CN114239150B - Airplane inflection connecting structure and anti-fatigue design method thereof - Google Patents
Airplane inflection connecting structure and anti-fatigue design method thereof Download PDFInfo
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- CN114239150B CN114239150B CN202111614563.6A CN202111614563A CN114239150B CN 114239150 B CN114239150 B CN 114239150B CN 202111614563 A CN202111614563 A CN 202111614563A CN 114239150 B CN114239150 B CN 114239150B
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The application belongs to the field of aviation connection structure design, and particularly relates to an airplane inflection connection structure and an anti-fatigue design method thereof. The method comprises the following steps: joint, shear horn piece and connection horn box. The joint comprises a joint outer edge strip arranged on the outer side of the joint web plate, a joint inner edge strip arranged on the inner side of the joint web plate, and a joint outer edge strip connected with the side wall plate of the machine body; the shearing fillet comprises a first fillet outer edge strip and a second fillet outer edge strip which are arranged on the outer side of the fillet web plate, the first fillet outer edge strip is connected with the second fillet outer edge strip, a preset angle is formed between the first fillet outer edge strip and the second fillet outer edge strip, the first fillet outer edge strip is connected with the top plate or the floor of the airplane, and the second fillet outer edge strip is connected with the side wall plate of the airplane body; the connecting angle box comprises an angle box edge strip and an angle box web plate, two vertical ribs are respectively arranged at two ends of an assembly formed by the angle box edge strip and the angle box web plate, and the angle box edge strip is connected with a top plate or a floor of the airplane; the joint web, the corner piece web and the corner box web are connected through fasteners.
Description
Technical Field
The application belongs to the field of aviation connection structure design, and particularly relates to an airplane inflection connection structure and an anti-fatigue design method thereof.
Background
In the design process of the airplane structure, an inflection connecting structure form is inevitably existed, such as the connection of a fuselage frame and a floor, the connection of an airtight top plate of an upper single-wing airplane and a fuselage side wall, and the like. At present, the structure generally adopts an L-shaped corner piece connection mode, but the connection structure has the characteristics of larger load of a fastener close to a turning part and higher stress of a structural hole edge, so that the connection structure is easy to generate hole edge cracks or fastener fracture faults, even the fault condition of 'sugar-coated haws on a stick' with a plurality of connection holes communicated in a crack manner, and the fatigue performance is poorer.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide an airplane inflection connecting structure and an anti-fatigue design method thereof, so as to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
a first aspect of the present application provides an aircraft inflected connection structure including:
the connector comprises a connector outer edge strip, a connector inner edge strip and a connector web plate, the connector outer edge strip is arranged on the outer side of the connector web plate, the connector inner edge strip is arranged on the inner side of the connector web plate, and the connector outer edge strip is connected with a side wall plate of the machine body;
the corner piece is cut, the corner piece comprises a first corner piece outer edge strip, a second corner piece outer edge strip and a corner piece web plate, the first corner piece outer edge strip and the second corner piece outer edge strip are arranged on the outer side of the corner piece web plate, the first corner piece outer edge strip is connected with the second corner piece outer edge strip, a preset angle is formed between the first corner piece outer edge strip and the second corner piece outer edge strip, the first corner piece outer edge strip is connected with a top plate or a floor of an airplane, and the second corner piece outer edge strip is connected with a side wall plate of the airplane body;
the angle box comprises an angle box edge strip, an angle box web plate and two vertical ribs, wherein the angle box edge strip is connected with the angle box web plate, the two vertical ribs are respectively arranged at two ends of an assembly formed by the angle box edge strip and the angle box web plate, and the angle box edge strip is connected with a top plate or a floor of an airplane;
the joint web plate is arranged between the fillet web plate and the corner box web plate, and the joint web plate, the fillet web plate and the corner box web plate are connected through fasteners.
In at least one embodiment of the present application, the joint outer flange strip is connected to the side wall panel of the fuselage by bolts or rivets.
In at least one embodiment of the present application, the first gusset outer edge strip is connected to the aircraft roof or floor by bolts or rivets.
In at least one embodiment of the present application, the second gusset outer flange is connected to the side wall panel of the fuselage by means of bolts or rivets.
In at least one embodiment of this application, the shearing fillet still includes the turn-ups, the turn-ups sets up on the fillet web, and with second fillet outer fringe strip borders on, the turn-ups passes through the bolt or rivet and is connected with the stringer of fuselage side wall board.
In at least one embodiment of the present application, the corner box strip is connected to the aircraft roof or floor by bolts or rivets.
In at least one embodiment of the present application, the tab web, the gusset web, and the corner box web are connected by bolts.
A second aspect of the present application provides a method for designing an aircraft inflection connection structure to resist fatigue, wherein the method includes:
optimizing the joint, specifically: setting the joint to be a preset length which is the maximum length allowed by the structure, and optimizing the structural form of the joint inner edge strip so that the extension line of the joint inner edge strip is positioned in the middle position of the connecting part of the first corner piece outer edge strip and the top plate or the floor of the airplane;
the shearing angle sheet is optimized, and specifically comprises the following steps: a stud is arranged between the first gusset outer edge strip and the gusset web plate;
the material of the airplane inflection connecting structure is optimized, and the method specifically comprises the following steps: the strength of the airplane inflection connecting structure is improved by changing the structural material.
In at least one embodiment of the application, the stud is arranged in the middle and/or at the end of the connecting part of the first corner piece outer fringe and the top plate or the floor of the airplane.
In at least one embodiment of the present application, the strength of the aircraft inflection connection structure is improved by replacing the material of the aircraft inflection connection structure with an aluminum alloy and a titanium alloy.
The invention has at least the following beneficial technical effects:
the utility model provides an aircraft inflection connection structure reduces structure quantity on the one hand, realizes that the structure subtracts heavy purpose, and on the other hand optimizes load transfer and nail and carries the distribution, reaches the controllable purpose in life-span, makes things convenient for engineering application.
Drawings
FIG. 1 is a schematic illustration of an aircraft inflection connection configuration in accordance with an embodiment of the present application;
FIG. 2 is a schematic view of a joint according to an embodiment of the present application;
FIG. 3 is a schematic view of a shear horn according to an embodiment of the present application;
FIG. 4 is a schematic view of a connection horn of an embodiment of the present application.
Wherein:
1-a linker; 11-a joint outer edge strip; 12-a joint inner bead; 13-a joint web; 2-shearing the corner pieces; 21-a first gusset peripheral strip; 22-a second corner piece peripheral strip; 23-fillet webs; 24-flanging; 3-connecting the corner boxes; 31-corner box edge strip; 32-corner box web.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. 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 a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the accompanying drawings are illustrative and intended to explain the present application and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "central," "longitudinal," "lateral," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings, which are based on the orientation or positional relationship shown in the drawings, and are used for convenience in describing the present application and for simplicity in description, but do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application will be described in further detail with reference to fig. 1 to 4.
The first aspect of the application provides an aircraft inflection connection structure, which comprises a joint 1, a shear corner piece 2 and a connection corner box 3.
Specifically, joint 1 includes joint outer fringe 11, joint inner fringe 12 and joint web 13, as shown in fig. 2, will connect outer fringe 11 and joint inner fringe 12 to be connected through joint web 13, and the three is integrated into one piece structure, and wherein, connects outer fringe 11 and sets up in the outside of connecting web 13, connects inner fringe 12 and sets up the inboard at joint web 13, connects outer fringe 11 and is connected with fuselage side wall board. In the present embodiment, the joint outer edge 11 is provided with a mounting hole, and the joint outer edge 11 is connected to the side wall plate of the fuselage by a bolt or a rivet.
As shown in fig. 3, the shearing fillet 2 includes a first fillet outer fringe 21, a second fillet outer fringe 22 and a fillet web 23, the first fillet outer fringe 21 and the second fillet outer fringe 22 are both disposed at the outer side of the fillet web 23, the first fillet outer fringe 21 is connected with the second fillet outer fringe 22, and a predetermined angle is formed between the first fillet outer fringe 21 and the second fillet outer fringe 22, the first fillet outer fringe 21, the second fillet outer fringe 22 and the fillet web 23 are of an integrally formed structure, the first fillet outer fringe 21 is connected with the top plate or the floor of the airplane, and the second fillet outer fringe 22 is connected with the side wall plate of the airplane body. In this embodiment, the first gusset outer edge strip 21 is provided with a mounting hole, the first gusset outer edge strip 21 is connected to the roof or floor of the aircraft by a bolt or a rivet, the second gusset outer edge strip 22 is also provided with a mounting hole, and the second gusset outer edge strip 22 is connected to the side wall panel of the aircraft body by a bolt or a rivet. Advantageously, in this embodiment, the shear horn 2 further comprises a flange 24, the flange 24 being provided on the horn web 23 and abutting the second horn peripheral strip 22, the flange 24 being connected to the stringers of the fuselage sidewall panels by means of bolts or rivets.
Further, as shown in fig. 4, the connection corner box 3 includes a corner box flange 31, a corner box web 32, and two studs, the corner box flange 31 is connected to the corner box web 32, the two studs are respectively disposed at two ends of the assembly formed by the corner box flange 31 and the corner box web 32, and the corner box flange 31 is connected to the top plate or the floor of the aircraft. In this embodiment, the corner box edge strip 31 is connected to the aircraft roof or floor by bolts or rivets.
The utility model provides an aircraft inflection connection structure, connector web 13 set up between fillet web 23 and corner box web 32, connect connector web 13, fillet web 23 and corner box web 32 through the fastener. In the present embodiment, the joint web 13, the gusset web 23, and the corner box web 32 are connected by bolts.
Based on the above airplane inflection connection structure, a second aspect of the present application provides an anti-fatigue design method for an airplane inflection connection structure, including:
optimizing the joint 1, specifically: setting the joint 1 to a predetermined length which is the maximum length allowed by the structure, and optimizing the structural form of the joint inner edge strip 12 so that the extension line of the joint inner edge strip 12 is positioned at the middle position of the connecting part of the first corner piece outer edge strip 21 and the top plate or the floor of the airplane;
the shearing angle piece 2 is optimized, and specifically comprises the following steps: studs are arranged between the first gusset outer edge strip 21 and the gusset web 23;
the material of the airplane inflection connecting structure is optimized, and the method specifically comprises the following steps: the strength of the airplane inflection connecting structure is improved by changing the structural material.
In the preferred embodiment of the present application, the stud is provided at the middle and/or end of the connection portion of the first corner piece outer fringe 21 and the aircraft roof or floor, and may be provided in one or more. In this embodiment, a stud is added to each of the middle and end portions of the connection portion between the first corner piece outer edge strip 21 and the top plate or the floor of the airplane, so that the structural stability is improved. The strength of the airplane inflection connecting structure is improved by replacing the material of the airplane inflection connecting structure with aluminum alloy into titanium alloy.
According to the anti-fatigue design method for the airplane inflection connecting structure, the joint structure is optimized, the joint length is increased, and meanwhile, the structural form of the inner edge strip of the joint is optimized, so that the extension line of the inner edge strip is positioned in the middle of the connecting part, the transmission form of the whole inflection structure is controlled by changing the angle of the inner edge strip of the joint and the end form of the inner edge strip, the aim of controlling the distribution of nail loads of the connecting part is fulfilled, the received loads can be distributed by adding two more nails, and the nail loads are smaller; the shear angle piece structure is optimized, the middle and end studs are added, the structural material is changed, and the connection strength and the structural stability of the connection part are improved.
According to the airplane inflection connecting structure and the anti-fatigue design method thereof, the structure of the connecting structure is optimized by optimizing the structural form and the connecting mode of the connecting part, so that the local force transmission path of the structure is improved, the local stress level of the structure is reduced, and the anti-fatigue performance of the connecting structure is improved; on the other hand, the connecting form of the connecting part is improved, the distribution of nail transmission load is reasonably controlled on the basis of structural optimization, the nail load of the end head of the connecting part is reduced, and the fatigue performance of the connecting hole and the fatigue life of a connecting fastener are improved.
In one embodiment of the present application, in a connection structure at an inflection point of an original airplane in the prior art, under a certain fatigue load spectrum, the fatigue life analysis results are shown in table 1:
TABLE 1
Under the same fatigue load spectrum, the fatigue life analysis result of the airplane inflection connecting structure is shown in table 2, and the comparison with the load and the fatigue life of the connecting fastener in the prior art is shown in table 3:
TABLE 2
| Serial number | Details of the analysis | Maximum stress/MPa | Fatigue life/flight landing |
| 1 | Joint | 167 | 29671 |
| 2 | Connecting section bar | 392 | 22971 |
| 3 | Shearing angle piece | 412 | 24275 |
TABLE 3
According to the airplane inflection connecting structure and the anti-fatigue design method thereof, theoretical analysis and fatigue test verify that the local stress level and the end nail load of the connecting structure can be effectively reduced, the fatigue life of the structure and the connecting fastener is prolonged, and the purpose of improving the fatigue performance of the connecting part is achieved.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. An aircraft inflection connection structure, comprising:
the connector (1) comprises a connector outer edge strip (11), a connector inner edge strip (12) and a connector web plate (13), wherein the connector outer edge strip (11) is arranged on the outer side of the connector web plate (13), the connector inner edge strip (12) is arranged on the inner side of the connector web plate (13), and the connector outer edge strip (11) is connected with a side wall plate of a machine body;
the corner piece (2) is cut, the corner piece (2) comprises a first corner piece outer edge strip (21), a second corner piece outer edge strip (22) and a corner piece web plate (23), the first corner piece outer edge strip (21) and the second corner piece outer edge strip (22) are arranged on the outer side of the corner piece web plate (23), the first corner piece outer edge strip (21) is connected with the second corner piece outer edge strip (22) and forms a preset angle with the second corner piece outer edge strip, the first corner piece outer edge strip (21) is connected with a top plate or a floor of an airplane, and the second corner piece outer edge strip (22) is connected with a side wall plate of the airplane body;
the corner box (3) is connected, the corner box (3) comprises a corner box edge strip (31), a corner box web (32) and two vertical ribs, the corner box edge strip (31) is connected with the corner box web (32), the two vertical ribs are respectively arranged at two ends of an assembly formed by the corner box edge strip (31) and the corner box web (32), and the corner box edge strip (31) is connected with a top plate or a floor of an airplane;
wherein the joint web (13) is arranged between the gusset web (23) and the corner box web (32), and the joint web (13), the gusset web (23) and the corner box web (32) are connected through fasteners.
2. An aircraft inflected joint structure according to claim 1 wherein said joint outer edge strip (11) is connected to the fuselage sidewall panel by means of bolts or rivets.
3. An aircraft inflection connection structure as claimed in claim 2, wherein the first gusset outer edge strip (21) is connected to the aircraft roof or floor by bolts or rivets.
4. An aircraft inflected joint structure according to claim 3 wherein said second gusset outer flange (22) is connected to the side wall panel of the fuselage by means of bolts or rivets.
5. An aircraft inflection connection structure as claimed in claim 4, wherein said shear tab (2) further comprises a flange (24), said flange (24) being provided on said tab web (23) and abutting said second tab outer bead (22), said flange (24) being connected to the stringer of the fuselage sidewall panel by means of bolts or rivets.
6. An aircraft inflection connection structure as claimed in claim 5, wherein the corner box flange (31) is connected to the aircraft roof or floor by bolts or rivets.
7. Aircraft inflection connection according to claim 6, characterized in that said joint web (13), said gusset web (23) and said corner box web (32) are bolted.
8. An aircraft inflected joint structure fatigue design method based on any one of claims 1 to 7, characterized by comprising:
optimizing the joint (1), specifically: setting the joint (1) to a preset length which is the maximum length allowed by the structure, and optimizing the structural form of the joint inner edge strip (12) so that the extension line of the joint inner edge strip (12) is positioned in the middle position of the connection part of the first corner piece outer edge strip (21) and the top plate or the floor of the airplane;
the shearing angle piece (2) is optimized, and the method specifically comprises the following steps: set up the stud between first gusset outer fringe strip (21) and gusset web (23);
the material of the airplane inflection connecting structure is optimized, and the method specifically comprises the following steps: the strength of the airplane inflection connecting structure is improved by changing the structural material.
9. The method for designing the aircraft inflection connection structure as claimed in claim 8, wherein the studs are arranged at the middle and/or end of the connection part of the first corner piece peripheral strip (21) and the aircraft roof or floor.
10. The method for designing an aircraft inflection connection structure as claimed in claim 8, wherein the strength of the aircraft inflection connection structure is improved by replacing the material of the aircraft inflection connection structure with an aluminum alloy and a titanium alloy.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111614563.6A CN114239150B (en) | 2021-12-27 | 2021-12-27 | Airplane inflection connecting structure and anti-fatigue design method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111614563.6A CN114239150B (en) | 2021-12-27 | 2021-12-27 | Airplane inflection connecting structure and anti-fatigue design method thereof |
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| CN114239150A CN114239150A (en) | 2022-03-25 |
| CN114239150B true CN114239150B (en) | 2022-08-19 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2203996B (en) * | 1987-04-28 | 1991-04-03 | Verto Limited | Edging strip |
| CN207045788U (en) * | 2017-08-04 | 2018-02-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of T tails aircraft vertical fin spar testpieces |
| CN109383846A (en) * | 2017-08-04 | 2019-02-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of T tail aircraft vertical fin spar testpieces |
| CN211308946U (en) * | 2019-12-10 | 2020-08-21 | 精功（绍兴）复合材料有限公司 | Undercarriage stay bar longitudinal beam structure |
| CN213717049U (en) * | 2020-09-18 | 2021-07-16 | 陕西飞机工业（集团）有限公司 | Reinforcing structure of antenna with detachable outside of machine body |
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