Wing body butt joint structure participating in longitudinal load transfer of fuselage

Abstract

The invention belongs to the field of aircraft structure design, and particularly relates to a wing body butt joint structure participating in fuselage longitudinal load transfer. The structure comprises a plurality of wing body butt joint angle boxes which are arranged in parallel; the first wing body butt joint belt plate is used for lapping two wing body butt joint corners on the outer side; the second wing body butt joint belt plate is used for lapping two wing body butt joint corners on the inner side; the wing body butt joint angle box, the first wing body butt joint belt plate and the second wing body butt joint belt plate jointly form a frame type butt joint structure; the upper side of the frame type butt joint structure is connected with the central wing upper wall plate and the fuselage upper wall plate, and the lower side of the frame type butt joint structure is connected with the central wing lower wall plate and the fuselage lower wall plate. The front side of the frame-type butt joint structure is connected with the central wing spar, and the rear side is connected with the longitudinal side wall of the fuselage. The shearing force and the bending moment between the fuselage and the wings are mainly transmitted through the wing body butt joint structure connected with the central wing spar, and the wing is simple in structure, mature in manufacturing process, low in cost, easy to assemble and light in weight.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural design, and specifically relates to a wing-body docking structure that participates in the longitudinal load transfer of the fuselage. Background Technology

[0002] The wing-fuselage joint structure is a critical load-bearing structure for aircraft and a key area for transferring loads from the outer wing to the fuselage. This area experiences high loads and complex coordination. Most aircraft have independently designed wings and fuselages, with wing-fuselage joints on the wing spars connecting them to the fuselage frame. This type of joint is commonly used in large passenger and transport aircraft and does not participate in the overall load transfer of the fuselage. However, deformation coordination issues exist in the connection area between the center wing and the fuselage. Another method involves using double-ear joints at the roots of the fore and aft spars of the outer wing to connect to a single-ear joint on the fuselage frame. When the load is high, high-strength materials are required, and the structure needs to increase the material separation surface.

[0003] For beam-type wings, the center wing is eliminated, retaining only the outer wing, with the fuselage running continuously along the flight path. Double-ear joints are arranged at the roots of the front and rear spars of the outer wing, and single-ear joints are arranged at the corresponding positions on the fuselage frame. The wing-fuselage connection is completed through these single and double-ear joints. This centralized joint connection structure provides a clear load transfer path and high structural efficiency, making it suitable for applications with low wing loads. However, when the wing load is high, the stress level at the joint is high, increasing the strength requirements for the joint pins. High-strength materials are needed, and inconsistencies between the joint material and the beam material increase the separation surface at the structural joint. Changes in materials and the increase in the separation surface significantly increase structural weight and manufacturing costs.

[0004] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Summary of the Invention

[0005] The purpose of this application is to provide a wing-body docking structure that participates in longitudinal load transfer of the fuselage, so as to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] A wing-body docking structure participating in longitudinal load transfer of the fuselage includes:

[0008] Wing-body docking angle boxes, wherein multiple wing-body docking angle boxes are arranged in parallel;

[0009] The first wing-body docking strip plate is used to overlap the two outer wing-body docking angle boxes;

[0010] The second wing-body docking strip is used to overlap the two inner wing-body docking angle boxes.

[0011] The wing-body docking angle box, the first wing-body docking strip, and the second wing-body docking strip together form a frame docking structure; the upper side of the frame docking structure is connected to the upper wall panel of the central wing and the upper wall panel of the fuselage, respectively, and the lower side is connected to the lower wall panel of the central wing and the lower wall panel of the fuselage, respectively; the front side of the frame docking structure is connected to the central wing spars, and the rear side is connected to the longitudinal sidewall of the fuselage.

[0012] In at least one embodiment of this application, the wing-body docking corner box includes an upper edge strip, a belly plate, a lower edge strip, and a support column. The upper edge strip, the belly plate, and the lower edge strip form a U-shaped structure, and the support column is integrally formed with the upper edge strip, the belly plate, and the lower edge strip, respectively.

[0013] The upper edge strip of the corner box is connected to the upper wall panel of the central wing and the upper wall panel of the fuselage, respectively.

[0014] The corner box web is connected to the central wing beam;

[0015] The lower edge strip of the corner box is connected to the lower wall panel of the central wing and the lower wall panel of the fuselage, respectively;

[0016] The corner box support is connected to the longitudinal side wall of the fuselage.

[0017] In at least one embodiment of this application, the longitudinal sidewall of the fuselage is connected to the corner box support via an adapter plate.

[0018] In at least one embodiment of this application, a system through hole is provided on the corner box support, and the system through holes on the multiple wing-body docking corner boxes form an installation passage for the actuation system, and the actuation system bracket is installed on the corner box support.

[0019] In at least one embodiment of this application, the number of wing-body docking angle boxes is equal to the number of longitudinal sidewalls of the fuselage.

[0020] In at least one embodiment of this application, the wing-body docking angle box is arranged in the same position as the central wing spars and the longitudinal sidewalls of the fuselage.

[0021] In at least one embodiment of this application, the first wing-body docking strip includes a first web, a first flange, and a first strut. The first web and the first flange form an L-shaped structure, and the first strut is integrally formed with the first web and the first flange, respectively.

[0022] The first web plate is connected to the corner box web plate and the central wing beam, respectively;

[0023] The first edge strip is connected to the upper edge strip of the corner box, the upper wall panel of the central wing, and the upper wall panel of the fuselage, respectively, or is connected to the lower edge strip of the corner box, the lower wall panel of the central wing, and the lower wall panel of the fuselage, respectively.

[0024] In at least one embodiment of this application, a step difference is provided at the connection between the first edge strip and the upper edge strip or the lower edge strip of the corner box.

[0025] In at least one embodiment of this application, the second wing-body docking strip includes a second web, a second flange, and a second strut. The second web and the second flange form an L-shaped structure, and the second strut is integrally formed with the second web and the second flange, respectively.

[0026] The second web plate is connected to the corner box web plate and the central wing beam, respectively;

[0027] The second edge strip is connected to the upper edge strip of the corner box, the upper wall panel of the central wing, and the upper wall panel of the fuselage, respectively, or to the lower edge strip of the corner box, the lower wall panel of the central wing, and the lower wall panel of the fuselage, respectively.

[0028] In at least one embodiment of this application, each of the second wing-body docking strips is provided with a plurality of second struts.

[0029] In at least one embodiment of this application, a step difference is provided at the connection between the second edge strip and the upper edge strip or the lower edge strip of the corner box.

[0030] The invention has at least the following beneficial technical effects:

[0031] The wing-body docking structure involved in the longitudinal load transfer of the fuselage in this application allows the shear force and bending moment between the fuselage and the wing to be mainly transferred through the wing-body docking structure connected to the central wing spars. The structure is simple, the manufacturing process is mature, the cost is low, the assembly is simple, and the weight is light. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of a wing-body docking structure participating in longitudinal load transfer of the fuselage, according to one embodiment of this application;

[0033] Figure 2 This is a schematic diagram of a wing-body docking angle box according to one embodiment of this application;

[0034] Figure 3 This is a schematic diagram of the wing-body docking angle box assembly according to one embodiment of this application;

[0035] Figure 4 This is a schematic diagram of the first wing-body docking strip according to one embodiment of this application;

[0036] Figure 5This is a schematic diagram of the assembly of the first wing-body docking strip plate according to one embodiment of this application;

[0037] Figure 6 This is a schematic diagram of the overlap between the wing-body docking angle box and the wing-body docking strip plate according to one embodiment of this application.

[0038] in:

[0039] 1-Wing-body docking corner box; 101-Corner box upper edge strip; 102-Corner box web; 103-Corner box lower edge strip; 104-System through hole; 105-Corner box support; 2-First wing-body docking strip plate; 201-First web; 202-First edge strip; 203-First support; 3-Second wing-body docking strip plate;

[0040] 11- Upper central wing panel; 12- Central wing spars; 13- Lower central wing panel; 14- Upper fuselage panel; 15- Lower fuselage panel. Detailed Implementation

[0041] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0042] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0043] The following is in conjunction with the appendix Figures 1 to 6 This application will be described in further detail.

[0044] This application provides a wing-body docking structure that participates in longitudinal load transfer of the fuselage, including: a wing-body docking angle box 1, a first wing-body docking strip 2, and a second wing-body docking strip 3.

[0045] Specifically, such as Figure 1 As shown, multiple wing-body docking angle boxes 1 are arranged in parallel; the first wing-body docking strip plate 2 is used to overlap the two outer wing-body docking angle boxes 1; the second wing-body docking strip plate 3 is used to overlap the two inner wing-body docking angle boxes 1; the wing-body docking angle boxes 1, the first wing-body docking strip plate 2, and the second wing-body docking strip plate 3 together form a frame docking structure; the upper side of the frame docking structure is connected to the upper wall panel 11 of the central wing and the upper wall panel 14 of the fuselage, respectively, and the lower side is connected to the lower wall panel 13 of the central wing and the lower wall panel 15 of the fuselage, respectively; the front side of the frame docking structure is connected to the central wing spars 12, and the rear side is connected to the longitudinal sidewall of the fuselage. The wing-body docking angle boxes 1, the first wing-body docking strip plate 2, and the second wing-body docking strip plate 3 can be connected as a whole by welding or fasteners, or they can be a one-piece molded structure.

[0046] The wing-body docking structure involved in the longitudinal load transfer of the fuselage in this application can continuously increase the number of wing-body docking angle boxes 1, first wing-body docking strips 2 and second wing-body docking strips 3 according to the increase in the number of longitudinal sidewalls of the fuselage.

[0047] In one embodiment of this application, the wing-body docking structure consists of four wing-body docking corner boxes 1, four first wing-body docking strips, and two second wing-body docking strips 3.

[0048] like Figure 2-3 As shown, the wing-fuselage docking corner box 1 includes an upper edge strip 101, a belly plate 102, a lower edge strip 103, and a support column 105. The upper edge strip 101, belly plate 102, and lower edge strip 103 form a U-shaped structure. The support column 105 is integrally formed with the upper edge strip 101, belly plate 102, and lower edge strip 103. The upper edge strip 101 is connected to the upper wall panel 11 of the central wing and the upper wall panel 14 of the fuselage by fasteners. The belly plate 102 is connected to the spars 12 of the central wing by fasteners. The lower edge strip 103 is connected to the lower wall panel 13 of the central wing and the lower wall panel 15 of the fuselage by fasteners. The support column 105 is connected to the longitudinal sidewall of the fuselage by fasteners.

[0049] In a preferred embodiment of this application, the corner box support 105 provides space for the connection of the longitudinal sidewall of the fuselage. The height of the support allows for the connection of four rows of fasteners, with ample space. The longitudinal sidewall of the fuselage can be directly overlapped with the corner box support 105, or it can be connected to the corner box support 105 via an adapter plate.

[0050] In a preferred embodiment of this application, a system through hole 104 is provided on the corner box support 105. The system through holes 104 on the multiple wing-body docking corner boxes 1 form an installation passage for the actuation system. The actuation system bracket is installed on the corner box support 105. When the actuation system needs to be fixed or additional brackets are needed, the corner box support 105 is used as an installation platform.

[0051] In a preferred embodiment of this application, the number of wing-body docking angle boxes 1 is equal to the number of longitudinal sidewalls of the fuselage. When arranged, the wing-body docking angle boxes 1 are positioned in the same location as the central wing spars 12 and the longitudinal sidewalls of the fuselage to avoid eccentricity and to better transfer longitudinal loads to the wing.

[0052] like Figure 4-5 As shown, the first wing-body docking strip 2 includes a first web 201, a first flange 202, and a first strut 203. The first web 201 and the first flange 202 form an L-shaped structure. The first strut 203 is integrally formed with the first web 201 and the first flange 202. The first web 201 is connected to the corner box web 102 and the central wing spars 12. The first flange 202 is connected to the upper flange 101 of the corner box, the upper wall panel 11 of the central wing, and the fuselage wall panel 14, or to the lower flange 103 of the corner box, the lower wall panel 13 of the central wing, and the lower fuselage wall panel 15. A step difference is provided at the connection between the first flange 202 and the upper flange 101 or the lower flange 103 of the corner box, such as... Figure 6 As shown.

[0053] Furthermore, the second wing-body docking strip 3 has a similar structural form to the first wing-body docking strip 2, and the second wing-body docking strip 3 is an extended version of the first wing-body docking strip 2 along the spanwise direction of the wing. The second wing-body docking strip 3 includes a second web, a second flange, and a second strut. The second web and the second flange form an L-shaped structure, and the second strut is integrally formed with the second web and the second flange. The second web is connected to the corner box web 102 and the central wing spars 12. The second flange is connected to the corner box upper flange 101, the central wing upper wall panel 11, and the fuselage upper wall panel 14, or to the corner box lower flange 103, the central wing lower wall panel 13, and the fuselage lower wall panel 15. In a preferred embodiment of this application, each second wing-body docking strip 3 is provided with multiple second struts along its spanwise length, and the position of the struts can be finely adjusted according to the coordination of fasteners and surrounding structures. A step difference is provided at the connection between the second flange and the corner box upper flange 101 or the corner box lower flange 103, such as... Figure 6 As shown.

[0054] The wing-body docking structure involved in the longitudinal load transfer of the fuselage in this application completes the production and heat treatment of the wing-body docking angle box 1 and the two wing-body docking strips according to the above-mentioned structural form, and prepares fasteners, sealants, etc.; the docking of the central wing box section and the fuselage box section is completed through the wing-body docking angle box and strips; and the fasteners are sealed, the mating surfaces are sealed, and the corners are filled with sealant.

[0055] The wing-body docking structure involved in the longitudinal load transfer of the fuselage in this application transmits the fuselage bending moment mainly through the wing-body docking angle box 2 and the first wing-body docking strip 2 in the docking area between the wing and the fuselage. The axial force of the stringers and panels on the upper and lower wing surfaces of the fuselage is transmitted to the upper and lower panels and wing spars of the central wing. The force is then balanced by the shearing of the fasteners of the panels and the wing-body docking angle box / strip 2 and the tension of the wing spars and the wing-body docking angle box / strip 2.

[0056] This application presents a wing-body docking structure that participates in the longitudinal load transfer of the fuselage. In view of the size limitations of large UAVs and the requirements for field disassembly and installation, the outer wing is transported separately and the central wing is integrated with the fuselage design. The structure is designed to participate in the longitudinal load transfer of the fuselage, so that the shear force and bending moment between the fuselage and the wing are mainly transferred through the wing-body docking structure connected to the central wing spars. The structure is simple, the manufacturing process is mature, the cost is low, the assembly is simple, and the weight is light.

[0057] The wing-body docking structure involved in longitudinal load transfer of the fuselage in this application has the following advantages:

[0058] 1. It has a simple structure, is lightweight, and has a mature manufacturing process. It does not require additional forging or other processes, and the possibility of deviations is small.

[0059] 2. The material selection can be the same as that of the central wing spars; high-strength alloys are not required, resulting in low cost.

[0060] 3. The modular design of the docking structure facilitates assembly;

[0061] 4. The arrangement of wing-body docking angle boxes and strips can be increased or decreased according to the layout of the longitudinal sidewalls of the fuselage, resulting in high design flexibility.

[0062] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A wing-body docking structure participating in longitudinal load transfer of the fuselage, characterized in that, include: Wing-body docking angle boxes (1), multiple wing-body docking angle boxes (1) are arranged in parallel; The first wing-body docking strip (2) is used to overlap the two outer wing-body docking angle boxes (1); The second wing-body docking strip (3) is used to overlap the two inner wing-body docking angle boxes (1); The wing-body docking angle box (1), the first wing-body docking strip plate (2), and the second wing-body docking strip plate (3) together form a frame docking structure; the upper side of the frame docking structure is connected to the upper wall panel (11) of the central wing and the upper wall panel (14) of the fuselage respectively, and the lower side is connected to the lower wall panel (13) of the central wing and the lower wall panel (15) of the fuselage respectively; the front side of the frame docking structure is connected to the central wing spars (12), and the rear side is connected to the longitudinal sidewall of the fuselage.

2. The wing-body docking structure participating in longitudinal load transfer of the fuselage according to claim 1, characterized in that, The wing-body docking corner box (1) includes an upper edge strip (101), a belly plate (102), a lower edge strip (103), and a support column (105). The upper edge strip (101), the belly plate (102), and the lower edge strip (103) form a U-shaped structure. The support column (105) is integrally formed with the upper edge strip (101), the belly plate (102), and the lower edge strip (103). The upper edge strip (101) of the corner box is connected to the upper wall panel (11) of the central wing and the upper wall panel (14) of the fuselage respectively; The corner box web (102) is connected to the central wing beam (12); The lower edge strip (103) of the corner box is connected to the lower wall panel (13) of the central wing and the lower wall panel (15) of the fuselage respectively; The corner box support (105) is connected to the longitudinal side wall of the fuselage.

3. The wing-body docking structure participating in longitudinal load transfer of the fuselage according to claim 2, characterized in that, The longitudinal sidewall of the fuselage is connected to the corner box support (105) via a transition plate.

4. The wing-body docking structure participating in longitudinal load transfer of the fuselage according to claim 3, characterized in that, The corner box support (105) is provided with a system through hole (104), and the system through holes (104) on the multiple wing-body docking corner boxes (1) form an installation passage for the actuation system, and the actuation system bracket is installed on the corner box support (105).

5. The wing-body docking structure participating in longitudinal load transfer of the fuselage according to claim 4, characterized in that, The number of the wing-body docking angle boxes (1) is equal to the number of the longitudinal sidewalls of the fuselage.

6. The wing-body docking structure participating in longitudinal load transfer of the fuselage according to claim 5, characterized in that, When the wing-body docking angle box (1) is arranged, it is in the same position as the central wing spars (12) and the longitudinal sidewall of the fuselage.

7. The wing-body docking structure participating in longitudinal load transfer of the fuselage according to claim 6, characterized in that, The first wing-body docking strip (2) includes a first web plate (201), a first flange (202) and a first support (203). The first web plate (201) and the first flange (202) form an L-shaped structure, and the first support (203) is integrally formed with the first web plate (201) and the first flange (202) respectively. The first web plate (201) is connected to the corner box web plate (102) and the central wing beam (12) respectively; The first edge strip (202) is connected to the upper edge strip (101) of the corner box, the upper wall panel (11) of the central wing and the upper wall panel (14) of the fuselage, or to the lower edge strip (103) of the corner box, the lower wall panel (13) of the central wing and the lower wall panel (15) of the fuselage.

8. The wing-body docking structure participating in longitudinal load transfer of the fuselage according to claim 7, characterized in that, A step difference is provided at the connection between the first edge strip (202) and the upper edge strip (101) or the lower edge strip (103) of the corner box.

9. The wing-body docking structure participating in longitudinal load transfer of the fuselage according to claim 8, characterized in that, The second wing-body docking strip (3) includes a second web, a second flange and a second support. The second web and the second flange form an L-shaped structure. The second support is integrally formed with the second web and the second flange. The second web plate is connected to the corner box web plate (102) and the central wing beam (12) respectively; The second edge strip is connected to the upper edge strip of the corner box (101), the upper wall panel of the central wing (11) and the upper wall panel of the fuselage (14) respectively, or to the lower edge strip of the corner box (103), the lower wall panel of the central wing (13) and the lower wall panel of the fuselage (15) respectively.

10. The wing-body docking structure participating in longitudinal load transfer of the fuselage according to claim 9, characterized in that, Each of the second wing-body docking strips (3) is provided with a plurality of second struts.

11. The wing-body docking structure participating in longitudinal load transfer of the fuselage according to claim 10, characterized in that, A step difference is provided at the connection between the second edge strip and the upper edge strip (101) or the lower edge strip (103) of the corner box.

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