Aircraft wing body connecting frame structure

Abstract

The utility model belongs to the technical field of aviation structure design, and particularly relates to an aircraft wing body connecting frame structure. The aircraft wing body connecting frame structure comprises a cap-shaped cross beam, the cross beam comprises a web plate, two side plates and two turned-over edges, a mounting groove is formed between the web plate and the two side plates, and openings are formed in the two ends of the web plate; the number of the U-shaped connectors is two, the U-shaped connectors are arranged in the mounting groove, and the positions of the U-shaped connectors correspond to the positions of the openings; the number of the vertical beams is two, and one end of each vertical beam is inserted into the cross beam through the opening; the number of the auxiliary vertical beams is two, one ends of the auxiliary vertical beams are arranged on the outer sides of the side plates of the cross beam and connected with the side plates of the cross beam, the U-shaped connectors and the vertical beams through bolts, and the other ends of the auxiliary vertical beams are connected with the vertical beams through bolts. Under the bidirectional bending load and the torsional load, the section of the vertical beam can bear the load in the corresponding direction, the section strength requirement is met, and the economical efficiency of the structure is guaranteed.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aviation structure design, and particularly relates to an aircraft wing-body connecting frame structure. BACKGROUND

[0002] In a general aircraft, the wing-body connecting frame is an important main load-bearing component, which bears large load, complex load type, high local stress of the structure, and is difficult to design. Generally, an I-shaped section machining frame is used to bear the bending load and torsional load of the frame in the design, but under this cross-section form, a large weight cost is paid, and the economy is not dominant, which is a factor that needs to be considered for the general aircraft.

[0003] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the aforementioned deficiencies of the prior art. CONTENT OF THE INVENTION

[0004] The application aims to provide an aircraft wing-body connecting frame structure to solve at least one problem existing in the prior art.

[0005] The technical solution of the application is:

[0006] An aircraft wing-body connecting frame structure comprises:

[0007] A cross beam in a hat type, comprising a web, two side plates and two flanges, an installation groove is formed between the web and the two side plates, and openings are formed at both ends of the web;

[0008] Two U-shaped joints, which are arranged in the installation groove and correspond to the positions of the openings;

[0009] Two vertical beams, one end of each vertical beam is inserted into the cross beam through the opening;

[0010] Two auxiliary vertical beams, one end of each auxiliary vertical beam is arranged outside the side plate of the cross beam and connected to the side plate of the cross beam, the U-shaped joint and the vertical beam through bolts, and the other end of each auxiliary vertical beam is connected to the vertical beam through a bolt.

[0011] In at least one embodiment of the application, corresponding bolt holes are formed in the two side plates of the cross beam and the U-shaped joint, and the cross beam and the U-shaped joint are connected to the wing joint through bolts.

[0012] In at least one embodiment of the application, the U-shaped joint has a first connecting plate and a second connecting plate, and the spacing between the first connecting plate and the second connecting plate is adapted to the opening.

[0013] In at least one embodiment of the present application, the vertical beam comprises a first sheet bending piece, a second sheet bending piece, a third sheet bending piece and a fourth sheet bending piece, wherein the first sheet bending piece and the second sheet bending piece are connected by rivets to form a first sheet bending piece group, the third sheet bending piece and the fourth sheet bending piece are connected by rivets to form a second sheet bending piece group, and the first sheet bending piece group and the second sheet bending piece group are connected by rivets to form a vertical beam with a cross-section in the shape of a Chinese character.

[0014] In at least one embodiment of the present application, the third sheet bending piece and the fourth sheet bending piece are provided with a plurality of inflection structures on the second sheet bending piece group.

[0015] In at least one embodiment of the present application, the auxiliary vertical beam has an expansion section at one end outside the side plate of the cross beam, and part of the expansion section is directly connected to the side plate of the cross beam by bolts.

[0016] The utility model has at least the following beneficial technical effects:

[0017] The aircraft wing-body connecting frame structure of the present application can withstand corresponding loads in the corresponding direction under bidirectional bending load and torsional load, meets the cross-section strength requirement, and ensures the economy of the structure. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 is a schematic diagram of the aircraft wing-body connecting frame structure of one embodiment of the present application as a whole;

[0019] Figure 2 is a schematic diagram of the aircraft wing-body connecting frame structure of one embodiment of the present application in part;

[0020] Figure 3 is a schematic diagram of a U-shaped joint of one embodiment of the present application;

[0021] Figure 4 is a schematic diagram of a vertical beam of one embodiment of the present application.

[0022] Wherein:

[0023] 1-U-shaped joint; 2-auxiliary vertical beam; 3-vertical beam; 4-cross beam; 5-first sheet bending piece; 6-second sheet bending piece; 7-third sheet bending piece; 8-fourth sheet bending piece. DETAILED DESCRIPTION

[0024] 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. The embodiments of this application are described in detail below in conjunction with the drawings.

[0025] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and 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, be constructed and operated in a specific orientation. Therefore, it should not be understood as limiting the scope of protection of this application.

[0026] The following is combined with Figures 1 to 4 This application is described in further detail.

[0027] The present application provides an aircraft wing-fuselage connection frame structure, comprising: a crossbeam 4, a U-shaped joint 1, a vertical beam 3 and an auxiliary vertical beam 2.

[0028] Specifically, such as Figures 1-2 As shown, the crossbeam 4 includes a web, two side plates and two flanges, wherein two side plates are symmetrically arranged on both sides of the web, and each side plate is provided with a corresponding flange. The crossbeam 4 is in the shape of a hat as a whole, and a mounting groove is formed between the web of the crossbeam 4 and the two side plates, and openings are provided at both ends of the web.

[0029] Each of the U-shaped joints 1, vertical beams 3, and auxiliary vertical beams 2 comprises two. The U-shaped joints 1 are positioned in the mounting slots of the crossbeam 4, with the two U-shaped joints 1 corresponding to the openings at either end of the web. One end of the vertical beam 3 is inserted into the crossbeam 4 through the opening. One end of the auxiliary vertical beam 2 is positioned outside the side panel of the crossbeam 4. The auxiliary vertical beam 2 is connected to the side panel of the crossbeam 4, the U-shaped joints 1, and the vertical beam 3 via bolts (not shown). The other end of the auxiliary vertical beam 2 is also connected to the vertical beam 3 via bolts (not shown).

[0030] The aircraft wing-to-future connection frame structure of the present application has corresponding bolt holes on the two side panels of the crossbeam 4 and the U-shaped joint 1. The crossbeam 4 and the U-shaped joint 1 are connected to the wing joint through bolts. The load transmitted by the wing can be transmitted to the U-shaped joint 1 through the connecting bolts, and then diffused to the vertical beams 3 and crossbeams 4 of the aircraft wing-to-future connection frame structure.

[0031] In a preferred embodiment of the present application, the U-shaped joint 1 has a first connecting plate and a second connecting plate, and the distance between the first connecting plate and the second connecting plate is adapted to the opening on the web, that is, the distance between the first connecting plate and the second connecting plate is not greater than the opening on the web.

[0032] In the preferred embodiment of the present application, in order to bear the bidirectional bending load and torsional load of the wing-body frame, the cross-section of the vertical beam 3 is designed as follows: Figure 4 The shape shown. Wherein, the vertical beam 3 includes a first sheet metal bend 5, a second sheet metal bend 6, a third sheet metal bend 7 and a fourth sheet metal bend 8, wherein the first sheet metal bend 5 and the second sheet metal bend 6 are connected by rivets to form a first sheet metal bend group, the third sheet metal bend 7 and the fourth sheet metal bend 8 are connected by rivets to form a second sheet metal bend group, and the first sheet metal bend group and the second sheet metal bend group are connected by rivets to form a vertical beam 3 with a U-shaped cross section. The vertical beam 3 is composed of 4 groove-shaped sheet metal bends, and finally forms a U-shaped cross section. The first sheet metal bend 5 and the second sheet metal bend 6, the third sheet metal bend 7 and the fourth sheet metal bend 8 are respectively combined into a cross section, the first sheet metal bend 5 and the second sheet metal bend 6 are connected by rivets, and the third sheet metal bend 7 and the fourth sheet metal bend 8 are connected by rivets. The fatigue performance of this combined cross section is better than that of the integral machined parts.

[0033] Advantageously, in this embodiment, a plurality of inflection structures are provided on the second sheet-bent part group formed by the third sheet-bent part 7 and the fourth sheet-bent part 8 to increase the allowable pressure loss value of the groove-shaped sheet-bent part.

[0034] In the aircraft wing-fuselage connection frame structure of the present application, the entire combined cross-section of the vertical beam 3 has a large cross-sectional inertia moment in both directions when subjected to lateral and vertical bending moments, which can effectively reduce the stress on the frame cross-section; in addition, the cross-section is combined into a closed cross-section, which is better for transmitting shear force under torsional load.

[0035] In a preferred embodiment of the present application, the auxiliary vertical beam 2 has an expansion section at one end located on the outside of the side plate of the cross beam 4. A part of the expansion section is connected to the side plate of the cross beam 4, the U-shaped joint 1 and the vertical beam 3 in sequence through bolts, and another part of the expansion section is directly connected to the side plate of the cross beam 4 through bolts to improve the reliability of the connection.

[0036] The aircraft wing-body connecting frame structure of the application can bear the load in the corresponding direction under the bidirectional bending load and the torsional load, meets the section strength requirement, and ensures the economy of the structure.

[0037] The above merely provides the specific implementation of the application, but the protection scope of the application is not limited to this, any person skilled in the art can easily think of the changes or replacements within the technical range disclosed by the application, which should be covered in the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.

Claims

1. An aircraft wing-body junction frame structure, characterized by, The utility model relates to a kind of wing joint, including: Beam (4), cap type, the beam (4) includes one web, two side plates and two flanging, the web is formed installation slot between two side plates, and the both ends of the web are provided with opening; U-shaped joint (1), including two, the U-shaped joint (1) is arranged in the installation slot, and the U-shaped joint (1) corresponds with the position of the opening; Vertical beam (3), including two, one end of the vertical beam (3) is inserted into the beam (4) by the opening; Auxiliary vertical beam (2), including two, one end of the auxiliary vertical beam (2) is arranged outside the side plate of the beam (4), and is connected with the side plate of the beam (4), the U-shaped joint (1) and the vertical beam (3) by bolt, the other end of the auxiliary vertical beam (2) is connected with the vertical beam (3) by bolt.

2. The aircraft wing-body join frame structure according to claim 1, characterized in that, Corresponding bolt hole is formed on the two side plates of the beam (4) and the U-shaped joint (1), and the beam (4) and the U-shaped joint (1) are connected with wing joint by bolt.

3. The aircraft wing-body join frame structure according to claim 1, characterized in that, The U-shaped joint (1) has first connecting plate and second connecting plate, and the spacing between the first connecting plate and the second connecting plate is matched with the opening.

4. The aircraft wing-body join frame structure according to claim 1, characterized in that, The vertical beam (3) includes first sheet bending piece (5), second sheet bending piece (6), third sheet bending piece (7) and fourth sheet bending piece (8), wherein the first sheet bending piece (5) and the second sheet bending piece (6) are connected by rivet to form a first sheet bending piece group, the third sheet bending piece (7) and the fourth sheet bending piece (8) are connected by rivet to form a second sheet bending piece group, and the first sheet bending piece group and the second sheet bending piece group are connected by rivet to form a vertical beam (3) with a back-shaped section.

5. The aircraft wing-body join frame structure according to claim 4, characterized in that, The third sheet bending piece (7) and the fourth sheet bending piece (8) are provided with a plurality of inflection structures on the second sheet bending piece group.

6. The aircraft wing-body join frame structure according to claim 1, wherein, The end of the auxiliary vertical beam (2) outside the side plate of the beam (4) has an expansion section, and part of the expansion section is directly connected with the side plate of the beam (4) by bolt.

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