CN111319752A - Sliding type flexible composite material skin based on corrugated structure - Google Patents
Sliding type flexible composite material skin based on corrugated structure Download PDFInfo
- Publication number
- CN111319752A CN111319752A CN202010180768.7A CN202010180768A CN111319752A CN 111319752 A CN111319752 A CN 111319752A CN 202010180768 A CN202010180768 A CN 202010180768A CN 111319752 A CN111319752 A CN 111319752A
- Authority
- CN
- China
- Prior art keywords
- composite material
- fiber
- composite
- corrugated
- sheet
- 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.)
- Granted
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
A sliding flexible composite material skin based on a corrugated structure is composed of a composite material corrugated plate, a composite material thin plate and an elastomer layer. The connection relationship is as follows: the composite material sheet is adhered to the horizontal adhesive surface of the composite material corrugated plate, the left side of the composite material sheet is adhered to the horizontal adhesive surface at the wave crest, the composite material sheet is overlapped on the composite material sheet at the adjacent wave crest at the right side, and the elastomer layer is tightly adhered to the composite material sheet. The composite material corrugated plate has the characteristics of high rigidity in the corrugation direction and high external rigidity of the composite material sheet, can realize a large deformation function, can resist external pneumatic load, has the advantages of simple structure and light weight, and is a practical and feasible variant wing flexible skin scheme.
Description
Technical Field
The invention provides a sliding type flexible composite material skin based on a corrugated structure, and belongs to the field of composite material structure design.
Technical Field
In the field of aviation, a "morphing aircraft" is an aircraft that can achieve enhanced performance within a mission profile by changing its geometry, with the most critical technology being morphing wings. Morphing wings require a flexible skin that can both perform the function of large deformations in-plane, and also have sufficient out-of-plane stiffness to withstand aerodynamic loads. Currently, there are a variety of materials or structures that may be used for the flexible skin of a morphing aircraft, including shape memory alloys, honeycomb structures, telescoping structures, etc., but these structures are difficult to meet in terms of weight, structural complexity, or maintaining a smooth aerodynamic surface. Therefore, the invention provides a sliding type flexible composite material skin based on a corrugated structure, which consists of a composite material corrugated plate, a composite material thin plate and an elastomer layer, has the capability of bending deformation and tensile deformation in the corrugated direction, has enough out-of-plane rigidity to resist aerodynamic load, can maintain a smooth aerodynamic surface, has the advantages of simple structure, light structural weight and the like, and is suitable for being used as the flexible skin of the wing of a morphing aircraft.
Disclosure of Invention
1. The purpose is as follows: the invention aims to provide a sliding type flexible composite material skin based on a corrugated structure, which can realize a large deformation function, has certain out-of-plane rigidity and can maintain a smooth aerodynamic surface.
2. The technical scheme is as follows: the invention is composed of a composite corrugated plate, a composite thin plate and an elastomer layer. Their connection relationship is as follows: (1) the cross section contour line of the composite material corrugated plate is continuous corrugation, and a horizontal gluing surface with a certain length is arranged at each wave crest and is used for gluing with the composite material thin plate; (2) the length of the composite material sheet is slightly longer than one wavelength, the left side of the composite material sheet is glued to the horizontal gluing surface at the wave crest and is lapped on the composite material sheet at the adjacent wave crest at the right side, and the upper surfaces of all the composite material sheets are positioned on the same plane; (3) the elastomer layer is closely attached to the composite sheet. The composite material corrugated plate structure has larger deformability in the corrugation direction, and when a certain tensile force is applied in the corrugation direction, the composite material corrugated plate can generate large deformation in the corrugation direction; in the deformation process of the composite corrugated plate, the composite thin plate glued on each gluing surface translates along with the composite corrugated plate, the grooves between adjacent wave crests can be covered by the composite thin plate all the time, and the composite thin plate has large out-of-plane rigidity, so the structure has the capability of resisting pneumatic load; the elastomer layer has high elasticity and a smooth surface, and the whole sliding type flexible composite material skin based on the corrugated structure can have a smooth pneumatic surface by covering the composite material sheet.
The composite corrugated plate is a unidirectional belt laminated corrugated plate made of carbon fibers, glass fibers, Kevlar fibers and boron fibers, and a woven material corrugated plate made of the carbon fibers, the glass fibers, the Kevlar fibers and the boron fibers.
The elastomer layer is made of silicon rubber, nitrile rubber, fiber reinforced silicon rubber, fiber reinforced nitrile rubber, piezoelectric fiber silicon rubber composite material and piezoelectric fiber nitrile rubber composite material.
3. The advantages and the effects are as follows: the invention relates to a sliding type flexible composite material skin based on a corrugated structure, which can realize a large deformation function along the corrugated direction by reasonably and skillfully assembling a composite material corrugated plate, a composite material thin plate and an elastomer layer, has certain out-of-plane rigidity and smooth pneumatic surface, has the advantages of simple structure and light weight, and is a practical and feasible scheme of the variant wing flexible skin.
Drawings
Fig. 1 is a front view schematically showing a composite material corrugated plate in an initial state. In fig. 1: the parts 1, 2, 3 and 4 are all glued surfaces.
Fig. 2 is a schematic front view of a composite corrugated board in a stretched state.
Figure 3 is a schematic front view of a sliding flexible composite skin based on a corrugated structure in an initial state. In fig. 3: the parts 5, 6, 7, 8 are all composite material sheets, and the part 9 is an elastomer layer.
Figure 4 is a side view schematic of a slip-on flexible composite skin based on a corrugated structure in an initial state.
Figure 5 is a schematic front view of a slip-on flexible composite skin based on a corrugated structure in a stretched state.
Figure 6 is a side view schematic of a slip-on flexible composite skin based on a corrugated structure in a stretched state.
Detailed Description
The invention is further described below with reference to the drawings and the examples.
The sliding type flexible composite material skin with the large deformation function and based on the corrugated structure comprises a composite material corrugated plate, a composite material thin plate and an elastic bodyAnd (3) layer composition. The cross-sectional shape of the composite material corrugated plate (as shown in figure 1) is continuous
The wave crest is provided with a glue joint surface 1, a glue joint surface 2, a glue joint surface 3 and a glue joint surface 4, wherein the composite corrugated plate is a unidirectional tape laminated corrugated plate made of carbon fibers, glass fibers, Kevlar fibers and boron fibers, and a woven corrugated plate made of the carbon fibers, the glass fibers, the Kevlar fibers and the boron fibers. The composite corrugated plate has large deformation capacity along the corrugation direction, and when a certain tensile force is applied to two ends of the composite corrugated plate, the composite corrugated plate is subjected to large deformation (as shown in figure 2). The length of the composite material sheet is slightly longer than one wavelength, the left part of the composite material sheet is glued on the glued joint surface at the wave crest and is overlapped on the composite material sheet at the adjacent wave crest at the right side, for example, the composite material sheet 5, the composite material sheet 6, the composite material sheet 7 and the composite material sheet 8 are respectively glued on the glued joint surface 1, the glued joint surface 2, the glued joint surface 3 and the glued joint surface 4 (as shown in fig. 3) and are overlapped on the composite material sheet at the adjacent wave crest at the right side. The elastomer layer 9 is covered on the composite material sheet, wherein the elastomer layer is made of silicon rubber, nitrile rubber, fiber reinforced silicon rubber, fiber reinforced nitrile rubber, piezoelectric fiber silicon rubber composite material and piezoelectric fiber nitrile rubber composite material. The composite corrugated plate, the composite thin plate and the elastomer layer form a sliding type flexible composite skin based on a corrugated structure and having a large deformation function.
Fig. 3 and 4 are a schematic front view and a schematic side view of a sliding flexible composite skin based on a corrugated structure in an initial state, respectively. The composite corrugated plate structure has larger deformation capacity in the corrugation direction, and when a certain tensile force is applied in the corrugation direction, the composite corrugated plate can generate large deformation in the corrugation direction (as shown in fig. 5 and 6); in the deformation process of the composite corrugated plate, the composite thin plate glued on each gluing surface can move horizontally, but the grooves between the adjacent wave crests of the composite corrugated plate can be still covered by the composite thin plates on the gluing surfaces of the two wave crests, and the structure has the capability of resisting pneumatic load because the composite thin plates have large out-of-plane rigidity; the elastomer layer has high elasticity and a smooth surface, and the whole sliding type flexible composite material skin based on the corrugated structure can have a smooth pneumatic surface by covering the composite material sheet.
Claims (4)
1. A sliding flexible composite material skin based on a corrugated structure is composed of a composite material corrugated plate, a composite material thin plate and an elastomer layer. Their connection relationship is as follows: (1) the cross section contour line of the composite material corrugated plate is continuous corrugation, and a horizontal gluing surface with a certain length is arranged at each wave crest and is used for being connected with the composite material thin plate; (2) the length of the composite material thin plate is slightly longer than one wavelength, the left side of the composite material thin plate is glued to the horizontal gluing surface at the wave crest and is lapped on the composite material thin plate at the adjacent wave crest at the right side, and the upper surfaces of all the composite material thin plates are positioned on the same plane; (3) the elastomer layer is closely attached to the composite sheet. The composite corrugated plate has large deformation capacity, and the composite sheet has large out-of-plane rigidity, so the sliding flexible composite skin based on the corrugated structure has large deformation capacity and resists aerodynamic load.
2. The composite corrugated board of claim 1 is a unidirectional tape laminated corrugated board made of carbon fiber, glass fiber, Kevlar fiber and boron fiber, and a braided corrugated board made of carbon fiber, glass fiber, Kevlar fiber and boron fiber.
3. The composite sheet of claim 1 is a unidirectional tape laminate sheet made of carbon fiber, glass fiber, Kevlar fiber and boron fiber, and a woven material sheet made of carbon fiber, glass fiber, Kevlar fiber and boron fiber. The cross section of the composite material sheet is in the shape of
The lower surface of the left short side of the composite material thin plate is glued to the horizontal gluing surface of the composite material corrugated plateOn, the long limit in composite material sheet right side is lapped on the composite material sheet of the adjacent crest department in right side, and the length of composite material sheet should make the flexible composite material covering of slidingtype based on ripple structure in the in-process that tensile deformation, the recess between the adjacent crest of composite material buckled plate can be covered by the composite material sheet all the time.
4. The elastomeric layer of claim 1 is silicone rubber, nitrile rubber, fiber reinforced silicone rubber, fiber reinforced nitrile rubber, piezoelectric fiber silicone rubber composites, and piezoelectric fiber nitrile rubber composites.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010180768.7A CN111319752B (en) | 2020-03-16 | 2020-03-16 | Sliding type flexible composite material skin based on corrugated structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010180768.7A CN111319752B (en) | 2020-03-16 | 2020-03-16 | Sliding type flexible composite material skin based on corrugated structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111319752A true CN111319752A (en) | 2020-06-23 |
| CN111319752B CN111319752B (en) | 2021-07-27 |
Family
ID=71164644
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010180768.7A Active CN111319752B (en) | 2020-03-16 | 2020-03-16 | Sliding type flexible composite material skin based on corrugated structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111319752B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114590394A (en) * | 2022-04-19 | 2022-06-07 | 北京航空航天大学 | Flexible skin based on dot matrix corrugated structure |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2853881A1 (en) * | 2003-04-17 | 2004-10-22 | Nourrissat Philippe Jacques Pi | Wing unit for e.g. aircraft, has jacks with end fixed to spar and another end fixed to interior of upper surface of fixed part to permit relative movements of mobile part with respect to fixed part |
| US20070138341A1 (en) * | 2004-12-07 | 2007-06-21 | Joshi Shiv P | Transformable skin |
| CN101723084A (en) * | 2008-10-27 | 2010-06-09 | 通用电气航空系统有限公司 | Corrugated skins for aircraft and methods of their manufacture |
| CN207902733U (en) * | 2018-01-19 | 2018-09-25 | 北京京东尚科信息技术有限公司 | The aerofoil leading edge structure of Fixed Wing AirVehicle |
| CN108639357A (en) * | 2018-07-18 | 2018-10-12 | 大连理工大学 | A kind of pressurized reservoir covering with carrying and deformation one |
| CN110510103A (en) * | 2019-08-19 | 2019-11-29 | 北京航空航天大学 | A kind of aircraft flexible composite covering and preparation method thereof |
-
2020
- 2020-03-16 CN CN202010180768.7A patent/CN111319752B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2853881A1 (en) * | 2003-04-17 | 2004-10-22 | Nourrissat Philippe Jacques Pi | Wing unit for e.g. aircraft, has jacks with end fixed to spar and another end fixed to interior of upper surface of fixed part to permit relative movements of mobile part with respect to fixed part |
| US20070138341A1 (en) * | 2004-12-07 | 2007-06-21 | Joshi Shiv P | Transformable skin |
| CN101723084A (en) * | 2008-10-27 | 2010-06-09 | 通用电气航空系统有限公司 | Corrugated skins for aircraft and methods of their manufacture |
| CN207902733U (en) * | 2018-01-19 | 2018-09-25 | 北京京东尚科信息技术有限公司 | The aerofoil leading edge structure of Fixed Wing AirVehicle |
| CN108639357A (en) * | 2018-07-18 | 2018-10-12 | 大连理工大学 | A kind of pressurized reservoir covering with carrying and deformation one |
| CN110510103A (en) * | 2019-08-19 | 2019-11-29 | 北京航空航天大学 | A kind of aircraft flexible composite covering and preparation method thereof |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114590394A (en) * | 2022-04-19 | 2022-06-07 | 北京航空航天大学 | Flexible skin based on dot matrix corrugated structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111319752B (en) | 2021-07-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111439368B (en) | Variable camber wing based on flexible skin of composite material corrugated plate | |
| EP2703283B1 (en) | Bonded composite aircraft wing | |
| US8528862B2 (en) | Systems and methods for reducing noise in aircraft fuselages and other structures | |
| US6110567A (en) | Composite structural panel having a face sheet reinforced with a channel stiffener grid | |
| CN107571985B (en) | Truss type ultra-light integral wing structure | |
| US7931240B2 (en) | Cellular support structures used for controlled actuation of fluid contact surfaces | |
| US9114588B2 (en) | Skin-stiffener transition assembly, method of manufacture and application of said skin-stiffener transition assembly | |
| US6553734B1 (en) | Composite structural panel with undulated body | |
| RU2009119050A (en) | REINFORCED CASING FOR AIR OR SPACE AIRCRAFT WITH MULTI-LAYER HIGH RIGIDITY STRINGER AND THE RELATED MULTI-LAYER STRINGER | |
| US20070205332A1 (en) | Sandwich-structure flat actuator and application to structural torsion | |
| CN110979636A (en) | Wing with fishbone-shaped flexible structure | |
| KR20150128665A (en) | Triaxial fiber-reinforced composite laminate | |
| JPH0455864B2 (en) | ||
| CN111319752B (en) | Sliding type flexible composite material skin based on corrugated structure | |
| CN101678891B (en) | Reinforced panel | |
| Kardomateas | Elasticity solutions for sandwich orthotropic cylindrical shells under external/internal pressure or axial force | |
| US20130104966A1 (en) | Strain Isolation Layer Assemblies and Methods | |
| JP5355154B2 (en) | FRP sandwich panel | |
| JP2011240925A (en) | Composite structural member with progressive rigidity | |
| JP2011240925A5 (en) | ||
| CN111319753B (en) | Nested sliding type flexible composite material skin based on corrugated structure | |
| JP2003146294A (en) | Flex beam | |
| JPH04215599A (en) | Super-lightweight sandwich panel | |
| Rose et al. | Finite element modeling of the buckling response of sandwich panels | |
| CN208021709U (en) | A kind of flexible covering |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |