CN207389526U - A kind of flexible covering for deforming aircraft - Google Patents
A kind of flexible covering for deforming aircraft Download PDFInfo
- Publication number
- CN207389526U CN207389526U CN201721201727.1U CN201721201727U CN207389526U CN 207389526 U CN207389526 U CN 207389526U CN 201721201727 U CN201721201727 U CN 201721201727U CN 207389526 U CN207389526 U CN 207389526U
- Authority
- CN
- China
- Prior art keywords
- spring
- covering
- skeleton
- aircraft
- flexible covering
- 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.)
- Expired - Fee Related
Links
Landscapes
- Laminated Bodies (AREA)
Abstract
The utility model is related to it is a kind of deform aircraft flexible covering, including flexure spring skeleton and super-elasticity silicon rubber thin slice, it is characterized in that：Flexure spring skeleton is woven by one-dimensional wire spring and two-dimentional quadrangle spring, and as the sandwich of layers of covering, in flexure spring skeleton both sides covered with super-elasticity silicon rubber thin slice, novel flexible covering is made.The beneficial effects of the utility model are：Flexure spring skeleton solves the problems, such as in flexible covering face as the main load component of covering and normal stiffness is insufficient, which has in preferable face and normal direction bearing capacity made of alloy spring steel.
Description
Technical field
The utility model is related to a kind of type aircraft materials, and in particular to a kind of flexible covering for deforming aircraft.
Background technology
Variant aircraft is respectively provided with excellent property by changing the geometry of wing and fuselage under different flight state
Energy.Therefore, wing and airframe structure should have adaptivity.Variant aircraft flexible covering design be variant aircraft development most
One of big difficult point.At present, three classes are mainly summarized as in the flexible covering of flexible covering field hot research both at home and abroad：Based on flexibility
Cellular covering, the covering based on corrugated plating and the covering based on high-molecular compound.Wherein：The covering manufacture work of flexible honeycomb
Skill is complicated, of high cost, moreover, because bearing loads in plane with rubber, causes bearing capacity low；The covering mechanical characteristic of corrugated plating
Difference, in-plane deformation amount are smaller；The covering strength and stiffness characteristic of high-molecular compound is poor, and not only bearing capacity compares in face for it
It is small, and normal stiffness is also not big enough.Particularly covering cannot carry outer load during the change of covering shape, greatly limit
Its application range on the variant aircraft.
Utility model content
The utility model main purpose is to solve the above problems, and provides a kind of flexible covering for deforming aircraft, the flexibility
Covering can not only eliminate the shortcomings that above-mentioned three kinds of flexible coverings, and have designability with normal stiffness in its face, be allowed to
The basic material for being likely to become stealthy intelligent flexible covering is applied among variant aircraft development.
In order to solve the above technical problems, a kind of technical solution that the utility model uses is：A kind of flexibility for deforming aircraft
Covering, including flexure spring skeleton and super-elasticity silicon rubber thin slice, flexure spring skeleton is by one-dimensional wire spring and two-dimentional quadrangle
Spring weaves, the sandwich of layers as covering;In flexure spring skeleton both sides covered with super-elasticity silicon rubber thin slice.
One-dimensional wire spring shape is the wave linear shape in same plane.Two-dimentional quadrangle spring shape be quadrangle, four
Apex portion is torque spring, and the spiral number of turns of torque spring are undetermined, and the mechanical property according to needed for covering is different and changes, four
The torque spring on four vertex is connected into two-dimentional quadrangle spring by straight line.One-dimensional wire spring plays braiding, by two dimension four
Side shape spring is woven into flexure spring skeleton.The effect of flexure spring skeleton is：With normal direction major part load in bearing plane, maintain
Aircraft skin shape.Novel flexible covering is made covered with super-elasticity silicon rubber thin slice in flexure spring skeleton both sides.Super-elasticity
The effect of silicon rubber is, keeps aircraft surfaces fairing, bears aerodynamic loading, by aerodynamic loading be transferred to flexure spring skeleton and
In aircraft load part beams and rib.
The beneficial effects of the utility model are：
（1）Flexure spring skeleton solves flexible illiteracy as the main load component of covering made of alloy spring steel
In surface and the problem of normal stiffness is insufficient, which has in preferable face and normal direction bearing capacity;
（2）In face and the designability of normal stiffness.According to the different demands of flexible covering deformation performance, flexibility can be changed
Spring skeleton parameter obtains the different flexible covering of deformation performance;
（3）The flexible covering can be as deformation aircraft development and the new material of development.
Description of the drawings
Fig. 1 is a kind of full perspective view for the flexible covering for deforming aircraft；
Fig. 2 is the schematic diagram of flexure spring skeleton；
Fig. 3 is the schematic diagram of the one-dimensional wire spring two kind two-dimentional quadrangle spring different with torque spring spiral number of turns.
It is attached：The mark of each component is as follows in figure：1st, flexure spring skeleton；11st, one-dimensional wire spring；12nd, two-dimentional quadrangle bullet
Spring；121st, torque spring；2nd, super-elasticity silicon rubber.
Specific embodiment
The preferred embodiment of the utility model is described in detail below in conjunction with the accompanying drawings, so that the advantages of the utility model
It is easier to be readily appreciated by one skilled in the art with feature, it is apparent specific so as to be made to the scope of protection of the utility model
It defines.
- 3 are please referred to Fig.1, the utility model is related to a kind of flexible covering for deforming aircraft, including 1 He of flexure spring skeleton
Super-elasticity silicon rubber thin slice 2, flexure spring skeleton 1 are woven by one-dimensional wire spring 11 and two-dimentional quadrangle spring 12, as
The sandwich of layers of covering.
One-dimensional 11 shape of wire spring is the wave linear shape in same plane, the equation of line can be SIN function or other
Function.Two-dimentional 12 shape of quadrangle spring is quadrangle, and four apex portions are torque spring 121, and four straight lines are by four
The torque spring on a vertex connects into two-dimentional quadrangle spring 12.One-dimensional wire spring 11 plays braiding, by two-dimentional quadrangle bullet
Spring 12 is woven into flexure spring skeleton.The effect of flexure spring skeleton 1 is：Fly in bearing plane with normal direction major part load, maintenance
Machine covering shape.
Novel flexible covering is made covered with super-elasticity silicon rubber thin slice 2 in 1 both sides of flexure spring skeleton.Super-elasticity silicon rubber
The effect of glue 2 is to keep aircraft surfaces fairing, bear aerodynamic loading, and aerodynamic loading is transferred to flexure spring skeleton and is flown
In machine load part beams and rib.
It is presented as in the flexible covering face with normal stiffness designability：According to the deformation of flexible covering needed for deformation aircraft
Performance is different, changes the shape function of one-dimensional wire spring, the spiral number of turns of torque spring of two-dimentional quadrangle spring, spring skeleton
The diameter of material, the thickness of the intensity and toughness characteristic of alloy spring steel and super-elasticity silicon rubber, intensity and toughness characteristic, it is all available
The different flexible covering of deformation performance.
The above description is only the embodiments of the present invention, and it does not limit the scope of the patent of the present invention, every
Equivalent structure or equivalent flow shift made based on the specification and figures of the utility model, is directly or indirectly used in
Other related technical areas are similarly included in the utility model patent protection domain.
Claims (3)
1. a kind of flexible covering for deforming aircraft, including flexure spring skeleton and super-elasticity silicon rubber thin slice, it is characterized in that：It is flexible
Spring skeleton is woven by one-dimensional wire spring and two-dimentional quadrangle spring, as the sandwich of layers of covering, in flexure spring skeleton
Both sides are covered with super-elasticity silicon rubber thin slice.
2. a kind of flexible covering for deforming aircraft according to claim 1, it is characterized in that：One-dimensional wire spring shape is same
Wave linear shape in plane.
3. a kind of flexible covering for deforming aircraft according to claim 1, it is characterized in that：Two-dimentional quadrangle spring shape is
Quadrangle, four apex portions are torque spring, and spiral number of turns mechanical property according to needed for covering of torque spring is different and changes
Become, the torque spring on four vertex is connected into two-dimentional quadrangle spring by four straight lines.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721201727.1U CN207389526U (en) | 2017-09-19 | 2017-09-19 | A kind of flexible covering for deforming aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721201727.1U CN207389526U (en) | 2017-09-19 | 2017-09-19 | A kind of flexible covering for deforming aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207389526U true CN207389526U (en) | 2018-05-22 |
Family
ID=62404595
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721201727.1U Expired - Fee Related CN207389526U (en) | 2017-09-19 | 2017-09-19 | A kind of flexible covering for deforming aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207389526U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533270A (en) * | 2018-11-30 | 2019-03-29 | 南京航空航天大学 | One-way expansion yielding flexibility covering in a kind of face with bending resistance outside face |
| CN109625237A (en) * | 2018-12-02 | 2019-04-16 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of reticulated flexible structure and aircraft |
| CN113525523A (en) * | 2021-07-22 | 2021-10-22 | 哈尔滨工程大学 | Whale fat fluid anti-drag noise-reduction skin based on flexible joint vibration-reduction unit lattice structure |
-
2017
- 2017-09-19 CN CN201721201727.1U patent/CN207389526U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533270A (en) * | 2018-11-30 | 2019-03-29 | 南京航空航天大学 | One-way expansion yielding flexibility covering in a kind of face with bending resistance outside face |
| CN109625237A (en) * | 2018-12-02 | 2019-04-16 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of reticulated flexible structure and aircraft |
| CN113525523A (en) * | 2021-07-22 | 2021-10-22 | 哈尔滨工程大学 | Whale fat fluid anti-drag noise-reduction skin based on flexible joint vibration-reduction unit lattice structure |
| CN113525523B (en) * | 2021-07-22 | 2022-12-13 | 哈尔滨工程大学 | Whale-simulated fluid anti-drag noise-reduction skin based on flexible joint vibration-reduction unit lattice structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207389526U (en) | A kind of flexible covering for deforming aircraft | |
| CN107571985B (en) | Truss type ultra-light integral wing structure | |
| US6064352A (en) | Composite isogrid structures for parabolic surfaces | |
| CN100562594C (en) | The guard member of blade inlet edge | |
| Vocke III et al. | Development and testing of a span-extending morphing wing | |
| AU2017200151B2 (en) | Laminar flow panel | |
| CN207725604U (en) | A kind of composite material honeycomb interlayer siding suitable for high aspect ratio wing | |
| Chen et al. | Composite flexible skin with large negative Poisson’s ratio range: numerical and experimental analysis | |
| CN102700704A (en) | Deformation skin for aircraft | |
| Kudva et al. | Design, fabrication, and testing of the DARPA/Wright Lab'smart wing'wind tunnel model | |
| CN104417749A (en) | An aircraft structure and method of manufacture | |
| US20130280079A1 (en) | Propeller blade with metallic foam spar core | |
| CN109436293A (en) | A kind of shock wave control device | |
| US20150367936A1 (en) | Optimized Core for a Structural Assembly | |
| CN113844636B (en) | Omega-shaped flexible skin honeycomb structure | |
| Tang et al. | A combined airfoil with secondary feather inspired by the golden eagle and its influences on the aerodynamics | |
| CN103661925A (en) | Determination method for automatic variable-pitch propeller based on composite material | |
| CN202977737U (en) | A spaceborne lightweight net-shaped reflector antenna | |
| EP3715241A1 (en) | A stiffened structural component for an aircraft | |
| CN202686751U (en) | Honeycomb sandwich structure covering | |
| CN208021709U (en) | A kind of flexible covering | |
| CN109533314B (en) | Pneumatic appearance of light unmanned helicopter rotor blade | |
| Wakayama et al. | Evaluation of adaptive compliant trailing edge technology | |
| CN101367434A (en) | Stressed-skin construction capable of implementing large area deformation | |
| CN111319752B (en) | Sliding type flexible composite material skin based on corrugated structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180522 Termination date: 20180919 |