CN222432573U - Aircraft fuselage assembly and aircraft fuselage - Google Patents
Aircraft fuselage assembly and aircraft fuselage Download PDFInfo
- Publication number
- CN222432573U CN222432573U CN202421251156.2U CN202421251156U CN222432573U CN 222432573 U CN222432573 U CN 222432573U CN 202421251156 U CN202421251156 U CN 202421251156U CN 222432573 U CN222432573 U CN 222432573U
- Authority
- CN
- China
- Prior art keywords
- aircraft fuselage
- embedded
- supporting member
- support
- support piece
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000007423 decrease Effects 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 11
- 238000003780 insertion Methods 0.000 description 8
- 230000037431 insertion Effects 0.000 description 8
- 230000013011 mating Effects 0.000 description 5
- 229910000838 Al alloy Inorganic materials 0.000 description 3
- 230000007774 longterm Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
Landscapes
- Connection Of Plates (AREA)
Abstract
An aircraft fuselage assembly and an aircraft fuselage relate to the field of aircrafts and comprise a first support piece and a second support piece, wherein a first embedded part is arranged at the end part of the first support piece, a first matching hole matched with the first embedded part is formed in the second support piece, and the first embedded part can be embedded into the first matching hole so that the first support piece is connected with the second support piece. The device has the advantages of simple structure, convenient installation, more stable and firm installation structure and strong reliability. The aircraft body comprises a third support piece and the aircraft body assembly, wherein a second embedded part is arranged at one end, far away from the first embedded part, of the first support piece, and a second matching hole matched with the second embedded part is formed in the third support piece. The device is simple to install, light in weight and high in stability.
Description
Technical Field
The utility model relates to the field of aircrafts, in particular to an aircraft fuselage assembly and an aircraft fuselage.
Background
At present, the existing aircraft/unmanned aerial vehicle fuselage adopts aluminum alloy plates, and a plurality of aluminum alloy plates form an aircraft fuselage frame through screw/spiral connection, so that the mode has poor stability and weak long-term use reliability.
In view of this, the present application has been made.
Disclosure of utility model
A first object of the present utility model is to provide an aircraft fuselage assembly that is simple in structure, convenient to install, more stable and reliable in installation structure.
A second object of the utility model is to provide an aircraft fuselage which is simple to install, light in weight and stable.
Embodiments of the present utility model are implemented as follows:
An aircraft fuselage assembly comprises a first support and a second support, wherein a first embedded part is arranged at the end part of the first support, a first matching hole matched with the first embedded part is formed in the second support, and the first embedded part can be embedded into the first matching hole so that the first support is connected with the second support.
Further, a plurality of first embedded parts are arranged at intervals at the end part of the first supporting piece, and a plurality of first matching holes matched with the first embedded parts are formed in the second supporting piece.
Further, when the first embedding portion is embedded in the first matching hole, an included angle a between a plane in which the first supporting piece is located and a plane in which the second supporting piece is located is larger than 0 °.
Further, the central axis of the first embedded part is parallel to the plane of the first supporting piece.
Further, the diameter of the first embedded portion decreases in a direction along the central axis of the first embedded portion and away from the first support.
Further, the cross section of the first embedded portion is polygonal.
The aircraft fuselage comprises a third support piece and the fuselage assembly, wherein a second embedded part is arranged at one end of the first support piece, which is far away from the first embedded part, and a second matching hole matched with the second embedded part is formed in the third support piece.
Further, an included angle B between the plane of the second supporting piece and the plane of the third supporting piece is smaller than 90 degrees.
Further, the plurality of first supports are disposed at intervals along the circumferential direction of the second support and the third support.
Further, the first support, the second support and the third support are all provided with a plurality of lightening holes.
The embodiment of the utility model has the beneficial effects that:
According to the aircraft fuselage assembly provided by the embodiment of the utility model, a traditional contact type connection mode through bolts can be changed into component connection between the first support piece and the second support piece, and the first support piece and the second support piece are mutually connected and mutually limited through the mortise-tenon structure, so that acting force is absorbed through the first support piece and the second support piece, and the stability and the firmness of connection between the first support piece and the second support piece are further improved.
In general, the aircraft fuselage assembly provided by the embodiment of the utility model has the advantages of simple structure, convenience in installation, more stable and firm installation structure and high reliability. The aircraft fuselage is realized based on the fuselage subassembly, and its installation is simple, and fuselage light in weight, stability is strong.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present utility model and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a fuselage assembly according to an embodiment of the present utility model;
FIG. 2 is an exploded view of a fuselage assembly provided in an embodiment of the present utility model;
FIG. 3 is a schematic structural view of an aircraft fuselage according to an embodiment of the present utility model;
FIG. 4 is an exploded view of an aircraft fuselage according to an embodiment of the present utility model;
fig. 5 is a schematic view of a part of an aircraft fuselage according to an embodiment of the present utility model.
The icons are 100-fuselage assembly, 110-first support, 111-first insert, 112-, second insert, 120-second support, 121-first mating hole;
1000-an aircraft fuselage, 200-a third support, 210-a second mating hole.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments of the present utility model. The components of the embodiments of the present utility model generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the utility model, as presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. 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.
It should be noted that like reference numerals and letters refer to like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
In the description of the present utility model, it should be noted that, directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., are directions or positional relationships based on those shown in the drawings, or are directions or positional relationships conventionally put in use of the inventive product, are merely for convenience of describing the present utility model and simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
Furthermore, the terms "parallel," "perpendicular," and the like, do not denote that the components are required to be absolutely parallel or perpendicular, but may be slightly inclined. For example, "parallel" merely means that the directions are more parallel than "perpendicular" and does not mean that the structures must be perfectly parallel, but may be slightly tilted.
Furthermore, the terms "horizontal," "vertical," "overhang," and the like do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present utility model, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, or may be directly connected, or may be indirectly connected through an intermediate medium, or may be in communication with the inside of two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.
Examples
At present, the existing aircraft fuselage all adopts polylith aluminium alloy plate to pass through screw/bolted connection to realize the equipment of fuselage, but the effort between the adjacent backup pad of this kind of mode is acted on screw/bolt completely, thereby leads to stability and the fastness of whole fuselage all to have certain deficiency, and screw/bolt are very easy not hard up in long-term use, thereby lead to showing the state of becoming flexible between the support piece, and then lead to the loose unstability of aircraft fuselage, thereby influence normal flight.
For the above reasons, referring to fig. 1 and 2, the present embodiment provides an aircraft fuselage 1000 assembly 100, which includes a first support member 110 and a second support member 120, wherein the end portion of the first support member 110 is provided with a first embedded portion 111, the second support member 120 is provided with a first matching hole 121 that matches the first embedded portion 111, and the first embedded portion 111 can be embedded into the first matching hole 121, so that the first support member 110 and the second support member 120 are connected.
Specifically, the end of the first support member 110 is provided with a plurality of first embedded parts 111 at intervals, and the second support member 120 is provided with a plurality of first engaging holes 121 engaged therewith.
The first insertion portion 111 is provided at one end of the first support 110 that contacts the second support 120, and the plurality of first insertion portions 111 are provided at intervals along the central axis of the end surface of the first insertion portion 111.
It should be noted that the positions of the first fitting holes 121 are set according to the positions of the first insertion portions 111, so as to ensure that a plurality of first insertion portions 111 can be simultaneously inserted into each of the first fitting holes 121.
It should be noted that, the central axis of the first embedded portion 111 is parallel to the plane of the first support 110.
Through the design, the traditional mode of contact type connection through the bolts can be changed into component connection between the first support piece 110 and the second support piece 120, and the first support piece 110 and the second support piece 120 are mutually connected and mutually limited through the mortise and tenon structure, so that acting force is absorbed through the first support piece 110 and the second support piece 120, and the stability and the firmness of connection between the first support piece 110 and the second support piece 120 are further improved.
In general, the aircraft fuselage 1000 assembly 100 provided by the embodiment of the utility model has the advantages of simple structure, convenient installation, more stable and firm installation structure and strong reliability.
In this embodiment, when the first embedding portion 111 is embedded in the first mating hole 121, the included angle a between the plane of the first supporting member 110 and the plane of the second supporting member 120 is greater than 0 °, and in order to enable better transmission of the force between the first supporting member 110 and the second supporting member 120, the included angle a is preferably 90 °.
In some embodiments, the diameter of the first embedded portion 111 decreases along the central axis of the first embedded portion 111 and away from the first support 110. The first insertion portion 111 is generally tapered or trapezoidal, so as to be more conveniently inserted into the first fitting hole 121 and is interference-fitted with the first fitting hole 121.
In other embodiments, the diameter of the first insertion portion 111 is unchanged along the central axis of the first insertion portion 111 and away from the first support 110, and is directly inserted into the first mating hole 121.
Further, since the force between the first support 110 and the second support 120 mainly acts on the first embedded portion 111, the cross section of the first embedded portion 111 is polygonal, preferably rectangular, in order to enable the first embedded portion 111 to carry a larger shearing force.
In addition, referring to fig. 3 to 5, an aircraft fuselage 1000 is further provided in the present embodiment, which includes a third support member 200 and the fuselage assembly 100, wherein a second embedded portion 112 is disposed at an end of the first support member 110 away from the first embedded portion 111, and a second mating hole 210 that mates with the second embedded portion 112 is formed in the third support member 200.
Specifically, the included angle B between the plane of the second supporting member 120 and the plane of the third supporting member 200 is smaller than 90 °, and in order to make the fuselage more stable, the included angle B is preferably 0 °, i.e. the plane of the second supporting member 120 is parallel to the plane of the third supporting member 200.
Further, the plurality of first supports 110 are disposed at intervals in the circumferential direction of the second and third supports 120 and 200. Thereby further ensuring the firmness and stability of the whole fuselage.
In addition, in order to further reduce the weight of the fuselage, in the present embodiment, the first support 110, the second support 120, and the third support 200 are each provided with a plurality of lightening holes. In order to ensure the balance of the fuselage, the lightening holes are arranged as symmetrically and uniformly as possible.
It should be noted that, in order to further secure the connection between the plurality of first supports 110 and the second supports 120 and the third supports 200, further fixing may be performed by means of screws/bolts/rivets after the installation of the whole body is completed.
In summary, the aircraft fuselage 1000 assembly 100 provided by the utility model has the advantages of simple structure, convenient installation, more stable and firm installation structure and strong reliability. The aircraft fuselage 1000 is realized based on a fuselage assembly 100, which is simple to install, light in weight and stable.
The above description is only of the preferred embodiments of the present utility model and is not intended to limit the present utility model, but various modifications and variations can be made to the present utility model by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included in the protection scope of the present utility model.
Claims (10)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202421251156.2U CN222432573U (en) | 2024-06-03 | 2024-06-03 | Aircraft fuselage assembly and aircraft fuselage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202421251156.2U CN222432573U (en) | 2024-06-03 | 2024-06-03 | Aircraft fuselage assembly and aircraft fuselage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN222432573U true CN222432573U (en) | 2025-02-07 |
Family
ID=94399784
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202421251156.2U Active CN222432573U (en) | 2024-06-03 | 2024-06-03 | Aircraft fuselage assembly and aircraft fuselage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN222432573U (en) |
-
2024
- 2024-06-03 CN CN202421251156.2U patent/CN222432573U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102369138B (en) | Coupling assembly, joiner containing coupling assembly, and preparation method of joiner | |
| CN103141000B (en) | For forming the connector of electrical connection between two plates | |
| RU2406646C2 (en) | Lateral load transfer joint and its application | |
| JP2013504468A (en) | Radome and apparatus for attaching the radome to an aircraft | |
| CN112693623B (en) | Missile grid rudder hinge moment model claw disc type self-locking positioning structure | |
| CN222432573U (en) | Aircraft fuselage assembly and aircraft fuselage | |
| WO2016180002A1 (en) | Device mounting apparatus | |
| CN207141380U (en) | A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure | |
| TW201828532A (en) | Dish antenna and method for manufacturing bracket thereof and dish stand assembly thereof | |
| US4653951A (en) | Zero free-play joint for deployable space structures | |
| CN105711815B (en) | A kind of propeller fast assembling-disassembling self-locking mechanism | |
| EP3130534A1 (en) | Airplane wing assembly | |
| CN107512399B (en) | Box-shaped beam type engine main mounting joint | |
| CN109506914B (en) | Tail stock pitch-changing fatigue test device | |
| CN204368408U (en) | For being fixedly connected with the mounting structure of model plane fuselage and wing | |
| CN103186189A (en) | Mainboard fixing device | |
| CN112548462B (en) | Spot welding clamp for airplane parts | |
| CN210509945U (en) | Universal ball fixing support | |
| CN220623536U (en) | Pin-connected panel camera fixed bolster | |
| CN112392564A (en) | Connection structure of outer loop machine casket and radials | |
| CN206031805U (en) | Core plate during multiaxis aircraft is general | |
| CN216913502U (en) | An aircraft foreskin support rod base fixing tool | |
| CN216102744U (en) | Connection locking structure of aircraft wing and vertical take-off and landing rod | |
| CN213775918U (en) | Accurate positioning assembly of aluminum alloy pleasure-boat | |
| CN111926979A (en) | Keel corner and pulley structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |