CN109204779A - A kind of self- recoverage wing cover system based on marmem - Google Patents
A kind of self- recoverage wing cover system based on marmem Download PDFInfo
- Publication number
- CN109204779A CN109204779A CN201811329933.XA CN201811329933A CN109204779A CN 109204779 A CN109204779 A CN 109204779A CN 201811329933 A CN201811329933 A CN 201811329933A CN 109204779 A CN109204779 A CN 109204779A
- Authority
- CN
- China
- Prior art keywords
- marmem
- wing cover
- shape
- alloy wire
- composite bundle
- 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.)
- Withdrawn
Links
- 239000002131 composite material Substances 0.000 claims abstract description 23
- 229910001285 shape-memory alloy Inorganic materials 0.000 claims abstract description 19
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 16
- 239000000956 alloy Substances 0.000 claims abstract description 16
- 238000010438 heat treatment Methods 0.000 claims abstract description 8
- 125000000391 vinyl group Chemical group [H]C([*])=C([H])[H] 0.000 claims description 9
- 229920002554 vinyl polymer Polymers 0.000 claims description 9
- 229910000831 Steel Inorganic materials 0.000 claims description 6
- 239000010959 steel Substances 0.000 claims description 6
- 238000010276 construction Methods 0.000 claims description 4
- 230000015654 memory Effects 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 2
- 230000005611 electricity Effects 0.000 claims 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 claims 1
- 239000010931 gold Substances 0.000 claims 1
- 229910052737 gold Inorganic materials 0.000 claims 1
- 230000036244 malformation Effects 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 4
- 230000010354 integration Effects 0.000 abstract description 3
- 230000003446 memory effect Effects 0.000 description 9
- 238000001816 cooling Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 229910000734 martensite Inorganic materials 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 229920003023 plastic Polymers 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- VGGSQFUCUMXWEO-UHFFFAOYSA-N Ethene Chemical compound C=C VGGSQFUCUMXWEO-UHFFFAOYSA-N 0.000 description 1
- 239000005977 Ethylene Substances 0.000 description 1
- IAYPIBMASNFSPL-UHFFFAOYSA-N Ethylene oxide Chemical compound C1CO1 IAYPIBMASNFSPL-UHFFFAOYSA-N 0.000 description 1
- 206010037660 Pyrexia Diseases 0.000 description 1
- 230000006399 behavior Effects 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The self- recoverage wing cover system based on marmem that the invention discloses a kind of, marmem composite bundle are arranged in the upper and lower surfaces of wing cover structure by anchor.The marmem composite bundle for being arranged in wing cover structure upper and lower surfaces is respectively 5, and totally 10.The present invention may make shape-memory alloy wire beam to shrink, realize the effect of adjustment malformation by being powered to lectrothermal alloy wire.The Highgrade integration of marmem composite bundle can avoid the shortcomings that using not compact additional heating device bring structure, occupancy extensive work space.It for this structure being chronically in atmospheric environment of wing cover, is not only inconvenient using additional heating device, but also the performance that will affect structure plays.The present invention is equipped with shape-memory alloy wire Shu Zuowei driving force group, and with the variation of external load, the meeting of structure generates different deformations.
Description
Technical field
The self- recoverage wing cover system based on marmem that the present invention relates to a kind of, belongs to field of antenna.
Background technique
It is largely highlighted relative to traditional antenna in airborne platform surface, skin antenna can preferably merge flat with weapon
Platform, it is with the obvious advantage in aerodynamics characteristic, stealth, it is contemplated that future can be widely applied to opportunity of combat of new generation, unmanned plane, early warning
In the Weapons platform constructions such as dirigible, battleship of new generation, tank, missile-borne, spaceborne.The design of structure, telecommunication function integration makes to cover
Skin antenna has mechanics bearing function simultaneously, but also as the ability of transceiving electromagnetic wave.However, the malformation meeting of skin antenna
Very important influence is brought to electrical property.Therefore it is necessary to the malformations to skin antenna to carry out dynamic adjustment.
The deformation of wing cover structure can be adjusted using shape memory effect alloy.Shape memory effect refers to
SMA (Shap Memory Alloy) is under certain conditions after certain plastic deformation, and when being heated to certain temperature, SMA is again
The phenomenon that being completely recovered to original form before deforming.Shape memory effect can be divided into three kinds: one way, round trip and whole shape
Memory effect.Mostly use additional external cooling device or heating device, structure not tight using marmem application at present
It gathers, is not suitable for the environment of limited working space.Come particularly with this structure being chronically in atmospheric environment of wing cover
It says, is inconvenient using additional heating device, the performance that also will affect structure plays.
Summary of the invention
In view of the above problems, the present invention provides a kind of self- recoverage wing cover system based on marmem, when
When marmem composite bundle is powered, the heat that resistance wire generates can be such that shape-memory alloy wire temperature increases.When shape is remembered
Recall alloy wire temperature raising reach its deformation temperature after can shrink, give structure apply a pulling force, play adjustment malformation
Purpose.
In order to solve problem above, present invention employs following technical solutions: it is a kind of based on marmem from extensive
Multiple wing cover system, which is characterized in that including wing cover structure, marmem composite bundle and anchor, shape
Memorial alloy composite bundle is arranged in the upper and lower surfaces of wing cover structure by anchor.
The marmem composite bundle for being arranged in wing cover structure upper and lower surfaces is respectively 5, and totally 10.
The marmem composite bundle includes shape-memory alloy wire beam, polytetroxide vinyl hose, electrothermal alloy
Silk, insulating sleeve；Wherein, polytetroxide vinyl hose is wrapped in outside shape-memory alloy wire beam, and lectrothermal alloy wire is wrapped in poly- four
Outside ethylene oxide hose, insulating sleeve is wrapped in lectrothermal alloy wire.
The anchor is made of steel plate, is equipped on the steel plate around hole and anchor hole, marmem composite bundle
Across around hole, anchored on anchor hole by bolt.
The utility model has the advantages that the present invention may make shape-memory alloy wire beam to shrink, realize and adjust by being powered to lectrothermal alloy wire
The effect of whole malformation.The Highgrade integration of marmem composite bundle can avoid using additional heating device bring
Structure is not compact, occupies the shortcomings that extensive work space.Particularly with this knot being chronically in atmospheric environment of wing cover
It for structure, is not only inconvenient using additional heating device, but also the performance that will affect structure plays.The present invention is equipped with 10 groups
Shape-memory alloy wire Shu Zuowei driving force group, with the variation of external load, the meeting of structure generates different deformations.For each
Kind deformation state, has a kind of optimal energization scheme to be corresponding to it.It can be achieved to adjust the dynamic of malformation in this way.Wing
Stressed-skin construction can undertake different external loads under actual working condition, generate different deformation states, therefore become to structure
The dynamic adjustment of shape is very necessary.
Detailed description of the invention
Fig. 1 is the self- recoverage wing cover architectural schematic based on marmem.
Fig. 2 is that shape-memory alloy wire beam anchors schematic diagram.
Fig. 3 is the shape memory effect schematic diagram that initial temperature terminates the SMA of temperature Af or more in martensite reverse transformation.
Fig. 4 is SMA deformation behaviour schematic diagram.
Fig. 5 is the sectional view of marmem composite bundle.
Specific embodiment
It is further elaborated below with reference to the present invention.
As shown in Figure 1, the present invention provides a kind of self- recoverage wing cover system based on marmem, including machine
Wing stressed-skin construction 1, marmem composite bundle 2 and anchor 3, marmem composite bundle 2 pass through 3 cloth of anchor
The upper and lower surfaces in wing cover structure 1, respectively 5 are set, totally 10.
As shown in Fig. 2, the anchor 3 is made of steel plate 8, it is equipped on steel plate 8 around hole 9 and anchor hole 10, shape
Shape memory alloys composite bundle 2 is passed through around hole 9, is anchored on anchor hole 10 by bolt 11.
As shown in figure 3, the original state of SMA is completely austenitic state, and it is cooling to SMA first, so that its temperature is down to horse
Family name's body phase transformation terminates temperature Mf hereinafter, SMA is converted into twin crystal martensite state；Wing cover system is by extraneous load action
When, it will cause SMA that certain plastic deformation occurs；Then it is heated, its temperature is made to come back to Af or more, SMA turns again
Completely austenitic state is turned to, the shape before being restored to deformation.(note: Mf and Af is two critical-temperatures of SMA, and temperature is lower than
When MF, SMA is martensitic state；When temperature is higher than Af, SMA is austenitic state)
As shown in figure 4, shape memory effect can be divided into three kinds: one way, round trip and whole shape memory effect.One way
Shape memory effect refers to that the plastic deformation of certain limit occurs at a lower temperature for SMA, the shape before deformation is returned to after heating
Then shape is maintained for the shape invariance；Double process shape-memory effect refers to SMA when heated and can be restored to shape when high temperature
Shape can be restored to the shape when low temperature when cooling；Whole shape memory effect refers to that SMA can be restored to high temperature when heated
When shape, become identical as shape when high temperature when cooling and be orientated opposite shape.
The determination process of energization scheme is that wing cover structure 1 can generate amount of deflection, wing cover structure under load action
The amount of deflection of 1 surface all the points forms a deflection field, uses w0It indicates.When each marmem composite bundle 2 is powered, it can give
Wing cover structure 1 applies an active force, equally can be to one deflection field of generation.In the present invention, there are 10 shape memories to close
Golden composite bundle 2 is used as driving force group, and corresponding deflection field uses w respectively1、w2...w10It indicates.Under small deflection theory, Ke Yizhi
It connects and multiple deflection fields is overlapped.For arbitrary initial deflection field w0, all there are two types of shapes for every marmem composite bundle 2
State, energization or no power.Therefore, one 2 are shared10Kind assembled scheme, selecting a kind of pair of structure to use in all schemes most has
The combination of benefit, that is, can determine energization scheme.With the variation of external load, there is a kind of optimal energization scheme to be corresponding to it.
As shown in figure 5, the marmem composite bundle 2 is soft including shape-memory alloy wire beam 4, polytetroxide ethylene
Pipe 5, lectrothermal alloy wire 6, insulating sleeve 7；Wherein, polytetroxide vinyl hose 5 is wrapped in outside shape-memory alloy wire beam 4, electric heating
Alloy wire 6 is wrapped in outside polytetroxide vinyl hose 5, and insulating sleeve 7 is wrapped in lectrothermal alloy wire 6；Meeting after lectrothermal alloy wire 6 is powered
Fever, heat are transmitted on shape-memory alloy wire beam 4 by polytetroxide vinyl hose 5, make 4 liters of shape-memory alloy wire beam
Temperature；When temperature raising reaches deformation temperature, shape-memory alloy wire beam 4 will be shunk, and realized and applied to wing cover structure 1
The effect of one pulling force.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, several improvement and deformations can also be made, these improvement and deformations
Also it should be regarded as protection scope of the present invention.
Claims (4)
1. a kind of self- recoverage wing cover system based on marmem, which is characterized in that including wing cover structure
(1), marmem composite bundle (2) and anchor (3), marmem composite bundle (2) pass through anchor (3) cloth
Set the upper and lower surfaces in wing cover structure (1).
2. a kind of self- recoverage wing cover system based on marmem according to claim, which is characterized in that
The marmem composite bundle (2) for being arranged in wing cover structure (1) upper and lower surfaces is respectively 5, and totally 10.
3. a kind of self- recoverage wing cover system based on marmem according to claim, which is characterized in that
The marmem composite bundle (2) includes shape-memory alloy wire beam (4), polytetroxide vinyl hose (5), electrothermal alloy
Silk (6), insulating sleeve (7)；Wherein, polytetroxide vinyl hose (5) is wrapped in shape-memory alloy wire beam (4) outside, electrothermal alloy
Silk (6) is wrapped in polytetroxide vinyl hose (5) outside, and insulating sleeve (7) is wrapped in lectrothermal alloy wire (6)；Lectrothermal alloy wire (6) is logical
It can generate heat after electricity, heat is transmitted on shape-memory alloy wire beam (4) by polytetroxide vinyl hose (5), closes shape memory
Spun gold beam (4) heating；When temperature raising reaches deformation temperature, shape-memory alloy wire beam (4) will be shunk, and be realized to wing
Stressed-skin construction (1) applies a pulling force.
4. a kind of self- recoverage wing cover system based on marmem according to claim, which is characterized in that
The anchor (3) is made of steel plate (8), is equipped on steel plate (8) around hole (9) and anchor hole (10), shape memory closes
Golden composite bundle (2) passes through around hole (9), is anchored on anchor hole (10) by bolt (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811329933.XA CN109204779A (en) | 2018-11-09 | 2018-11-09 | A kind of self- recoverage wing cover system based on marmem |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811329933.XA CN109204779A (en) | 2018-11-09 | 2018-11-09 | A kind of self- recoverage wing cover system based on marmem |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109204779A true CN109204779A (en) | 2019-01-15 |
Family
ID=64995670
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811329933.XA Withdrawn CN109204779A (en) | 2018-11-09 | 2018-11-09 | A kind of self- recoverage wing cover system based on marmem |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109204779A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920864A (en) * | 2019-10-29 | 2020-03-27 | 南京航空航天大学 | Two-way variant mechanism and method driven by shape memory alloy thin plate |
| CN112078778A (en) * | 2019-06-13 | 2020-12-15 | 海鹰航空通用装备有限责任公司 | Folding expansion device of intelligence |
| CN113428345A (en) * | 2021-07-30 | 2021-09-24 | 中国计量大学 | Piezoelectric large-displacement deformation wing based on shape memory polymer skin and method thereof |
| CN115649415A (en) * | 2022-12-29 | 2023-01-31 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Distributed shape memory alloy driven active deformation skin structure |
| CN115675833A (en) * | 2022-12-29 | 2023-02-03 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Polymorphic deformation wing based on active deformation skin |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005000671A2 (en) * | 2003-02-04 | 2005-01-06 | Ilc Dover, Inc. | Deployable, rigidizable wing |
| CN103158860A (en) * | 2013-03-19 | 2013-06-19 | 哈尔滨工业大学 | Variable trailing edge wing driven by combination of shape memory alloy and piezoelectric fibrous composite material |
| CN104454415A (en) * | 2014-12-10 | 2015-03-25 | 北京航空航天大学 | Brake cable type shape memory alloy driver |
| KR20160002477A (en) * | 2014-06-30 | 2016-01-08 | 서울대학교산학협력단 | Shape Changeable Main Wings of Unmanned Aerial Vehicle |
| WO2016018477A1 (en) * | 2014-07-29 | 2016-02-04 | The Boeing Company | Shape memory alloy actuator system for composite aircraft structures |
| CN108238248A (en) * | 2017-12-30 | 2018-07-03 | 哈尔滨工业大学深圳研究生院 | A kind of flexible wing and flapping wing robot |
| CN209634718U (en) * | 2018-11-09 | 2019-11-15 | 中国电子科技集团公司第十四研究所 | A kind of self- recoverage wing cover system based on marmem |
-
2018
- 2018-11-09 CN CN201811329933.XA patent/CN109204779A/en not_active Withdrawn
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005000671A2 (en) * | 2003-02-04 | 2005-01-06 | Ilc Dover, Inc. | Deployable, rigidizable wing |
| CN103158860A (en) * | 2013-03-19 | 2013-06-19 | 哈尔滨工业大学 | Variable trailing edge wing driven by combination of shape memory alloy and piezoelectric fibrous composite material |
| KR20160002477A (en) * | 2014-06-30 | 2016-01-08 | 서울대학교산학협력단 | Shape Changeable Main Wings of Unmanned Aerial Vehicle |
| WO2016018477A1 (en) * | 2014-07-29 | 2016-02-04 | The Boeing Company | Shape memory alloy actuator system for composite aircraft structures |
| CN104454415A (en) * | 2014-12-10 | 2015-03-25 | 北京航空航天大学 | Brake cable type shape memory alloy driver |
| CN108238248A (en) * | 2017-12-30 | 2018-07-03 | 哈尔滨工业大学深圳研究生院 | A kind of flexible wing and flapping wing robot |
| CN209634718U (en) * | 2018-11-09 | 2019-11-15 | 中国电子科技集团公司第十四研究所 | A kind of self- recoverage wing cover system based on marmem |
Non-Patent Citations (2)
| Title |
|---|
| U. ICARDI、L. FERRERO: "SMA Actuated Mechanism for an Adaptive Wing", 《JOURNAL OF AEROSPACE ENGINEERING》, pages 140 - 143 * |
| 刘俊兵: "差动式形状记忆合金驱动器驱动性能研究", 《现代机械》, no. 1, pages 4 - 7 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112078778A (en) * | 2019-06-13 | 2020-12-15 | 海鹰航空通用装备有限责任公司 | Folding expansion device of intelligence |
| CN110920864A (en) * | 2019-10-29 | 2020-03-27 | 南京航空航天大学 | Two-way variant mechanism and method driven by shape memory alloy thin plate |
| CN110920864B (en) * | 2019-10-29 | 2022-06-17 | 南京航空航天大学 | Two-way variant mechanism and method driven by shape memory alloy thin plate |
| CN113428345A (en) * | 2021-07-30 | 2021-09-24 | 中国计量大学 | Piezoelectric large-displacement deformation wing based on shape memory polymer skin and method thereof |
| CN115649415A (en) * | 2022-12-29 | 2023-01-31 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Distributed shape memory alloy driven active deformation skin structure |
| CN115675833A (en) * | 2022-12-29 | 2023-02-03 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Polymorphic deformation wing based on active deformation skin |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109204779A (en) | A kind of self- recoverage wing cover system based on marmem | |
| CN103419925B (en) | Marmem active spar for blade twist | |
| CN105304408B (en) | A kind of shape memory alloy temperature control current switch | |
| CN209634718U (en) | A kind of self- recoverage wing cover system based on marmem | |
| CN106255638B (en) | Sail including shape memory material elements, for the device and method of its operation | |
| DE102006023616A1 (en) | Arrangement and method for generating energy from solar radiation | |
| CN103350424B (en) | The corrosion-proof lightweight of Shape-based interpolation memory polymer is without the need to oil feeder mechanical arm | |
| CN103757571B (en) | The gamma-TiAl alloy tiny complete lamellar structure preparation method of lamellar interface preferred orientation | |
| CN106594048A (en) | Bolt assembly of shape memory alloy cable clamp | |
| CN106589438A (en) | Light-response shape memory composite material and preparing method and application method thereof | |
| CN103826422B (en) | Microchannel cooling device | |
| CN106476665B (en) | A kind of vehicle-mounted multipotency cup holder and control method based on semiconductor refrigerating | |
| KR20100137235A (en) | A bending-type actuator by using a shape memory alloy wire(sma),composite strip, and spring | |
| CN206820037U (en) | A kind of lightweight lithium battery box of phase-change heat material | |
| JP6223664B2 (en) | Thermoelectric power generation from feeder | |
| CN104498847B (en) | Thin-walled cavity structure aluminium alloy post method for controlling heat treatment deformation | |
| CN103147944B (en) | Two-section tower type solar thermal power generation system | |
| CN207833358U (en) | A kind of spaceborne temperature regulating device based on thermal conductive wire heat transfer | |
| CN111487733B (en) | Anti-freezing heat-preservation type optical cable in extremely cold weather | |
| CN204064069U (en) | The cold thermal energy storage device of a kind of solar electrical energy generation | |
| Rahnema et al. | ENDF/B-VI benchmark calculations for the Doppler coefficient of reactivity | |
| CN111937717A (en) | Crop water replenishing protection device for high-temperature weather blade transpiration | |
| Seow et al. | Shape memory alloy as actuator to deflect a wing flap | |
| DE202014103290U1 (en) | Vehicle with heat storage | |
| CN104099544A (en) | Whole course memory effect acquisition method for shape memory alloy |
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 | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190115 |
|
| WW01 | Invention patent application withdrawn after publication |