Wing and undercarriage connecting structure and design method

Abstract

The invention belongs to the field of aircraft structure design, and particularly relates to a wing and undercarriage connecting structure and a design method. According to the structure, the lower end of a door-shaped frame is connected with a main rotating shaft; one end of the inner pull rod is connected with the inner side of the lower end of the door-shaped frame, and the other end is connected with the wing through the inner pull rod joint; one end of the outer pull rod is connected with the outer side of the lower end of the door-shaped frame, and the other end is connected with the wing through an outer pull rod joint; the spar inner side joint is mounted on the inner side of the upper end of the door-shaped frame and is connected with the wing; the spar outer side joint is mounted on the outer side of the upper end of the door-shaped frame and is connected with the wing; the shear pin shaft joint is mounted in the middle of the upper end of the door-shaped frame and is connected with the wing; one end of the rear beam inside pull rod is connected with the spar inside joint, and the other end is connected with the shear pin shaft joint; and one end of the rear beam outside pull rod is connected with the spar outside joint, and the other end is connected with the shear pin shaft joint. The device is light in weight, high in rigidity and clear in load path.

Description

Technical Field

[0001] The present application belongs to the field of aircraft structure design, and in particular relates to a wing and landing gear connection structure and a design method. Background Art

[0002] The aircraft main landing gear connection structure is a key structure of the aircraft. Its function is to transfer the load of the aircraft during take-off and landing and taxiing to the fuselage structure. The design of the connection structure not only affects the safety of the aircraft, but also affects the overall layout and structural efficiency of the aircraft to a certain extent. For large and medium-sized aircraft, since the loads in all directions of the main take-off are large, the rigidity, strength and load transmission route design requirements of the landing gear connection structure are relatively high. If the design is improper, the connection joint may bear large loads in three directions, which brings risks.

[0003] For aircraft with unconventional layouts, due to space and overall layout limitations, the main launch connection structure cannot transmit the main launch load by connecting to the fuselage structure, nor can it directly transmit the main launch load to the wing through the traditional nacelle structure. At the same time, in order to meet the movement space when the main landing gear is retracted forward under the wing and when the landing gear is retracted and extended, the main launch main shaft is often arranged behind the wing box and far away from the rear beam, resulting in a large load magnitude transmitted from the main launch connection structure to the wing box structure, and the connection structure design is difficult.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0005] The purpose of the present application is to provide a wing and landing gear connection structure and design method to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] A first aspect of the present application provides a wing and landing gear connection structure, comprising:

[0008] A door-shaped frame, the lower end of which is connected to the main shaft of the main starter;

[0009] An inner tie rod, one end of which is connected to the inner side of the lower end of the door-shaped frame, and the other end of which is connected to the wing through an inner tie rod joint;

[0010] An outer tie rod, one end of which is connected to the outer side of the lower end of the door-shaped frame, and the other end of which is connected to the wing through an outer tie rod joint;

[0011] A spar inner side joint, the spar inner side joint is installed on the inner side of the upper end of the door-shaped frame, and the spar inner side joint is connected to the wing;

[0012] A wing spar outer side joint, the wing spar outer side joint is installed on the outer side of the upper end of the door-shaped frame, and the wing spar outer side joint is connected to the wing;

[0013] A shear pin joint, the shear pin joint being installed at the middle of the upper end of the door-shaped frame and connected to the wing;

[0014] An inner tie rod of the rear beam, one end of which is connected to the inner joint of the wing beam, and the other end of which is connected to the shear pin joint;

[0015] A rear beam outer pull rod, one end of which is connected to the wing beam outer joint, and the other end of which is connected to the shear pin shaft joint.

[0016] In at least one embodiment of the present application, the door-shaped frame includes:

[0017] A door-shaped frame cross beam, wherein a shear pin is provided in the middle of the door-shaped frame cross beam;

[0018] The inner side beam of the door-shaped frame is located on the inner side of the door-shaped frame cross beam, the lower end of the inner side beam of the door-shaped frame is provided with a main starter and main rotating shaft inner single ear and an inner pull rod single ear, and the upper end is provided with a door-shaped frame inner upper double ear;

[0019] The outer side beam of the door-shaped frame is located on the outer side of the door-shaped frame cross beam, the lower end of the outer side beam of the door-shaped frame is provided with a main starter and main rotating shaft outer single ear and an outer pull rod single ear, and the upper end is provided with a door-shaped frame outer upper double ear;

[0020] An inner oblique beam, the two ends of which are respectively connected to the door-shaped frame cross beam and the inner side beam of the door-shaped frame;

[0021] An outer oblique beam, two ends of which are respectively connected to the door-shaped frame cross beam and the outer side beam of the door-shaped frame.

[0022] In at least one embodiment of the present application, a first inner tie rod double ear is provided at one end of the inner tie rod, and a second inner tie rod double ear is provided at the other end, and the first inner tie rod double ear is hinged to the inner tie rod single ear on the inner side beam of the door frame.

[0023] In at least one embodiment of the present application, the outer pull rod has the same structure as the inner pull rod.

[0024] In at least one embodiment of the present application, the inner tie rod joint includes:

[0025] An inner tie rod joint bottom plate, wherein the inner tie rod joint bottom plate is connected to the wing lower wall plate;

[0026] An inner tie rod joint ear piece, wherein the inner tie rod joint ear piece is arranged on the inner tie rod joint bottom plate and is used for being hinged with the second inner tie rod double ears.

[0027] In at least one embodiment of the present application, the outer tie rod joint has the same structure as the inner tie rod joint.

[0028] In at least one embodiment of the present application, the inner side joint of the spar comprises:

[0029] A joint rear bottom plate, the joint rear bottom plate being connected to the rear beam web;

[0030] A joint lower bottom plate, which is arranged at the lower end of the joint rear bottom plate and is used to be connected to the wing lower wall plate;

[0031] A joint upper top plate, which is arranged at the upper end of the joint rear bottom plate and is used to connect with the wing upper wall plate;

[0032] The inner side joint ear of the wing spar is arranged on the rear bottom plate of the joint and is used for being hinged with the inner upper double ears of the door-shaped frame;

[0033] A single-ear joint for the inner pull rod of the rear beam, wherein the single-ear joint for the inner pull rod of the rear beam is arranged on the rear bottom plate of the joint and is used for connecting with the inner pull rod of the rear beam.

[0034] In at least one embodiment of the present application, the structure of the outboard joint of the spar is the same as that of the inboard joint of the spar.

[0035] In at least one embodiment of the present application, the shear pin joint comprises:

[0036] A joint bottom plate, wherein a bearing is installed on the front side of the joint bottom plate through a shear pin joint ear, the bearing is connected to the shear pin, and the rear side of the joint bottom plate is connected to the rear beam web;

[0037] A rear beam inner tie rod single-ear joint, the rear beam inner tie rod single-ear joint is arranged on the inner side of the joint bottom plate, and is used to connect with the rear beam inner tie rod;

[0038] A single-ear joint for the outer side tie rod of the rear beam, wherein the single-ear joint for the outer side tie rod of the rear beam is arranged on the outer side of the joint bottom plate and is used for connecting with the outer side tie rod of the rear beam.

[0039] In at least one embodiment of the present application, the bearing and the shear pin are matched with a small clearance.

[0040] In at least one embodiment of the present application, the plane of the shear pin joint ear is perpendicular to the shear pin axis.

[0041] In at least one embodiment of the present application, the inner tie rod, the outer tie rod, the inner tie rod of the rear beam, and the outer tie rod of the rear beam all adopt an I-shaped cross-section.

[0042] A second aspect of the present application provides a method for designing a wing-to-landing gear connection structure, which is used to design the wing-to-landing gear connection structure as described above, comprising:

[0043] Step 1: Perform preliminary arrangement of the intersection points of the wing and landing gear connection structure;

[0044] Step 2: Construct a load transfer model for the connection structure between the wing and the landing gear, and preliminarily evaluate the load at each intersection and the force magnitude of each load transfer structure;

[0045] Step 3: Preliminarily design the dimensions of each intersection point and each load-carrying structure, and determine whether each intersection point meets the requirements based on the lug dimensions;

[0046] Step 4: Optimize the lateral load transfer path topology;

[0047] Step 5: Obtain an optimized connection structure between the wing and the landing gear according to the topology optimization results;

[0048] Step 6: Check the optimized connection structure between the wing and the landing gear.

[0049] In at least one embodiment of the present application, in step 1, preliminary arrangement of intersection points of the wing and landing gear connection structure is performed, including:

[0050] The intersection points of the single inner ear of the main shaft, the double ears of the first inner pull rod and the double ears of the second inner pull rod are collinear;

[0051] The intersection points of the main starter main shaft outer single ear, the first outer pull rod double ears and the second outer pull rod double ears are collinear;

[0052] The intersection points of the inner and outer double ears of the door frame and the shear pin axis are collinear.

[0053] In at least one embodiment of the present application, in step six, the optimized wing and landing gear connection structure is checked including stress, strain, and displacement checks.

[0054] The invention has at least the following beneficial technical effects:

[0055] The wing and landing gear connection structure of the present application provides a spatial triangular truss-like wing and landing gear connection structure, which directly transmits the main take-off main shaft load to the wing; realizes the transmission of the main take-off heading, vertical and lateral loads along different routes, takes into account the optimal load-bearing form of each structure while ensuring that the joint ear piece only bears the in-plane load, and the load analysis is simple; the structure has the characteristics of light weight, high rigidity, clear load route, and space saving. BRIEF DESCRIPTION OF THE DRAWINGS

[0056] Figure 1 It is a schematic diagram of the connection structure between the wing and the landing gear according to one embodiment of the present application;

[0057] Figure 2 It is a schematic diagram of a door-shaped frame, an inner tie rod and an outer tie rod according to an embodiment of the present application;

[0058] Figure 3 is a schematic diagram of an inner tie rod joint according to an embodiment of the present application;

[0059] Figure 4 is a schematic diagram of an inner side joint of a wing spar according to an embodiment of the present application;

[0060] Figure 5 is a schematic diagram of a shear pin joint according to an embodiment of the present application;

[0061] Figure 6 is a flow chart of a design method for a wing and landing gear connection structure according to an embodiment of the present application;

[0062] Figure 7 is a schematic diagram of the intersection arrangement of an implementation method of the present application;

[0063] Figure 8 This is a schematic diagram of the load transfer at the intersection point inside the main shaft of the main starter according to an embodiment of the present application;

[0064] Fig. 9 is a schematic diagram of a door-shaped frame according to an embodiment of the present application;

[0065] Fig.10 It is a schematic diagram of the assembly of the wing and landing gear connection structure according to one embodiment of the present application.

[0066] in:

[0067] 1-door frame; 101-single ear inside the main shaft; 102-single ear outside the main shaft; 103-side beam inside the door frame; 104-side beam outside the door frame; 105-double ears inside the door frame; 106-double ears outside the door frame; 107-shear pin; 108-inside diagonal beam; 109-outside diagonal beam; 2-inside tie rod; 3-outside tie rod; 4-inside tie rod joint; 401-inside tie rod joint ear; 402-inside tie rod joint bottom plate; 5-outside tie rod joint; 6- Inner joint of wing spar; 601-inner joint ear of wing spar; 602-single ear joint of inner tie rod of rear spar; 603-lower bottom plate of joint; 604-upper top plate of joint; 605-rear bottom plate of joint; 7-outer joint of wing spar; 8-shear pin joint; 801-bearing; 802-single ear joint of outer tie rod of rear spar; 803-single ear joint of inner tie rod of rear spar; 804-bottom plate of joint; 805-plane of joint ear; 806-axis line of shear pin; 9-inner tie rod of rear spar; 10-outer tie rod of rear spar. DETAILED DESCRIPTION

[0068] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment 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 them. 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 construed 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. The embodiments of this application are described in detail below in conjunction with the drawings.

[0069] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0070] The following is combined with Figures 1 to 10 This application is described in further detail.

[0071] The first aspect of the present application provides a wing and landing gear connection structure, including: a door-shaped frame 1, an inner tie rod 2, an outer tie rod 3, an inner tie rod joint 4, an outer tie rod joint 5, an inner joint of a wing beam 6, an outer joint of a wing beam 7, a shear pin joint 8, an inner tie rod of a rear beam 9 and an outer tie rod of a rear beam 10.

[0072] Specifically, Figure 1 As shown, the lower end of the door-shaped frame 1 is connected to the main starter main shaft; one end of the inner tie rod 2 is connected to the inner side of the lower end of the door-shaped frame 1, and the other end is connected to the wing through the inner tie rod joint 4; one end of the outer tie rod 3 is connected to the outer side of the lower end of the door-shaped frame 1, and the other end is connected to the wing through the outer tie rod joint 5; the inner joint 6 of the wing beam is installed on the inner side of the upper end of the door-shaped frame 1, and the inner joint 6 of the wing beam is connected to the wing; the outer joint 7 of the wing beam is installed on the outer side of the upper end of the door-shaped frame 1, and the outer joint 7 of the wing beam is connected to the wing; the shear pin joint 8 is installed in the middle part of the upper end of the door-shaped frame 1, and the shear pin joint 8 is connected to the wing; one end of the inner tie rod 9 of the rear beam is connected to the inner joint 6 of the wing beam, and the other end is connected to the shear pin joint 8; one end of the outer tie rod 10 of the rear beam is connected to the outer joint 7 of the wing beam, and the other end is connected to the shear pin joint 8.

[0073] In a preferred embodiment of the present application, Figure 2 As shown, the door frame 1 includes: a door frame cross beam, an inner side beam 103 of the door frame, an outer side beam 104 of the door frame, an inner oblique beam 108 and an outer oblique beam 109 . A shear pin 107 is provided in the middle of the door-shaped frame crossbeam; the inner side beam 103 of the door-shaped frame is located on the inner side of the door-shaped frame crossbeam, and the lower end of the inner side beam 103 of the door-shaped frame is provided with a main start and main rotating shaft inner single ear 101 and an inner pull rod single ear, and the upper end is provided with a door-shaped frame inner upper double ears 105; the outer side beam 104 of the door-shaped frame is located on the outer side of the door-shaped frame crossbeam, and the lower end of the outer side beam 104 of the door-shaped frame is provided with a main start and main rotating shaft outer single ear 102 and an outer pull rod single ear, and the upper end is provided with a door-shaped frame outer upper double ears 106; the two ends of the inner oblique beam 108 are respectively connected to the door-shaped frame crossbeam and the inner side beam 103 of the door-shaped frame; the two ends of the outer oblique beam 109 are respectively connected to the door-shaped frame crossbeam and the outer side beam 104 of the door-shaped frame.

[0074] In this embodiment, the inner rod 2 has a first inner rod double ear 202 at one end and a second inner rod double ear 201 at the other end. The first inner rod double ear 202 is hinged to the inner rod single ear on the inner side beam 103 of the door frame. The outer rod 3 has the same structure as the inner rod 2.

[0075] In a preferred embodiment of the present application, Figure 3As shown, the inner tie rod joint 4 includes: an inner tie rod joint base plate 402 and an inner tie rod joint ear piece 401. The inner tie rod joint base plate 402 is connected to the wing lower wall plate; the inner tie rod joint ear piece 401 is arranged on the inner tie rod joint base plate 402, and is used to be hinged with the second inner tie rod double ears 201. The outer tie rod joint 5 has the same structure as the inner tie rod joint 4.

[0076] In a preferred embodiment of the present application, Figure 4 As shown, the inner spar joint 6 includes: a joint rear bottom plate 605, a joint lower bottom plate 603, a joint upper top plate 604, a spar inner joint lug 601 and a rear spar inner tie rod single-ear joint 602. The joint rear bottom plate 605 is connected to the rear spar web; the joint lower bottom plate 603 is arranged at the lower end of the joint rear bottom plate 605, and is used to connect with the wing lower wall plate; the joint upper top plate 604 is arranged at the upper end of the joint rear bottom plate 605, and is used to connect with the wing upper wall plate; the spar inner joint lug 601 is arranged on the joint rear bottom plate 605, and is used to be hinged with the upper double ears 105 in the door-shaped frame; the rear spar inner tie rod single-ear joint 602 is arranged on the joint rear bottom plate 605, and is used to connect with the rear spar inner tie rod 9. The spar outer joint 7 has the same structure as the spar inner joint 6.

[0077] In a preferred embodiment of the present application, Figure 5 As shown, the shear pin joint 8 includes: a joint bottom plate 804, a rear beam inner tie rod single-ear joint 803 and a rear beam outer tie rod single-ear joint 802. The front side of the joint bottom plate 804 is installed with a bearing 801 through a shear pin joint ear, and the bearing 801 is connected to the shear pin 107. The rear side of the joint bottom plate 804 is connected to the web of the rear beam; the rear beam inner tie rod single-ear joint 803 is arranged on the inner side of the joint bottom plate 804, and is used to connect with the rear beam inner tie rod 9; the rear beam outer tie rod single-ear joint 802 is arranged on the outer side of the joint bottom plate 804, and is used to connect with the rear beam outer tie rod 10. Advantageously, the bearing 801 and the shear pin 107 are matched with a small clearance. The shear pin joint ear plane 805 is perpendicular to the shear pin axis 806.

[0078] In a preferred embodiment of the present application, the inner tie rod 2, the outer tie rod 3, the inner tie rod 9 of the rear beam, and the outer tie rod 10 of the rear beam all adopt an I-shaped cross-section.

[0079] The wing and landing gear connection structure of the present application has the following beneficial effects:

[0080] (1) A single-ear structure is set at the lower end of the inner and outer side beams of the door-shaped frame to connect with the main shaft of the main lift, so as to bear the heading, vertical and lateral loads of the main shaft of the main lift. The door-shaped frame 1 and the inner and outer tie rods are hinged by a single and double ear, and then the load-bearing triangle formed by the inner and outer side beams of the door-shaped frame and the inner and outer tie rods transmits the vertical and heading loads of the inner and outer intersections of the main shaft of the main lift to the wing box section through the side beams and tie rods. The lateral load of the main lift is transmitted to the shear pin 107 through the inner and outer inclined beams of the door-shaped frame 1, and then to the wing box section, see Figure 1 .

[0081] (2) The inner and outer tie rod joints are single-ear joints. The joint base is connected to the lower wall of the wing. Figure 2 .

[0082] (3) Double ears are set at the upper ends of the inner and outer side beams of the door-shaped frame to connect with the inner and outer joints of the wing beam respectively, so as to realize the transmission of the vertical and azimuth loads of the main shaft to the wing box section. The upper top plate and lower bottom plate of the inner and outer joints of the wing beam are connected to the upper wall plate and lower wall plate of the wing respectively, and the rear bottom plate of the joint is connected to the web plate of the rear beam. The inner and outer tie rods of the rear beam are used to connect the inner and outer joints of the wing beam with the shear pin shaft joint 8 to provide lateral support for the ear piece. The inner and outer joints of the wing beam have similar structures. The structure of the inner joint is shown in Fig. Figure 3 ;

[0083] (4) The plane 805 of the shear pin joint ear of the shear pin joint 8 is perpendicular to the shear pin axis 806 of the shear pin 107, so as to be more conducive to transmitting the lateral load of the door frame. The shear pin bottom plate is connected to the web of the rear beam. The bearing 801 is pressed into the joint ear. The bearing 801 and the door frame shear pin 107 are matched with a small clearance to release the axial movement and rotation of the shear pin 107 and only limit the lateral movement of the shear pin 107, so as to ensure that the shear pin 107 only transmits the lateral load. Figure 4 .

[0084] (5) All tie rod connection structures in the wing and landing gear connection structure (including inner and outer tie rods, inner and outer tie rods of the rear beam) are double-ear joints at both ends, and the middle structure is an I-shaped section.

[0085] The second aspect of the present application provides a method for designing a wing-to-landing gear connection structure, such as Figure 6 As shown, the following steps are included:

[0086] Step 1: Perform preliminary arrangement of the intersection points of the wing and landing gear connection structure;

[0087] Step 2: Construct a load transfer model for the connection structure between the wing and the landing gear, and preliminarily evaluate the load at each intersection and the force magnitude of each load transfer structure;

[0088] Step 3: Preliminarily design the dimensions of each intersection point and each load-carrying structure, and determine whether each intersection point meets the requirements based on the lug dimensions;

[0089] Step 4: Optimize the lateral load transfer path topology;

[0090] Step 5: Obtain an optimized connection structure between the wing and the landing gear according to the topology optimization results;

[0091] Step 6: Check the optimized connection structure between the wing and the landing gear.

[0092] The design method of the wing and landing gear connection structure of the present application, first, in step one, a preliminary arrangement of the intersection points of the wing and landing gear connection structure is performed. The intersection points of the main starter main shaft inner single ear (101), the first inner tie rod double ears (202) and the second inner tie rod double ears (201) are collinear; the intersection points of the main starter main shaft outer single ear (102), the first outer tie rod double ears and the second outer tie rod double ears are collinear; the intersection points of the inner upper double ears (105) of the door-shaped frame, the outer upper double ears (106) of the door-shaped frame and the shear pin (107) are collinear. At the same time, a gap of 1-3mm is reserved between the single and double ear pieces to release the lateral constraints of the ear pieces and facilitate the assembly of parts. This arrangement can avoid additional bending of the ear pieces to the greatest extent, such as Figure 7 shown.

[0093] In step 2, after the preliminary arrangement of the intersection points is completed, the load transfer model of the wing and landing gear connection structure can be simplified into several spatial triangular truss structures. Taking the load transfer of the intersection points on the inner side of the main shaft of the main lift as an example, the load transfer diagram is as follows: Figure 8 The main vertical load and azimuth load and the moment generated by the load are mainly transmitted through the triangular truss formed by the inner side rod 2 and the inner side beam 103 of the door-shaped frame. The lateral load and the moment generated by the load are transmitted through the triangular truss formed by the inner side beam 103 of the door-shaped frame and the inner oblique beam 108. The load of each intersection and the force of each load-transmitting structure can be preliminarily evaluated through simple mechanical analysis.

[0094] In step three, the intersection load and structural stress conditions obtained in step two are used to evaluate the size of the wing box intersection joint lugs, the door frame side beams and the tie rod structure, and whether to re-coordinate the intersection position is considered based on the lug size. Considering the fastener installation controls, try to ensure that the intersection is close to the wing lower wing surface or wing spar to ensure that the moment generated by the intersection load on the wing box is minimized (the distance between the lug at the intersection and the wing box is 50-80mm), which is conducive to the design of the connection joint at the wing box section.

[0095] In step 4, the lateral load transfer path of the door frame is re-optimized according to the lateral load, the force transfer path structure is sampled according to the topological optimization result, the lateral load at the shear pin is evaluated, and the appropriate bearing is selected.

[0096] In step 5, the structure is preliminarily sampled and designed based on the topology optimization results to determine the detailed dimensions of each connection structure;

[0097] In step 6, the preliminary sample model of the connection structure is checked, including stress, strain, displacement, etc., and the detailed structure is re-optimized. The final door frame connection structure is as follows Fig. 9 As shown in the assembly diagram Fig.10 shown.

[0098] The wing and landing gear connection structure and design method of the present application, the force transmission path of the wing and main lift connection structure takes into account the optimal load-bearing mode of each connection structure and the main lift movement space, through the main lift connection structure of the spatial triangular truss, the vertical and heading loads and lateral loads of the landing gear are transmitted along different paths, the force transmission path is clear, and the heavy-loaded joint ears are prevented from bearing out-of-plane loads. The structure is efficient, light in weight, easy to assemble, and saves space.

[0099] 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 wing and landing gear connection structure, characterized in that: include: A door-shaped frame (1), the lower end of which is connected to the main shaft of the main starter; An inner tie rod (2), one end of the inner tie rod (2) being connected to the inner side of the lower end of the door-shaped frame (1), and the other end of the inner tie rod (2) being connected to the wing via an inner tie rod joint (4); An outer tie rod (3), one end of which is connected to the outer side of the lower end of the door-shaped frame (1), and the other end of which is connected to the wing via an outer tie rod joint (5); A wing spar inner side joint (6), the wing spar inner side joint (6) is installed on the inner side of the upper end of the door-shaped frame (1), and the wing spar inner side joint (6) is connected to the wing; A wing spar outer side joint (7), the wing spar outer side joint (7) is installed on the outer side of the upper end of the door-shaped frame (1), and the wing spar outer side joint (7) is connected to the wing; A shear pin joint (8), the shear pin joint (8) being mounted at the middle of the upper end of the door-shaped frame (1), the shear pin joint (8) being connected to the wing; A rear beam inner tie rod (9), one end of which is connected to the wing beam inner joint (6), and the other end of which is connected to the shear pin joint (8); A rear beam outer pull rod (10), one end of which is connected to the wing beam outer joint (7), and the other end of which is connected to the shear pin shaft joint (8).

2. The wing and landing gear connection structure according to claim 1, characterized in that: The door-shaped frame (1) comprises: A door-shaped frame cross beam, wherein a shear pin (107) is arranged in the middle of the door-shaped frame cross beam; The inner side beam (103) of the door-shaped frame is located on the inner side of the door-shaped frame cross beam, the lower end of the inner side beam (103) of the door-shaped frame is provided with a main starter and main rotating shaft inner single ear (101) and an inner pull rod single ear, and the upper end is provided with a door-shaped frame inner upper double ear (105); The outer side beam (104) of the door-shaped frame is located outside the cross beam of the door-shaped frame, the lower end of the outer side beam (104) of the door-shaped frame is provided with a main starter and main rotating shaft outer single ear (102) and an outer pull rod single ear, and the upper end is provided with a door-shaped frame outer double ears (106); An inner oblique beam (108), the two ends of which are respectively connected to the door-shaped frame cross beam and the inner side beam (103) of the door-shaped frame; An outer oblique beam (109), two ends of which are respectively connected to the door-shaped frame cross beam and the outer side beam (104) of the door-shaped frame.

3. The wing and landing gear connection structure according to claim 2, characterized in that: One end of the inner pull rod (2) is provided with a first inner pull rod double ear (202), and the other end is provided with a second inner pull rod double ear (201), and the first inner pull rod double ear (202) is hinged to the inner pull rod single ear on the inner side beam (103) of the door-shaped frame.

4. The wing and landing gear connection structure according to claim 3, characterized in that: The outer pull rod (3) has the same structure as the inner pull rod (2).

5. The wing and landing gear connection structure according to claim 4, characterized in that: The inner tie rod joint (4) comprises: An inner tie rod joint bottom plate (402), wherein the inner tie rod joint bottom plate (402) is connected to the lower wall plate of the wing; An inner tie rod joint ear piece (401), the inner tie rod joint ear piece (401) is arranged on the inner tie rod joint bottom plate (402), and is used for being hinged with the second inner tie rod double ears (201).

6. The wing and landing gear connection structure according to claim 5, characterized in that: The structure of the outer tie rod joint (5) is the same as that of the inner tie rod joint (4).

7. The wing and landing gear connection structure according to claim 6, characterized in that: The spar inner side joint (6) comprises: A joint rear bottom plate (605), wherein the joint rear bottom plate (605) is connected to the rear beam web; A joint lower base plate (603), the joint lower base plate (603) is arranged at the lower end of the joint rear base plate (605) and is used to connect with the wing lower wall plate; A joint upper top plate (604), the joint upper top plate (604) is arranged at the upper end of the joint rear bottom plate (605) and is used to connect with the wing upper wall plate; The spar inner side joint ear piece (601), the spar inner side joint ear piece (601) is arranged on the joint rear bottom plate (605), and is used for being hinged with the inner upper double ears (105) of the door-shaped frame; A rear beam inner pull rod single-ear joint (602), wherein the rear beam inner pull rod single-ear joint (602) is arranged on the joint rear bottom plate (605) and is used for connecting with the rear beam inner pull rod (9).

8. The wing and landing gear connection structure according to claim 7, characterized in that: The structure of the spar outer side joint (7) is the same as that of the spar inner side joint (6).

9. The wing and landing gear connection structure according to claim 8, characterized in that: The shear pin joint (8) comprises: A joint base plate (804), the front side of the joint base plate (804) being provided with a bearing (801) via a shear pin joint lug, the bearing (801) being connected to the shear pin (107), and the rear side of the joint base plate (804) being connected to the web of the rear beam; A rear beam inner pull rod single-ear joint (803), the rear beam inner pull rod single-ear joint (803) is arranged on the inner side of the joint bottom plate (804) and is used to connect with the rear beam inner pull rod (9); A rear beam outer pull rod single-ear joint (802), wherein the rear beam outer pull rod single-ear joint (802) is arranged on the outer side of the joint bottom plate (804) and is used for connecting with the rear beam outer pull rod (10).

10. The wing and landing gear connection structure according to claim 9, characterized in that: The bearing (801) and the shear pin (107) are matched with each other with a small clearance.

11. The wing and landing gear connection structure according to claim 10, characterized in that: The plane (805) of the shear pin joint ear is perpendicular to the shear pin axis (806).

12. The wing and landing gear connection structure according to claim 11, characterized in that: The inner tie rod (2), the outer tie rod (3), the inner tie rod (9) of the rear beam, and the outer tie rod (10) of the rear beam all adopt an I-shaped cross section.

13. A method for designing a wing-to-landing gear connection structure, used for designing a wing-to-landing gear connection structure as claimed in claim 12, characterized in that: include: Step 1: Perform preliminary arrangement of the intersection points of the wing and landing gear connection structure; Step 2: Construct a load transfer model for the connection structure between the wing and the landing gear, and preliminarily evaluate the load at each intersection and the force magnitude of each load transfer structure; Step 3: Preliminarily design the dimensions of each intersection point and each load-carrying structure, and determine whether each intersection point meets the requirements based on the lug dimensions; Step 4: Optimize the lateral load transfer path topology; Step 5: Obtain an optimized connection structure between the wing and the landing gear according to the topology optimization results; Step 6: Check the optimized connection structure between the wing and the landing gear.

14. The wing and landing gear connection structure according to claim 13, characterized in that: In step 1, the intersection points of the wing and landing gear connection structure are initially arranged, including: The intersection points of the main starter main shaft inner single ear (101), the first inner pull rod double ears (202) and the second inner pull rod double ears (201) are collinear; The intersection points of the main starter main rotating shaft outer single ear (102), the first outer pull rod double ears and the second outer pull rod double ears are collinear; The intersection points of the inner double ears (105) of the door-shaped frame, the outer double ears (106) of the door-shaped frame and the shear pin shaft (107) are collinear.

15. The wing and landing gear connection structure according to claim 14, characterized in that: In step six, the optimized wing and landing gear connection structure is checked including stress, strain and displacement checks.

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