CN207725604U - A kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing - Google Patents
A kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing Download PDFInfo
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- CN207725604U CN207725604U CN201721750920.0U CN201721750920U CN207725604U CN 207725604 U CN207725604 U CN 207725604U CN 201721750920 U CN201721750920 U CN 201721750920U CN 207725604 U CN207725604 U CN 207725604U
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- siding
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- aspect ratio
- high aspect
- honeycomb
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Abstract
A kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing, it is characterized in that, honeycomb interlayer siding includes exterior skin (1), glued membrane (2), inside panel (3) and honeycomb core (4), the outer surface of honeycomb core (4) is wrapped in 1 layer of glued membrane (2), and be evenly arranged on exterior skin (1), then exterior skin (1), be wrapped on the glued membrane (2) of honeycomb core (4) arrange inside panel (3).Its excellent in mechanical performance forms an independent integrated structure form with carrying/posting, has given full play to the good advantage of Composite Panels load performance, and collapsing load is high.
Description
Technical field
The utility model belongs to Aviation Composite Structure technical field, and in particular to one kind being suitable for high aspect ratio wing
Composite material honeycomb interlayer siding.
Background technology
Altitude Long Endurance Unmanned Air Vehicle flying height is high, and cruise duration is long, and combat radius is big, can perform global scouting prison
Depending on, persistently it is permanent scout etc. multiple-tasks, be the developing direction of long-range unmanned aerial vehicle.Due to Altitude Long Endurance Unmanned Air Vehicle voyage,
Rigors in endurance and economy, must be requested that wing area is big, and the span is wide, to ensure the lift for having enough.Make a general survey of generation
The advanced Altitude Long Endurance Unmanned Air Vehicle in boundary, wing design is maximum what is common is that using high aspect ratio wing, such as it is external nobody
Machine " global hawk ".
A distinguishing feature in high aspect ratio wing design：Root bending moment is big, and top airfoil is pressurized seriously, wainscot root
Stability problem protrudes.To solve this problem, many high aspect ratio wings can select composite material integral panel structure type,
Wherein most commonly seen is Composite Material Stiffened Panel structure type, is glued by covering and rib and is molded, is critically important hold
Power structure.But traditional Composite Material Stiffened Panel structural integrity is not good enough, there is apparent covering/rib interface, this boundary
Face is easy to that unsticking occurs first in rib edge, and then expands to entire covering/rib interface, causes entire composite material
The destruction of Material Stiffened Panel, influences aircraft safety.Thus it is difficult to give full play of the good advantage of Composite Panels load performance.
Utility model content
Purpose of utility model
The purpose of this utility model is to propose a kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing,
Excellent in mechanical performance, good integrity is simple for process, and can effectively avoid apparent exposed interface.
Technical solution
A kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing, honeycomb interlayer siding include exterior skin 1,
Glued membrane 2, inside panel 3 and honeycomb core 4 are wrapped in the outer surface of honeycomb core 4 with 1 layer of glued membrane 2, and are evenly arranged in exterior skin
On 1, then in exterior skin 1, be wrapped on the glued membrane 2 of honeycomb core 4 arrangement inside panel 3.
A kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing, the material of the inside panel 3
It is identical as exterior skin 1 with thickness.
A kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing, the honeycomb core 4 are rectangle,
Four edges are equipped with chamfered angle, and angle of splaying is 20 degree.
A kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing, the different installations on wing
Region adjusts the height of the honeycomb core 4 as needed.
Advantageous effect
The utility model has the advantage that is with advantageous effect, and the utility model proposes one kind being suitable for high aspect ratio machine
The composite material honeycomb interlayer siding of the wing, excellent in mechanical performance form an independent integration with carrying/posting
Structure type, has given full play to the good advantage of Composite Panels load performance, and collapsing load is high.
The honeycomb core edge of the composite material honeycomb interlayer siding of the utility model design is effective to solve using design of splaying
Rigidity of having determined mutation problems, improve the boundary strength of honeycomb core edge.
The composite material honeycomb interlayer siding good integrity of the utility model design, simple for process, honeycomb core is in addition to that can make
It is outer for structural unit carrying, the effect of inside panel core model is also played during laying and in solidification process, reduces die for special purpose
The manufacturing cost of tool.For more sandwich sidings, laying method is still disposable laying, reduces process and cost.
Relatively smooth and smooth, the inviolent thickness of composite material honeycomb interlayer siding inner surface of the utility model design
Degree mutation so that inner body design and manufacture are more simple, without making specific downset areas.
Description of the drawings
Fig. 1 is the exhibition of the utility model to schematic cross-section；
Fig. 2 is the utility model honeycomb core fringe region schematic diagram；
Wherein, 1- exterior skins, 2- glued membranes, 3- inside panels, 4- honeycomb cores.
Specific implementation mode
The utility model is described in further detail below in conjunction with the accompanying drawings, is please referred to Fig.1 to Fig. 2.
As shown in Figure 1, a kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing, which is characterized in that
Including exterior skin 1, glued membrane 2, inside panel 3 and honeycomb core 4, the outer surface of honeycomb core 4 is wrapped in 1 layer of glued membrane 2, and
Be evenly arranged on exterior skin 1, then in exterior skin 1, be wrapped on the glued membrane 2 of honeycomb core 4 arrangement inside panel 3.Its at
Type scheme is：Laying exterior skin 1 first；Honeycomb core 4 then is wrapped up with 1 layer of glued membrane 2, and is fixed in 1 inner surface of exterior skin
On；Last laying goes out inside panel 3, co-curing molding.
Preferably, the exterior skin 1 is formed using carbon fibre composite ZT7G3198P/LT-03A layings, and thickness is
0.4mm, laying angle are [45/0].
Preferably, the glued membrane 2 selects LWF-2C, this glued membrane, which is white, carrier adhesive, and it is solid altogether to can be used for plate-honeycomb core
Change and use, thickness 0.3mm is light-weight.
Preferably, using being formed with carbon fibre composite ZT7G3198P/LT-03A layings, thickness is the inside panel 3
0.4mm, laying angle are [0/45].
Preferably, it is the aramid fiber paper honeycomb core material of JY2-1.83-48 that the honeycomb core 4, which selects the trade mark,.
As shown in Fig. 2, the honeycomb core edge of the composite material honeycomb interlayer siding of the utility model design is set using splaying
Meter, effective solution rigidity mutation problems, improves the boundary strength of honeycomb core edge.
Claims (4)
1. a kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing, which is characterized in that honeycomb interlayer siding packet
Exterior skin (1), glued membrane (2), inside panel (3) and honeycomb core (4) are included, the outer surface of honeycomb core (4) is wrapped in 1 layer of glued membrane (2),
And be evenly arranged on exterior skin (1), then in exterior skin (1), be wrapped on the glued membrane (2) of honeycomb core (4) in arrangement
Covering (3).
2. a kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing according to claim 1, feature
It is, the material and thickness of the inside panel (3) are identical as exterior skin (1).
3. a kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing according to claim 1, feature
It is, the honeycomb core (4) is rectangle, and four edges are equipped with chamfered angle, and angle of splaying is 20 degree.
4. a kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing according to claim 1, feature
It is, the different installation regions on wing adjust the height of the honeycomb core (4) as needed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721750920.0U CN207725604U (en) | 2017-12-14 | 2017-12-14 | A kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721750920.0U CN207725604U (en) | 2017-12-14 | 2017-12-14 | A kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207725604U true CN207725604U (en) | 2018-08-14 |
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| CN201721750920.0U Active CN207725604U (en) | 2017-12-14 | 2017-12-14 | A kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109687139A (en) * | 2018-12-07 | 2019-04-26 | 中国航空工业集团公司济南特种结构研究所 | A kind of structure enhancing radome root rigidity |
| CN110145678A (en) * | 2019-05-13 | 2019-08-20 | 湖北三江航天红阳机电有限公司 | A kind of compound shell pieces of large scale complexity honeycomb sandwich construction and integral forming method |
| CN110879130A (en) * | 2018-09-06 | 2020-03-13 | 舜宇光学（浙江）研究院有限公司 | Imaging quality testing method of visual optical system and testing pattern unit thereof |
| CN112027055A (en) * | 2020-07-06 | 2020-12-04 | 西安飞机工业（集团）有限责任公司 | Composite material integral wall plate structure and manufacturing method |
| CN112507454A (en) * | 2020-12-04 | 2021-03-16 | 中国航空工业集团公司成都飞机设计研究所 | Fiber layering and layer losing method for reinforcing large-area metal structure composite material |
| CN113119499A (en) * | 2021-03-26 | 2021-07-16 | 哈尔滨玻璃钢研究院有限公司 | Composite material wing panel with telescopic function and forming method thereof |
| CN113211925A (en) * | 2021-05-11 | 2021-08-06 | 上海卫星工程研究所 | Non-equal thickness honeycomb sandwich plate |
-
2017
- 2017-12-14 CN CN201721750920.0U patent/CN207725604U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110879130A (en) * | 2018-09-06 | 2020-03-13 | 舜宇光学（浙江）研究院有限公司 | Imaging quality testing method of visual optical system and testing pattern unit thereof |
| CN109687139A (en) * | 2018-12-07 | 2019-04-26 | 中国航空工业集团公司济南特种结构研究所 | A kind of structure enhancing radome root rigidity |
| CN110145678A (en) * | 2019-05-13 | 2019-08-20 | 湖北三江航天红阳机电有限公司 | A kind of compound shell pieces of large scale complexity honeycomb sandwich construction and integral forming method |
| CN110145678B (en) * | 2019-05-13 | 2022-06-17 | 湖北三江航天红阳机电有限公司 | Large-size complex honeycomb sandwich structure composite shell sheet and integral forming method |
| CN112027055A (en) * | 2020-07-06 | 2020-12-04 | 西安飞机工业（集团）有限责任公司 | Composite material integral wall plate structure and manufacturing method |
| CN112507454A (en) * | 2020-12-04 | 2021-03-16 | 中国航空工业集团公司成都飞机设计研究所 | Fiber layering and layer losing method for reinforcing large-area metal structure composite material |
| CN113119499A (en) * | 2021-03-26 | 2021-07-16 | 哈尔滨玻璃钢研究院有限公司 | Composite material wing panel with telescopic function and forming method thereof |
| CN113211925A (en) * | 2021-05-11 | 2021-08-06 | 上海卫星工程研究所 | Non-equal thickness honeycomb sandwich plate |
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