CN204368409U - A kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing - Google Patents
A kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing Download PDFInfo
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- CN204368409U CN204368409U CN201420814946.7U CN201420814946U CN204368409U CN 204368409 U CN204368409 U CN 204368409U CN 201420814946 U CN201420814946 U CN 201420814946U CN 204368409 U CN204368409 U CN 204368409U
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Abstract
The utility model belongs to aviation field, relates to a kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing.Material Stiffened Panel comprises covering, plate-plate glued membrane, plate-core glued membrane, hat muscle, core and Zone R weighting material; Covering is arranged 1 laminate-plate glued membrane; Be wrapped in the outside face of core with 1 laminate-core glued membrane, and be evenly arranged on plate-plate glued membrane; Bottom core, Zone R fills Zone R weighting material; Plate-plate glued membrane, Zone R weighting material and plate-core glued membrane arranges hat muscle.The utility model proposes a kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing, its globality is better, without obvious covering/rib interface, reduce the probability of rib edge generation unsticking, define the integrated structure form that independently has carrying/posting, give full play of the advantage that Composite Material Stiffened Panel load performance is good.
Description
Technical field
The utility model belongs to aviation field, relates to a kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing.
Background technology
Altitude Long Endurance Unmanned Air Vehicle flying height is high, and cruise duration is long, and combat radius is large, and can perform the multiple-tasks such as global reconnaissance and surveillance, lasting permanent scouting, be the developing direction of long-range unmanned aerial vehicle.Due to the rigors of Altitude Long Endurance Unmanned Air Vehicle when voyage, boat and in economy, necessarily require wing area large, the span is wide, to guarantee having enough lift.Make a general survey of the Altitude Long Endurance Unmanned Air Vehicle of world advanced person, the maximum common ground of wing design adopts high aspect ratio wing, exactly as external unmanned plane " global hawk ".
A distinguishing feature in high aspect ratio wing design: root bending moment is large, wainscot pressurized is serious, and the stability problem of top airfoil root is given prominence to.For addressing this problem, a lot of high aspect ratio wing can select Composite Material Stiffened Panel version.Composite Material Stiffened Panel structure is the common version of present generation aircraft, and glueing joint shaping by covering and rib, is very important load-carrying construction.But traditional Composite Material Stiffened Panel structural integrity is not good enough, have obvious covering/rib interface, this interface is easy to first unsticking occur in rib edge, and then expands to whole covering/rib interface, cause the destruction of whole Composite Material Stiffened Panel, affect aircraft safety.Thus be difficult to give full play of the good advantage of Composite Material Stiffened Panel load performance.
Summary of the invention
The purpose of this utility model proposes a kind of advanced composite material hat Material Stiffened Panel being applicable to high aspect ratio wing, and its globality is better, and effectively can avoid obvious covering/rib interface.
Technical solution of the present utility model is, Material Stiffened Panel comprises covering 1, plate-plate glued membrane 201, plate-core glued membrane 202, hat muscle 3, core 4 and Zone R weighting material 5, and covering 1 is arranged 1 laminate-plate glued membrane 201; Be wrapped in the outside face of core 4 with 1 laminate-core glued membrane 202, and be evenly arranged on plate-plate glued membrane 201; Bottom core 4, Zone R fills Zone R weighting material 5; Plate-plate glued membrane 201, Zone R weighting material 5 and plate-core glued membrane 202 arranges hat muscle 3.
The material of described hat muscle 3 is identical with covering 1, and hat muscle 3 is different at the thickness of zones of different.
The two ends of described core 4 is provided with chamfered angle, angle of splaying 30 degree.
The advantage that the utility model has and beneficial effect are, the utility model proposes a kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing, its globality is better, without obvious covering/rib interface, reduce the probability of rib edge generation unsticking, define the integrated structure form that independently has carrying/posting, give full play of the advantage that Composite Material Stiffened Panel load performance is good.
The local of the composite material hat Material Stiffened Panel of the utility model design is similar to foamed sandwich structure, excellent in mechanical performance, compared with the Material Stiffened Panel of conventional non-foam core, the anti-unstability performance of hat rib sidewall is better, improves the load-carrying capacity of whole Material Stiffened Panel structure.
The composite material hat Material Stiffened Panel two ends of the utility model design adopts design of splaying, and actv. solves rigidity mutation problems, improves the boundary strength of end.
The composite material hat Material Stiffened Panel technique of the utility model design is simple, foam core is except can be used as structural unit carrying, also in laying process He in solidification process, play the effect of core, decreased the manufacturing cost of particular manufacturing craft, there is not solidification rear mold and extract difficult problem.For many ribs wallboard, laying method is still disposable laying, decreases operation and cost.
The composite material hat Material Stiffened Panel inside face of the utility model design is comparatively smooth and smooth, does not have violent abrupt changes in thickness, makes interior metal part (as metal ribs) design and manufaction simple, without the need to making specific downset areas.
Accompanying drawing explanation
Fig. 1 is chordwise section schematic diagram of the present utility model;
Fig. 2 is the utility model end regions schematic diagram.
Wherein, 1-covering, 201-plate-plate glued membrane, 202-plate-core glued membrane, 3-hat muscle, 4-core, 5-R district weighting material.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is described in further detail, refers to Fig. 1 to Fig. 2.
As shown in Figure 1, a kind of composite material hat Material Stiffened Panel for high aspect ratio wing, is characterized in that, comprises covering 1, plate-plate glued membrane 201, plate-core glued membrane 202, hat muscle 3, core 4 and Zone R weighting material 5.Covering 1 is arranged 1 laminate-plate glued membrane 201; Be wrapped in the outside face of core 4 with 1 laminate-core glued membrane 202, and be evenly arranged on plate-plate glued membrane 201; Bottom core 4, Zone R fills Zone R weighting material 5; Plate-plate glued membrane 201, Zone R weighting material 5 and plate-core glued membrane 202 arranges hat muscle 3.Its shaping scheme is: first separately solidify covering 1, and on covering 1 paving 1 laminate-plate glued membrane 201; Wrap up core 4 with 1 laminate-core glued membrane 202 subsequently, and be fixed on the plate-plate glued membrane 201 on covering 1 surface; Bottom core 4, Zone R fills Zone R weighting material 5 afterwards; Last laying goes out hat muscle 3, glueds joint co-curing shaping.
Preferably, described covering 1 adopts carbon fiber composite material T700/LT-03A laying to form, and thickness is 2mm, and laying angle is [45/0/-45/90/0/-45/0/45]
s, and according to the independent curing molding of T700/LT-03A forming requirements.
Preferably, described hat muscle 3 adopts and forms with carbon fiber composite material T700/LT-03A laying, the laying adopting different-thickness in zones of different is needed: foam core area thickness is 1mm, and laying angle is [-45/0/45/90/-45/0/45/0] according to intensity; General area thickness 0.5mm, laying angle is [-45/90/45/0].
Preferably, described core 4 selects the trade mark to be the PMI foam of ROHACELL 71 WF.
Preferably, described plate-plate glued membrane 201 and plate-core glued membrane 202 all select LWF-2B (δ 0.2), and this glued membrane is that white has carrier adhesive, can glued joint co-curing use for plate-plate, plate-foam core simultaneously.
Preferably, described Zone R weighting material 5 is made for carbon fiber composite material T700/LT-03A one-way tape wraps up 1 layer of LWF-2B (δ 0.2) glued membrane.
As shown in Figure 2, the composite material hat Material Stiffened Panel two ends of the utility model design adopts design of splaying, and angle of splaying 30 degree, actv. solves rigidity mutation problems, improves the boundary strength of end.
Claims (3)
1. one kind is applicable to the composite material hat Material Stiffened Panel of high aspect ratio wing, it is characterized in that, Material Stiffened Panel comprises covering (1), plate-plate glued membrane (201), plate-core glued membrane (202), hat muscle (3), core (4) and Zone R weighting material (5); At the upper layout 1 laminate-plate glued membrane (201) of covering (1); Be wrapped in the outside face of core (4) with 1 laminate-core glued membrane (202), and be evenly arranged on plate-plate glued membrane (201); Core (4) bottom Zone R fills Zone R weighting material (5); At plate-plate glued membrane (201), Zone R weighting material (5) and plate-core glued membrane (202) upper layout hat muscle (3).
2. a kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing according to claim 1, it is characterized in that, the material of described hat muscle (3) is identical with covering (1), and hat muscle (3) is different at the thickness of zones of different.
3. a kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing according to claim 1, it is characterized in that, the two ends of described core (4) is provided with chamfered angle, angle of splaying 30 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420814946.7U CN204368409U (en) | 2014-12-19 | 2014-12-19 | A kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420814946.7U CN204368409U (en) | 2014-12-19 | 2014-12-19 | A kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204368409U true CN204368409U (en) | 2015-06-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420814946.7U Active CN204368409U (en) | 2014-12-19 | 2014-12-19 | A kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing |
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| CN (1) | CN204368409U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106564198A (en) * | 2015-10-10 | 2017-04-19 | 陕西飞机工业（集团）有限公司 | Method for bonding foam layer and aluminum alloy skin |
| CN107471687A (en) * | 2017-07-04 | 2017-12-15 | 西安飞机工业（集团）有限责任公司 | The fill method of Zone R in a kind of composite liquid shaping |
| CN108216570A (en) * | 2017-12-14 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of high aspect ratio wing main plane structure |
| CN109018437A (en) * | 2018-06-21 | 2018-12-18 | 北京空间飞行器总体设计部 | A kind of deck board suitable for space capsule |
| CN109551830A (en) * | 2018-11-07 | 2019-04-02 | 中国航空工业集团公司西安飞机设计研究所 | Composite Panels |
| CN112407234A (en) * | 2020-11-19 | 2021-02-26 | 航天彩虹无人机股份有限公司 | Skin for sensor unmanned aerial vehicle wing and manufacturing method thereof |
| CN112571815A (en) * | 2020-10-29 | 2021-03-30 | 成都飞机工业（集团）有限责任公司 | Rib positioning method of reinforced wall plate |
| CN112849392A (en) * | 2020-12-21 | 2021-05-28 | 中国航天空气动力技术研究院 | Solar airplane light rectifying structure and preparation method thereof |
| CN115302814A (en) * | 2022-10-09 | 2022-11-08 | 成都泰格尔航天航空科技股份有限公司 | Forming method of cap-shaped reinforced wall plate of high-aspect-ratio wing |
-
2014
- 2014-12-19 CN CN201420814946.7U patent/CN204368409U/en active Active
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106564198A (en) * | 2015-10-10 | 2017-04-19 | 陕西飞机工业（集团）有限公司 | Method for bonding foam layer and aluminum alloy skin |
| CN107471687A (en) * | 2017-07-04 | 2017-12-15 | 西安飞机工业（集团）有限责任公司 | The fill method of Zone R in a kind of composite liquid shaping |
| CN108216570A (en) * | 2017-12-14 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of high aspect ratio wing main plane structure |
| CN108216570B (en) * | 2017-12-14 | 2023-08-18 | 中航(成都)无人机系统股份有限公司 | Main wing surface structure of high aspect ratio wing |
| CN109018437A (en) * | 2018-06-21 | 2018-12-18 | 北京空间飞行器总体设计部 | A kind of deck board suitable for space capsule |
| CN109018437B (en) * | 2018-06-21 | 2020-06-05 | 北京空间飞行器总体设计部 | Cabin plate suitable for spacecraft sealed cabin |
| CN109551830A (en) * | 2018-11-07 | 2019-04-02 | 中国航空工业集团公司西安飞机设计研究所 | Composite Panels |
| CN112571815A (en) * | 2020-10-29 | 2021-03-30 | 成都飞机工业（集团）有限责任公司 | Rib positioning method of reinforced wall plate |
| CN112571815B (en) * | 2020-10-29 | 2022-06-14 | 成都飞机工业（集团）有限责任公司 | Rib positioning method of reinforced wall plate |
| CN112407234A (en) * | 2020-11-19 | 2021-02-26 | 航天彩虹无人机股份有限公司 | Skin for sensor unmanned aerial vehicle wing and manufacturing method thereof |
| CN112849392A (en) * | 2020-12-21 | 2021-05-28 | 中国航天空气动力技术研究院 | Solar airplane light rectifying structure and preparation method thereof |
| CN115302814A (en) * | 2022-10-09 | 2022-11-08 | 成都泰格尔航天航空科技股份有限公司 | Forming method of cap-shaped reinforced wall plate of high-aspect-ratio wing |
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| C14 | Grant of patent or utility model | ||
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| CP01 | Change in the name or title of a patent holder | ||
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Address after: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee after: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute Address before: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee before: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute |