An aircraft access door connection structure including a gooseneck joint with a stop boss

Abstract

The utility model relates to a kind of aircraft access cover connecting structure of gooseneck joint with limiting boss, belong to aircraft body structure field, by improving traditional gooseneck joint, limiting boss is set on the inner bending wall surface of the neck of gooseneck joint, limiting boss is in contact with mouth frame to form limiting when access cover is opened, to avoid to cause knock damage to mouth frame and gooseneck joint, solve the problem that gooseneck joint and mouth frame knock easily cause both damage in prior art.

Description

Technical Field

[0001] This utility model relates to the field of aircraft airframe structure, specifically to an aircraft hatch connection structure including a gooseneck connector with a limiting boss, used for limiting the opening of the aircraft maintenance hatch. Background Technology

[0002] Maintenance access panels on aircraft are frequently opened and closed. Internal maintenance is performed by opening these access panels. The connection between the access panels and the aircraft is generally achieved using a plate nut and bolts, but quick-release locks and other fasteners are also used. In all these connection methods, opening the access panel requires tools to disassemble the fasteners, which is time-consuming and labor-intensive.

[0003] Existing tool-free quick-opening and closing mechanisms for hatches typically employ a push-button hatch lock + hinge or push-button hatch lock + gooseneck connector connection. In the push-button hatch lock + hinge structure, the hinge plate is installed on the hatch and the aircraft fuselage. Because installing the hinge guide bar requires creating an installation notch in the fuselage structure, it can lead to poor sealing. Furthermore, the hinge guide bar may protrude from its theoretical surface, affecting the aircraft's local aerodynamic performance. To address the shortcomings of hinge connections, a push-button hatch lock + gooseneck connector structure can be used as an alternative. However, with traditional gooseneck connectors, during hatch opening, the lack of a limiting function in the gooseneck connector causes the inner curved wall of the neck to collide with the edge of the hatch frame (the hatch frame is a door-frame structure fixed around the hatch mounting hole in the fuselage for engagement with the hatch when closed). Prolonged use can easily damage the hatch frame and gooseneck connector. To prevent damage to the gooseneck joint and frame from impacts, elastic anti-impact material is usually pasted on the inner curved wall of the neck of the gooseneck joint. However, pasting this elastic material increases the installation process, and the pasted elastic material is prone to falling off during impacts.

[0004] Therefore, it is necessary to provide an aircraft hatch connection structure including a gooseneck connector with a limiting boss to solve the above problems. Summary of the Invention

[0005] Technical problem to be solved: In order to avoid the shortcomings of the prior art, this utility model provides an aircraft hatch connection structure including a gooseneck connector with a limiting boss. By improving the traditional gooseneck connector, a limiting boss is provided on the inner curved wall of the neck of the gooseneck connector. The limiting boss contacts the hatch frame when the hatch is opened to form a limit, thereby avoiding collision damage to the hatch frame and the gooseneck connector.

[0006] The technical solution of this utility model is: a gooseneck connector with a limiting boss, comprising: a gooseneck connector body, one end of the gooseneck connector body is hinged to a support fixed to the inner wall of the machine body, the other end of the gooseneck connector body is fixedly connected to the inner wall of the cap, the middle part of the gooseneck connector body is its neck, and a radially protruding limiting boss is provided on the inner curved wall surface of its neck, the limiting boss is used to limit the opening angle of the cap.

[0007] A further technical solution of this utility model is: one end of the gooseneck connector body is provided with a hinge hole, and a hinge shaft is passed through the hinge hole and hinged to the support; the other end of the gooseneck connector body is provided with a fixing plate, and the fixing plate and the cover are fixedly connected by fasteners.

[0008] A further technical solution of this utility model is that the limiting boss and the gooseneck connector body are integral structures.

[0009] A further technical solution of this utility model is: the position of the limiting boss on the inner curved wall of the gooseneck connector body is set according to the opening angle of the cap.

[0010] A further technical solution of this utility model is: the radial inner wall surface of the limiting boss is a curved surface, and the curvature of the curved surface is consistent with the curvature of the inner curved wall surface of the gooseneck connector body at its location.

[0011] An aircraft hatch connection structure includes: a gooseneck connector, a support, a hatch, and a push-button hatch lock. The support is a double-ear support, with two supports fixed side-by-side to the inner wall of the fuselage on one side of the hatch hole. Two gooseneck connectors are hinged to the two supports respectively, and the fixing plate of the gooseneck connector is attached to and fixedly connected to the inner wall of the hatch. The hatch is used to cover the hatch hole on the fuselage. When the hatch is closed, it overlaps with the hatch frame. When the hatch is flipped open outward around the hinge of the gooseneck connector, it is used for internal maintenance of the fuselage. The push-button hatch lock is used to lock the hatch and the hatch frame when the hatch is closed.

[0012] A further technical solution of this utility model is: the hinge end of the gooseneck joint is clamped between the two lugs of the support, the hinge hole of the gooseneck joint and the hinge hole on the two lugs of the support have the same diameter and are aligned, and the hinge is achieved by bolts passing through the hinge hole of the gooseneck joint and the hinge hole on the two lugs of the support.

[0013] A further technical solution of this utility model is that the end of the bolt is locked by a nut, which is used to prevent the bolt from falling off.

[0014] A further technical solution of this utility model is: wear-resistant bushings are installed in the hinge holes of the gooseneck joint and the hinge holes on the double lugs of the support.

[0015] The beneficial effects of this utility model are as follows: This utility model provides an aircraft hatch connection structure including a gooseneck connector with a limiting boss. By improving the traditional gooseneck connector, and in conjunction with a support and a push-button hatch lock, it can ensure tool-free and rapid opening and closing of the hatch while maintaining its sealing performance. The support and gooseneck connector, located inside the aircraft body, will not affect the local aerodynamic performance of the aircraft. Crucially, this utility model, by providing a limiting boss on the inner curved wall of the gooseneck of the connector, gives the gooseneck connector a limiting function, thereby controlling the opening angle of the hatch and ensuring that the hatch can only open within a limited range. When the hatch is opened to the limit position, the end of the limiting boss facing away from the hinge end of the gooseneck connector will engage with the edge of the hatch frame, forming a limit. This avoids impacts to the hatch frame and prevents wear and tear on the gooseneck connector body, thus improving the service life of the gooseneck connector and hatch frame.

[0016] This utility model of gooseneck connector has a simple and reliable structure, is flexible and convenient to open, and is easy to process and produce, making it highly practical. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the overall structure of a gooseneck connector with a limiting boss according to this utility model;

[0019] Figure 2 A schematic diagram of an aircraft hatch connection structure using a gooseneck connector with a limiting boss.

[0020] Figure 3 A schematic diagram of the hinged connection between the gooseneck joint with the limiting boss and the support.

[0021] Figure 4 This is a schematic diagram of the opening process of an aircraft hatch connection structure according to the present invention (not opened to the limit position).

[0022] In the figure: 1. Gooseneck connector, 11. Gooseneck connector body, 12. Hinge hole, 13. Limiting boss, 14. Fixing plate; 2. Body, 21. Cover hole, 3. Support, 31. Ear, 32. Mounting part, 4. Cover, 5. Mouth frame, 6. Bolt, 7. Nut, 8. Bushing. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0024] Example 1

[0025] This embodiment provides a gooseneck connector with a limiting boss. The gooseneck connector is a type of connecting connector. Because its shape resembles a curved gooseneck, it is called a gooseneck connector. In this embodiment, the gooseneck connector 1 is used to connect the aircraft body 2 and the cover 4. One end of it is hinged to the inner wall of the body 2, and the other end is fixed to the cover 4, which is used to realize the rotation opening and closing of the cover 4.

[0026] like Figure 1 , Figure 2 As shown, the gooseneck connector 1 in this embodiment includes a gooseneck connector body 11. One end of the gooseneck connector body 11 has a single-ear structure and a hinge hole 12 for hinged connection with a support 3 fixed to the inner wall of the machine body 2 and located on one side of the cover hole 21 of the machine body 2. The other end of the gooseneck connector body 11 has a fixing plate 14, which fits against the inner wall surface of the cover 4 and is fixedly connected by fasteners. In this embodiment, the fixing plate 14 and the cover are connected by a high-lock bolt assembly, which includes a high-lock bolt and a corresponding nut.

[0027] The gooseneck connector body 11 has its neck at the center, and a radially protruding limiting boss 13 is provided on the inner curved wall of the neck. The limiting boss 13 is used to limit the opening angle of the cap 4 to prevent the gooseneck connector body 11 from colliding with the mouth frame 5. In this embodiment, the limiting boss 13 and the gooseneck connector body 11 are integral structures. In other embodiments, the limiting boss 13 can be processed separately and installed on the inner curved wall of the neck of the gooseneck connector body 11 by fasteners. The position of the limiting boss 13 on the inner curved wall of the gooseneck connector body 11 is set according to the opening angle of the cap 4. By limiting the opening angle of the cap 4, it is possible to prevent the gooseneck connector body 11 from colliding with the edge of the mouth frame 5 when the cap 4 is overturned. The opening angle range of the cap 4 must ensure that it can be opened for internal maintenance of the machine body 2. The radial inner wall of the limiting boss 13 is curved, and the curvature of its curved surface is consistent with the curvature of the inner curved wall of the gooseneck connector body 11 at its location. Its radial protrusion height does not affect the normal opening and flipping of the gooseneck connector 1.

[0028] To reduce the weight of the gooseneck connector 1, recesses are provided on both sides of the gooseneck connector body 11, so that the cross-section of the gooseneck connector body 11 forms an I-shaped structure, which can both ensure the supporting rigidity of the gooseneck connector body 11 and reduce weight.

[0029] Example 2

[0030] This embodiment provides an aircraft hatch connection structure, such as Figure 2-4 As shown, the structure includes the gooseneck connector 1 in Embodiment 1, and also includes a support 3, a cover 4, and a push-button cover lock.

[0031] The support 3 is a double-ear support, with two supports 3 fixed side by side to the inner wall of the body 2, located on one side of the cover hole 21 on the body 2. The support 3 is fixedly connected to the body 2 by a high-lock bolt assembly. Specifically, the bottom of the support 3 is its mounting part 32, which fits against the inner wall of the body 2. The mounting part 32 has bolt holes, and the corresponding bolt mounting holes are provided on the body 2. By inserting high-lock bolts and locking them with high-lock nuts, the support 3 and the body 2 are fixedly connected. The two ears 31 of the support 3 are parallel and perpendicular to the mounting part 32 of the support 3. The two ears 31 have hinge holes perpendicular to the ears, which are used to insert bolts 6 to achieve hinge connection with the gooseneck joint 1.

[0032] Two gooseneck joints 1 are hinged to two supports 3 in a one-to-one correspondence. The single-ear structure end of the gooseneck joint 1 is inserted between the two ears 31 of the support 3, and the hinge hole 12 of the gooseneck joint 1 is aligned with the hinge hole on the two ears 31. The hinge hole 12 of the gooseneck joint 1 has the same diameter as the hinge hole of the ear 31. The bolt 3, as the hinge shaft, is inserted into the hinge hole of the gooseneck joint 1 and the two ears 31, and is locked by the nut 7 to prevent the bolt 6 from falling off. The hinge between the gooseneck joint 1 and the support 3 is achieved by the bolt 6.

[0033] To prevent wear on the hinge holes 12 of the gooseneck connector 1 and the hinge holes on the two lugs 31 during use, bushings 8 are installed inside the hinge holes 12 of the gooseneck connector 1 and the hinge holes of the lugs 31. Figure 3 As shown, bushing 8 is a stepped bushing with an inner diameter that matches the outer diameter of bolt 6, ensuring that bolt 6 can be inserted into bushing 8. Its outer diameter has a large-diameter section and a small-diameter section, forming a stepped outer diameter. A bushing 8 is installed in the hinge holes of both lugs 31 of support 3. During installation, the large-diameter section of bushing 8 is located outside the lug 31, and the outer diameter of the small-diameter section of bushing 8 is interference-fitted with the hinge hole on the lug 31. Figure 1 As shown, two bushings 8 are installed inside the hinge hole 12 of the gooseneck joint 1. The small diameter sections of the two bushings are opposite each other, so that the small diameter section of the bushing 8 is pressed into the hinge hole 12 of the gooseneck joint 1, and the large diameter section of the bushing 8 is placed outside the hinge hole 12 of the gooseneck joint 1. When the bushing 8 wears out, the service life of the gooseneck joint 1 and the support 3 is improved by replacing the bushing 8.

[0034] The cover 4 is used to cover the cover hole 21 on the machine body 2. When the cover 4 is closed, it overlaps with the cover frame 5. When the cover 4 is flipped outward around the hinge point of the gooseneck joint 1, i.e., the bolt 6, it allows for internal maintenance of the machine body 2. The cover frame 5 is a door frame structure fixed around the cover mounting hole 21 on the machine body 2 and used to cooperate with the cover 4 when it is closed. It serves to reinforce the area around the cover hole 21 and prevent damage to the area around the cover hole 21. At the same time, it can also achieve a tight fit with the cover 4 and ensure the sealing performance of the cover 4. In this embodiment, an elastic sealing material is provided between the contact surfaces of the cover frame 5 and the cover 4. This material provides cushioning and wear resistance when the cover 4 is closed, improves the sealing performance of the cover 4 when closed, and prevents the cover 4 and the cover frame 5 from bumping against each other.

[0035] The push-button cover lock is used to lock the cover 4 and the frame 5 when the cover 4 is closed. It is fixed to the inner wall of the cover 4 and located at the end of the cover 4 away from the support 3, which is not shown in the attached figure. The push-button cover lock in this embodiment adopts a standard part of the aviation industry, which is a push-button spring snap lock, model HB2-71. Its unlocking switch is located on the outer wall of the cover 4. The cover 4 is unlocked and opened by pressing the switch.

[0036] Specific working principle

[0037] When the cover 4 is opened, the push-button cover lock is unlocked, and the cover 4 flips outward around the bolt 6 towards the outside of the body 2. At this time, the gooseneck connector 1 flips outward along with the cover 4. When the cover 4 is flipped to a limited angle, the limiting boss 13 of the gooseneck connector 1 contacts the mouth frame 5 to form a limit. When the cover 4 is closed, push the cover 4 towards the body 2 until the cover 4 contacts the mouth frame 5. The locking tongue of the push-button cover lock engages with the mouth frame 5 to lock the cover 4.

[0038] When installing the cap connection structure, first fix the fixing plate 14 of the gooseneck connector 1 to the cap 4 using a high-lock bolt assembly, then fix the mounting part 32 of the support 3 to the body 2 using a high-lock bolt assembly, then align the hinge hole 12 of the gooseneck connector 1 with the hinge hole of the double lug of the support 3, insert the bolt 6, then put the nut 7 on the bolt 6 and tighten it to complete the installation.

[0039] When disassembling the cap connection structure, remove the hinge between the connecting support 3 and the gooseneck connector 1, first remove the nut 7, then remove the bolt 6, and separate the support 3 from the gooseneck connector 1; then remove the high-locking bolt assembly connecting the fixing plate 14 and the cap 2; finally, remove the high-locking bolt assembly connecting the support 3 and the body 2 to complete the disassembly.

[0040] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A gooseneck joint with a limiting boss, characterized in that, include: The gooseneck connector body has one end hinged to a support fixed to the inner wall of the machine body, and the other end fixedly connected to the inner wall of the cap. The middle part of the gooseneck connector body is its neck, and a radially protruding limiting boss is provided on the inner curved wall surface of its neck. The limiting boss is used to limit the opening angle of the cap.

2. The gooseneck joint with a limiting boss according to claim 1, characterized in that, One end of the gooseneck connector body is provided with a hinge hole, and a hinge shaft is passed through the hinge hole and hinged to the support; the other end of the gooseneck connector body is provided with a fixing plate, and the fixing plate and the cover are fixedly connected by fasteners.

3. The gooseneck joint with a limiting boss according to claim 1, characterized in that, The limiting boss and the gooseneck connector body are integral structures.

4. The gooseneck joint with a limiting boss according to claim 1, characterized in that, The position of the limiting boss on the inner curved wall of the gooseneck connector body is set according to the opening angle of the cap.

5. The gooseneck joint with a limiting boss according to claim 1, characterized in that, The radial inner wall surface of the limiting boss is curved, and the curvature of the curved surface is consistent with the curvature of the inner curved wall surface of the gooseneck connector body at its location.

6. An aircraft hatch connection structure, characterized in that, include: The gooseneck connector, support, cap, and push-button cap lock as described in claim 2; The support is a double-ear support, with two supports fixed side by side to the inner wall of the machine body on one side of the cap hole; two gooseneck joints are hinged to the two supports respectively, and the fixing plate of the gooseneck joint is attached to and fixedly connected to the inner wall of the cap; the cap is used to cover the cap hole on the machine body, and when the cap is closed, it overlaps with the cap frame. When the cap is flipped open outward around the hinge of the gooseneck joint, it is used for internal maintenance of the machine body; the push-type cap lock is used to lock the cap and the cap frame when the cap is closed.

7. The aircraft hatch connection structure according to claim 6, characterized in that, The hinge end of the gooseneck connector is clamped between the two lugs of the support. The hinge hole of the gooseneck connector and the hinge hole on the two lugs of the support have the same diameter and are aligned. The hinge is achieved by bolts passing through the hinge hole of the gooseneck connector and the hinge hole on the two lugs of the support.

8. The aircraft hatch connection structure according to claim 7, characterized in that, The end of the bolt is locked by a nut, which is used to prevent the bolt from falling off.

9. The aircraft hatch connection structure according to claim 7, characterized in that, Wear-resistant bushings are installed in the hinge holes of the gooseneck joint and the hinge holes on the double lugs of the support.

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