Composite material spar web trepanning reinforcing structure
By designing the L-shaped reinforcement structure and symmetrical side reinforcement structure on the web and edge strip of composite spar, the problems of load bearing capacity and stress concentration caused by the spar opening are solved, and the structural strengthening and safety improvement are achieved.
Patent Information
- Application Number
- CN202420844262.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-04-23
- Publication Date
- 2025-04-04
- Estimated Expiration
- 2034-04-23
AI Technical Summary
In aircraft structural design, spar openings will lead to a decrease in overall load-bearing capacity and stress concentration, affecting structural safety and service life, especially in the position of composite spar web edges, which are difficult to strengthen the holes.
Using the L-shaped reinforcement structural member and the symmetrical side reinforcement structural member, a symmetrical side reinforcement structure is formed by a first reinforcement plate fitted with the composite spar web and a second reinforcement plate fitted with the edge strip, thereby enhancing the reinforcement effect of the spar web and edge strip.
The strengthening of the spar web and edge area is achieved, the layered stress at the opening is reduced, and the overall load-bearing capacity and safety of the structure are improved.
Smart Images
Figure CN222713727U_ABST
Abstract
Description
Technical Field
[0001] The present application belongs to the field of wing spar structure design, and in particular relates to a composite material wing spar web opening reinforcement structure. Background Art
[0002] In the aircraft structure design process, there is usually a need to open holes in the aircraft structure for various reasons, such as system line openings, maintenance openings, weight reduction openings, etc. As an important load-bearing structure of the wing box section, the wing spar has high structural stress and high safety requirements. Opening holes will cause the overall bearing capacity of the wing spar to decrease and more serious stress concentration, resulting in a decrease in the static and fatigue strength of the structure, affecting the safety and service life of the structure. Therefore, the opening parts must be reinforced in the design.
[0003] For composite wing spar webs, the methods of opening reinforcement can be divided into external reinforcement, internal material reinforcement and co-curing treatment. External reinforcement: that is, adding reinforcement structure around the circular hole or elliptical hole. This reinforcement structure can be distributed on one side of the hole, on both sides of the opening structure, or a boss structure can be set on one side. The reinforcement method currently accepted by most is symmetrical reinforcement on both sides of the opening, because the structural asymmetry caused by unilateral reinforcement will cause tension-bending and tension-shear coupling; reinforcement inside the composite material: on the one hand, adding internal reinforcement structure is likely to cause the original structural load-bearing design to be destroyed and reduce the load-bearing capacity of the structure. On the other hand, this method has higher process requirements and increases cost and time; in addition, co-curing molding technology has stronger bonding and higher efficiency, and can be used to reinforce the openings of composite wing spar when the reinforcement effect is high. However, these reinforcement methods are mostly applicable when the opening is located at the center of the beam web or there is no redundant structure around the hole. When the opening is located at the edge of the beam web, especially when there is a transition connection between the spar and the flange, such as an I-beam structure or a C-beam structure, the influence of the hole edge structure also needs to be considered when reinforcing the opening. Utility Model Content
[0004] In order to solve the above problems, the present application provides a composite material wing spar web opening reinforcement structure, including a composite wing spar web with a circular opening, an L-shaped reinforcement structure member and a symmetrical side reinforcement structure member;
[0005] The L-shaped reinforcement structure comprises a first reinforcement plate bonded to the web of the composite wing spar and a second reinforcement plate bonded to the spar cap of the composite wing spar. The symmetrical side reinforcement structure has the same shape as the first reinforcement plate. Both the symmetrical side reinforcement structure and the first reinforcement plate have circular openings. The L-shaped reinforcement structure is bonded to the web and the cap on one side of the composite wing spar having the cap. The symmetrical side reinforcement structure is arranged on the web on the other side of the composite wing spar.
[0006] Preferably, the first reinforcing plate includes a semicircular plate at the end and a rectangular plate at the root.
[0007] Preferably, the circular opening is located at a position of the web close to the edge strip.
[0008] Preferably, the web, the L-shaped reinforcing structural member and the symmetrical side reinforcing structural members are fixedly connected by a plurality of fasteners.
[0009] Preferably, the opening diameters of the L-shaped reinforcing structural member (1) and the symmetrical side reinforcing structural member (2) are smaller than or equal to the opening diameter of the original web, with a deviation within 2 mm.
[0010] Preferably, the ratio of the final structural thickness of the combination of the L-shaped reinforcement structure and the symmetrical side reinforcement structure and the original beam web to the original web thickness is between 2-2.5.
[0011] Preferably, the L-shaped reinforcement structure member and the symmetrical side reinforcement structure member are made of aluminum alloy.
[0012] Preferably, the edge protrusion of the opening of the L-shaped reinforcing structure forms a sleeve which is sleeved in the symmetrical side reinforcing structure and the opening of the web.
[0013] Preferably, the opening of the symmetrical side reinforcing structural member is larger than the opening of the web, and the end of the sleeve has a flange, and the cross section of the flange is connected to the cross section of the opening of the symmetrical side reinforcing structural member.
[0014] The advantages of the present application include: the L-shaped reinforcement structure can achieve the reinforcement of the wing beam web and the reinforcement of the nearby edge strip area; the aperture of the reinforcement part is smaller than the aperture of the corresponding web opening, which can reduce the delamination stress at the original beam web opening to a certain extent; the reinforcement of the beam web opening is symmetrical, the reinforcement effect is good, and the structural form is simple and easy to process and produce. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Figure 1 A schematic structural diagram of a web opening reinforcement assembly of the present invention;
[0016] Figure 2 Schematic diagram of the original open-hole web;
[0017] Figure 3 Schematic diagram of an L-shaped reinforcement structure of the present invention;
[0018] Figure 4 Schematic diagram of the web symmetrical side reinforcement structure of the present invention;
[0019] Figure 5 Schematic diagram of the overall connection component structure after opening reinforcement;
[0020] Figure 6 Front and side views of the connection component structure after opening reinforcement. DETAILED DESCRIPTION
[0021] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.
[0022] The present invention proposes a method for strengthening the openings of I-shaped or C-shaped composite spar web structures. Figure 1-Figure 6 As shown in the figure, at the web and flange of an I-shaped or C-shaped beam, if the reinforcement is only connected to the beam web, it will cause greater stress concentration in the nearby web flange transition area, and ultimately fail to achieve the desired reinforcement effect. Therefore, an L-shaped reinforcement structure is designed for the opening position set at the upper and lower ends of the beam web, close to the flange side, which can achieve the reinforcement of both the spar web and the nearby flange area.
[0023] To achieve this goal, composite spar web opening reinforcement structures such as Figure 1 As shown, it consists of two structural parts, one is Figure 3 The L-shaped reinforcement structure is connected to the beam web and beam flange by bolts; the other is Figure 4 The reinforcement structure on the other side of the web shown can form a symmetrical reinforcement form on the beam web, and is connected to the beam web and the reinforcement structure on the other side by bolts.
[0024] When designing a reinforcement structure, the size of the reinforcement structure parts needs to be determined based on the original opening size and position. The size is divided into the opening size of the reinforcement part and the thickness of the reinforcement part; in addition, the number and layout of the corresponding connecting rivets need to be specifically designed for the structure.
[0025] The relationship between the hole diameter D of the reinforcement part and the hole diameter d of the web is: d-2mm≤D≤d. Making the original hole diameter larger than the reinforcement hole diameter can reduce the local delamination stress of the original beam web.
[0026] The relationship between the thickness of the reinforced assembly ts and the original web thickness t is: ts = 2.0-2.5t.
[0027] The L-shaped reinforcement structure must have an arc transition, and the arc transition form and angle should be consistent with the original structure.
[0028] The edge of the opening of the L-shaped reinforcing structure part is raised to form a sleeve that is sleeved in the opening of the symmetrical side reinforcing structure part and the web. The opening of the symmetrical side reinforcing structure part is larger than the web opening. The end of the sleeve has a flange, and the flange section is connected to the cross-section of the opening of the symmetrical side reinforcing structure part, which is not shown in the figure.
[0029] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.
Claims
1. A composite material wing spar web opening reinforcement structure, characterized in that: It includes a composite spar web with circular openings, an L-shaped reinforcement structure, and a symmetrical side reinforcement structure; The L-shaped reinforcement structure comprises a first reinforcement plate bonded to the web of the composite wing spar and a second reinforcement plate bonded to the spar cap of the composite wing spar. The symmetrical side reinforcement structure has the same shape as the first reinforcement plate. Both the symmetrical side reinforcement structure and the first reinforcement plate have circular openings. The L-shaped reinforcement structure is bonded to the web and the cap on one side of the composite wing spar having the cap. The symmetrical side reinforcement structure is arranged on the web on the other side of the composite wing spar.
2. The composite material wing spar web opening reinforcement structure according to claim 1, characterized in that: The first reinforcing plate includes a semicircular plate at the end and a rectangular plate at the root.
3. The composite material wing spar web opening reinforcement structure according to claim 1, characterized in that: The circular opening is located at a position of the web close to the edge strip.
4. The composite material wing spar web opening reinforcement structure according to claim 1, characterized in that: The web, the L-shaped reinforcement structure and the symmetrical side reinforcement structure are fixedly connected by a plurality of fasteners.
5. The composite material wing spar web opening reinforcement structure according to claim 1, characterized in that: The opening diameters of the L-shaped reinforcing structural member (1) and the symmetrical side reinforcing structural member (2) are smaller than or equal to the opening diameter of the original web plate, with a deviation within 2 mm.
6. The composite material wing spar web opening reinforcement structure according to claim 1, characterized in that: The ratio of the final structural thickness of the combination of the L-shaped reinforcement structure and the symmetrical side reinforcement structure and the original beam web to the original web thickness is between 2-2.
5.
7. The composite material wing spar web opening reinforcement structure according to claim 1, characterized in that: The L-shaped reinforcement structure and the symmetrical side reinforcement structure are made of aluminum alloy.
8. The composite material wing spar web opening reinforcement structure according to claim 1, characterized in that: The edge of the opening of the L-shaped reinforcing structure part is raised to form a sleeve which is sleeved in the opening of the symmetrical side reinforcing structure part and the web plate.
9. The composite material wing spar web opening reinforcement structure according to claim 8, characterized in that: The opening of the symmetrical side reinforcing structural member is larger than the opening of the web, and the end of the sleeve has a flange, and the section of the flange is connected with the section of the opening of the symmetrical side reinforcing structural member.