CN221273530U - Material-increasing manufacturing aircraft nacelle tail cone structure - Google Patents
Material-increasing manufacturing aircraft nacelle tail cone structure Download PDFInfo
- Publication number
- CN221273530U CN221273530U CN202323349291.9U CN202323349291U CN221273530U CN 221273530 U CN221273530 U CN 221273530U CN 202323349291 U CN202323349291 U CN 202323349291U CN 221273530 U CN221273530 U CN 221273530U
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- CN
- China
- Prior art keywords
- skin
- edge strip
- skin portion
- strip section
- lapping edge
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 16
- 239000000654 additive Substances 0.000 claims abstract description 20
- 230000000996 additive effect Effects 0.000 claims abstract description 20
- 239000003351 stiffener Substances 0.000 claims description 7
- 230000003014 reinforcing effect Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 5
- 239000002131 composite material Substances 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Abstract
The application belongs to the field of aircraft structural design, and particularly relates to an additive manufacturing aircraft nacelle tail cone structure. Comprising the following steps: a skin comprising a first skin portion and a second skin portion, the first skin portion having a greater degree of curvature than the second skin portion, the first skin portion and the second skin portion together forming a cap; the lapping edge strip comprises a first lapping edge strip section and a second lapping edge strip section, the first lapping edge strip section is lapped at the edge of the first skin portion, the second lapping edge strip section is lapped at the edge of the second skin portion, and the first lapping edge strip section and the second lapping edge strip section jointly form a frame; the frame web is arranged on the frame; the skin, the overlap cap and the frame web are integrally formed through additive manufacturing. The application provides a small-size caudal vertebra structure scheme, which has simple and convenient process and simple and reliable structure form and can ensure the strength and rigidity of the structure.
Description
Technical Field
The application belongs to the field of aircraft structural design, and particularly relates to an additive manufacturing aircraft nacelle tail cone structure.
Background
The tail cone structure is generally a semi-closed structure, and when the tail cone skin is formed by adopting a traditional metal forming mode, the tail cone must be formed in a segmented mode and then mechanically connected or welded. If the composite material skin is adopted, the composite material skin is limited by the bending radius of the composite material, and if the tail end of the tail cone is smaller in size, the tail end cannot be formed. The metal skin and skeleton structure or V-shaped composite skin and metal skeleton structure is used, fasteners are needed in the connection and assembly process of the metal structure, and for small-size tail cone structures, the cross section size is small, the assembly relationship is complex, or blind connection fasteners are used, so that the connection reliability of the blind connection fasteners is low according to the prior art, and the risk of falling is caused by pneumatic suction in the flight process.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of utility model
It is an object of the present application to provide an additive manufactured aircraft nacelle tail cone structure that solves at least one of the problems of the prior art.
The technical scheme of the application is as follows:
An additively manufactured aircraft nacelle tail cone structure comprising:
A skin comprising a first skin portion and a second skin portion, the first skin portion having a greater degree of curvature than the second skin portion, the first skin portion and the second skin portion together forming a cap;
the lapping edge strip comprises a first lapping edge strip section and a second lapping edge strip section, the first lapping edge strip section is lapped at the edge of the first skin portion, the second lapping edge strip section is lapped at the edge of the second skin portion, and the first lapping edge strip section and the second lapping edge strip section jointly form a frame;
the frame web is arranged on the frame;
Wherein, the covering, the overlap joint edge strip and the frame web are manufactured integrally through the additive.
In at least one embodiment of the application, the skin is a variable thickness structure.
In at least one embodiment of the application, the skin is provided with drain holes.
In at least one embodiment of the present application, the frame web is provided with a viewing window.
In at least one embodiment of the present application, the skin further comprises a stiffener, the stiffener being disposed inside the skin;
Wherein, the covering, the overlap joint edge strip, the frame web and the stiffener are manufactured integrally through additive manufacturing.
The utility model has at least the following beneficial technical effects:
The material-increasing manufactured aircraft nacelle tail cone structure can ensure the appearance of the tail cone end, the whole tail cone structure is integrally formed by material-increasing manufacturing, no fastener is connected, the number of parts, assembly relation and the number of fasteners can be reduced, and the weight can be effectively reduced; the additive manufacturing can effectively ensure the forming thickness of the part, the vibration environment of the tail airflow is complex, the faults caused by the problems of uneven thickness of the part and the like can be effectively reduced, and the maintenance cost is reduced.
Drawings
FIG. 1 is a first angular view of an additive manufactured aircraft nacelle tail cone structure according to one embodiment of the application;
FIG. 2 is a first angular cross-sectional view of an additive manufactured aircraft nacelle tail cone structure according to one embodiment of the application;
FIG. 3 is a second angular view of an additive manufactured aircraft nacelle tail cone structure according to one embodiment of the application.
Wherein:
1-covering; 2-lapping the edge strip; 3-frame webs.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying 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 some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are illustrative and intended to explain the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the 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 should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate describing the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present application.
The application is described in further detail below with reference to fig. 1 to 3.
The application provides an additive manufacturing aircraft nacelle tail cone structure, which comprises the following components: skin 1, overlap cap 2 and frame web 3.
Specifically, the skin 2 includes a first skin portion having a larger curvature and a second skin portion having a smaller curvature, the first skin portion and the second skin portion together forming a hat shape as shown. The lapping edge strip 2 comprises a first lapping edge strip section and a second lapping edge strip section, the first lapping edge strip section is U-shaped and has larger curvature, the first lapping edge strip section is lapped at the edge of the first skin portion, the second lapping edge strip section is C-shaped and has smaller curvature, the second lapping edge strip section is lapped at the edge of the second skin portion, and the first lapping edge strip section and the second lapping edge strip section jointly form a frame; the frame web 3 is arranged on the inner side of the frame; wherein the skin 1, the overlap cap 2 and the frame web 3 are integrally formed by additive manufacturing.
In the preferred embodiment of the application, the skin 1 can be designed into a variable thickness structure according to the strength analysis structure and the use environment condition, and the lowest point of the skin 1 can be provided with a drain hole so as to facilitate the outflow of accumulated water in the closed structure.
In the preferred embodiment of the application, the frame web 3 is provided with an opening as a viewing window to facilitate viewing of the interior of the caudal vertebra.
Advantageously, in this embodiment, the inner side of the skin 1 is further provided with stiffeners 4, and the skin 1, the overlap flange 2, the frame web 3 and the stiffeners 4 are integrally formed by additive manufacturing.
The material-increasing manufactured aircraft nacelle tail cone structure is a metal material part and is arranged at the tail part of an aircraft cover body to play a role in rectification, and is integrally formed by adopting a material-increasing manufacturing process method. The skin 1 is used for maintaining the whole structural shape, and can be designed into other specific structural forms according to the aircraft shape; the structural overall rigidity is improved through the frame web plates 3 and the reinforcing ribs 4; the overlap cap 2 is intended to be connected to the front structure, the part itself not requiring any connection.
The material-increasing manufactured aircraft nacelle tail cone structure can ensure the appearance of the tail cone end, the whole tail cone structure is integrally formed by material-increasing manufacturing, no fastener is connected, the number of parts, assembly relation and the number of fasteners can be reduced, and the weight can be effectively reduced; the additive manufacturing can effectively ensure the forming thickness of the part, the vibration environment of the tail airflow is complex, the faults caused by the problems of uneven thickness of the part and the like can be effectively reduced, and the maintenance cost is reduced. The application provides a small-size caudal vertebra structure scheme, which has simple and convenient process and simple and reliable structure form and can ensure the strength and rigidity of the structure.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. An additively manufactured aircraft nacelle tail cone structure, comprising:
A skin (1), the skin (1) comprising a first skin portion and a second skin portion, the first skin portion having a greater degree of curvature than the second skin portion, the first skin portion and the second skin portion together forming a cap;
the lapping edge strip (2), the lapping edge strip (2) comprises a first lapping edge strip section and a second lapping edge strip section, the first lapping edge strip section is lapped at the edge of the first skin portion, the second lapping edge strip section is lapped at the edge of the second skin portion, and the first lapping edge strip section and the second lapping edge strip section jointly form a frame;
a frame web (3), wherein the frame web (3) is arranged on the frame;
Wherein the skin (1), the overlap cap (2) and the frame web (3) are integrally formed by additive manufacturing.
2. Additive manufactured aircraft nacelle tail cone structure according to claim 1, characterized in that the skin (1) is a variable thickness structure.
3. Additive manufactured aircraft nacelle tail cone structure according to claim 1, characterized in that the skin (1) is provided with drainage holes.
4. Additive manufactured aircraft nacelle tail cone structure according to claim 1, characterized in that the frame web (3) is provided with a viewing window.
5. Additive manufactured aircraft nacelle tail cone structure according to claim 1, further comprising a stiffener (4), the stiffener (4) being arranged inside the skin (1);
Wherein the skin (1), the overlap cap (2), the frame web (3) and the reinforcing ribs (4) are integrally formed by additive manufacturing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323349291.9U CN221273530U (en) | 2023-12-08 | 2023-12-08 | Material-increasing manufacturing aircraft nacelle tail cone structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323349291.9U CN221273530U (en) | 2023-12-08 | 2023-12-08 | Material-increasing manufacturing aircraft nacelle tail cone structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221273530U true CN221273530U (en) | 2024-07-05 |
Family
ID=91696187
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323349291.9U Active CN221273530U (en) | 2023-12-08 | 2023-12-08 | Material-increasing manufacturing aircraft nacelle tail cone structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221273530U (en) |
-
2023
- 2023-12-08 CN CN202323349291.9U patent/CN221273530U/en active Active
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