Aviation fastener row positioning frame and operation method thereof

Abstract

The invention relates to the technical field of aviation sealant construction, in particular to an aviation fastener row positioning frame and an operation method thereof.The row positioning frame comprises a row positioning frame body, and a double faced adhesive tape with release paper is arranged on the back face of the row positioning frame body; a plurality of mounting grooves which are in one-to-one correspondence with fasteners to be packaged are formed in the row positioning frame main body in a penetrating manner, the peripheral wall of each mounting groove extends from the front surface to the back surface of the row positioning frame main body to form an obliquely arranged corner cut type inclined surface, and a plurality of guide columns respectively surround the surface of each corner cut type inclined surface. According to the invention, the main body of the row positioning frame adopts an integral design, so that all fasteners in the whole area of the aircraft wing can be positioned at one time, and the occupied space around the row positioning frame is extremely small and can be reduced to a limit position without interference with other parts; the defect that a traditional independent positioning frame is prone to operation interference in a dense fastener arrangement scene is thoroughly overcome.

Description

Technical Field

[0001] This invention relates to the field of aviation sealant application technology, specifically to an aviation fastener positioning frame and its operation method. Background Technology

[0002] In the aviation field, fasteners on aircraft wing structures require sealant encapsulation after installation to ensure the aircraft's airtightness and structural stability. Currently, during the application of aviation sealants, fastener positioning typically employs individual positioning frames, such as the positioning frame used to adhere to the outer surface of the workpiece in the patent application for invention authorization number CN109127296B, which describes an aviation fastener sealing cap tool assembly. However, in practice, the aforementioned disclosed individual positioning frame has the following drawbacks: 1. Because the fasteners on the aircraft wing structure are mostly arranged in a tightly packed manner (e.g. Figure 1 As shown in the figure, a is the wing radius (R angle) and b is the fastener. The volume of the individual positioning frame is limited. When positioning the fasteners one by one, the positioning frames are prone to mutual interference, which cannot meet the normal production conditions of positioning one by one. 2. The positioning holes of the individual positioning frame need to be installed one by one, which is time-consuming and labor-intensive, greatly reducing the efficiency of the sealing construction. 3. In some confined spaces, it is not easy for operators and dismantling tools to access the individual positioning frame, which not only further increases the difficulty of operation, but also makes it easy for the positioning frame to be forgotten or for sealant residue to remain, posing a risk of foreign matter and making it difficult to ensure the consistency of the sealing construction quality. Summary of the Invention

[0003] This invention provides an aviation fastener assembly positioning frame and its operation method to solve the problems mentioned in the background art.

[0004] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows: A series of positioning frames for aviation fasteners includes a main body. The back of the main body is covered with double-sided adhesive with release paper. Several mounting slots, each corresponding to a fastener to be packaged, are formed through the main body. The peripheral wall of each mounting slot extends from the front to the back of the main body, forming an inclined chamfered surface. Multiple guide posts surround the surface of each chamfered surface. The centers of the guide posts are concentric with the centers of the corresponding mounting slots.

[0005] Preferably, the main body of the row positioning frame includes a positioning plate and a reinforcing rib frame. The reinforcing rib frame is connected to the edge of the positioning plate and extends protrudingly to one side of the positioning plate. The protruding extension end of the reinforcing rib frame along one side of the positioning plate is on the same side as the guide post, and the mounting groove is formed through the positioning plate.

[0006] Preferably, one edge of the reinforcing rib frame is provided with a rounded corner that matches the R-angle profile of the wing, and the surface of the rounded corner is provided with double-sided adhesive with release paper, and the double-sided adhesive with release paper on the surface of the rounded corner and the double-sided adhesive with release paper on the back of the main body of the row positioning frame are integrally formed.

[0007] Preferably, the end of the reinforcing rib frame away from the positioning plate and the end of the guide post away from the positioning plate are on the same horizontal plane.

[0008] Preferably, all of the guide posts are perpendicular to the front of the positioning plate, and each guide post has a chamfer on the side of its end away from the positioning plate.

[0009] Preferably, the positioning plate, the reinforcing frame, and the guide column are integrally formed.

[0010] Preferably, each of the chamfered surfaces is provided with at least three guide posts, and the three guide posts are equidistant from each other along the circumference of the mounting groove.

[0011] Preferably, each of the chamfered surfaces is provided with four guide posts, and the four guide posts are equidistant from each other along the circumference of the mounting groove.

[0012] To address the aforementioned technical problems, the present invention also provides an operation method for an aviation fastener positioning frame, comprising the following steps: S1. Based on the arrangement parameters of the fasteners on the aircraft parts, select a suitable row of positioning frame bodies, and take at least two positioning cores to install on two fasteners on the aircraft parts. S2. Remove the release paper from the bottom adhesive of the main body of the row positioning frame, align the mounting groove with the fastener on the aircraft part along the axis of the positioning core, and place the main body of the row positioning frame until the adhesive surface of the bottom of the main body of the row positioning frame is completely attached to the surface of the aircraft part. Then apply pressure evenly to press the main body of the row positioning frame to fix it tightly to the aircraft part. S3. After pulling out all the positioning cores in sequence, apply pressure again to press the main body of the row of positioning frames evenly to ensure that each mounting slot is tightly attached to the surface of the aircraft parts. S4. Fill the internal cavity of the sealing cap with aviation sealant. After the sealant is injected, slowly press the sealing cap down along the inner side wall of multiple guide posts and rotate it simultaneously. After the bottom of the sealing cap contacts the surface of the aircraft part, continue to rotate it 1-2 times to allow the excess sealant to overflow along the chamfered surface onto the upper surface of the main body of the row positioning frame. S5. Repeat step S4 to install the sealing cap and inject the sealant into each fastener on the aircraft parts in sequence until all fasteners corresponding to the mounting slots have been sealed. S6. After all the sealant has cured and set, use a non-metallic tool to insert into the adhesive-backed area, pry up and remove the main body of the row of positioning frames, and simultaneously remove any excess cured sealant. S7. Remove all sealing caps one by one along the axial direction of the sealing caps to complete the sealant encapsulation of the fasteners.

[0013] Preferably, in step S1, four positioning cores are respectively installed on the two outermost fasteners at both ends of the fastener to be sealed on the aircraft parts.

[0014] By adopting the above technical solution, the beneficial effects achieved by the present invention are as follows: In this invention, the main body of the row positioning frame adopts an integral design, which can achieve one-time positioning of all fasteners in the entire area of ​​the aircraft wing. Moreover, it occupies very little space around it and can be reduced to the limit position without interfering with other parts, thus completely solving the operational interference defects that are prone to occur in the traditional single positioning frame in the scenario of dense fastener arrangement.

[0015] Compared to the traditional method of positioning fasteners one by one using individual positioning frames, the main body of the row positioning frame of this invention only needs to use a few positioning cores to complete a precise positioning once. The operation time is only one-tenth of that of the traditional method, and several to dozens of fasteners can be positioned at once, which significantly shortens the construction time and greatly improves the packaging efficiency.

[0016] In this invention, the main body of the row positioning frame is compact. Its installation and removal do not require operators to enter the narrow space of the aircraft. The positioning and sealing of all fasteners in the narrow space can be completed in one go. This avoids the problem of traditional single positioning frames being difficult to operate in narrow spaces and prone to positioning omissions, and improves the applicability of construction in special scenarios.

[0017] In this invention, by using adhesive backing technology on the bottom of the main body of the row positioning frame, it is possible to ensure that the main body of the row positioning frame is in close contact with the surface of the aircraft parts, effectively preventing the sealant from seeping in from the gaps between the two contact surfaces; at the same time, the matching design of the rounded corners and the right-angled edges of the parts ensures that the sealant adhesive layer forms a natural overlap with the surface of the aircraft parts, significantly improving the sealing performance.

[0018] In this invention, the installation of the sealing cap is guided by multiple guide posts, which can effectively limit the offset of the sealing cap, ensure the accurate installation position of the sealing cap, and thus ensure the uniform thickness of the sealant layer; and the overall positioning design of the main body of the row of positioning frames and the subsequent one-time shaping operation make the construction effect unaffected by the difference in the skill level of the operators, which greatly improves the consistency of batch construction.

[0019] In this invention, the main body of the row of positioning frames is made of polymer material, which prevents it from sticking to the cured aviation sealant. After use, it can be reused after cleaning and re-applying adhesive, effectively reducing the replacement cost of the positioning frames. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the unsealed fasteners on the existing aircraft wing structure and the wing radius (R-angle).

[0021] Figure 2 This is a schematic diagram of the overall structure of the main body of the row positioning frame of the present invention.

[0022] Figure 3 for Figure 2 Enlarged schematic diagram of the structure at point A in the middle.

[0023] Figure 4 This is a schematic diagram of the process of using aerospace fasteners in a row of positioning frames to encapsulate fasteners.

[0024] In the diagram: 1. Main body of the row positioning frame; 11. Positioning plate; 12. Reinforcing rib frame; 2. Mounting groove; 3. Chamfered bevel; 4. Guide column; 5. Rounded corner; 6. Positioning core; 7. Sealing cap. Detailed Implementation

[0025] To better understand the above-mentioned objectives, features, and advantages of the present invention, the present invention will be further described below in conjunction with the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be combined with each other.

[0026] Numerous specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways than those described herein, and therefore the invention is not limited to the specific embodiments disclosed in the following specification.

[0027] like Figures 1-3As shown, the present invention provides an aviation fastener positioning frame, including a positioning frame body 1. The positioning frame body 1 is made of polymer material, which can prevent adhesion to the cured aviation sealant and is easy to clean. The back of the positioning frame body 1 is provided with double-sided adhesive with release paper. Several mounting grooves 2 corresponding to the fasteners to be sealed are opened through the positioning frame body 1. The mounting grooves 2 are circular mounting grooves. The peripheral wall of each mounting groove 2 extends from the front to the back of the positioning frame body 1 to form an inclined chamfered surface 3. The surface of each chamfered surface 3 is surrounded by multiple guide posts 4. The distribution center of the multiple guide posts 4 is concentric with the center of the corresponding mounting groove 2.

[0028] It is worth noting that the number and position of the mounting slots 2 can be customized according to the actual size of the aircraft parts and the number of fasteners, and the size and shape of the main body 1 of the row positioning frame can also be customized according to the actual situation. In addition, during actual production, the diameter of the mounting slots 2 needs to be appropriately enlarged to eliminate possible installation deviations during fastener installation.

[0029] As a further step, the main body 1 of the row positioning frame includes a positioning plate 11 and a reinforcing rib frame 12. The reinforcing rib frame 12 is connected to the edge of the positioning plate 11 and extends protrudingly toward one side of the positioning plate 11. The protruding extension end of the reinforcing rib frame 12 along one side of the positioning plate 11 is on the same side as the guide post 4, and the mounting groove 2 is opened through the positioning plate 11.

[0030] Specifically, the main body 1 of the row positioning frame is designed with reinforcing ribs 12 protruding from the mounting groove 2. This structure can ensure the strength of the main body 1 of the row positioning frame and prevent excess sealant from seeping out of the positioning frame. In addition, when excess sealant overflows onto the main body 1 of the row positioning frame, the design of the chamfered bevel 3 allows the bevel to form a scissor-cutting structure with the bottom edge of the sealing cap 7 when the row positioning frame is removed after construction. This is used to remove the excess sealant after it has cured, so that the sealant adhesive layer after sealing can achieve a natural overlap with the surface of the aircraft parts.

[0031] As a further step, one edge of the reinforcing frame 12 is provided with a rounded corner 5 that matches the R-angle profile of the wing, so that the main body of the row positioning frame 1 can be effectively attached to the R-angle surface of the aircraft parts. The surface of the rounded corner 5 is provided with double-sided adhesive with release paper, and the double-sided adhesive with release paper on the surface of the rounded corner 5 and the double-sided adhesive with release paper on the back of the main body of the row positioning frame 1 are integrally formed.

[0032] The main body 1 of the positioning frame adopts adhesive backing technology, ensuring that the adhesive is evenly applied to the bottom and rounded corners 5 of the main body 1. This method allows for the thinnest possible adhesive layer, creating excellent conditions for a natural overlap between the package and the aircraft part surface, avoiding steps or rough edges caused by excessively high mounting grooves 2 of the main body 1. Simultaneously, the excellent adhesive performance ensures that the main body 1 adheres firmly to the aircraft part surface during installation, preventing the aviation sealant used during packaging from seeping into the gaps between the main body 1 and the aircraft part surface. Furthermore, when the main body 1 needs to be removed after installation, no adhesive residue will remain on the aircraft part surface.

[0033] In a preferred embodiment, the end of the reinforcing rib frame 12 furthest from the positioning plate 11 is on the same horizontal plane as the end of the guide post 4 furthest from the positioning plate 11. In another embodiment, the end of the reinforcing rib frame 12 furthest from the positioning plate 11 is higher than the end of the guide post 4 furthest from the positioning plate 11. This design prevents the guide post 4 from protruding excessively, which would affect the overall aesthetics and storage.

[0034] As a further step, the multiple guide posts 4 are perpendicular to the front of the positioning plate 11, and each guide post 4 has a chamfer on the side of its end away from the positioning plate 11. The chamfer design at the top of the guide post 4 facilitates the quick entry of the sealing cap 7 into the inside of the multiple guide posts 4, thereby improving the installation speed.

[0035] Furthermore, the positioning plate 11, the reinforcing frame 12, and the guide column 4 are integrally formed.

[0036] As a further step, each chamfered bevel 3 is provided with at least three guide posts 4, and the three guide posts 4 are equidistantly arranged along the circumferential direction of the mounting groove 2.

[0037] As an optional implementation, each chamfered bevel 3 is provided with four guide posts 4, and the four guide posts 4 are equidistantly arranged along the circumferential direction of the mounting groove 2. Through the design of the four guide posts 4, the bottom edge of the sealing cap 7 can be installed downward along the inner side of the four guide posts 4 without offset, so as to achieve accurate and non-eccentric installation of the sealing cap 7 and promote uniform adhesive layer thickness on the fastener.

[0038] Combination Figure 4 As shown, the present invention also provides an operation method for an aviation fastener positioning frame, comprising the following steps: S1. Based on the arrangement parameters of the fasteners on the aircraft parts, select the appropriate row positioning frame body 1, and take at least two positioning cores 6 to install on the two fasteners on the aircraft parts. The positioning core 6 can be an inverted cylindrical or bowl-shaped part. The top of the positioning core 6 is provided with a gripping handle, and the bottom of the positioning core 6 is provided with a positioning cavity for fitting against the surface of the fastener. The inner diameter of the positioning cavity is approximately equal to the outer diameter of the bottom of the fastener, so that the positioning core 6 can fit tightly against the fastener, ensuring accurate positioning and preventing movement.

[0039] S2. Remove the release paper from the adhesive backing of the bottom of the main body 1 of the row positioning frame, align the mounting groove 2 with the fastener on the aircraft part along the axis of the positioning core 6, and slowly lower the main body 1 of the row positioning frame until the adhesive backing of the bottom of the main body 1 of the row positioning frame is completely attached to the surface of the aircraft part. Then apply pressure evenly to press the main body 1 of the row positioning frame to make it tightly fixed to the aircraft part, ensuring that there is no gap between the main body 1 of the row positioning frame and the aircraft part, and use the adhesive backing to achieve temporary fixation of the main body 1 of the row positioning frame, providing a stable operating reference for the subsequent installation of the sealing cap 7. The outer diameter of the positioning core 6 is closely matched with the inner diameter of the mounting groove 2 to ensure that the main body 1 of the row positioning frame will not shift during installation. The advantage of this positioning method is that only a few positioning cores 6 are needed to complete the precise positioning of the entire row positioning frame 1. Compared with the method of operating each positioning frame separately, the method proposed in this solution only takes about one-tenth of the operation time, which effectively improves production efficiency.

[0040] S3. After pulling out all the positioning cores 6 in sequence, apply pressure again to press the entire row of positioning frame body 1 evenly to ensure that each mounting slot 2 is tightly pressed against the surface of the aircraft part and completely compacted. This will eliminate any gaps or air bubbles that may exist between the row of positioning frame body 1 and the aircraft part, and prevent the sealant injected later from seeping into the contact surface between the bottom of the row of positioning frame body 1 and the aircraft part, thereby damaging the sealing effect of the bottom of the sealing cap 7 and the natural overlap transition of the adhesive layer.

[0041] S4. Fill the internal cavity of the sealing cap 7 with aviation sealant. After the sealant is injected, slowly press the sealing cap 7 down along the inner side wall of the multiple guide posts 4, and simultaneously rotate it clockwise or counterclockwise. After the bottom of the sealing cap 7 contacts the surface of the aircraft part, continue to rotate it 1-2 times so that the excess sealant overflows along the chamfered slope 3 onto the upper surface of the main body 1 of the row positioning frame. The system utilizes multiple guide posts 4 to limit the offset of the sealing cap 7, ensuring the coaxiality of the sealing cap 7 during installation. When the bottom of the sealing cap 7 contacts the bottom of the main body 1 of the row positioning frame and further contacts the surface of the aircraft part, the continued rotation serves the purpose of allowing excess sealant inside the sealing cap 7 to overflow upwards along the chamfered surface 3 of the circular mounting groove 2 under the action of rotational pressure. This sealant is then guided to the upper surface of the main body 1 of the row positioning frame, achieving centralized collection of excess sealant and preventing it from overflowing into other areas of the aircraft part.

[0042] S5. Repeat step S4 to install the sealing cap 7 and inject the sealant into each fastener on the aircraft parts in sequence until all fasteners corresponding to the mounting slots 2 have been sealed. S6. After all the sealant has cured and set, select a sharp and non-magnetic non-metallic tool (such as nylon or plastic) and insert it into the adhesive gap area. Slowly apply upward prying force to gradually lift the main body 1 of the row positioning frame from the surface of the aircraft parts and remove it as a whole. At the same time, remove the excess cured sealant. Specifically, this step removes excess cured sealant that overflows during the sealing cap 7 installation and sealing process, along with the removal of the main body 1 of the row of positioning frames. This simultaneously completes the one-time reshaping of excess sealant on the top of all sealing caps 7, eliminating the need for separate cleaning of excess sealant for each sealing cap 7. Compared to the separate operation of existing independent positioning frames, this simplifies the operation and solves the problems caused by using independent positioning frames (such as in many narrow spaces where removal tools are difficult to reach). It also avoids the risk of forgetting or leaving residues caused by individual removal, fundamentally solving the problem of excess material risk control.

[0043] S7. Remove all sealing caps 7 one by one along the axial direction of the sealing cap 7. At this time, a sealant layer is formed on the surface of the fastener on the aircraft part, which naturally overlaps with the surface of the part, and the sealant encapsulation of the fastener is completed.

[0044] As an optional implementation, in step S1, four positioning cores 6 are respectively installed on the two outermost fasteners at both ends of the fastener to be sealed on the aircraft parts. The installation of the four positioning cores 6 can be used to limit the four corners of the row positioning frame body 1, which is conducive to the stable initial positioning of the row positioning frame body 1, avoiding the problem of deviation when the row positioning frame body 1 is attached to the surface of the aircraft parts, and ensuring the accurate positioning of the row positioning frame body 1.

[0045] Furthermore, the main body 1 of the row positioning frame can be reused after each use simply by removing the cured sealant and reapplying adhesive, which greatly reduces the cost of use.

[0046] In summary, compared to a single positioning frame, the installation process of the main body 1 of the row positioning frame is simpler, faster, and more efficient. The positioning accuracy and installation speed far exceed the accuracy of installing a single positioning frame one by one. Since each mounting slot 2 requires an adhesive sealing operation, excess sealant will overflow onto the frame of the main body 1 of the row positioning frame during the sealing cap 7 installation and sealing operation. Even if it overflows into other mounting slots 2, it will not affect the installation of the next sealing cap 7, because subsequent mounting slots 2 require sealant sealing operations. During sealant sealing, the sealing cap 7 needs to be rotated to ensure uniform sealant thickness. At the same time, after being rotated into place, it continues to rotate 1-2 times, which, together with the chamfered bevel 3, forms a set of scissor-cutting structures to remove excess sealant.

[0047] The main body 1 of the row positioning frame has an adhesive backing. This design allows the main body 1 of the row positioning frame to adhere tightly to the surface of the aircraft parts during the bonding and fixing operation. The outermost edges of the row positioning frame main body 1 are designed with adhesive backing gaps, which facilitates the use of sharp tools for prying and peeling operations.

[0048] Therefore, the technical effects achieved by this invention are as follows: I. The main body 1 of the row positioning frame of the present invention adopts an integral design, which can realize the positioning of all fasteners in the entire area at one time, and its surrounding space is extremely small. It can be reduced to the extreme position without interfering with other parts, thus completely solving the operational interference defects that are prone to occur in the traditional single positioning frame in the scenario of dense fastener arrangement.

[0049] Second, compared with the traditional method of positioning fasteners one by one using individual positioning frames, the main body 1 of the row positioning frame of the present invention only needs to use a few positioning cores 6 to complete a precise positioning once. The operation time is only one-tenth of that of the traditional method. Furthermore, several to dozens of fasteners can be positioned at once, which significantly shortens the construction time and greatly improves the packaging efficiency.

[0050] Third, the main body 1 of the row positioning frame proposed in this invention is made of polymer material. This material does not stick to the cured aviation sealant. After use, it can be reused after cleaning and re-applying adhesive, which effectively reduces the replacement cost of the positioning frame.

[0051] Fourth, by guiding the installation of the sealing cap 7 through multiple guide posts 4, the offset of the sealing cap 7 can be effectively limited, ensuring that the sealing cap 7 is installed in an accurate position, thereby ensuring that the thickness of the sealant layer is uniform; and the overall positioning design of the main body 1 of the row positioning frame and the subsequent one-time shaping operation make the construction effect unaffected by the difference in the technical level of the operators, greatly improving the consistency of batch construction.

[0052] Fifth, the main body 1 of the row positioning frame of the present invention is compact in size. Its installation and removal do not require operators to enter the narrow space of the aircraft. The positioning and sealing operations of all fasteners in the narrow space can be completed in one go. This avoids the problem of difficult operation and easy positioning omission of traditional single positioning frames in narrow spaces, and improves the construction applicability in special scenarios.

[0053] VI. The bottom of the main body 1 of the row positioning frame of the present invention adopts the back adhesive technology, which can ensure that the main body 1 of the row positioning frame is tightly attached to the surface of the aircraft parts, effectively preventing the sealant from seeping in from the gap between the two contact surfaces; at the same time, the matching design of the rounded corner 5 and the right-angle edge of the parts ensures that the sealant adhesive layer forms a natural overlap with the surface of the aircraft parts, significantly improving the sealing performance.

[0054] In the description of this specification, the terms "one embodiment," "some embodiments," "specific embodiment," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0055] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A row positioning frame for aviation fasteners, characterized in that, The system includes a row of positioning frame main body (1), the back of which is provided with double-sided adhesive with release paper, and a number of mounting slots (2) corresponding to the fasteners to be sealed are opened through the row of positioning frame main body (1). The peripheral wall of each mounting slot (2) extends from the front to the back of the row of positioning frame main body (1) to form an inclined chamfered surface (3). The surface of each chamfered surface (3) is surrounded by a number of guide posts (4), and the distribution center of the number of guide posts (4) is concentric with the center of the corresponding mounting slot (2).

2. The aviation fastener positioning frame according to claim 1, characterized in that, The main body (1) of the row positioning frame includes a positioning plate (11) and a reinforcing frame (12). The reinforcing frame (12) is connected to the edge of the positioning plate (11) and extends protrudingly to one side of the positioning plate (11). The protruding extension end of the reinforcing frame (12) along one side of the positioning plate (11) is on the same side as the guide post (4), and the mounting groove (2) is opened through the positioning plate (11).

3. The aviation fastener positioning frame according to claim 2, characterized in that, One edge of the reinforcing rib frame (12) is provided with a rounded corner (5) that matches the R-angle profile of the wing. The surface of the rounded corner (5) is provided with double-sided adhesive with release paper, and the double-sided adhesive with release paper on the surface of the rounded corner (5) and the double-sided adhesive with release paper on the back of the main body (1) of the row positioning frame are integrally formed.

4. The aviation fastener row positioning frame according to claim 3, characterized in that, The end of the reinforcing frame (12) away from the positioning plate (11) and the end of the guide column (4) away from the positioning plate (11) are on the same horizontal plane.

5. The aviation fastener positioning frame according to claim 4, characterized in that, The multiple guide posts (4) are perpendicular to the front of the positioning plate (11), and each guide post (4) has a chamfer on the end away from the positioning plate (11).

6. The aviation fastener row positioning frame according to claim 5, characterized in that, The positioning plate (11), the reinforcing frame (12), and the guide column (4) are integrally formed structures.

7. The aviation fastener positioning frame according to claim 1, characterized in that, Each of the chamfered bevels (3) has at least three guide posts (4) on its surface, and the three guide posts (4) are equidistant from each other along the circumferential direction of the mounting groove (2).

8. The aviation fastener positioning frame according to claim 1, characterized in that, Each of the chamfered bevels (3) is provided with four guide posts (4), and the four guide posts (4) are equidistant from each other along the circumferential direction of the mounting groove (2).

9. A method of operating the aviation fastener positioning frame according to any one of claims 1-8, characterized in that, Includes the following steps: S1. Based on the arrangement parameters of the fasteners on the aircraft parts, select the appropriate row positioning frame body (1), and take at least two positioning cores (6) to install on the two fasteners on the aircraft parts. S2. Remove the release paper from the adhesive backing of the bottom of the main body of the row positioning frame (1), align the mounting groove (2) with the fastener on the aircraft part along the axial direction of the positioning core (6), and place the main body of the row positioning frame (1) until the adhesive backing of the bottom of the main body of the row positioning frame (1) is completely attached to the surface of the aircraft part. Then apply pressure evenly to press the main body of the row positioning frame (1) to make it tightly fixed to the aircraft part. S3. After pulling out all the positioning cores (6) in sequence, apply pressure again to press the main body (1) of the row of positioning frames evenly to ensure that each mounting slot (2) is in close contact with the surface of the aircraft parts. S4. Fill the internal cavity of the sealing cap (7) with aviation sealant. After the sealant is injected, press the sealing cap (7) down slowly along the inner side wall of multiple guide posts (4) and rotate it at the same time. After the bottom of the sealing cap (7) contacts the surface of the aircraft parts, continue to rotate it 1-2 times so that the excess sealant overflows along the chamfered slope (3) onto the upper surface of the main body (1) of the row positioning frame. S5. Repeat step S4 to install the sealing cap (7) and inject the sealant into each fastener on the aircraft parts in sequence until all fasteners corresponding to the mounting slots (2) have been sealed. S6. After all the sealant has cured and set, select a non-metallic tool to insert into the adhesive backing area, lift and remove the main body of the row of positioning frames (1), and remove excess cured sealant at the same time. S7. Remove all sealing caps (7) one by one along the axial direction of the sealing cap (7) to complete the sealant encapsulation of the fasteners.

10. The operation method of the aviation fastener row positioning frame according to claim 9, characterized in that, In step S1, four positioning cores (6) are taken and installed on the two outermost fasteners at both ends of the fastener to be sealed on the aircraft parts.

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