A variable camber wing trailing edge structure based on a slide

Abstract

The present invention belongs to the field of aircraft structure design, and relates to a variable camber wing trailing edge structure based on a slide. It comprises: a trailing edge cabin beam, a fixed bracket, a motion mechanism assembly, a motion mechanism support rod, a plurality of long spars, an upper trailing edge skin, a lower trailing edge skin, an ear piece with a slide groove, and a slide groove roller; during the camber process of the trailing edge of the variable camber wing, the relative position of the trailing edge skin and the trailing edge motion mechanism changes. The trailing edge skin and the motion mechanism solve the change in relative position between the two by adopting a slide groove, so that the movement of the motion mechanism and the deformation of the skin during the camber process of the trailing edge are coordinated, and the requirements for smooth deformation of the skin are met; the trailing edge skin and the motion mechanism are connected by a slide groove, which can meet the requirements for the change in the thickness of the airfoil of the trailing edge of the variable camber wing during the camber process, and meet the requirements for optimal aerodynamic performance.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft structure design, and relates to a variable-camber wing trailing edge structure based on a slide groove, and specifically to a structural form applied to the variable-camber wing trailing edge, connecting the wing trailing edge motion mechanism and the conventional wing trailing edge skin. Background Art

[0002] Variable-camber wings can adjust the camber of the wing profile to meet optimal aerodynamic requirements, improve flight efficiency, and reduce fuel consumption and noise. Currently, various structural solutions for variable-camber wing trailing edges, both domestically and internationally, include mechanical approaches (knuckle and eccentric beam) and rigid-flexible coupling solutions with a rigid-flexible connection. During the camber process, the relative position (including the relative angle) between the trailing-edge skin and the trailing-edge kinematic mechanism changes, often accompanied by a change in the chordwise length of the skin. Solutions to address the misaligned deformation and length changes between the skin and the kinematic mechanism during wing trailing-edge camber include flexible skins made of special materials, corrugated flexible skins, and flexible hinged connections between the skin and the main trailing-edge mechanism. These solutions either suffer from a rough aerodynamic profile that impacts aerodynamic performance or lack technical maturity, leaving many challenges to be addressed. Furthermore, the requirement for smooth and continuous camber during load-bearing camber cannot be fully met. Summary of the Invention

[0003] The purpose of the present invention is to address the problem that the existing trailing edge of a variable-camber wing cannot meet the requirements of smooth and continuous camber change during the load-bearing camber change process. A connection structure design scheme between the trailing edge drive mechanism and the skin of the variable-camber wing is proposed. This scheme not only realizes the smooth and continuous deformation of the skin during the load-bearing camber change process of the trailing edge, but also meets the requirements of the optimal aerodynamic shape during the trailing edge camber change process.

[0004] The idea of ​​the present invention is that the position of the trailing edge motion mechanism of the variable-camber wing changes as the trailing edge camber process progresses, and the shape of the trailing edge skin also changes as the trailing edge camber process progresses. During the trailing edge camber process, the relative position (including the relative angle) of the trailing edge skin and the trailing edge motion mechanism changes. The trailing edge skin and the trailing edge motion mechanism solve the change in relative position between the two by adopting a slide groove method, so that the movement of the motion mechanism during the trailing edge camber process is coordinated with the deformation of the skin, meeting the requirements for smooth deformation of the skin; the trailing edge skin and the motion mechanism are connected by a slide groove method, which can meet the requirements for the change in the thickness of the airfoil of the trailing edge of the variable-camber wing during the camber process, and meet the requirements for optimal aerodynamic performance. From the perspective of the slide groove connection between a single motion mechanism and the skin, on the one hand, the degree of freedom is released in the in-plane direction of the skin, so that the movement of the motion mechanism is coordinated with the deformation of the skin; on the other hand, the normal stiffness of the skin is guaranteed, which plays a supporting role for the skin, thereby ensuring that the skin can withstand aerodynamic loads and ensuring the smooth appearance of the wing skin. At the same time, the groove trajectories on the grooved ears on the upper and lower skins are designed to control the thickness of the airfoil at the trailing edge of the variable-camber wing, thereby meeting the requirements for the change in airfoil thickness during the camber process of the trailing edge of the variable-camber wing and meeting the requirements for optimal aerodynamic performance.

[0005] The present invention is realized by the following technical solutions: a variable camber wing based on a slide groove ear piece, comprising: a trailing edge cabin beam 1, a fixed bracket 13, a motion mechanism assembly, a plurality of motion mechanism support rods 5, a plurality of long stringers 7, a trailing edge upper skin 9, a trailing edge lower skin 10, a plurality of slide groove ear pieces 6, a plurality of slide groove rollers 8, and a plurality of roller pins; the motion mechanism assembly is composed of a plurality of motion mechanism rods, each motion mechanism rod is connected to the trailing edge upper skin 9 and the trailing edge lower skin 10 through its corresponding set of motion mechanism and skin connection structure, a set of motion mechanism and skin connection structure The structure includes a lug with a slide groove 6, a slide groove roller 8, and a roller pin; the trailing edge cabin beam 1 is connected to the wing main wing box, and the fixed bracket 13 is connected to the trailing edge cabin beam 1. One end of the motion mechanism component is installed on the fixed bracket 13, and the other end is connected to the slide groove on the trailing edge small rib through a roller; a certain number of motion mechanism support rods 5 grow on each motion mechanism rod, and the motion mechanism support rod 5 is connected to the lug with a slide groove 6 through the slide groove roller 8. The lug with a slide groove 6 is fixed on the corresponding long stringer 7, and several long stringers 7 are respectively fixed on the trailing edge upper skin 9 and the trailing edge lower skin 10.

[0006] The motion mechanism is a Watt six-bar linkage in principle.

[0007] The motion mechanism includes a first main rod 2, a second main rod 3, a third main rod 4, a first connecting rod 11, and a second connecting rod 12; the first main rod 2, the second main rod 3 and the third main rod 4 are coaxially hinged in sequence, and the other end of the first main rod 2 is connected to the fixed bracket 13; one end of the first connecting rod 11 is hinged to the fixed bracket 13, and the other end is hinged to the protrusion on the second main rod 3; both ends of the second connecting rod 12 are hinged to the protrusions on the first main rod 2 and the third main rod 4 respectively, and the other end of the third main rod 4 is connected to the sliding groove on the small rib on the rear edge through a roller.

[0008] The number of the motion mechanism support rods 5 is determined according to the space between the trailing edge upper skin 9 and the trailing edge lower skin 10 and the number of the provided long stringers 7 and is fixed on both sides of the first main rod 2, the second main rod 3 and the third main rod 4 respectively.

[0009] The lugs 6 with slide grooves are double-lug pieces, and each side of the lug piece has three surfaces forming a cone. Slide grooves 14 are provided on the opposite surfaces of the double-lug piece, and the other two surfaces are connecting surfaces 15 with the long stringers and are provided with connecting holes 16 that cooperate with the wing long stringers 7. The double-lug piece is connected to the wing long stringers 7 through the four connecting holes 16.

[0010] The long stringers 7 shown are evenly distributed on the wing skin, and the long stringers 7 are L-shaped.

[0011] The width of the chute 14 and the diameter of the chute roller 8 are determined by referring to the chute line. The chute is designed based on the chute line to ensure a smooth chute trajectory. The chute line on the chute lug is obtained through a series of analysis, calculations and optimization designs. The chute design based on the chute line also requires corresponding steps to complete.

[0012] Elaborate on them separately:

[0013] The end of the motion mechanism support rod 5 falls into the middle of a corresponding double ear piece with a slide groove ear piece 6. The end of the motion mechanism support rod 5 is provided with a roller hole 19 and the side wall is provided with a pin hole 20.

[0014] A roller groove 17 is opened in the symmetrical middle position of the slide roller 8. The slide roller 8 passes through the slide groove 14 on the slide groove ear piece 6 and the roller hole 19 on the motion mechanism support rod 5 in sequence. The roller pin passes through the pin hole 20 on the motion mechanism support rod 5 and falls into the roller groove 17.

[0015] The trailing edge upper skin 9 and the trailing edge lower skin 10 are dimensional components of the variable-camber wing trailing edge, and simultaneously bear the aerodynamic loads of the wing trailing edge. The trailing edge beam end of the trailing edge upper skin 9 is fixed to the trailing edge beam upper edge strip, and the trailing edge beam end of the trailing edge lower skin 10 is connected to the trailing edge beam lower edge strip, which can limit the normal movement of the skin and allow the skin to slide in the in-plane direction. The trailing edge upper skin 9 and the trailing edge lower skin 10 are connected at the trailing edge tail end.

[0016] Compared with the prior art, the present invention has the following beneficial technical effects:

[0017] The kinematic mechanism is connected to the wing skin via a one-dimensional slot on the slotted tab. Compared to a flexible hinge connection, this enhances the kinematic mechanism's normal support stiffness on the wing skin, thereby ensuring the wing skin's ability to withstand aerodynamic loads. The kinematic mechanism is connected to the wing skin via a one-dimensional slot on the slotted double tab, releasing the in-plane constraints between the kinematic mechanism and the wing skin. This allows the kinematic mechanism's deflection to be coordinated with the corresponding wing skin deformation, avoiding wrinkles during wing trailing edge deflection and ensuring smooth wing skin deformation. The slotted tab is simple, easy to machine, and reliable. The connection between the slotted tab, the kinematic mechanism, and the wing skin is simple and easy to operate. Based on the aerodynamic shape requirements of the trailing edge during camber, the slot solution allows for variations in airfoil thickness during this process, meeting airfoil thickness requirements.

[0018] In summary, the motion mechanism is connected to the wing skin through a lug with a slide groove, which solves the problem of deformation coordination between the motion mechanism and the wing skin and avoids the occurrence of skin wrinkles; ensures the normal support stiffness of the motion mechanism and the wing skin, meeting the requirements of precise deformation and load-bearing of the wing shape; and can adjust the airfoil thickness as required to meet the requirements of optimal aerodynamic performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of the overall structure of the variable camber wing trailing edge motion mechanism and the skin connection structure based on a slide groove of the present invention;

[0020] Figure 2 This is a schematic diagram of the overall structure of the variable camber wing trailing edge motion mechanism and the skin connection structure based on a slide groove of the present invention;

[0021] Figure 3 Schematic diagram of the structure of the lug with a slide groove in the present invention, wherein (a) is a side view of the lug with a slide groove, and (b) is a three-dimensional view of the lug with a slide groove;

[0022] Figure 4 Schematic diagram of the roller structure in the present invention;

[0023] Figure 5 Schematic diagram of the connection between the end of the support rod and the roller of the motion mechanism in the present invention.

[0024] in:

[0025] 1-trailing edge cabin beam; 2-first main rod; 3-second main rod; 4-third main rod; 5-movement mechanism support rod; 6-ear piece with slide groove; 7-long stringer; 8-roller; 9-trailing edge upper skin; 10-trailing edge lower skin; 11-first connecting rod; 12-second connecting rod; 13-fixed bracket; 14-slide groove; 15-connecting surface with long stringer; 16-connecting hole; 17-roller groove; 18-rounding; 19-roller hole; 20-pin hole on the movement mechanism support rod. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments 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 embodiments are part of the embodiments of this application, not all of the embodiments. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be understood as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

[0027] The following is combined with Figures 1 to 5 This application is described in further detail.

[0028] A variable camber wing based on a slide lug, comprising: a trailing edge cabin beam 1, a fixed bracket 13, a motion mechanism assembly, a motion mechanism support rod 5, a plurality of long stringers 7, a trailing edge upper skin 9, a trailing edge lower skin 10, a slide lug 6, and a slide roller 8; the motion mechanism assembly is composed of a plurality of groups of motion mechanisms, which are connected to the trailing edge upper skin 9 and the trailing edge lower skin 10 through the motion mechanism support rod 5 of each motion mechanism, the trailing edge cabin beam 1 is connected to the wing main wing box, the fixed bracket 13 is connected to the trailing edge cabin beam 1, one end of the motion mechanism assembly is installed on the fixed bracket 13, and the other end is installed on; a plurality of slide lugs 6 are connected to a plurality of long stringers 7 on the trailing edge upper skin 9 and the trailing edge lower skin 10, and the motion mechanism support rod 5 is connected to the slide lug 6 through the slide roller 8.

[0029] The kinematic mechanism is essentially a Watt six-bar linkage, comprising a first main rod 2, a second main rod 3, a third main rod 4, a first connecting rod 11, and a second connecting rod 12. The first main rod 2, the second main rod 3, and the third main rod 4 are coaxially hinged in sequence, with the other end of the first main rod 2 connected to a fixed bracket 13. One end of the first connecting rod 11 is hinged to the fixed bracket 13, and the other end is hinged to a protrusion on the second main rod 3. Both ends of the second connecting rod 12 are hinged to protrusions on the first main rod 2 and the third main rod 4, respectively. The other end of the third main rod 4 is connected to a sliding groove on the trailing edge rib via a roller.

[0030] The number of the kinematic mechanism support rods 5 is determined by the space between the trailing edge upper skin 9 and the trailing edge lower skin 10 and the number of long stringers 7 provided, and they are respectively fixed on both sides of the first main rod 2, the second main rod 3, and the third main rod 4. There are multiple kinematic mechanism support rods 5, and in this embodiment, there are a total of eleven kinematic mechanism support rods.

[0031] The lugs with slots 6 are double-eared, each with three conical surfaces. Slots 14 are located on the opposing surfaces of the lugs. During wing deflection, the trajectory of the slots on the lugs is determined through analysis, calculation, and comparison of the trajectory of the strut endpoints in the motion mechanism and the deformation of the wing's aerodynamic shape, using a series of geometric relationship mappings. The other two surfaces, which connect to the stringer surfaces 15, are equipped with connection holes 16 that mate with the wing stringers 7. The lugs are connected to the wing stringers 7 via these four holes 16.

[0032] Stringers 7 are evenly distributed across the wing skin and are L-shaped. Multiple stringers primarily support the upper and lower trailing edge skins and also secure the lugs with slots. The number of stringers 7 is determined by combining the number of kinematic mechanisms and skin connection structures. In this embodiment, there are eleven stringers 7.

[0033] The width of the chute 14 and the diameter of the chute roller 8 should be determined with reference to the chute line. The chute is designed based on the chute line to ensure that the chute track is smooth.

[0034] Method for confirming the optimized design of chute line:

[0035] 1) First, a series of typical aerodynamic shapes are determined as target deformation shapes for the variable camber wing trailing edge structure design;

[0036] 2) Preliminarily set the position of the end of the support rod 5 of all the kinematic mechanisms connected to the skin in the initial state;

[0037] 3) Performing kinematic analysis on the kinematic mechanism assembly and all kinematic mechanism struts 5 on the trailing edge of the variable-camber wing to obtain the corresponding relationship between the deflection angle of the kinematic mechanism assembly and a series of typical aerodynamic shapes of the trailing edge of the variable-camber wing; and obtaining the motion trajectories of all kinematic mechanism struts 5 as the kinematic mechanism assembly deflects.

[0038] 4) Several typical deflection angles of the trailing edge of a variable-camber wing and their corresponding aerodynamic shapes were selected as research objects. First, taking one of the typical deflection angles and its corresponding aerodynamic shape as an example, a fixed point on the trailing edge upper skin 9 or the trailing edge lower skin 10 was selected. A tangent line relative to the aerodynamic shape was drawn at this fixed point, and the relative geometric position relationship between the end of the moving strut 5 closest to this point and this tangent line was analyzed;

[0039] 5) Determine a tangent line of the fixed point of the skin in the initial aerodynamic shape of the trailing edge of the variable camber wing in 4) above, and map the relative position of the end of the moving strut 5 and the initial aerodynamic shape of the trailing edge based on the relative geometric position relationship between the end of the moving strut 5 and the tangent line in 4) above;

[0040] 6) Select one of the typical deflection angles of the trailing edge of the variable camber wing and its corresponding aerodynamic shape, and perform steps 4)-5) to obtain the relative position of the end of a certain motion mechanism support rod 5 relative to the trailing edge skin during the deflection motion of the trailing edge of the variable camber wing. Select a suitable method to connect the relative positions to form a motion trajectory of the end of the certain motion mechanism support rod 5 relative to the trailing edge skin. This motion trajectory is the slide groove line on the slide grooved tab connected to the end of the motion mechanism support rod 5;

[0041] 7) Perform steps 4) to 6) in sequence for each end of the motion mechanism support rod 5 to obtain the groove line on the grooved lug connected to each end of the motion mechanism support rod 5;

[0042] 8) The position coordinates of the end of each motion mechanism support rod 5 in the initial state are used as design variables, the high driving efficiency of the motion mechanism components is used as the optimization goal, and the shapes of all chute lines are used as optimization constraints. The chute line shapes are required to be smooth and single functions. The optimization design is carried out to finally obtain the optimal position of the end of the motion mechanism support rod 5 and the corresponding chute line.

[0043] The end of the kinematic mechanism support rod 5 fits between the two lugs of a corresponding slotted lug 6. A roller hole 19 is defined at the end of the kinematic mechanism support rod 5, and a pin hole 20 is defined in the sidewall. The size of the roller hole 19 is determined by the size of the roller. The trailing edge kinematic mechanism and the kinematic mechanism support rod are integrally formed. To reduce weight, the kinematic mechanism and the kinematic mechanism support rod are provided with lightening holes while maintaining structural strength and rigidity.

[0044] A roller groove 17 is defined symmetrically between the chute rollers 8. The chute rollers 8 sequentially pass through the chute 14 on the chute tab 6 and the roller hole 19 on the motion mechanism support rod 5. The roller pins pass through the pin holes 20 on the motion mechanism support rod 5 and fall into the roller groove 17. The chute rollers 8 can rotate within the roller holes 19 of the motion mechanism support rod 5, but axial displacement of the rollers is prevented. The ends of the chute rollers 8 are rounded 18 to facilitate their passage through the chute 14 holes and the roller holes 19 at the ends of the motion mechanism support rod 5.

[0045] The trailing edge upper skin 9 and the trailing edge lower skin 10 are dimensional components of the variable-camber wing trailing edge, and simultaneously bear the aerodynamic loads of the wing trailing edge. The trailing edge beam end of the trailing edge upper skin 9 is fixed to the trailing edge beam upper edge strip, and the trailing edge beam end of the trailing edge lower skin 10 is connected to the trailing edge beam lower edge strip, which can limit the normal movement of the skin and allow the skin to slide in the in-plane direction. The trailing edge upper skin 9 and the trailing edge lower skin 10 are connected at the trailing edge tail end.

[0046] Its operating principle is as follows: The variable-camber wing trailing edge kinematic mechanism deflects under the drive system, causing the position of the end of the kinematic mechanism support rod 5 to change accordingly. The chute roller 8, mounted within the roller hole 19 at the end of the kinematic mechanism support rod 5, follows the movement of the end of the kinematic mechanism support rod 5 and moves along a specific trajectory. Simultaneously, the chute roller 8 is mounted on the chute 14 of the chute tab 6 connected to the wing skin. As a result, the chute roller 8 slides on the chute 14 of the chute tab 6, simultaneously driving the chute tab 6 to move, which in turn causes the wing skin to flex and deform, meeting the wing's aerodynamic shape deformation requirements.

[0047] In order to meet the precise deformation requirements of the wing's aerodynamic shape and at the same time ensure the efficiency of the variable-camber trailing edge driven deformation, the slide track and roller cross-sectional diameter on each slide lug need to be optimized. This optimized design also involves the optimization of the relative position of the motion mechanism support rod and the motion mechanism.

[0048] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included in the scope of protection of the present application. A person skilled in the art of the present invention can make similar substitutions to the specific examples described, as long as they do not deviate from the structure of the present invention or exceed the scope defined by the claims, and they are all within the scope of protection of the present invention.

Claims

1. A variable camber wing trailing edge structure based on a chute, characterized in that: include: A trailing edge cabin beam (1), a fixed bracket (13), a kinematic mechanism assembly, a plurality of kinematic mechanism support rods (5), a plurality of long stringers (7), a trailing edge upper skin (9), a trailing edge lower skin (10), a plurality of lugs with slide grooves (6), a plurality of slide groove rollers (8), and a plurality of roller pins; the kinematic mechanism assembly is composed of a plurality of kinematic mechanism rods, each kinematic mechanism rod is connected to the trailing edge upper skin (9) and the trailing edge lower skin (10) through a corresponding set of kinematic mechanism and skin connection structures, a set of kinematic mechanism and skin connection structures comprising a lug with slide grooves (6), a slide groove roller, and a plurality of roller pins. (8), a roller pin; the trailing edge cabin beam (1) is connected to the wing main wing box, the fixed bracket (13) is connected to the trailing edge cabin beam (1), one end of the motion mechanism assembly is installed on the fixed bracket (13), and the other end is connected to the sliding groove on the trailing edge small rib through a roller; a plurality of motion mechanism support rods (5) are designed on each motion mechanism rod, the motion mechanism support rod (5) is connected to the lug with sliding groove (6) through the sliding groove roller (8), the lug with sliding groove (6) is fixed on the corresponding long stringer (7), and several long stringers (7) are respectively fixed on the trailing edge upper skin (9) and the trailing edge lower skin (10); The lug with a slide groove (6) is a double lug. Each side of the lug has three surfaces forming a cone. The opposite surfaces of the double lug are provided with slide grooves (14). The other two surfaces are connecting surfaces (15) with the long stringers and are provided with connecting holes (16) that match the wing long stringers (7). The double lug is connected to the wing long stringers (7) through the four connecting holes (16). The end of the motion mechanism support rod (5) falls into the middle of a corresponding double ear piece with a slide ear piece (6), and a roller hole (19) is opened on the end of the motion mechanism support rod (5) and a pin hole (20) is opened on the side wall; A roller groove (17) is provided at a symmetrical middle position of the slide roller (8). The slide roller (8) passes through the upper slide groove (14) of the slide lug (6) and the upper roller hole (19) of the motion mechanism support rod (5) in sequence. The roller pin passes through the pin hole (20) on the motion mechanism support rod (5) and falls into the roller groove (17).

2. The variable camber wing trailing edge structure based on the slide groove according to claim 1, characterized in that: The motion mechanism assembly belongs to a Watt six-bar linkage in principle.

3. The variable camber wing trailing edge structure based on the slide groove according to claim 1, characterized in that: The motion mechanism assembly comprises a first main rod (2), a second main rod (3), a third main rod (4), a first connecting rod (11), and a second connecting rod (12); the first main rod (2), the second main rod (3), and the third main rod (4) are coaxially hinged in sequence, and the other end of the first main rod (2) is connected to the fixed bracket (13); one end of the first connecting rod (11) is hinged to the fixed bracket (13), and the other end is hinged to the protrusion on the second main rod (3); both ends of the second connecting rod (12) are hinged to the protrusions on the first main rod (2) and the third main rod (4), respectively, and the other end of the third main rod (4) is connected to the sliding groove on the small rib of the rear edge through a roller.

4. The variable camber wing trailing edge structure based on a slide groove according to claim 1, characterized in that: The number of the motion mechanism support rods (5) is determined according to the space between the trailing edge upper skin (9) and the trailing edge lower skin (10) and the number of provided long stringers (7) and is respectively fixed on both sides of the first main rod (2), the second main rod (3), and the third main rod (4).

5. The variable camber wing trailing edge structure based on a slide groove according to claim 1, characterized in that: The long stringers (7) are evenly distributed on the wing skin, and the long stringers (7) are L-shaped.

6. The variable camber wing trailing edge structure based on a slide groove according to claim 1, characterized in that: The width of the chute (14) and the diameter of the chute roller (8) are determined with reference to the chute line, and the chute is designed based on the chute line.

7. The variable camber wing trailing edge structure based on a slide groove according to claim 1, characterized in that: The trailing edge upper skin (9) and the trailing edge lower skin (10) are dimensional components of the trailing edge of the variable-camber wing, and simultaneously bear the aerodynamic load of the trailing edge of the wing. The trailing edge cabin beam end of the trailing edge upper skin (9) is fixed on the trailing edge cabin beam upper edge strip, and the trailing edge cabin beam end of the trailing edge lower skin (10) is connected to the trailing edge cabin beam lower edge strip. The trailing edge upper skin (9) and the trailing edge lower skin (10) are connected at the trailing edge tail end.

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