CN220865646U - Aircraft fuselage interfacing structure and aircraft - Google Patents
Aircraft fuselage interfacing structure and aircraft Download PDFInfo
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- CN220865646U CN220865646U CN202322843685.3U CN202322843685U CN220865646U CN 220865646 U CN220865646 U CN 220865646U CN 202322843685 U CN202322843685 U CN 202322843685U CN 220865646 U CN220865646 U CN 220865646U
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- 210000001503 joint Anatomy 0.000 claims abstract description 91
- 238000003032 molecular docking Methods 0.000 claims abstract description 33
- 230000002349 favourable effect Effects 0.000 abstract 1
- 239000002131 composite material Substances 0.000 description 7
- 230000009286 beneficial effect Effects 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 5
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model relates to the technical field of airplane body butt joint, and provides an airplane body butt joint structure and an airplane, wherein the airplane body butt joint structure comprises: a butt joint frame; the docking frame includes: a frame-type main body and a butt-joint flange; one side of the main body part is fixedly connected with one of the machine bodies; the butt-joint edge strip is connected to the other side of the main body part and surrounds the main body part to form a butt joint, and the butt-joint end is used for embedding one end of the other machine body to be butted so that the butt-joint edge strip is attached to and connected with the skin of the other machine body. So set up, only need use a butt joint frame can realize the butt joint of two fuselages, simplified fuselage butt joint structure, lightened weight has improved the convenience of fuselage assembly, in addition, can lighten the holistic weight of aircraft, is favorable to the lightweight design of aircraft.
Description
Technical Field
The utility model relates to the technical field of docking of aircraft fuselages, in particular to an aircraft fuselage docking structure and an aircraft.
Background
The fuselage structure of the existing aircraft basically adopts a sectional design, so that the aircraft is convenient to manufacture and transport, and the complete fuselage is formed by butting all sections of fuselage, so that the fuselage butting of the aircraft is an important link of the aircraft assembly technology.
In the related art, a butt joint frame is generally arranged on the front and rear airframes, when the front and rear airframes are in butt joint, the frame web surfaces of the butt joint frames of the front and rear airframes are attached, and then the butt joint frames are fixed by using positioning pins to finish the butt joint of the front and rear airframes.
However, in the related art, the docking frame increases the weight of the front and rear frames, and the convenience of assembly is not sufficient.
Disclosure of utility model
The embodiment of the utility model provides an airplane body butt joint structure and an airplane, which are used for solving the problems that the front and rear airplane bodies are large in weight and insufficient in assembly convenience due to the butt joint structure in the prior art, and improving the convenience in assembly of the front and rear airplane bodies.
The utility model provides an aircraft fuselage interfacing structure, comprising: a butt joint frame;
the docking frame includes: a frame-type main body and a butt-joint flange;
One side of the main body part is fixedly connected with one of the machine bodies;
The butt-joint edge strip is connected to the other side of the main body part and surrounds the main body part to form a butt joint, and the butt-joint end is used for embedding one end of the other machine body to be butted so that the butt-joint edge strip is attached to and connected with the skin of the other machine body.
According to the aircraft fuselage interfacing structure provided by the utility model, the main body portion comprises a frame-type web;
The web plate is provided with a pair of butt joint surfaces, and the pair of butt joint surfaces are arranged on two opposite sides of the web plate and are used for respectively attaching one ends of two machine bodies to be butt-jointed;
The butt-joint edge strip is connected to the web.
According to the present utility model, there is provided an aircraft fuselage interfacing structure, the main body further comprising: a pair of wing plates connected to a side of the web facing away from the butt-joint edge strip;
the pair of wing plates are arranged around the web plate in a spacing fit mode, the space between the pair of wing plates is used for embedding one end of the machine body to be butted, and the pair of wing plates are respectively attached to the skin and the inner wall of the machine body.
According to the utility model, the docking structure of the airplane body further comprises a connecting band plate;
The butt joint frame is provided with a first end and a second end at one side, the first end and the second end are used for butt joint of the body beams of the two bodies, and the connecting band plate is matched between the first end and the second end;
The two sides of the connecting band plate are used for connecting two airframes respectively, and the two sides of the end part of the connecting band plate are used for connecting airframe beams of the two airframes respectively.
According to the aircraft fuselage butt joint structure provided by the utility model, the end part of the connecting band plate is provided with the extension part extending along the side direction, and the extension part is used for being connected with the fuselage girder.
According to the aircraft fuselage butt joint structure provided by the utility model, the web plate, the wing plate and the butt joint edge strip are integrally formed.
According to the aircraft fuselage butt joint structure provided by the utility model, the extension part is integrally formed on the connecting band plate.
According to the aircraft fuselage butt joint structure provided by the utility model, the butt joint frame and/or the connecting band plate are made of composite materials.
The utility model also provides an aircraft, which comprises a front aircraft body, a rear aircraft body and the aircraft body butt joint structure for connecting the front aircraft body and the rear aircraft body.
According to the aircraft provided by the utility model, the main body part is connected to the front fuselage, and the butt-joint edge strip is connected with the skin of the rear fuselage.
According to the aircraft provided by the utility model, the butt-joint edge strip is connected with the skin of the rear fuselage through rivet bonding.
According to the aircraft body butt joint structure and the aircraft, before the aircraft body is in butt joint, the main body part of the butt joint frame is fixedly connected to one end of one of the aircraft bodies to be in butt joint, then the other aircraft body is pushed by the sliding rail on the tooling, the other aircraft body is embedded into a butt joint interface formed by the butt joint edge strip, the butt joint edge strip is attached to the aircraft body skin of the other aircraft body, and finally the butt joint edge strip is fixed with the aircraft body skin in a rivet bonding mode and the like, so that the butt joint of the two aircraft bodies is completed; compared with the related art, the machine body butt joint structure provided by the embodiment of the utility model can realize the butt joint of two machine bodies by using only one butt joint frame, simplifies the machine body butt joint structure, lightens the weight, improves the convenience of machine body assembly, lightens the whole weight of an airplane and is beneficial to the lightweight design of the airplane.
Drawings
In order to more clearly illustrate the utility model or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the utility model, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of an aircraft fuselage interface structure according to an embodiment of the present utility model;
FIG. 2 is a schematic structural diagram of a docking frame according to an embodiment of the present utility model;
FIG. 3 is a second schematic view of a docking frame according to an embodiment of the present utility model;
Fig. 4 is a schematic structural view of a connection band plate according to an embodiment of the present utility model.
Reference numerals:
1. a front body; 2. a rear body; 3. a butt joint frame; 30. a main body portion; 300. a web; 301. a first wing plate; 302. a second wing plate; 31. a butt-joint edge strip; 4. connecting the band plates; 40. an extension.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present utility model more apparent, the technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present utility model, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
In order to facilitate understanding of the aircraft fuselage butt joint structure and the aircraft provided by the utility model, firstly, the application background is described, in the prior art, in order to facilitate manufacturing, transportation and the like of the aircraft, the aircraft fuselage is generally set to be of a sectional structure, all sections of the fuselage are butt-jointed to form a complete fuselage, in the related art, butt joint frames are generally arranged on the front fuselage and the rear fuselage, the frame web surfaces of the butt joint frames of the front fuselage and the rear fuselage are attached during butt joint, and then the butt joint of the front fuselage and the rear fuselage is completed by fixing the frame web surfaces by using positioning pins. However, in the related art, the front and rear frames are required to be provided with the butt joint frames, which can make the front and rear frames heavier, and the convenience of assembly is insufficient; and the butt joint frame can increase the whole weight of the aircraft, which is unfavorable for the lightweight design and performance optimization of the aircraft. Based on the above, the utility model provides the aircraft body docking structure and the aircraft, which are beneficial to improving the convenience of docking the aircraft body and simultaneously beneficial to the light design and the performance optimization of the aircraft.
The aircraft fuselage interfacing structure and aircraft of the present utility model are described below in connection with fig. 1-4.
Referring to fig. 1 and 2, an aircraft includes a front fuselage 1 and a rear fuselage 2, and an aircraft fuselage interface structure is used to connect the front fuselage 1 and the rear fuselage 2.
The aircraft fuselage docking structure comprises a docking frame 3; the docking frame 3 comprises a main body part 30 and a docking edge strip 31, wherein one side of the main body part 30 is fixedly connected with one of the machine bodies, the docking edge strip 31 is connected to the other side of the main body part 30 and is arranged around the main body part 30 to form a pair interface, and the docking edge strip 31 is used for embedding one end of the other machine body to be docked, so that the docking edge strip 31 is attached to and connected with the skin of the other machine body.
Before the machine body is actually docked, the main body part 30 of the docking frame 3 is fixedly connected to one end of one machine body to be docked, then the other machine body is pushed by a sliding rail on a tool, the other machine body is embedded into a docking port formed by the docking edge strip 31, the docking edge strip 31 is attached to the machine body skin of the other machine body, and then the docking edge strip 31 is fixed with the machine body skin in a rivet bonding mode and the like, so that docking of the two machine bodies is completed; compared with the related art, the machine body butt joint structure provided by the embodiment of the utility model can realize the butt joint of two machine bodies by using only one butt joint frame 3, simplifies the machine body butt joint structure, lightens the weight, improves the convenience of machine body assembly, lightens the whole weight of an airplane and is beneficial to the lightweight design of the airplane.
It will be appreciated that the body portion 30 may be fixedly attached to the front body 1 or to the rear body 2 prior to docking the bodies, and then the other body may be pushed toward the body to which the body portion 30 is attached to effect mating of the other body with the docking flange 31. In this embodiment, the main body 30 is connected to the front body 1 in advance, and the rear body 2 is pushed in the direction of the front body 1 to engage the butt-joint cap 31 with the rear body 2.
Referring to fig. 2 and 3, the main body 30 includes a frame-shaped web 300, the web 300 has a pair of opposite joint surfaces respectively disposed on opposite sides of the web 300, the two joint surfaces are used for respectively attaching end surfaces of one end to be joined of the front fuselage 1 and the rear fuselage 2, and the butt-joint flange 31 is connected to the web 300. When in butt joint, the main body part 30 is fixedly connected to the front machine body 1, one butt joint surface of the web 300 is attached to the end face of one end of the front machine body 1 to be butt-jointed, then the rear machine body 2 is pushed to the front machine body 1 by using a sliding rail on a tool, the rear machine body 2 is embedded into a butt joint interface formed by the butt joint edge strip 31, and the butt joint edge strip 31 is attached to and connected with the skin of the rear machine body 2, so that the butt joint of the machine bodies is realized.
The main body part 30 further comprises a pair of wing plates connected to one side of the web 300, which is away from the butt-joint edge strip 31, the pair of wing plates are arranged around the web 300 and are matched at intervals, a space between the two wing plates is used for embedding one end to be butt-jointed of the front body 1, so that the two wing plates are respectively attached to the skin and the inner wall of the front body 1, and the wing plates and the body are connected in a rivet bonding connecting mode, so that the main body part 30 is fixed in advance on the front body 1.
Specifically, one of the wing plates is set to be a first wing plate 301, the other wing plate is set to be a second wing plate 302, the first wing plate 301 is connected to the outer side edge of the frame-shaped web 300 and is used for being adhered to and connected with the skin of the front fuselage 1, and the second wing plate 302 is connected to the inner side edge of the frame-shaped web 300 and is used for being adhered to and connected with the inner wall of the front fuselage 1; the butt-joint flange 31 is connected to the outer edge of the frame-shaped web 300, and the first wing plate 301, the butt-joint flange 31, the web 300 and the second wing plate 302 make the cross section of the butt-joint frame 3 in a J shape.
Specifically, the first wing plate 301, the second wing plate 302, the web 300 and the butt-joint flange 31 may be integrally formed, so as to ensure the connection strength and load transmission of the front fuselage 1 and the rear fuselage 2.
Specifically, the docking frame 3 may be made of an alloy material, such as an aluminum alloy, or a composite material, such as a carbon fiber composite laminate, and may be specifically selected according to actual needs.
In this embodiment, the docking frame 3 is made of a composite material to ensure the connection strength and load transfer between the front body 1 and the rear body 2.
It should be understood that the front body 1 and the main body 30 are not limited to the above connection method, and other structures that can realize the fixed connection of the main body 30 and the front body 1 can be applied to the present utility model.
As is well known, the front airframe 1 and the rear airframe 2 are internally provided with airframe beams, when the airframe is in butt joint, the airframe is not only required to be in butt joint, but also the connection strength between the airframe beams is required to be ensured, so that the overall butt joint strength of the airframe and the transmission of load during bending are ensured.
Based on the above, the opening at one side of the docking frame 3 is formed with a first end and a second end, where the positions of the first end and the second end respectively correspond to the positions of two side beams of the machine body, the connection mode of the machine body beam and the docking frame 3 is the same as the connection mode of the machine body and the docking frame 3, that is, the first wing plate 301 and the second wing plate 302 are respectively and fixedly connected with two sides of the front machine body 1 beam through rivet bonding and the like, and the docking edge strip 31 is fixedly connected with the rear machine body 2 beam through rivet bonding and the like.
The aircraft fuselage interfacing structure further comprises a connecting band plate 4; the connecting band plate 4 is matched between the first end and the second end and is used for covering the butt joint seam of the front fuselage and the rear fuselage between the first end and the second end, so that the appearance of the airplane is smoother and more attractive; the connecting band plate 4 is positioned at two sides of the butt joint and is used for connecting the front body and the rear body respectively, so that the connection of the front body and the rear body is realized.
The both ends of connecting band plate 4 are corresponding with the position of two fuselage roof beams of fuselage both sides respectively, and the both sides of connecting band plate 4 tip are connected with the fuselage roof beam of two fuselage around respectively, so, both can realize being connected between two fuselage roof beams around, also can realize being located the connection of fuselage roof beam of fuselage both sides, guarantee fuselage butt joint intensity and the load transfer when the fuselage receives the bending.
The extension portion 40 extending along the side direction is arranged at the end portion of the connecting band plate 4, and the extension portion 40 is used for being connected with the body beam, so that the connection area of the connecting band plate 4 and the body beam can be increased, the connection strength is improved, and the load transmission is ensured.
Specifically, the extension portion 40 is integrally formed on the connection band plate 4, so as to ensure the connection strength and load transmission of the fuselage girder.
Specifically, the connecting band plate 4 may be made of an alloy material, such as an aluminum alloy, or a composite material, such as a carbon fiber composite laminate, or the like, and may be specifically selected according to actual requirements.
In this embodiment, the connection band plate 4 is made of a composite material, so as to ensure the connection strength of the front and rear airframes, the front and rear airframe beams and the airframe beams at different positions.
The following describes an aircraft provided by the present utility model, and the aircraft described below and the aircraft fuselage interfacing structure described above may be referred to correspondingly to each other.
Referring to fig. 1, an aircraft includes a front fuselage 1, a rear fuselage 2, and the above-described aircraft fuselage interfacing structure for connecting the front fuselage 1 and the rear fuselage 2.
The main body 30 of the docking frame 3 is connected to the front fuselage 1, the first wing plate 301 is attached to the skin of the front fuselage 1, the second wing plate 302 is attached to the inner wall of the front fuselage 1, and the first wing plate 301 and the second wing plate 302 can be fixedly connected to the front fuselage 1 through rivet bonding.
The back fuselage 2 gomphosis is in butt joint mouth that butt joint rim 31 formed, and butt joint rim 31 is laminated with the covering of back fuselage 2, and butt joint rim 31 and the covering of back fuselage 2 can pass through rivet bonding's mode fixed connection.
The connecting band plate 4 is covered on the butt joint of the front and rear fuselage between the first end and the second end, and can shield the butt joint to make the appearance of the aircraft smoother and more attractive.
The connecting band plate 4 is positioned at two sides of the butt joint and is respectively fixed with the front machine body and the rear machine body in a rivet bonding or screw mode, so that the connection of the front machine body and the rear machine body is realized.
The extension part 40 is fixedly connected with the front and back machine body beams in a rivet bonding or screw mode, so that the connection of the front and back machine body beams and the machine body beams at different positions is realized, and the connection strength and load transmission of the front and back machine bodies are ensured.
The novel innovation point of the utility model is that: before the machine body is in butt joint, the main body part 30 of the butt joint frame 3 is fixedly connected to one end of one machine body to be in butt joint, then the other machine body is pushed by a sliding rail on a tool, the other machine body is embedded into a butt joint interface formed by the butt joint edge strip 31, the butt joint edge strip 31 is attached to a machine body skin of the other machine body, and finally the butt joint edge strip 31 is fixed with the machine body skin in a rivet bonding mode and the like, so that the butt joint of the two machine bodies is completed; compared with the related art, the machine body butt joint structure provided by the embodiment of the utility model can realize the butt joint of two machine bodies by using only one butt joint frame 3, simplifies the machine body butt joint structure, lightens the weight, improves the convenience of machine body assembly, lightens the whole weight of an airplane and is beneficial to the lightweight design of the airplane.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present utility model, and are not limiting; although the utility model has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present utility model.
Claims (10)
1. An aircraft fuselage interfacing structure comprising: a butt joint frame (3);
the docking frame (3) comprises: a frame-type main body (30) and a butt-joint flange (31);
One side of the main body part (30) is used for being fixedly connected with one of the machine bodies;
The butt-joint edge strip (31) is connected to the other side of the main body part (30) and surrounds the main body part (30) to form a butt joint, and the butt joint is used for embedding one end of the other fuselage to be butted so that the butt-joint edge strip (31) is attached to and connected with the skin of the other fuselage.
2. The aircraft fuselage interface structure of claim 1, wherein the main body portion (30) comprises a frame-like web (300);
the web plate (300) is provided with a pair of butt joint surfaces, and the pair of butt joint surfaces are arranged on two opposite sides of the web plate (300) and are used for respectively attaching one ends of two machine bodies to be butt-jointed;
the butt-joint flange (31) is connected to the web (300).
3. The aircraft fuselage interfacing structure of claim 2, wherein the main body portion (30) further comprises: a pair of wings connected to a side of the web (300) facing away from the butt-flange (31);
the pair of wing plates are arranged around the web plate (300) in a spacing fit mode, and the space between the pair of wing plates is used for embedding one end of the machine body to be butted, so that the pair of wing plates are respectively attached to the skin and the inner wall of the machine body.
4. An aircraft fuselage interfacing structure according to any one of claims 1-3, further comprising a connecting band plate (4);
A first end and a second end are formed at one side opening of the butt joint frame (3), the first end and the second end are used for butt joint of the body beams of the two bodies, and the connecting band plate (4) is matched between the first end and the second end;
The two sides of the connecting band plate (4) are used for connecting two airframes respectively, and the two sides of the end part of the connecting band plate (4) are used for connecting airframe beams of the two airframes respectively.
5. An aircraft fuselage interfacing structure according to claim 4, characterized in that the end of the connection band plate (4) is provided with extensions (40) extending in a lateral direction, the extensions (40) being intended for connection with a fuselage beam.
6. An aircraft fuselage interfacing structure according to claim 3, wherein the web (300), wing panels and interface flanges (31) are integrally formed.
7. The aircraft fuselage interfacing structure of claim 5, wherein the extension (40) is integrally formed with the connection band plate (4).
8. An aircraft characterized by comprising a front fuselage (1), a rear fuselage (2), and an aircraft fuselage interface structure according to any one of claims 1-7 for connecting the front fuselage (1) and the rear fuselage (2).
9. The aircraft according to claim 8, characterized in that the main body portion (30) is connected to the forward fuselage (1) and the butt-strap (31) is connected to the skin of the aft fuselage (2).
10. The aircraft according to claim 9, characterized in that the butt-strap (31) is connected to the skin of the aft fuselage (2) by means of rivet bonding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322843685.3U CN220865646U (en) | 2023-10-23 | 2023-10-23 | Aircraft fuselage interfacing structure and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322843685.3U CN220865646U (en) | 2023-10-23 | 2023-10-23 | Aircraft fuselage interfacing structure and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220865646U true CN220865646U (en) | 2024-04-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322843685.3U Active CN220865646U (en) | 2023-10-23 | 2023-10-23 | Aircraft fuselage interfacing structure and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220865646U (en) |
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2023
- 2023-10-23 CN CN202322843685.3U patent/CN220865646U/en active Active
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