Reinforcing plate and reinforcing structure of aircraft system opening

Abstract

The utility model discloses a reinforcing plate and a reinforcing structure of an airplane system opening, which can improve the fatigue performance of the connecting part of the reinforcing plate and a system part. A reinforcing plate is included in a reinforcing structure of an airplane system opening, the reinforcing structure further comprises a system part and an airplane body assembly with an opening, one side of the reinforcing plate in the thickness direction is overlapped and connected with the periphery of the opening of the airplane body assembly and an adjacent part, close to the periphery of the opening, of the system part, and a convex part is arranged on the reinforcing plate. The protruding portion protrudes from the plate surface of the reinforcement plate in the thickness direction, and when viewed in the thickness direction, the adjacent portion does not exceed the range of the opening, and the range of the portion where the adjacent portion and the reinforcement plate are connected does not exceed the range of the protruding portion.

Description

Technical Field

[0001] The utility model relates to the field of aircraft, in particular to a reinforcement plate for an aircraft system and a reinforcement structure for an opening of an aircraft system. Background Art

[0002] Aircraft fuselage components (such as skins and bulkheads) often have openings to allow for maintenance or access to related systems. These installed systems are directly or indirectly secured to the components. Generally speaking, these openings disrupt the continuity of the components, causing stress concentration in the area of ​​the opening. Therefore, reinforcement measures are required at these openings to improve the fatigue life of the components and reduce the risk of structural failure due to fatigue.

[0003] Among the aforementioned reinforcement methods, the most commonly used and most cost-effective is the reinforcing plate. Conventional reinforcement structures using reinforcing plates consist of system components, a body assembly, and the reinforcing plate. The reinforcing plate is a single-layer plate made of a composite metal material. The reinforcing plate is attached from one side to the periphery of the opening near the body assembly, and the system components are attached to the reinforcing plate from the other side through the opening.

[0004] In the aforementioned existing aircraft system opening reinforcement structures, system components are mostly small and lightweight components such as cover plates, placing lower fatigue performance requirements on the connection between the reinforcement plate and the system component. However, in addition to cover plates, system components also include larger and heavier components such as pipes. When these heavier components are present, stress increases at the connection between the reinforcement plate and the system component, creating a need to enhance fatigue performance at the connection between the reinforcement plate and the system component. Utility Model Content

[0005] The present invention is completed in view of the above problems, and its purpose is to provide a reinforcement plate and a reinforcement structure for an aircraft system opening, which can improve the fatigue performance of the connection part between the reinforcement plate and the system component.

[0006] In order to achieve the above-mentioned purpose, the present invention provides a reinforcing plate, which is included in a reinforcing structure of an aircraft system opening, the reinforcing structure also including a system component and a body component having an opening, the reinforcing plate overlapping and connected on one side in the thickness direction with the opening peripheral portion of the body component and the adjacent portion of the system component close to the opening peripheral portion, wherein a convex portion is provided on the reinforcing plate, the convex portion protruding from the plate surface of the reinforcing plate along the thickness direction, when viewed along the thickness direction, the adjacent portion does not exceed the range of the opening, and the range of the portion where the adjacent portion is connected to the reinforcing plate does not exceed the range of the convex portion.

[0007] According to this structure, by providing a protrusion on the reinforcing plate, and arranging the connection between the protrusion and the adjacent portion on the system component to not exceed the extent of the protrusion when viewed in the thickness direction, the thickness of the reinforcing plate at the connection with the system component is increased, stress is reduced, and fatigue performance of the connection is improved. Furthermore, since the adjacent portion does not exceed the extent of the opening in the body component when viewed in the thickness direction, the peripheral edge of the opening in the body component is not obscured by the system component, facilitating inspection of the peripheral edge of the opening during damage tolerance analysis.

[0008] Furthermore, in the reinforcing plate of the present invention, preferably, the reinforcing plate and the adjacent portion are fastened together by a detachable first fastener.

[0009] According to this structure, the system components can be attached and detached to perform maintenance and replacement of the system components.

[0010] In addition, in the reinforcing plate of the present invention, preferably, the first fastener includes a bolt and a nut, and a through hole for inserting the screw rod of the bolt is provided at the corresponding position of the reinforcing plate and the adjacent part, and the nut is threadedly engaged with the bolt from the one side.

[0011] In addition, in the reinforcing plate of the present invention, preferably, the ratio of the distance from the edge of the through hole to the edge of the opening to the diameter of the through hole is greater than 2, and the ratio of the distance from the edge of the through hole to the edge of the protrusion to the diameter of the through hole is greater than 2.

[0012] According to this structure, stress concentration due to the through hole is reduced at the connection portion between the reinforcing plate and the adjacent portion, and thus fatigue performance of the connection portion between the reinforcing plate and the adjacent portion can be improved.

[0013] In addition, in the reinforcing plate of the present invention, it is preferred that a recess is provided on the reinforcing plate, the recess is recessed from the surface of the one side of the reinforcing plate, and the bottom is connected to the through hole, and the nut can be fixedly received in the recess in a manner of restricted movement.

[0014] According to this structure, the system components can be removed and installed from a single surface, thereby facilitating the repair and replacement of the system components.

[0015] In addition, in the reinforcement plate of the present invention, preferably, the body component is a skin, and the reinforcement plate is fastened to the peripheral portion of the opening by a non-detachable second fastener, and a plurality of the second fasteners are arranged along the periphery of the opening and are spaced apart from the edge of the opening.

[0016] Furthermore, in the reinforcing plate of the present invention, preferably, the second fasteners are arranged in a plurality of rows at different intervals from the edge of the opening.

[0017] According to this structure, the skin and the reinforcing plate are connected by multiple rows of fasteners, which can improve the stability of the connection between the skin and the reinforcing plate.

[0018] Furthermore, in the reinforcing plate of the present invention, preferably, in the reinforcing plate, the thickness of the reinforcing plate at the second fastener close to the edge of the opening is greater than the thickness of the reinforcing plate at the second fastener away from the edge of the opening.

[0019] According to this structure, by providing a smaller thickness of the reinforcing plate at the non-stress concentration portion farther from the opening edge, the weight of the reinforcing plate can be reduced, thereby reducing the load on the aircraft.

[0020] Furthermore, in the reinforcing plate of the present invention, preferably, the protrusion extends into the opening.

[0021] The reinforcing plate of the present invention provides a protrusion within the region where it connects to the system component, thereby increasing the thickness and reducing stress in the portion of the plate that connects to the system component, thereby improving fatigue resistance in the connection. Furthermore, when viewed along the thickness direction, the adjacent portion does not extend beyond the opening of the airframe component. Therefore, the periphery of the airframe component opening is not obscured by the system component, facilitating inspection of the periphery during damage tolerance analysis. Furthermore, by providing a variable thickness structure within the reinforcing plate, the thickness of the plate in non-stress-concentrating areas is reduced, thereby achieving a lightweight reinforcing plate structure and reducing aircraft load. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1A This is a perspective view of the reinforcing plate according to the embodiment as viewed from above.

[0023] Figure 1B This is a perspective view of the reinforcing plate according to the embodiment as viewed from below.

[0024] Figure 2 It is a perspective view showing an aircraft skin with an opening according to an embodiment.

[0025] Figure 3 It is a perspective view showing system components according to the embodiment.

[0026] Figure 4 It is a perspective view of the reinforcement structure cut along the radial direction of the system component according to the embodiment.

[0027] Figure 5 It is a schematic diagram showing the structure of the recessed portion according to the embodiment.

[0028] Figure 6 It will Figure 4 A diagram showing a partially enlarged section after cutting in FIG.

[0029] (Explanation of Symbols)

[0030] 1 reinforcement plate;

[0031] 2 skin;

[0032] 3 system components;

[0033] 4 through holes;

[0034] 5 bolts;

[0035] 6 nuts;

[0036] 7 washers;

[0037] 8 first groove;

[0038] 9 second groove;

[0039] 11 boards;

[0040] 12 convex parts;

[0041] 13 convex part;

[0042] 14 Opening;

[0043] 21 opening;

[0044] 31 main body;

[0045] 32 adjacent parts. DETAILED DESCRIPTION

[0046] Hereinafter, an embodiment of the present invention will be described with reference to the accompanying drawings.

[0047] Figure 4 : is a perspective view showing the reinforcement structure of this embodiment. In this embodiment, the fuselage component is the skin that constitutes the aerodynamic shape of the fuselage. Figure 4 As shown, the reinforcement structure of this embodiment mainly includes a reinforcement plate 1, a skin 2, and a system component 3. For ease of description, the thickness direction of the reinforcement plate 1, i.e., the connection direction between the skin 2 and the reinforcement plate 1, is referred to as the up-down direction, and the side of the skin 2 relative to the reinforcement plate 1 at the connection between the skin 2 and the reinforcement plate 1 is referred to as the up-down direction.

[0048] Figure 2 This is a perspective view of a skin 2 with an opening 21 in this embodiment. The skin 2 is composed, for example, of a high-strength aluminum alloy and is secured to the aircraft system framework by riveting or other means, thereby forming the aircraft's aerodynamic shape. In this embodiment, the opening 21 formed in the skin 2 is circular. The size of the opening 21 can be appropriately adjusted based on the reinforcement plate 1 and system components 3 described below.

[0049] The portion surrounding the opening 21 in the skin 2 forms an opening peripheral portion connected to the reinforcing plate 1. This opening peripheral portion is connected to the reinforcing plate 1 via a second fastener. The second fastener is, for example, a non-removable fastener such as a rivet or a high-lock bolt. To install these fasteners, a plurality of nail holes are arranged circumferentially in the opening peripheral portion at positions spaced a certain distance from the edge of the opening 21, forming a first row of nail holes. Similarly, a second row of nail holes is provided further from the edge of the opening 21 than the first row of nail holes. Thus, the skin 2 and the reinforcing plate 1 can be connected via two circumferential rows of fasteners, improving the stability of the connection.

[0050] Figure 3 3D is a perspective view of the system component 3 of this embodiment. In this embodiment, the system component 3 includes a main body 31 and an adjacent portion 32 to which the reinforcing plate 1 is connected. In the main body 31, an upper portion and a lower portion are formed relative to the adjacent portion 32 in the vertical direction. Figure 3 As shown, in this embodiment, the lower portion is cylindrical with its longitudinal direction in the vertical direction, while the upper portion is hemispherical. The upper and lower portions have the same radial dimensions. When the system component 3 is mounted on the reinforcing plate 1 connected to the skin 2, the upper portion is positioned above the skin 2, while the lower portion extends downward through the opening in the skin 2. Furthermore, the lower portion is configured to fit through an opening 14 formed in the reinforcing plate 1, described later.

[0051] In this embodiment, the adjacent portion 32 is formed as a flange that protrudes radially outward from the main body 31 and extends in the vertical direction, and is connected to the boss 12 of the reinforcing plate 1 described later by a first fastener. The first fastener includes a bolt 5 and a nut 6, and a plurality of through holes for the screw rods of the bolts 5 to pass through are provided on the adjacent portion 32. Figure 4 As shown, when viewed in the up-down direction, the outer edge of the adjacent portion 32 is circular. In addition, the thickness of the adjacent portion 32 can be appropriately set according to the fatigue strength and fatigue performance actually required.

[0052] in addition, Figure 3 The illustrated system component 3 is merely an example; it may be any system component positioned within the opening of the aircraft skin system as required. For example, the outer edge of the adjacent portion 32 may also have a shape other than circular, such as a rectangle or hexagon. Furthermore, the structure of the main body 31 may be arbitrarily configured based on the functional requirements of the system component 3.

[0053] Figure 1A and Figure 1B This is a perspective view of the reinforcing plate 1 of this embodiment, wherein: Figure 1A shows the reinforcing plate 1 as viewed from above, Figure 1B The reinforcing plate 1 is shown as viewed from below.

[0054] like Figure 1A and Figure 1B As shown, the reinforcing plate 1 of this embodiment includes a plate body 11 and two bosses 12 and 13 protruding from both side surfaces of the plate body 11 in the vertical direction.

[0055] The panel body 11 is made of, for example, an aluminum alloy and is formed into an annular disk with a circular opening 14 at its center. The opening 14 is sized to allow the main body 31 of the system component 3 to pass through when the system component 3 is connected to the reinforcing plate 1. Furthermore, when viewed from above and below, the opening 14 is smaller than the opening 21 of the skin 2, and the outer edge of the panel body 11 is larger than the opening 21.

[0056] Bosses 12 and 13 project vertically from the upper and lower surfaces of plate body 11, respectively, and are integrally formed with plate body 11. These bosses can be fabricated, for example, by machining a metal plate such as by lathing. When viewed vertically, bosses 12 and 13 are annular in shape, concentric with plate body 11, and similarly have a circular opening 14 at their centers.

[0057] In this embodiment, the boss 12 is a portion of the reinforcing plate 1 for connecting with the adjacent portion 32 of the system component 3 and is formed on the upper side of the plate body 11. Figure 4 As shown, when the boss 12 is connected to the adjacent portion 32, the boss 12 overlaps and is connected to the adjacent portion 32. At this time, when viewed in the vertical direction, the outer edge of the boss 12 coincides with the outer edge of the adjacent portion 32. Furthermore, preferably, when the reinforcing plate 1 is connected to the skin 2, the boss 12 enters the opening 21 and the outer circumference of the boss 12 closely fits the inner circumference of the opening 21, that is, when viewed in the vertical direction, the outer edge of the boss 12 coincides with the edge of the opening 21.

[0058] As a result, when viewed from above, the system component 3 does not obstruct the perimeter of the opening in the skin 2. Therefore, when performing damage tolerance analysis on the skin 2, a primary aircraft structural component, maintenance personnel can directly inspect fatigue conditions such as cracks at the edges of the opening 21 and the edges of the first row of nail holes in the perimeter of the opening.

[0059] As shown in Figure 6, the height of the boss 12 protruding from the upper surface of the panel body 11 (i.e., the thickness of the boss 12) is the same as the thickness of the skin 2. However, this is not limiting, and the thickness of the boss 12 can be appropriately set according to the actual fatigue performance required, and can also be greater or less than the thickness of the skin.

[0060] The boss 13 is formed on the lower side of the plate body 11, and its outer peripheral size is not less than the outer peripheral size of the boss 12. Figure 6In the embodiment, the height of the boss 13 protruding from the lower plate surface of the plate body 11 (i.e., the thickness of the boss 13) is set to be substantially the same as the thickness of the boss 12. However, the thickness of the boss 13 can also be appropriately set according to the fatigue performance actually required.

[0061] like Figure 4 and Figure 6 As shown, a through hole 4 for inserting the screw rod of a bolt 5 is provided on the boss of the reinforcing plate 1. Through hole 4 extends vertically, with one end opening at the upper end surface of the boss 12 and the other end opening at the bottom surface of the first recess 8, described later. Furthermore, multiple through holes 4 are provided at angular intervals in the circumferential direction, preferably in the range of 30° to 45°.

[0062] In this embodiment, the through-holes 4 have a circular cross-sectional shape and a diameter of d. As described above, when the reinforcing plate 1 is mounted and connected to the skin 2, the outer periphery of the boss 12 closely mates with the inner periphery of the opening 21. In this case, in the radial direction of the opening 21, the distance from the center of the cross-sectional shape of each through-hole 4 to the edge of the opening 21 (i.e., to the outer edge of the boss 12) is preferably greater than 2.5d. In other words, the distance from the edge of each through-hole 4 to the edge of the opening 21 is preferably greater than 2d. Furthermore, in the radial direction, the distance from the center of the cross-sectional shape of each through-hole 4 to the edge of the opening 14 of the reinforcing plate 1 (i.e., the inner edge of the bosses 12 and 13) is also preferably greater than 2.5d. In other words, the distance from the edge of each through-hole 4 to the edge of the opening 14 is preferably greater than 2d. This reduces the stress concentration effect on both sides of the through-hole 4 in the radial direction of the bosses 12 and 13, thereby improving the fatigue performance of the connection between the reinforcing plate 1 and the system component 3.

[0063] In order to facilitate the single-sided disassembly and assembly of the system component 3 on the side where the system component 3 is installed (the upper side in this embodiment), as shown in FIG. Figure 5 、 Figure 6 As shown, a first groove 8 is formed on the lower end surface of the boss 13, which is sunken upward. The first groove 8 is open downward, and its upper inner surface (bottom) is connected to the through hole 4. In addition, multiple first grooves 8 are provided corresponding to the through holes 4. The inner shape of the first groove 8 is configured to limit the rotation of the nut 6. The first groove 8 can be configured accordingly based on the shape of the nut 6 used, and the depth of the first groove 8 is greater than the thickness of the nut 6 used.

[0064] Furthermore, to prevent the nut 6 from loosening and moving vertically along the screw rod, a second groove 9 for receiving the washer 7 is formed on the inner circumference of the first groove 8, below the lower end of the nut 6, when the upper end of the nut 6 abuts the bottom of the first groove 8. This second groove 9, recessed outward from the inner circumference of the first groove 8, accommodates and retains the washer 7. The washer 7, for example, is a radially elastically deformable spring washer. When compressed, it enters the first groove 8 and recovers in the second groove 9, where it is received and retained. In this manner, if the nut 6 loosens and moves downward along the bolt 5, the washer 7 abuts the nut 6 from below, limiting further downward movement and preventing it from falling out due to loosening. This prevents the nut 6 from rotating and preventing it from falling out due to loosening, enabling single-sided disassembly and assembly of the system component 3 and improving replacement efficiency.

[0065] In addition, as described above, the panel body 11 is connected to the peripheral portion of the opening of the skin 2 by a second fastener, and two rows of nail holes are provided in the portion other than the boss in the panel body 11 corresponding to the nail holes on the peripheral portion of the opening, namely, a first row of nail holes close to the opening 14 and a second row of nail holes farther away from the opening 14 than the first row of nail holes.

[0066] In the portion of the reinforcement plate body 11 connected to the skin 2, the portion close to the opening 21 is a stress concentration area requiring better fatigue performance, while the portion away from the opening 21 is a non-stress concentration area requiring relatively low fatigue performance.

[0067] Therefore, in this embodiment, if Figure 1B 、 Figure 4 as well as Figure 6 As shown, the plate body 11 of the reinforcement plate 1 has a variable thickness structure. Specifically, stepped portions are formed around the entire circumference at predetermined radial locations. The thickness of the portion radially inward (closer to the opening 14) of the stepped portion is greater than the thickness of the portion radially outward. The second row of nail holes in the plate body 11 is located in the thinner portion of the plate body 11, while the first row of nail holes is located in the thicker portion of the plate body 11. This reduces the thickness of the non-stress concentration areas of the reinforcement plate body 11, thereby reducing the weight of the reinforcement plate body 11 and, in turn, the load on the aircraft itself.

[0068] When assembling a reinforcement structure using the reinforcing plate 1 of this embodiment, the reinforcing plate 1 is first placed from below, overlapping and abutting against the skin 2. At this point, the bosses 12 on the reinforcing plate 1 enter and engage with the openings 21 in the skin 2. Rivets are then placed through two rows of pre-formed holes in the skin 2 opening perimeter and the plate 1 of the reinforcing plate body 11, securing the skin 2 and reinforcing plate 1 in an inseparable manner.

[0069] Next, the adjacent portion 32 of the system component 3 is overlapped with the boss 12 from above, and the system component 3 is removably connected to the reinforcing plate 1 using bolts 5 and nuts 6 previously secured in first grooves 8 on the boss 13. When the operator replaces the system component 3, thanks to the one-sided removable structure, they can simply remove the bolts 5 on the side where the system component 3 is mounted.

[0070] (Main Effects of This Embodiment)

[0071] According to the reinforcement plate of this embodiment, by providing a boss on the reinforcement plate and overlapping the adjacent part of the system component with the boss, the thickness of the part of the reinforcement plate connected to the system component is increased, the stress in this part is reduced, and the fatigue performance of the connection part is improved. In addition, when viewed along the thickness direction, the adjacent part does not exceed the range of the skin opening. Therefore, the peripheral edge of the skin opening will not be blocked by the system component. When performing damage tolerance analysis on the skin of the main structural component, the condition of the peripheral edge of the opening can be easily inspected, thereby improving the flight safety of the aircraft. By providing a variable thickness structure on the reinforcement plate, the thickness of the reinforcement plate in the non-stress concentration part is reduced, thereby achieving lightweight reinforcement plate structure and reducing aircraft load. In addition, by providing a structure for single-sided disassembly of the system component on the reinforcement plate, the inspection and replacement of the system component is facilitated.

[0072] The present invention has been described above by way of example with reference to the accompanying drawings. It is apparent that the specific implementation of the present invention is not limited to the above-mentioned embodiments.

[0073] In the above embodiment, bosses 12 and 13 are provided on the upper and lower sides of the reinforcing plate 1, respectively. However, this is not limiting. For example, a boss may be provided on only one side of the reinforcing plate 1 in the vertical direction, that is, only boss 12 or boss 13. In the case of providing only one of bosses 12 or 13, the height of the boss can be appropriately set to meet the fatigue performance requirements of the portion of the reinforcing plate 1 connected to the system component 3.

[0074] Furthermore, when only the boss 12 is provided, the first groove 8 can be omitted to prevent fatigue performance degradation caused by reducing the thickness of the connection portion due to the provision of the first groove 8. When only the boss 13 is provided, the adjacent portion 32 of the system component 3 is directly overlapped and connected to the plate body 11 of the reinforcing plate 1.

[0075] Furthermore, in the above embodiment, when the reinforcing plate 1, skin 2, and system component 3 are assembled, the outer edges of the boss 12, opening 21, and adjacent portion 32 overlap when viewed from above and below. However, this is not limiting. When the reinforcing plate 1 is attached to the skin 2, a gap may exist between the outer circumference of the boss 12 and the inner circumference of the opening 21, rather than a tight fit. In this case, the gap may require appropriate surface treatment.

[0076] Furthermore, the outer edge of the boss 12 does not necessarily need to coincide with the outer edge of the adjacent portion 32. The shape of the boss can be arbitrarily determined based on the actual shape of the adjacent portion 32, as long as the extent of the connection between the adjacent portion 32 and the reinforcing plate 1 does not exceed the extent of the boss when viewed in the vertical direction. For example, as described above, when only the boss 13 is provided, the adjacent portion 32 directly connects to the upper surface of the plate body 11 of the reinforcing plate 1 from above. Here, when the boss 13 is projected vertically onto the plate 1, the connection between the adjacent portion 32 and the plate body 11 falls within the projection of the boss 13.

[0077] Furthermore, in the above embodiment, the adjacent portion 32 of the system component 3 is formed integrally with the outer side of the main body 31, but the present invention is not limited thereto. For example, the system component 3 may be formed as a whole in a flat shape, with a portion of its main body directly connected to the reinforcing plate. In this case, the adjacent portion is the portion of the main body near the edge of the skin opening.

[0078] Furthermore, while the main body 31 in the above embodiment includes a portion that passes through the skin opening 21 and the reinforcing plate opening 14, this is not limiting. If the system component 3 is a component such as an indicator light, which has primary functional structures on only one side, the main body may not include a portion that passes through the aforementioned openings. In this case, if a boss is provided on the upper side of the reinforcing plate, the central opening of the reinforcing plate may not be provided.

[0079] Furthermore, in the above embodiment, the fuselage component is described as a skin, but the present invention is not limited thereto. The fuselage component may also be, for example, a bulkhead, stringer, or girder formed within the fuselage relative to the skin. System openings formed in these fuselage components can be reinforced using the reinforcement plates described in the above embodiment.

[0080] Furthermore, in the above embodiment, single-sided disassembly is achieved by limiting the rotation of the nut 6 with the first groove 8 and preventing the nut 6 from loosening and falling out with a spring washer held in the other groove. However, the method for achieving single-sided disassembly is not limited to this. For example, it can also be achieved by using any existing method such as a stop washer, a locking washer, a self-locking nut, etc. In addition, a nut with a spring washer can also be used instead of the nut and spring washer in this embodiment to achieve single-sided disassembly.

[0081] It should be understood that within the scope of the present invention, various parts in the embodiments can be freely combined, or various parts in the embodiments can be appropriately modified or omitted.

Claims

1. A reinforcing plate, included in a reinforcing structure for an aircraft system opening, the reinforcing structure also including a system component and an airframe component having an opening, wherein one side of the reinforcing plate in the thickness direction overlaps and connects with a peripheral edge of the opening of the airframe component and an adjacent portion of the system component near the peripheral edge of the opening, characterized in that: The reinforcing plate is provided with a convex portion, which protrudes from the plate surface of the reinforcing plate along the thickness direction. When viewed in the thickness direction, the adjacent portion does not exceed the range of the opening, and the range of a portion where the adjacent portion is connected to the reinforcing plate does not exceed the range of the protrusion.

2. The reinforcing plate according to claim 1, characterized in that: The reinforcing plate is fastened to the adjacent portion by a detachable first fastener.

3. The reinforcing plate according to claim 2, characterized in that: The first fastener includes a bolt and a nut, Through holes for inserting the screw rods of the bolts are provided at corresponding positions of the reinforcing plate and the adjacent portion. The nut is threadably fitted to the bolt from the one side.

4. The reinforcing plate according to claim 3, characterized in that: The ratio of the distance from the edge of the through hole to the edge of the opening to the diameter of the through hole is greater than 2, A ratio of a distance from an edge of the through hole to an edge of the protrusion to a diameter of the through hole is greater than or equal to 2.

5. The reinforcing plate according to claim 3 or 4, characterized in that: A recess is provided on the reinforcing plate, the recess is sunken from the surface of the one side of the reinforcing plate, and the bottom is communicated with the through hole. The nut can be fixedly received in the recess in a manner where movement thereof is restricted.

6. The reinforcing plate according to claim 1, characterized in that: The airframe component is a skin, The reinforcing plate is fastened to the peripheral edge of the opening by a second non-detachable fastener. A plurality of second fasteners are arranged along the periphery of the opening and are spaced apart from the edge of the opening.

7. The reinforcing plate according to claim 6, characterized in that: The second fasteners are arranged in a plurality of rows at different intervals from the edge of the opening.

8. The reinforcing plate according to claim 7, characterized in that: In the reinforcing plate, a thickness of the reinforcing plate at the second fastening piece close to the edge of the opening is greater than a thickness of the reinforcing plate at the second fastening piece far from the edge of the opening.

9. The reinforcing plate according to claim 1, characterized in that: The protrusion extends into the opening.

10. A reinforcing structure for an aircraft system opening, comprising a system component and an airframe assembly, wherein the airframe assembly has an opening, and the system component has an adjacent portion adjacent to a peripheral edge of the opening of the airframe assembly, wherein: It also includes the reinforcing plate according to any one of claims 1 to 9.

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