CN207045685U - A kind of lightweight airfoil structure - Google Patents
A kind of lightweight airfoil structure Download PDFInfo
- Publication number
- CN207045685U CN207045685U CN201720314979.9U CN201720314979U CN207045685U CN 207045685 U CN207045685 U CN 207045685U CN 201720314979 U CN201720314979 U CN 201720314979U CN 207045685 U CN207045685 U CN 207045685U
- Authority
- CN
- China
- Prior art keywords
- supporting member
- flexible covering
- covering
- airfoil structure
- lightweight
- 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
Landscapes
- Laminated Bodies (AREA)
Abstract
A kind of lightweight airfoil structure is the utility model is related to, it includes：Supporting member, supporting member section are streamlined；And flexible covering, the quantity of the flexible covering is multilayer, and flexible covering described in multilayer is pasted and fixed on the surface of the supporting member；The supporting member and flexible covering are low density material support.Lightweight airfoil structure of the present utility model is using the light-weighted supporting member of hard as support, the light-weighted flexible covering of multilayer is laid in supporting member outer surface, can effectively solve the breakage of outer layer metal covering and then cause the situation of composite skin content broken, in addition, it is also possible that the streamlined curved surface four corner of wing has stronger anti-extrusion (air pressure) ability, improve the intensity of wing, mitigate weight.
Description
Technical field
The invention belongs to aircraft systems design field, more particularly to a kind of lightweight airfoil structure.
Background technology
Wing is one of important component of aircraft, and on fuselage, its main effect is to produce lift.Wing is general
It is made up of the covering and inner frame on surface.The basic role of wing structure is to form the streamline profile of wing, while by external applied load
It is transmitted to fuselage.Wing should have enough intensity, rigidity and life-span under external load function, and enough rigidity had both referred to covering in gas
The ability of air foil shape is kept under dynamic load effect, the ability with flexural deformation is also reversed comprising wing resistance.
For existing wing structure as shown in figure 1, it is made up of covering 100 and skeleton 200, skeleton 200 generally comprises transverse direction
Skeleton and longitudinal framework, the skeleton 200 shown in figure are not drawn into horizontal skeleton.Covering 100 is fixed by rivet and skeleton 200
Form fairshaped section.In order to mitigate the weight of aircraft wing mechanism, existing covering 100 employs light-weight design, such as
By the way of metal skin interlayer lightweighting materials, referring to two kinds of structures of covering 100 shown in Fig. 2 and Fig. 3.In Fig. 2 and Fig. 3
In two kinds of shown structures of covering 100, covering 100 is by double layer of metal covering 101 and the structure of holding sheet 102 of lightweighting materials
Into, unlike in covering 100 in fig. 2 holding sheet 102 be solid sponge or plastics etc., and in the covering 100 shown in Fig. 3
In, holding sheet 102 is hollow alveolate texture, but metal skin 101 is generally made of aluminum alloy materials.
But above-mentioned wing structure still has following problem：
1) for the wing shown in Fig. 1, there is preferable intensity in the part that skeleton 200 is supported in covering 100, still
Then there is the problem of intensity is weaker in the overhanging portion between two adjacent skeletons 200, when pneumatic press is larger, easily
Collapsing for covering 100 is caused, and then influences aircraft safety；
2) for the covering 100 shown in Fig. 2 or Fig. 3, it is made as a result of double layer of metal material, when outer layer metal covers
After skin 101 is corroded due to damage or environment reason, holding sheet 102 and the metal skin 101 in nexine are easily made
Into accelerating to damage, cause covering 100 can not provide aerodynamic force.
Utility model content
It is an object of the invention to provide a kind of lightweight wing structure, for solving any of the above-described problem.
To reach above-mentioned purpose, the technical solution adopted by the present invention is：A kind of lightweight airfoil structure, it includes：Support
Component, supporting member section are streamlined；It is flexible described in multilayer and flexible covering, the quantity of the flexible covering are multilayer
Covering is pasted and fixed on the surface of the supporting member；The supporting member and flexible covering are that low density material is made.
According to one preferred embodiment of the present invention, the density of the supporting member and flexible covering is less than or equal to 2g/
cm3。
According to one preferred embodiment of the present invention, supporting member is hard foam.
According to one preferred embodiment of the present invention, the flexible covering is carbon fibre material.
According to one preferred embodiment of the present invention, the thickness of the flexible covering is 1mm to 2mm.
According to one preferred embodiment of the present invention, flexible covering is at least 5 layers to 10 layers.
According to one preferred embodiment of the present invention, in addition to multiple support bars, the support bar pass through the support structure
Part is connected with flexible covering.
The lightweight airfoil structure of the present invention is used as support using the light-weighted supporting member of hard, in supporting member appearance
The light-weighted flexible covering of multilayer is laid in face, can effectively be solved the breakage of outer layer metal covering and then be caused inside composite skin
Damaged situation, in addition to this it is possible to which so that the streamlined curved surface four corner of wing has stronger anti-extrusion (air pressure) energy
Power, improve the intensity of wing, mitigate weight.
Brief description of the drawings
Accompanying drawing herein is merged in specification and forms the part of this specification, shows the implementation for meeting the present invention
Example, and for explaining principle of the invention together with specification.
Fig. 1 is the wing structure schematic diagram of prior art.
Fig. 2 is a kind of composite skin schematic diagram of prior art.
Fig. 3 is another composite skin schematic diagram of prior art.
Fig. 4 is the vertical cross section of the lightweight wing structure of one embodiment of the invention.
Fig. 5 is the horizontal sectional drawing of the lightweight wing structure of one embodiment of the invention
Reference：
100- coverings, 101- metal skins, 102- holding sheets, 200- skeletons；1- supporting members, 2- flexible coverings, 3- branch
Strut.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.
The vertical sectional view of the lightweight wing structure of the present invention is illustrated in figure 4, in the lightweight aerofoil profile knot of the present invention
In structure, it includes：
Supporting member 1, the section of supporting member 1 is streamlined, and itself and conventional wing structure have same or like
Cross-section, the present invention accompanying drawing shown in section be upper surface be arc, lower surface be linear configuration；It is and soft
Property covering 2, the quantity of the flexible covering 2 is multilayer, and the flexible covering 2 of multilayer pastes or the cementing supporting member 1 that is fixed on
Surface, including upper and lower surface；Supporting member 1 and flexible covering 2 are that low density material is made.Pass through the branch of low-density
The wing structure that support component 1 and flexible covering 2 are formed has light weight, and has preferable structural strength, can meet nobody
The requirement of machine light load.It should be noted that lightweight airfoil structure and unmanned aerial vehicle body junction, strong in order to reach
The requirement of degree, it should be attached using metal structure.
One embodiment of the present invention, lightweight that supporting member 1 and flexible covering 2 are selected, low density material
Density is less than or equal to 2g/cm3, because the density of aluminum alloy materials is less times greater than 2g/cm3If therefore from more than this value range
Material does not have light-weighted purpose then.
In the present invention, supporting member 1 is in material selection, in addition to the density issue of material to be considered, it is also necessary to examine
Consider supporting construction 1 and want role, supporting construction 1 needs to play a supporting role to flexible covering 2, therefore its will have compared with
Good rigidity or hardness, therefore in a preferred embodiment of the invention, what supporting member 1 was selected is hard foam, hard bubble
Foam can meet supporting member 1 in hardness and quality double requirements.
In the present invention, because flexible covering 2 instead of traditional aluminum covering, therefore flexible covering 2 needs enough
Good intensity, therefore in one embodiment of the present invention, the flexible covering is carbon fibre material, and carbon fibre material has
Preferable intensity and superior light weight characteristic.After changing flexible covering 2 into carbon fibre materials by aluminum metal material, can solve
The shortcomings that traditional composite intermediate layer covering, i.e., when traditional composite intermediate layer outer side metal skin damage or after come off, folder
Hold layer 102 and nexine metal skin easily causes the situation for accelerating damage, and in the present invention, because flexible covering 2 is multilayer,
Even if outermost flexible covering 2 damages, the flexible covering 2 of the second layer still with preferable intensity and provides protective action.
In a preferred embodiment of the invention, flexible covering 2 is at least 5 layers to 10 layers, why selects above-mentioned numeral to be
Because when the thickness of the flexible covering 2 used is 1mm to 2mm, the flexible covering 2 less than 5 layers can cause wing overall structure
Intensity decreases, and can then increase process time and cost etc. higher than 10 layers.It should be noted that in order to improve layer flexible covering
2 intensity, the bonding when flexible covering 2 is pasted and is fixed on supporting member 1 and between layer flexible covering 2, is used
The mode that vacuum is pasted.
In addition, in a preferred embodiment of the invention, lightweight wing structure also includes multiple support bars 3, as shown in Figure 5
The horizontal sectional drawing of lightweight wing structure as of the invention, from the figure, it can be seen that support bar 3 through supporting member 1 it
It is connected afterwards with flexible covering 2.Support bar 3 can be that flexible covering 2 provides extra support force, to prevent wing relatively strong pneumatic
It is deformed and damages under pressure.In the accompanying drawing of the present invention, multiple support bars 3 are well-regulated interspersed to be distributed in supporting member 1
It is interior.Preferably, support bar 3 is also made of nonmetallic light material.
The lightweight airfoil structure of the present invention is used as support using the light-weighted supporting member of hard, in supporting member appearance
The light-weighted flexible covering of multilayer is laid in face, can effectively be solved the breakage of outer layer metal covering and then be caused inside composite skin
Damaged situation, in addition to this it is possible to which so that the streamlined curved surface four corner of wing has stronger anti-extrusion (air pressure) energy
Power, improve the intensity of wing, mitigate weight.
It is described above, it is only the optimal embodiment of the present invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art the invention discloses technical scope in, the change or replacement that can readily occur in,
It should all be included within the scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Enclose and be defined.
Claims (7)
1. a kind of lightweight airfoil structure, it is characterised in that the lightweight airfoil structure includes
Supporting member (1), supporting member (1) section are streamlined；And
Flexible covering (2), the quantity of the flexible covering (2) is multilayer, and flexible covering (2) described in multilayer is pasted and fixed on described
The surface of supporting member (1)；
The supporting member (1) and flexible covering (2) are that low density material is made.
2. lightweight airfoil structure according to claim 1, it is characterised in that the supporting member (1) and flexible covering
(2) density is less than or equal to 2g/cm3。
3. lightweight airfoil structure according to claim 2, it is characterised in that supporting member (1) is hard foam.
4. lightweight airfoil structure according to claim 2, it is characterised in that the flexible covering (2) is carbon fiber material
Material.
5. lightweight airfoil structure according to claim 4, it is characterised in that the thickness of the flexible covering (2) is 1mm
To 2mm.
6. lightweight airfoil structure according to claim 5, it is characterised in that flexible covering (2) is at least 5 layers to 10
Layer.
7. lightweight airfoil structure according to claim 1, it is characterised in that also including multiple support bars (3), the branch
Strut (3) is connected through the supporting member (1) with flexible covering (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720314979.9U CN207045685U (en) | 2017-03-29 | 2017-03-29 | A kind of lightweight airfoil structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720314979.9U CN207045685U (en) | 2017-03-29 | 2017-03-29 | A kind of lightweight airfoil structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207045685U true CN207045685U (en) | 2018-02-27 |
Family
ID=61488382
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720314979.9U Active CN207045685U (en) | 2017-03-29 | 2017-03-29 | A kind of lightweight airfoil structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207045685U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108583931A (en) * | 2018-05-21 | 2018-09-28 | 北京正兴弘业科技有限公司 | A kind of small and medium size unmanned aerial vehicles Advanced Manufacturing Technology |
-
2017
- 2017-03-29 CN CN201720314979.9U patent/CN207045685U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108583931A (en) * | 2018-05-21 | 2018-09-28 | 北京正兴弘业科技有限公司 | A kind of small and medium size unmanned aerial vehicles Advanced Manufacturing Technology |
| CN108583931B (en) * | 2018-05-21 | 2020-11-03 | 沈观清 | Advanced manufacturing process for small and medium-sized unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8226870B2 (en) | Pressure bulkhead made of composite material for an aircraft | |
| CN101801783B (en) | Pressure bulkhead and method for subdivision of an aircraft or spacecraft | |
| CN101652240B (en) | Method for hybrid composite panel systems | |
| AU2014200352B2 (en) | Composite laminated plate having reduced crossply angle | |
| US8490920B2 (en) | Composite bulkhead and skin construction | |
| CN107571985A (en) | A kind of ultralight whole wing structure of truss-like | |
| EP2117814B1 (en) | Shell element as part of an aircraft fuselage | |
| US20080283664A1 (en) | Aircraft Fuselage Structure | |
| RU2523726C2 (en) | Aerodynamic structure having airfoil, with corrugated reinforcing element | |
| US7753313B1 (en) | Composite wing slat for aircraft | |
| CN102227557B (en) | Wind wheel blade and wind-driven electricity generation device using same | |
| JP2014500172A5 (en) | ||
| CA2628585A1 (en) | Weight optimized pressurizable aircraft fuselage structures having near elliptical cross sections | |
| CN105398563A (en) | Wing of membrane structure | |
| WO2004014726A1 (en) | Composite tail cone assembly for a helicopter | |
| CN105508142A (en) | Multi-girder structure large size wind power blade and production method thereof | |
| CN106167085B (en) | For airframe pressure bulkhead and include the aircraft of this pressure bulkhead | |
| RU2009124189A (en) | FUSELAGE OF A PLANE OR SPACE AIRCRAFT FROM A HYBRID DESIGN OF CARBON PLASTIC / METAL WITH METAL FRAME | |
| CA2473346A1 (en) | Lightweight structure particularly for aircraft | |
| CN210479007U (en) | Light wing of small unmanned aerial vehicle | |
| CA2649339A1 (en) | Fuselage structure and method for the production of a fuselage structure | |
| CN205417779U (en) | Combined material passenger train roof | |
| CN207045685U (en) | A kind of lightweight airfoil structure | |
| CN101242991A (en) | Framework wing box for a wing | |
| CN106507756B (en) | High-strength light unmanned plane vertical fin |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |