

[0027] S43. Fill the sealing area of ​​the wing root fairing body with potting compound to form a potting sealing area, cure and polish the potting compound so that the potting compound is flush with the edge of the first skin and the edge of the second skin;

[0028] S44. The edges of the first skin, the edges of the second skin, and the potting and sealing area are sealed together.

[0029] The beneficial effects of this invention are:

[0030] The wing root fairing body proposed in this invention comprises a first part and a second part as its core material. Both the first and second parts are plate-shaped and interconnected to form an "L"-shaped core material. Thus, when forming the core material, the heat-setting process used in existing technologies is not required. Only the first and second parts need to be machined, and the potting compound mounting groove is formed simultaneously with the first part, reducing manufacturing time. Dividing the core material into two parts reduces the thickness requirement of the core material blank or eliminates the need to combine thinner core material blanks into thicker ones, thereby saving raw materials and reducing production costs. Subsequently, the first and second parts are interconnected to form an "L"-shaped core material, and finally, the skin is wrapped and sealed onto the outer surface of the core material. Thus, the wing root fairing body is formed, the manufacturing method is relatively simple, the processing difficulty is low, the production cycle is short, and the processing cost is relatively low.

[0031] The manufacturing method of the wing root fairing body proposed in this invention is relatively simple, easy to process, and has a short production cycle, thus avoiding excessive processing costs for the wing root fairing body.

[0032] During the manufacturing process, a first and a second component are first formed. While forming the first component, a potting compound mounting groove is machined into it. The first and second components are then connected to form the core material. Finally, the potting compound is installed in the mounting groove using expanding foam, and the skin is then wrapped and encapsulated on the outer surface of the core material. The potting compound is also simultaneously encapsulated within the skin using expanding foam. Thus, the wing root fairing body is formed. The manufacturing method is relatively simple, with low processing difficulty, a short production cycle, and relatively low processing costs. Attached Figure Description

[0033] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments of the present invention will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the content of the embodiments of the present invention and these drawings without creative effort.

[0034] Figure 1 This is a schematic diagram of the wing root fairing provided in Embodiment 1 of the present invention;

[0035] Figure 2 This is an exploded structural diagram of the wing root fairing provided in Embodiment 1 of the present invention;

[0036] Figure 3This is an exploded structural diagram of the core material of the wing root fairing provided in Embodiment 1 of the present invention;

[0037] Figure 4 This is a schematic diagram of the structure of the potting component for the wing root fairing provided in Embodiment 1 of the present invention;

[0038] Figure 5 This is a flowchart of the manufacturing method of the wing root fairing body provided in Embodiment 2 of the present invention;

[0039] Figure 6 This is a flowchart illustrating the process of potting and curing the sealing area of ​​the wing root fairing in the manufacturing method of the wing root fairing provided in Embodiment 2 of the present invention.

[0040] In the picture:

[0041] 1. Core material; 11. First component; 111. Insertion tooth; 12. Second component; 121. Insertion groove;

[0042] 2. Potting components;

[0043] 3. Skin; 31. First skin; 32. Second skin. Detailed Implementation

[0044] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0045] In the description of this invention, 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 invention based on the specific circumstances.

[0046] 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.

[0047] In the description of this embodiment, the terms "upper," "lower," "left," and "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0048] Example 1

[0049] See Figures 1-4 This embodiment provides a wing root fairing cover, which has a relatively simple manufacturing method, low processing difficulty, and short production cycle, thus avoiding excessive processing costs for the wing root fairing cover.

[0050] Specifically, in this embodiment, the wing root fairing includes a core material 1, a potting compound 2, and a skin 3.

[0051] The core material 1 includes a first part 11 and a second part 12. Both the first part 11 and the second part 12 are plate-shaped and are connected to each other to form a core material 1 with an "L" shaped cross section.

[0052] Optionally, in this embodiment, the core material 1 is a foam core material. Using a foam core material can significantly reduce the weight of the wing root fairing while supporting the aerodynamic shape of the fairing, and effectively maintain the consistency of the wing root fairing strength.

[0053] The first component 11 is provided with a potting component mounting groove, and a potting component 2 is provided in the potting component mounting groove.

[0054] The skin 3 is encapsulated on the outer surface of the core material 1.

[0055] Optionally, in this embodiment, the skin 3 is made of carbon fiber fabric. The skin 3 directly bears the aerodynamic load and transmits it to the core material 1 for overall load bearing, while also bearing the wear and tear from all external forces such as light, water, wind, and biological agents.

[0056] The wing root fairing housing provided in this embodiment has a core material 1 comprising a first part 11 and a second part 12. Both the first part 11 and the second part 12 are plate-shaped and interconnected to form an L-shaped core material 1. Thus, when forming the core material 1, there is no need to use the heat-setting process of existing technologies. Only the first part 11 and the second part 12 need to be machined. Simultaneously, a potting component mounting groove for installing the potting component 2 is formed during the machining of the first part 11, reducing manufacturing time. Then, the first part 11 and the second part 12 are interconnected to form the L-shaped core material 1. The potting component 2 is then installed into the potting component mounting groove. Finally, the skin 3 is wrapped and encapsulated on the outer surface of the core material 1, while the potting component 2 is also encapsulated within the skin 3. Therefore, the wing root fairing housing is formed, the manufacturing method is relatively simple, the processing difficulty is low, the production cycle is short, and the processing cost is relatively low.

[0057] Specifically, in this embodiment, the first part 11 is provided with a plurality of potting component mounting slots, and each potting component mounting slot is provided with a potting component 2.

[0058] Specifically, in this embodiment, the potting component mounting groove is formed simultaneously with the formation of the first part 11 and the second part 12. A potting component 2 can be installed in the potting component mounting groove, and the potting component 2 is located at the connection point between the wing root fairing and the fuselage.

[0059] The potting compound 2 can enhance the connection strength between the wing root and the fuselage, improve the stability of the overall structure, and reduce vibration and noise during flight, thereby improving comfort and safety.

[0060] Specifically, when installing the potting compound 2, the outer periphery of the potting compound 2 is coated with expanding foam, which on the one hand makes the potting compound 2 stably installed in the potting compound mounting groove, and on the other hand makes the potting compound 2 stably encapsulated in the skin 3.

[0061] Specifically, in this embodiment, the skin 3 includes a first skin 31 and a second skin 32, which are respectively cured and formed on opposite sides of the core material 1.

[0062] Specifically, with reference to the actual orientation of the product, the first skin 31 is located on the upper surface of the core material 1, and the second skin 32 is located on the lower surface of the core material 1.

[0063] Furthermore, to ensure the accuracy of the relative positions of the first component 11 and the second component 12 when they are connected, in this embodiment, see... Figure 2 and Figure 3 One of the first part 11 and the second part 12 is provided with a plug tooth 111, and the other is provided with a plug groove 121 that engages with the plug tooth 111.

[0064] Preferably, there are multiple insertion teeth 111, and the insertion slots 121 are arranged in a one-to-one correspondence with the insertion teeth 111.

[0065] Furthermore, in order to ensure the stability of the connection between the first part 11 and the second part 12, the insertion teeth 111 are inserted into the insertion slots 121 and adhesive is provided between them.

[0066] The adhesive can make the connection between the first part 11 and the second part 12 more secure; at the same time, the setting of the insertion teeth 111 and the insertion groove 121 makes the bonding area larger, thereby making the connection between the first part 11 and the second part 12 more stable.

[0067] Furthermore, on the opposite sides of the core material 1, at the joint between the insertion teeth 111 and the insertion groove 121, an adhesive film is applied. The presence of the adhesive film can further increase the connection stability at the joint between the insertion teeth 111 and the insertion groove 121.

[0068] Preferably, the width of the adhesive film exceeds the size of the seam by 40mm-50mm.

[0069] It should be noted that before applying the adhesive film, the flatness of the connection between the first component 11 and the second component 12 needs to be checked. If the height difference between the first component 11 and the second component 12 at the connection is greater than 0.2mm, the connection needs to be sanded to ensure that the height difference between the first component 11 and the second component 12 at the connection is less than 0.2mm.

[0070] Furthermore, in this embodiment, the edge of the core material 1 is chamfered, and the size of the chamfer is not less than a set angle.

[0071] Since the thickness of core material 1 gradually decreases at the edges, during the operation of the wing root fairing, the edges of core material 1 are easily damaged or deformed due to improper protection or impact. Therefore, the chamfer size of the edge of core material 1 is limited to not less than the set angle.

[0072] Optionally, in this embodiment, the angle is set to 20°.

[0073] Example 2

[0074] See Figure 5 This embodiment provides a method for manufacturing a wing root fairing.

[0075] Specifically, the manufacturing method of the wing root fairing includes the following steps:

[0076] S1. Processing to form a first part 11 and a second part 12, and simultaneously manufacturing a potting component mounting groove on the first part 11;

[0077] S2. Connect the first component 11 and the second component 12 together to form the core material 1;

[0078] S3. Install the potting compound 2 into the potting compound mounting groove using foam adhesive, and encapsulate the skin 3 on the outer surface of the core material 1.

[0079] Specifically, during step S3, the entire outer periphery of the potting compound 2 is coated with expanding foam. When the skin 3 is wrapped and encapsulated on the outer surface of the core material 1, the potting compound 2 is also encapsulated within the skin 3 by the expanding foam.

[0080] The manufacturing method of the wing root fairing provided in this embodiment is relatively simple, easy to process, and has a short production cycle, thus avoiding excessive processing costs for the wing root fairing.

[0081] During the manufacturing process, the first component 11 and the second component 12 are first formed. While forming the first component 11, a potting compound mounting groove is machined onto it. Then, the first component 11 and the second component 12 are connected to form the core material 1. Finally, the potting compound 2 is installed into the potting compound mounting groove using expanding foam. The skin 3 is then wrapped and encapsulated on the outer surface of the core material 1, and the potting compound 2 is simultaneously encapsulated within the skin 3 using expanding foam. Thus, the wing root fairing body is formed. The manufacturing method is relatively simple, the processing difficulty is low, the production cycle is short, and the processing cost is relatively low.

[0082] Specifically, in this embodiment, in step S1, the two pieces of foam material are processed into a first part 11 and a second part 12 (i.e., processed in halves). The first part 11 is provided with insertion teeth 111, and the second part 12 is provided with insertion grooves 121. The insertion teeth 111 and the insertion grooves 121 can be inserted and fitted together, so that the first part 11 and the second part 12 can be precisely aligned when joined, avoiding the core material from slipping during the curing of the parts and reducing the difficulty of production.

[0083] Meanwhile, in this embodiment, the method of processing in half effectively improves the utilization rate of raw materials and reduces costs compared with the traditional whole processing method.

[0084] Specifically, in this embodiment, considering factors such as the possibility of bumps and damage during transportation, and the ease of operation in the production and manufacturing process such as laying and compaction, it is necessary to limit the angle and width of the core material 1 and the edge dimensions of the wing root fairing.

[0085] Specifically, since the thickness of the core material gradually decreases at the edges, during the operation of the wing root fairing, the edges of the core material 1 are easily damaged or deformed due to improper protection or impacts. Therefore, the chamfer size of the edge of the core material 1 is limited to not less than a set angle.

[0086] Optionally, in this embodiment, the angle is set to 20°.

[0087] At the same time, the shape of the upper and lower panels of the wing root cover needs to be adjusted accordingly to ensure that the width of the panel area is not less than 12.7mm, so as to match the core material 1, which reduces the difficulty of laying and compacting, and effectively reduces the risk of moisture absorption at the edge of the wing root cover.

[0088] Specifically, in this embodiment, the processing of the potting compound 2 and the processing of the first component 11 and the second component 12 are parallel processes. While processing the first component 11 and the second component 12, the potting compound 2 can be pre-formed, which saves a lot of production time compared to the traditional method of processing the core material first and then potting the potting compound.

[0089] It is understandable that potting component 2 is formed through potting processing.

[0090] Specifically, in this embodiment, in step S1, the first component 11 is provided with multiple potting component mounting slots. Each potting component mounting slot can accommodate one potting component 2.

[0091] That is, in this embodiment, while the first part 11 is being processed, a potting installation groove is being processed on the first part 11 simultaneously, which is carried out in sync with the processing of the core material 1, thus shortening the overall manufacturing cycle of the wing root fairing body.

[0092] Specifically, in this embodiment, in step S2, when the first component 11 and the second component 12 are connected to each other to form the core material 1, the insertion teeth 111 are inserted into the insertion grooves 121, and adhesive is provided between them. Subsequently, an adhesive film is applied to the joint between the insertion teeth 111 and the insertion grooves 121. The width of the adhesive film exceeds the size of the joint by 40mm-50mm.

[0093] In step S2, before bonding the adhesive film, the flatness of the connection between the first component 11 and the second component 12 needs to be checked. If the height difference between the first component 11 and the second component 12 at the connection is greater than 0.2mm, the connection needs to be sanded to control the height difference between the first component 11 and the second component 12 at the connection to be less than 0.2mm.

[0094] Specifically, in this embodiment, in step S3, the skin 3 includes a first skin 31 and a second skin 32, and the first skin 31 and the second skin 32 are respectively cured and formed on opposite sides of the core material 1.

[0095] Furthermore, to prevent the core material 1 from absorbing moisture, in this embodiment, the manufacturing method of the wing root fairing also includes the following steps:

[0096] S4. Fill and cure the sealing area of ​​the wing root fairing.

[0097] By performing step S4, it is possible to prevent the foam core material from absorbing moisture when exposed to air.

[0098] Specifically, see Figure 6 In this embodiment, step S4 includes:

[0099] S41. Remove material from the edge of the wing root fairing housing inward by a set dimension;

[0100] S42. A protective film is used to cover and protect the first skin 31 and the second skin 32.

[0101] S43. Fill the sealing area of ​​the wing root fairing body with potting compound to form a potting sealing area, cure and polish the potting compound so that the potting compound is flush with the edge of the first skin 31 and the edge of the second skin 32.

[0102] S44. The edges of the first skin 31, the edges of the second skin 32, and the filling and sealing area are sealed together.

[0103] Optionally, in this embodiment, the size is set to be no less than 5mm. Specifically, in this embodiment, the size is set to 5mm.

[0104] Optionally, in this embodiment, the protective film is adhesive tape.

[0105] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art will be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A wing root fairing housing, characterized in that, include: The core material (1) includes a first part (11) and a second part (12), both of which are plate-shaped and connected to each other to form the core material (1) with an "L" shaped cross section. The potting component (2) is provided with a potting component mounting groove on the first split body (11), and the potting component (2) is provided in the potting component mounting groove. Skin (3) covers and encapsulates the outer surface of the core material (1); One of the first split body (11) and the second split body (12) is provided with a plug tooth (111), and the other is provided with a plug groove (121) that is plugged into and engaged with the plug tooth (111). The insertion teeth (111) are inserted into the insertion slots (121) and adhesive is provided between them.

2. The wing root fairing housing according to claim 1, characterized in that, On the opposite two sides of the core material (1), at the joint of the insertion teeth (111) and the insertion groove (121), an adhesive film is applied.

3. The wing root fairing housing according to claim 1, characterized in that, The first split body (11) is provided with a plurality of potting component mounting slots, and each potting component mounting slot is provided with a potting component (2).

4. The wing root fairing housing according to claim 1, characterized in that, The edge of the core material (1) is chamfered, and the size of the chamfer is not less than a set angle.

5. A method for manufacturing a wing root fairing housing, characterized in that, The process for forming the wing root fairing body as described in any one of claims 1-4 includes the following steps: S1. Process to form a first part (11) and a second part (12), and simultaneously manufacture a potting installation groove on the first part (11); S2. Connect the first part (11) and the second part (12) to each other to form the core material (1). S3. The potting compound (2) is installed in the potting compound mounting groove with foam adhesive, and the skin (3) is wrapped and encapsulated on the outer surface of the core material (1).

6. The method for manufacturing the wing root fairing body according to claim 5, characterized in that, In step S3, the skin (3) includes a first skin (31) and a second skin (32), and the first skin (31) and the second skin (32) are respectively cured and formed on opposite sides of the core material (1).

7. The method for manufacturing the wing root fairing body according to claim 6, characterized in that, The manufacturing method of the wing root fairing body further includes the following steps: S4. Fill and cure the sealing area of ​​the wing root fairing.

8. The method for manufacturing the wing root fairing body according to claim 7, characterized in that, Step S4 includes: S41. Remove material from the edge of the wing root fairing body inward by a set dimension; S42. The first skin (31) and the second skin (32) are sealed and protected with a protective film; S43. Fill the sealing area of ​​the wing root fairing body with potting compound to form a potting sealing area, cure and polish the potting compound so that the potting compound is flush with the edge of the first skin (31) and the edge of the second skin (32); S44. The edges of the first skin (31), the edges of the second skin (32), and the potting and sealing area are sealed together.

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