CN114590394A - Flexible skin based on dot matrix corrugated structure - Google Patents
Flexible skin based on dot matrix corrugated structure Download PDFInfo
- Publication number
- CN114590394A CN114590394A CN202210408016.0A CN202210408016A CN114590394A CN 114590394 A CN114590394 A CN 114590394A CN 202210408016 A CN202210408016 A CN 202210408016A CN 114590394 A CN114590394 A CN 114590394A
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- CN
- China
- Prior art keywords
- corrugated
- corrugated structure
- lattice
- dot matrix
- flexible skin
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- 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.)
- Pending
Links
- 239000011159 matrix material Substances 0.000 title claims abstract description 15
- 229920001971 elastomer Polymers 0.000 claims abstract description 14
- 239000000806 elastomer Substances 0.000 claims abstract description 14
- 239000002131 composite material Substances 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 230000008901 benefit Effects 0.000 abstract description 4
- 239000000835 fiber Substances 0.000 description 10
- 229920000459 Nitrile rubber Polymers 0.000 description 6
- 229920002379 silicone rubber Polymers 0.000 description 6
- 239000000463 material Substances 0.000 description 3
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 229920000271 Kevlar® Polymers 0.000 description 2
- 239000004696 Poly ether ether ketone Substances 0.000 description 2
- 239000004952 Polyamide Substances 0.000 description 2
- 229920000491 Polyphenylsulfone Polymers 0.000 description 2
- 229910052796 boron Inorganic materials 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 239000003365 glass fiber Substances 0.000 description 2
- 239000004761 kevlar Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 229920002647 polyamide Polymers 0.000 description 2
- 229920000515 polycarbonate Polymers 0.000 description 2
- 239000004417 polycarbonate Substances 0.000 description 2
- 229920002530 polyetherether ketone Polymers 0.000 description 2
- 238000003491 array Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000008093 supporting effect Effects 0.000 description 1
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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T70/00—Maritime or waterways transport
- Y02T70/10—Measures concerning design or construction of watercraft hulls
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
A flexible skin based on a lattice corrugated structure is composed of the lattice corrugated structure and an elastomer layer. The connection relationship is as follows: obtain dot matrix ripple structure with the ingenious array of buckled plate, inside two liang of relative wave troughs of the inside buckled plate of dot matrix ripple structure are connected, utilize the connecting rod to connect each ripple unit and buckled plate, cover elastomer layer on dot matrix ripple structure surface. The flexible skin has large deformation capacity, can carry external pneumatic load and keep a smooth pneumatic surface, 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 flexible skin based on a lattice corrugated structure, and belongs to the field of aviation structure design.
Technical Field
In the field of morphing airplanes, morphing wings refer to aircrafts which can change the geometrical shapes of wings and achieve the optimal aerodynamic benefit of each task section in the whole flight task. Whatever the style of morphing wing, there is a need for a flexible skin with out-of-plane load bearing capacity and large in-plane deflection capacity. At present, various flexible skins made of intelligent materials or structures exist at home and abroad, but the flexible skin structures have the problems of complex structure, heavy weight, slow deformation response and the like. Therefore, the flexible skin based on the lattice corrugated structure is provided, consists of the lattice corrugated structure and the elastomer layer, and has the advantages of simple structure and light weight. The skin has good stretching and bending deformation capacities along the corrugation direction, has good bearing capacity along the vertical corrugation direction, can maintain smooth pneumatic appearance in the deformation process, and has strong practicability.
Disclosure of Invention
1. The purpose is as follows: the invention aims to provide a flexible skin based on a lattice corrugated structure, which has an out-of-plane bearing capacity, maintains the smooth aerodynamic shape of an airfoil surface and can realize large deformation capacity.
2. The technical scheme is as follows: the invention consists of a lattice corrugated structure and an elastomer layer. Their connection relationship is as follows: (1) the lattice corrugated structure is obtained by combining corrugated plates and connecting rods, the cross sections of the corrugated plates are continuous corrugated units, and the shapes of the corrugated units are
A plurality of corrugated plate arrays are connected through connecting rods to form a dot matrix corrugated structure, the outer side of the dot matrix corrugated structure is a single corrugated plate, the inner part of the dot matrix corrugated structure is a corrugated plate which is opposite to each other in pairs, the wave trough of the corrugated plate is connected with the wave trough of the corrugated plate, and the cross section of the corrugated plate array is in the shape of a square
The two sections of the connecting rods are connected with wave crests of the corrugated plates on the outer sides, and adjacent corrugated units of the corrugated plates and the transverse corrugated plates are connected at the same time to form a dot matrix corrugated structure; (2) the elastomer layer is closely covered on the surface of the lattice corrugated structure. The lattice corrugated structure has large deformability along the corrugated direction, has certain in-plane rigidity perpendicular to the corrugated direction and is used for bearing pneumatic load; the surface of the elastic body layer is smooth and has good elasticity, and the elastic body layer is attached to the surface of the lattice corrugated structure, so that the flexible skin of the lattice corrugated structure is ensured to have a smooth pneumatic appearance in the deformation process.
The lattice corrugated structure is a unidirectional tape laminated plate and a woven material plate which are made of polyamide, polycarbonate, polyphenylsulfone, polyether ether ketone, carbon fiber, glass fiber, Kevlar fiber and boron fiber.
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 flexible skin based on the lattice corrugated structure is formed by combining the lattice corrugated structures in an array mode in a smart mode by utilizing the anisotropic characteristic of corrugated plates and covering an elastomer layer, so that the skin has good large deformation capacity, certain out-of-plane rigidity and smooth pneumatic appearance. The flexible skin of the morphing wing has simple structure and light weight, and is a practical and feasible flexible skin scheme of the morphing wing.
Drawings
Figure 1 is a schematic view of a corrugated sheet in a normal state.
Figure 2 is a schematic view of a corrugated sheet in a stretched condition.
FIG. 3 is a schematic diagram of the lattice corrugation structure in the normal state.
FIG. 4 is a schematic view of the lattice corrugation structure in a stretched state.
FIG. 5 is a schematic view of a flexible skin based on a lattice corrugation structure in a normal state.
FIG. 6 is a schematic view of a flexible skin based on a lattice corrugation structure in a stretched state.
In fig. 1: 1. a corrugated unit.
In fig. 2: and F is tensile load.
In fig. 3: 2. a connecting rod.
In fig. 4: and F is tensile load.
In fig. 5: 3. elastomer layer, 4. lattice corrugated structure.
In fig. 6: and F is tensile load.
Detailed Description
The invention is further described below with reference to the drawings and the examples.
The invention relates to a flexible skin composed of a lattice corrugated structure based on the lattice corrugated structureAnd an elastomeric layer. The lattice corrugated structure 4 is formed by combining corrugated plates and connecting rods 2, wherein the cross sections of the corrugated plates are formed by continuous corrugated units 1 (shown in figure 1). The corrugated plate is a unidirectional tape laminated plate and a woven material plate which are made of polyamide, polycarbonate, polyphenylsulfone, polyether ether ketone, carbon fiber, glass fiber, Kevlar fiber and boron fiber. The buckled plate has anisotropy, and is less along ripple direction rigidity, and when applying certain tensile load for the buckled plate along the ripple direction, the buckled plate can produce big tensile deformation (as shown in figure 2), and the buckled plate is great at perpendicular to ripple direction rigidity, possesses the bearing capacity. Connect the buckled plate array and obtain dot matrix ripple structure through the connecting rod, the dot matrix ripple structure outside is single buckled plate, inside buckled plate two liang of opposite and trough are connected, cross sectional shape is
The two ends of the connecting piece are connected with wave crests of corrugated plates outside the dot matrix corrugated structure, and are simultaneously connected with adjacent corrugated units of the corrugated plates and transverse corrugated plates (as shown in figure 3). The lattice corrugation structure can generate large deformation along the corrugation direction (as shown in fig. 4) when a certain tensile load is applied along the corrugation direction (i.e. longitudinal direction), and can not generate large deformation in the transverse direction due to the existence of the connecting rods. On perpendicular to ripple direction, buckled plate and connecting rod possess certain rigidity, therefore lattice corrugated structure possesses certain bearing capacity. The elastomer layer 3 covers the surface of the lattice corrugated structure (as shown in fig. 5), and 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 elastomeric layer has good elasticity and a smooth surface. When a certain tensile force is applied in the corrugation direction, the flexible skin based on the lattice corrugation structure can generate large tensile deformation, and the elastic body layer covered on the surface of the flexible skin generates tensile deformation along with the large tensile deformation due to the elasticity of the flexible skin (as shown in figure 6), so that the airfoil surface of the flexible skin is ensured to be smooth in the deformation process. In the direction vertical to the corrugation, the flexible skin can bear the external pneumatic load due to the supporting action of the corrugated plates and the connecting rods, and maintain the pneumatic appearance of the flexible skin. The flexible skin formed by the lattice corrugated structure and the elastomer layer has large deformation capacity and pneumatic load capacity outside the bearing surface, and can keep a smooth pneumatic appearance while deforming.
Claims (1)
1. The utility model provides a flexible skin based on dot matrix ripple structure which characterized in that: the composite material consists of a lattice corrugated structure and an elastomer layer; their connection relationship is as follows: (1) the lattice corrugated structure is obtained by a corrugated plate array, corrugated plates in the lattice corrugated structure are oppositely connected in pairs through wave troughs, and each corrugated unit and each corrugated plate are connected by a connecting rod; (2) the elastomer layer is tightly attached to the lattice corrugated structure; corrugated structure is less along ripple orientation upper rigidity, and perpendicular to ripple orientation possesses great rigidity, and dot matrix corrugated structure can produce big deformation applying certain tensile load along the ripple orientation, and in perpendicular to ripple orientation, buckled plate and connecting rod possess the bearing capacity, and the elastomer layer possesses good elasticity and glossy surface, so flexible covering based on dot matrix corrugated structure possesses big deformability and resists the ability of off-plane pneumatic load to can keep glossy aerodynamic surface at the deformation process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210408016.0A CN114590394A (en) | 2022-04-19 | 2022-04-19 | Flexible skin based on dot matrix corrugated structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210408016.0A CN114590394A (en) | 2022-04-19 | 2022-04-19 | Flexible skin based on dot matrix corrugated structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114590394A true CN114590394A (en) | 2022-06-07 |
Family
ID=81813274
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210408016.0A Pending CN114590394A (en) | 2022-04-19 | 2022-04-19 | Flexible skin based on dot matrix corrugated structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114590394A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102013218520A1 (en) * | 2013-09-16 | 2015-03-19 | Airbus Operations Gmbh | Method for producing a fiber composite component, fiber composite component, and structural component for an aircraft or spacecraft |
| CN106800084A (en) * | 2017-02-10 | 2017-06-06 | 哈尔滨工业大学 | It is a kind of with the deformation skin structure that can design Poisson's ratio |
| 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 |
| CN111319752A (en) * | 2020-03-16 | 2020-06-23 | 北京航空航天大学 | Sliding type flexible composite material skin based on corrugated structure |
| CN111591433A (en) * | 2019-11-12 | 2020-08-28 | 中国科学院兰州化学物理研究所 | Flexible skin and preparation method and application thereof |
| CN113844636A (en) * | 2021-10-19 | 2021-12-28 | 大连理工大学 | Omega-shaped flexible skin honeycomb structure |
-
2022
- 2022-04-19 CN CN202210408016.0A patent/CN114590394A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102013218520A1 (en) * | 2013-09-16 | 2015-03-19 | Airbus Operations Gmbh | Method for producing a fiber composite component, fiber composite component, and structural component for an aircraft or spacecraft |
| CN106800084A (en) * | 2017-02-10 | 2017-06-06 | 哈尔滨工业大学 | It is a kind of with the deformation skin structure that can design Poisson's ratio |
| 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 |
| CN111591433A (en) * | 2019-11-12 | 2020-08-28 | 中国科学院兰州化学物理研究所 | Flexible skin and preparation method and application thereof |
| CN111319752A (en) * | 2020-03-16 | 2020-06-23 | 北京航空航天大学 | Sliding type flexible composite material skin based on corrugated structure |
| CN113844636A (en) * | 2021-10-19 | 2021-12-28 | 大连理工大学 | Omega-shaped flexible skin honeycomb structure |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20220607 |
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