CN205440845U - Flexible skin subassembly - Google Patents
Flexible skin subassembly Download PDFInfo
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- CN205440845U CN205440845U CN201620181696.7U CN201620181696U CN205440845U CN 205440845 U CN205440845 U CN 205440845U CN 201620181696 U CN201620181696 U CN 201620181696U CN 205440845 U CN205440845 U CN 205440845U
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- flexible covering
- ring bodies
- covering assembly
- rod
- embedded skeleton
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Abstract
The utility model discloses a flexible skin subassembly. Flexible skin subassembly includes embedded skeleton and covering, the covering parcel embedded skeleton, embedded skeleton includes the basic unit of the embedded skeleton of a plurality of flexible skin, the elastic support structure is formed to the basic unit of the embedded skeleton of each flexible skin, the elastic support structure is used for elastic support the external applied load that flexible skin subassembly received. Adopt that this kind of flexible skin subassembly that the structure formed has that with low costs, in -plane deformation volume is big, intensity and the big advantage of rigidity.
Description
Technical field
This utility model relates to aircraft flexible covering technical field, is specifically related to a kind of flexible covering assembly.
Background technology
Flexible covering technology and product are one of the key elements that cannot walk around of variant aircraft development, and currently, both at home and abroad in flexible covering field, the flexible covering of study hotspot mainly has three classes: (1) eyelid covering based on flexible honeycomb；(2) eyelid covering based on corrugated plating；(3) eyelid covering based on macromolecular compound.
The shortcoming that above-mentioned three class flexible coverings are respectively provided with himself.Such as: first kind flexible covering manufacturing process is complicated, cost is high, is additionally, since by rubber bearing plane internal load, causes bearing capacity low；Equations of The Second Kind flexible covering mechanical characteristic is poor, and in-plane deformation amount is smaller；3rd class flexible covering strength and stiffness characteristic is poor, on the one hand, in face, bearing capacity is smaller, and on the other hand, normal stiffness is the biggest, particularly, can not carry this feature during alteration of form, significantly limit its range of application on variant aircraft.
Thus, it is desirable to have a kind of technical scheme overcomes or at least alleviates at least one the problems referred to above of prior art.
Utility model content
The purpose of this utility model is to provide a kind of flexible covering assembly overcome or at least alleviate at least one the problems referred to above of the prior art.
For achieving the above object, this utility model provides a kind of flexible covering assembly, described flexible covering assembly includes embedded skeleton and eyelid covering, described eyelid covering wraps up described embedded skeleton, described embedded skeleton includes the base unit of the embedded skeleton of multiple flexible covering, the base unit composition elastic support structure of the described embedded skeleton of each flexible covering, described elastic support structure is for flexibly supporting the external applied load suffered by described flexible covering assembly.
Preferably, the base unit of the embedded skeleton of described flexible covering includes ring bodies and rod-like structure, and wherein, described rod-like structure is tangent with the curved section of ring bodies.
Preferably, described rod-like structure is tangent with described ring bodies periphery.
Preferably, the quantity of described rod-like structure is two, and described two rod-like structure are tangent with described ring bodies periphery respectively, thus form inscribe body or circumscribed body.
Preferably, described ring bodies is Wrapping formed along himself axial direction.
Preferably, described ring bodies is Wrapping formed along himself circumferential direction.
Preferably, described ring bodies is circular annuli, elliptical annular body, square ring body.
Preferably, described ring bodies and described rod-like structure use spring steel material to make.
Preferably, described ring bodies includes closed ring bodies, open ring bodies and half-annuli.
Preferably, described flexible covering assembly is used for aircraft.
Flexible covering assembly low cost of the present utility model, load is good, stable performance.
Accompanying drawing explanation
Fig. 1 is the structural representation of the base unit of the embedded skeleton of flexible covering in the flexible covering assembly according to this utility model first embodiment.
Reference:
| 1 | Ring bodies | 2 | Rod-like structure |
Detailed description of the invention
Clearer for the purpose making this utility model implement, technical scheme and advantage, below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is further described in more detail.In the accompanying drawings, the most same or similar label represents same or similar element or has the element of same or like function.Described embodiment is a part of embodiment of this utility model rather than whole embodiments.The embodiment described below with reference to accompanying drawing is exemplary, it is intended to be used for explaining this utility model, and it is not intended that to restriction of the present utility model.Based on the embodiment in this utility model, the every other embodiment that those of ordinary skill in the art are obtained under not making creative work premise, broadly fall into the scope of this utility model protection.Below in conjunction with the accompanying drawings embodiment of the present utility model is described in detail.
In description of the present utility model, it will be appreciated that, term " " center ", " longitudinally ", " laterally ", " front ", " afterwards ", " left ", " right ", " vertically ", " level ", " push up ", " end " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, it is for only for ease of description this utility model and simplifies description, rather than indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that restriction to this utility model protection domain.
Fig. 1 is the structural representation of the base unit of the embedded skeleton of flexible covering in the flexible covering assembly according to this utility model first embodiment.
Flexible covering assembly as shown in Figure 1 includes embedded skeleton and eyelid covering, eyelid covering wraps up embedded skeleton, embedded skeleton includes the base unit of the embedded skeleton of multiple flexible covering, the base unit composition elastic support structure of the embedded skeleton of each flexible covering, elastic support structure is for flexibly supporting the external applied load suffered by flexible covering assembly.
The flexible covering assembly using this structure to be formed has that low cost, in-plane deformation amount be big, intensity and the big advantage of rigidity.
Seeing Fig. 1, in the present embodiment, the base unit of the embedded skeleton of flexible covering includes ring bodies 1 and rod-like structure 2, and wherein, rod-like structure 2 is tangent with the curved section of ring bodies.
In the present embodiment, rod-like structure 2 is tangent with ring bodies 1 periphery.
Seeing Fig. 1, in the present embodiment, the quantity of rod-like structure 2 is two, and two rod-like structure 2 are tangent with ring bodies periphery respectively, thus form inscribe body or circumscribed body.
In an alternative embodiment, ring bodies 1 is Wrapping formed along himself axial direction.Thus increase its axial strength.
It is understood that in another alternative, ring bodies 1 is Wrapping formed along himself circumferential direction.Thus increase its circumferential strength.
It is understood that ring bodies 1 can be arbitrary shape, such as, ring bodies is circular annuli, elliptical annular body, square ring body.
In the present embodiment, ring bodies 1 uses spring steel material to make with rod-like structure 2.
It is understood that ring bodies 1 includes closed ring bodies, open ring bodies and half-annuli.For example, closed ring bodies be any point on this ring bodies i.e. as the starting point of this ring bodies, also serve as the terminal after ring bodies one week.Open ring status be any point on this ring bodies i.e. as the starting point of this shape body, and behind a week of this ring bodies, have another some terminal as this ring bodies.
Half-annuli is, any point of this ring bodies is as starting point, and another point that its straight line crossing the center of circle is connected is as terminal, and 2 arc length formed are this ring bodies half as arc length during full circle.
Advantageously, the flexible covering assembly in the present embodiment is used for aircraft.
Last it is noted that above example is only in order to illustrate the technical solution of the utility model, it is not intended to limit.Although this utility model being described in detail with reference to previous embodiment, it will be understood by those within the art that: the technical scheme described in foregoing embodiments still can be modified by it, or wherein portion of techniques feature is carried out equivalent；And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of this utility model each embodiment technical scheme.
Claims (10)
1. a flexible covering assembly, it is characterized in that, described flexible covering assembly includes embedded skeleton and eyelid covering, described eyelid covering wraps up described embedded skeleton, described embedded skeleton includes the base unit of the embedded skeleton of multiple flexible covering, the base unit composition elastic support structure of the described embedded skeleton of each flexible covering, described elastic support structure is for flexibly supporting the external applied load suffered by described flexible covering assembly.
2. flexible covering assembly as claimed in claim 1, it is characterized in that, the base unit of the embedded skeleton of described flexible covering includes ring bodies (1) and rod-like structure (2), and wherein, described rod-like structure (2) is tangent with the curved section of ring bodies.
3. flexible covering assembly as claimed in claim 2, it is characterised in that described rod-like structure (2) is tangent with described ring bodies (1) periphery.
4. flexible covering assembly as claimed in claim 3, it is characterised in that the quantity of described rod-like structure (2) is two, and described two rod-like structure (2) are tangent with described ring bodies periphery respectively, thus form inscribe body or circumscribed body.
5. flexible covering assembly as claimed in claim 2, it is characterised in that described ring bodies (1) is Wrapping formed along himself axial direction.
6. flexible covering assembly as claimed in claim 2, it is characterised in that described ring bodies (1) is Wrapping formed along himself circumferential direction.
7. flexible covering assembly as claimed in claim 2, it is characterised in that described ring bodies (1) is circular annuli, elliptical annular body, square ring body.
8. flexible covering assembly as claimed in claim 2, it is characterised in that described ring bodies (1) and described rod-like structure (2) use spring steel material to make.
9. flexible covering assembly as claimed in claim 2, it is characterised in that described ring bodies (1) includes closed ring bodies, open ring bodies and half-annuli.
10. flexible covering assembly as claimed in claim 1, it is characterised in that described flexible covering assembly is used for aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620181696.7U CN205440845U (en) | 2016-03-09 | 2016-03-09 | Flexible skin subassembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620181696.7U CN205440845U (en) | 2016-03-09 | 2016-03-09 | Flexible skin subassembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205440845U true CN205440845U (en) | 2016-08-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620181696.7U Active CN205440845U (en) | 2016-03-09 | 2016-03-09 | Flexible skin subassembly |
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| CN (1) | CN205440845U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106425309A (en) * | 2016-11-14 | 2017-02-22 | 北京星航机电装备有限公司 | Method for machining and manufacturing titanium alloy folding airfoils |
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2016
- 2016-03-09 CN CN201620181696.7U patent/CN205440845U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106425309A (en) * | 2016-11-14 | 2017-02-22 | 北京星航机电装备有限公司 | Method for machining and manufacturing titanium alloy folding airfoils |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |