A fastener for aerospace sealing devices

Abstract

The application discloses a fastener for a spaceflight sealing device and belongs to the technical field of spaceflight fastening structures. When a locking piece after sealing glue solidification is disassembled, a special-shaped sink is first inserted, a rotating disc is quickly rotated, the rotating disc drives a friction shaft to rotate, the friction shaft generates heat in the sink hole, the heat is conducted to a stud, the temperature of friction heats the solidified sealing glue, after the sealing glue is melted, the special-shaped through groove on the screw head is rotated through a hexagonal screw cutter, and the whole fastener can be taken out. The fastener can be non-destructively removed in the state of being hit by the sealing glue without relying on other heating tools, the disassembly integrity of the workpiece is guaranteed, damage to the threads of the structural parts is not easy, the whole locking piece structure is compact without gaps, has the physical characteristics of high strength and deformation resistance, the fastener is convenient to disassemble, the part damage rate is reduced, and the part cost is saved for the maintenance engineering in the spaceflight field.

Description

Technical Field

[0001] This invention belongs to the field of aerospace fastening structure technology, specifically relating to a fastener used in aerospace sealing devices. Background Technology

[0002] Aerospace fasteners are used in large quantities and across a wide range of applications, with extremely high requirements for their quality and reliability. Over a million fasteners are used in a single model, and a problem with any one of them can lead to model failure or even total failure. The complex and diverse model requirements necessitate that aerospace fasteners adapt to various complex and demanding environmental conditions. The extremely wide range of service environments necessitates that aerospace fasteners meet extreme environmental conditions such as wide temperature ranges, high vibration, high impact, and strong radiation.

[0003] Common fasteners are screws with threaded heads. These fasteners have a simple structure and can be used to lock and connect aerospace components. To increase their tightness and ensure the extreme environmental adaptability of aerospace components, sealant can be added to the threaded holes at the connection points of aerospace structures. The sealant ensures a tight connection between the fastener and the aerospace component and also ensures the sealing of the aerospace component. When disassembling aerospace components after applying sealant, the fastener is extremely difficult to remove because the sealant has solidified. Forced disassembly can easily damage the threaded holes, causing damage to the aerospace component and resulting in a waste of materials. Heating the sealant with heating tools can also easily damage the structure of the aerospace component, and the sealant at the threads is unlikely to reach its melting temperature. Summary of the Invention

[0004] In view of this, the purpose of the present invention is to provide a fastener for aerospace sealing devices, wherein a temporary heating structure is provided inside the fastener for disassembling the fastener to melt the sealant at the threaded hole of the aerospace component.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] This invention includes a screw body, which comprises a stud and a screw head. A layer of sealant is applied around the stud, and a friction core is also included. A cylindrical countersunk hole is coaxially formed inside the stud. A disc-shaped groove with a diameter larger than the countersunk hole is formed inside the screw head. The friction core includes a friction shaft and a rotating disk. The friction shaft is fixed to one side of the rotating disk and is rotatably disposed within the countersunk hole. The area around the friction shaft is roughened. The rotating disk is coaxially rotatably disposed within the groove. A shaped through groove is formed at the top of the screw head, leading to the rotating disk. A shaped countersunk groove is formed on the rotating disk, with a cross-sectional area smaller than the through groove. The friction core rotates within the screw body and heats the stud.

[0007] Furthermore, the screw head includes a cap and a lower seat. The lower seat is integral with the stud. The cap is upside down on the lower seat. The inner side of the cap and the outer side of the lower seat are threaded together. The irregular through groove is formed on the upper end face of the cap. The groove is formed on the upper end face of the lower seat. A rubber ring is provided on the upper end face of the lower seat outside the groove.

[0008] Furthermore, a pressure ring is provided at the lower edge of the cover.

[0009] Furthermore, the outer side of the rotating disk has several U-shaped slots, and steel balls are placed inside the U-shaped slots. The steel balls partially leak out from the U-shaped slots, and when the rotating disk is placed in the slot, the steel balls abut against the inside of the slot.

[0010] Furthermore, three insertion holes are arrayed on the top side of the lower seat.

[0011] Furthermore, the friction shaft has several elastic protrusions on its side.

[0012] The beneficial effects of this invention are as follows:

[0013] This invention allows for the application of sealant into holes during the connection of aerospace structures. Once the sealant solidifies, it enhances the strength and sealing of the connection. When tightening the fastener, a hexagonal screwdriver of the appropriate size is inserted into a hexagonal groove to screw the fastener in, completing the connection. To disassemble the fastener after the sealant has solidified, first rotate the hexagonal screwdriver corresponding to the groove on the rotating disc. After inserting the screwdriver into the groove, quickly rotate the rotating disc. The rotating disc drives the friction shaft to rotate, generating heat through friction within the countersunk hole. This heat is conducted to the stud, and the friction temperature heats the solidified sealant, causing it to melt. Once melted, the entire fastener can be removed by rotating the groove on the screw head using the hexagonal screwdriver. This fastener allows for non-destructive removal of the sealed component without the need for other heating tools, ensuring the integrity of the disassembly and minimizing damage to the threads of structural parts. The entire locking structure is tight and gapless, possessing high strength and resistance to deformation. In the structural connections of aerospace sealing devices, it enhances the sealing performance and stability. This fastener is easy to disassemble, reducing component damage rates and saving component costs for maintenance projects in the aerospace field.

[0014] Other advantages, objectives, and features of the invention will be set forth in the following description and will be apparent to those skilled in the art in some respects, or may be learned by practice of the invention. The objectives and other advantages of the invention can be realized and obtained through the following description. Attached Figure Description

[0015] To make the objectives, technical solutions, and beneficial effects of this invention clearer, the following figures are provided for illustration:

[0016] Figure 1 This is an overall schematic diagram of the fastener according to an embodiment of the present invention;

[0017] Figure 2 This is a locking cross-sectional view of the fastener according to an embodiment of the present invention;

[0018] Figure 3 for Figure 2 Enlarged view of point A;

[0019] Figure 4 This is a schematic diagram of the assembly of the screw body according to an embodiment of the present invention;

[0020] Figure 5 This is a schematic diagram of the disassembly aid tool for the stud and lower seat of the present invention;

[0021] Figure 6 for Figure 2 Enlarged view of point B;

[0022] The following are the markings in the attached diagram: 1. Screw body; 11. Stud; 111. Countersunk hole; 12. Screw head; 121. Cap; 122. Lower seat; 123. Groove; 124. Irregular through groove; 125. Irregular countersunk groove; 126. Rubber ring; 127. Pressure ring; 128. Insertion hole; 2. Friction inner core; 21. Friction shaft; 211. Elastic protrusion; 22. Rotating disk; 221. U-shaped groove; 222. Steel ball. Detailed Implementation

[0023] like Figures 1-4 As shown, this invention discloses a fastener for aerospace sealing devices, used for connecting and locking aerospace structural components, and featuring a unique heat-melting disassembly function. The specific structure is as follows (see reference). Figure 1 and Figure 2This fastener includes a screw body 1 and a friction core 2. The screw body 1 includes a stud 11 and a screw head 12. The stud 11 has a coaxial cylindrical countersunk hole 111 inside. The screw head 12 has a disc-shaped groove 123 with a diameter larger than the countersunk hole 111 inside. The friction core 2 includes a friction shaft 21 and a rotating disk 22. The friction shaft 21 is fixed to one side of the rotating disk 22 and is rotatably disposed within the countersunk hole 111. The friction shaft 21 is roughened around its perimeter. The rotating disk 22 is coaxially rotatably disposed within the groove 123. The outer diameter of screw 12 is smaller than the inner diameter of countersunk hole 111; a special-shaped through groove 124 is opened at the top of the screw head 12, the special-shaped through groove 124 is a hexagonal hole, the special-shaped through groove 124 leads to the rotating disk 22, a special-shaped countersunk groove 125 is opened on the rotating disk 22, the special-shaped countersunk groove 125 is a hexagonal hole, the cross-sectional size of the special-shaped countersunk groove 125 is smaller than that of the special-shaped through groove 124, the screw body 1 is tightened by rotating the special-shaped through groove 124 by rotating the hexagonal head, the friction inner core 2 rotates in the screw body 1 and heats the stud 11 by rotating the special-shaped countersunk groove 125 by rotating the hexagonal head.

[0024] When connecting aerospace structures, the fasteners of this structure can be sealed with sealant inside the holes. After the sealant solidifies, it can improve the firmness and sealing of the connection. When locking the fastener, a hexagonal screwdriver of the corresponding size is inserted into the hexagonal groove 124 to screw the locking part in, thus completing the connection. When disassembling the locking part after the sealant has solidified, first rotate the hexagonal screwdriver corresponding to the groove 125 on the rotating disk 22, insert it into the groove 125, and then quickly rotate the rotating disk 22. The rotating disk 22 drives the friction shaft 21 to rotate. The friction shaft 21 generates heat through friction in the countersunk hole 111, which is conducted to the stud 11. The temperature of the friction will heat the solidified sealant, causing it to melt. After it melts, the entire fastener can be removed by rotating the groove 124 on the screw head 12 with the hexagonal screwdriver. This fastener allows for non-destructive removal of the sealed component without the need for other heating tools, ensuring the integrity of the disassembly and minimizing damage to the threads of structural parts. The entire locking structure is tight and gapless, possessing high strength and resistance to deformation. In the structural connections of aerospace sealing devices, it enhances the sealing performance and stability. This fastener is easy to disassemble, reducing component damage rates and saving component costs for maintenance projects in the aerospace field.

[0025] In further proposals, such as Figure 2 and Figure 4As shown, the screw head 12 includes a cover 121 and a lower seat 122. The lower seat 122 is integral with the stud 11. The cover 121 is upside down on the lower seat 122. The inner side of the cover 121 and the outer side of the lower seat 122 are threaded together. The irregular through groove 124 is formed on the upper end face of the cover 121. A pressure ring 127 is provided on the lower edge of the cover 121. The groove 123 is formed on the upper end face of the lower seat 122. A rubber ring 126 is provided on the upper end face of the lower seat 122 outside the groove 123. Three insertion holes 128 are also arrayed on the top side of the lower seat 122.

[0026] This design optimizes the specific structure of the fastener, making it easier to assemble. When assembling the fastener, the friction core 2 can be directly inserted into the countersunk hole 111 at the upper end of the lower seat 122, along with the rubber ring, and finally the cover 121 is tightened. When the fastener locks the structural component, rotating the irregular through groove 124 causes the fastener to screw into the threaded hole of the structural component. Continued force is applied to rotate the fastener, causing the cover 121 to press down on the rubber ring, deforming it. The cover 121 presses down on the surface of the structural component, providing outward tension to the stud 11, thus providing additional tension to the structural component and enhancing its sealing and fit. This locking mechanism facilitates assembly; each component is installed via an insertion and tightening method. Each part can be manufactured separately, resulting in a highly integrated fastener that will not lose any components. In the further optimized structure, a pressure ring 127 is provided at the lower edge of the cover 121 to provide more contact and pressing area for the cover 121; there is a gap between the rotating disk 22 and the recess, so the temperature between the cover 121 and the lower seat 122 will not overheat and the sealant will not melt. When this fastener is removed from the aerospace structure, the sealant at the threaded hole melts, and when the irregular through groove 124 is rotated, the cover 121 is prevented from unscrewing first. To prevent the cover 121 from accidentally unscrewing, the stud 11 remains in the threaded hole. Three insertion holes 128 are provided on the top side of the lower seat 122, and configured as follows: Figure 5 The disassembly aid tool assists in the disassembly of the stud 11. It is worth noting that thread-locking adhesive can also be added to the threads between the cover 121 and the lower seat 122 to improve the overall tightness of the fastener.

[0027] In further proposals, such as Figure 2 and Figure 3 As shown, the outer side of the rotating disk 22 has several U-shaped slots 221, and steel balls 222 are placed inside the U-shaped slots 221. The steel balls 222 partially protrude from the U-shaped slots 221. When the rotating disk 22 is placed in the groove 123, the steel balls 222 abut against the inner side of the groove 123.

[0028] In this design, a U-shaped slot 221 is provided on the outside of the rotating disk 22, allowing the steel ball 222 to be directly inserted during fastener assembly, facilitating assembly. The steel ball 222 is inserted into the slot 123 along with the rotating disk 22. This provides a smoother rotation space for the rotating disk 22 within the slot 123, reducing friction between the rotating disk 22 and the slot 123 support. Furthermore, it prevents temperature rise at the rotating disk 22 and the lower seat 122, ensuring that the sealant between the cover 121 and the lower seat 122 is not melted when melting the sealant around the stud 11. When disassembling the entire fastener from the aerospace component, the connection between the cover 121 and the lower seat 122 is tighter than that between the stud 11 and the threaded hole. Therefore, the stud 11 can be removed from the threaded hole earlier, ensuring the integrity of the entire fastener, reducing the need for auxiliary tools, and improving disassembly efficiency.

[0029] In further proposals, such as Figure 2 and Figure 6 As shown, the friction shaft 21 has several elastic protrusions 211 on its side.

[0030] In this scheme, by setting several elastic protrusions 211, when the friction shaft 21 rotates in the countersunk hole 111, the elastic protrusions 211 always abut against the side wall of the countersunk hole 111, providing more frictional contact, avoiding the failure of frictional contact between the friction shaft 21 and the countersunk hole 111, and improving the heating effect of the friction shaft 21.

[0031] Finally, it should be noted that the above preferred embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail through the above preferred embodiments, those skilled in the art should understand that various changes can be made to it in form and detail without departing from the scope defined by the claims of the present invention.

Claims

1. A fastener for an aerospace sealing device, comprising a screw body (1), the screw body (1) including a stud (11) and a screw head (12), wherein a layer of sealant is applied around the stud (11), characterized in that: It also includes a friction core (2), in which a cylindrical countersunk hole (111) is coaxially formed inside the stud (11), and a disc-shaped groove (123) with a diameter larger than the countersunk hole (111) is formed inside the screw head (12). The friction core (2) includes a friction shaft (21) and a rotating disk (22). The friction shaft (21) is fixed to one side of the rotating disk (22), and the friction shaft (21) is rotatably disposed in the countersunk hole (111). The friction shaft (21) is circumferentially... The surrounding surface is roughened. The rotating disk (22) is coaxially rotatably disposed in the groove (123). A special-shaped through groove (124) is opened at the top of the screw head (12), and the special-shaped through groove (124) leads to the rotating disk (22). A special-shaped recessed groove (125) is opened on the rotating disk (22). The cross-sectional size of the special-shaped recessed groove (125) is smaller than that of the special-shaped through groove (124). The friction inner core (2) rotates in the screw body (1) and heats the stud (11).

2. The fastener for aerospace sealing devices according to claim 1, characterized in that: The screw head (12) includes a cover (121) and a lower seat (122). The lower seat (122) is integral with the stud (11). The cover (121) is upside down on the lower seat (122). The inner side of the cover (121) and the outer side of the lower seat (122) are threaded together. The irregular through groove (124) is opened on the upper end face of the cover (121). The groove body (123) is opened on the upper end face of the lower seat (122). The upper end face of the lower seat (122) is provided with a rubber ring (126) outside the groove body (123).

3. The fastener for aerospace sealing devices according to claim 2, characterized in that: The lower edge of the cover (121) is provided with a pressure ring (127).

4. The fastener for aerospace sealing devices according to claim 2, characterized in that: The rotating disk (22) has several U-shaped slots (221) arranged on its outer side. The U-shaped slots (221) contain steel balls (222). The steel balls (222) partially protrude from the U-shaped slots (221). When the rotating disk (22) is placed in the groove (123), the steel balls (222) abut against the inner side of the groove (123).

5. The fastener for aerospace sealing devices according to claim 2, characterized in that: The lower seat (122) also has three sockets (128) arranged on the top side, which are used in conjunction with disassembly auxiliary tools.

6. The fastener for aerospace sealing devices according to claim 2, characterized in that: The friction shaft (21) has several elastic protrusions (211) on its side.

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