CN104443354B - A kind of wing with self adaptation variable camber trailing edge - Google Patents
A kind of wing with self adaptation variable camber trailing edge Download PDFInfo
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- CN104443354B CN104443354B CN201410677233.5A CN201410677233A CN104443354B CN 104443354 B CN104443354 B CN 104443354B CN 201410677233 A CN201410677233 A CN 201410677233A CN 104443354 B CN104443354 B CN 104443354B
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- eyelid covering
- trailing edge
- wing
- variable camber
- back rest
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- 230000006978 adaptation Effects 0.000 title claims abstract description 13
- 210000000744 eyelid Anatomy 0.000 claims abstract description 62
- 229910001285 shape-memory alloy Inorganic materials 0.000 claims description 14
- 239000004593 Epoxy Substances 0.000 claims description 7
- 150000001875 compounds Chemical class 0.000 claims description 7
- 239000011521 glass Substances 0.000 claims description 7
- 239000002131 composite material Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 229920001971 elastomer Polymers 0.000 claims description 2
- 239000000806 elastomer Substances 0.000 claims description 2
- 239000000835 fiber Substances 0.000 claims description 2
- 241000256844 Apis mellifera Species 0.000 claims 1
- 239000000203 mixture Substances 0.000 claims 1
- 239000007787 solid Substances 0.000 claims 1
- 238000010276 construction Methods 0.000 abstract description 3
- 230000003044 adaptive effect Effects 0.000 description 7
- 230000015572 biosynthetic process Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000005755 formation reaction Methods 0.000 description 4
- 229910000521 B alloy Inorganic materials 0.000 description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 238000010008 shearing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000002520 smart material Substances 0.000 description 1
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Abstract
The invention discloses a kind of wing with self adaptation variable camber trailing edge, including main wing, rim segment after the back rest and variable camber, after described variable camber, rim segment is connected with main wing by the back rest, after described variable camber, rim segment includes upper surface eyelid covering and lower surface eyelid covering, first end of upper surface eyelid covering is connected with the back rest respectively with the first end of lower surface eyelid covering, the other end of upper surface eyelid covering is connected by rigidity trailing edge with the other end of lower surface eyelid covering, upper surface eyelid covering is connected by a slide mechanism near the part of rigidity trailing edge with lower surface eyelid covering, described slide mechanism is connected with the back rest by shape memory actuator.The wing with self adaptation variable camber trailing edge of technical solution of the present invention compared with similar wing compare, have that simple in construction, light weight, development cost be low, flying quality advantages of higher, the aeroperformance of aircraft can be greatly improved, improve the pneumatic efficiency of aircraft, oil consumption can be reduced, reduce the use cost of total life cycle.
Description
Technical field
The present invention relates to a kind of wing structure, particularly relate to a kind of wing structure with adaptive performance.
Background technology
Improve aircraft aerodynamic performance, realize the emphasis that efficient, flexible, safe flight always is that airplane design personnel study, along with rudder face replacements such as raising and the variation of aerial mission of vehicle flight speeds, the front and rear edges wing flaps that chain of command is commonly used from deformable control surface in early days.Even to this day, utilize rudder face to handle and be also faced with the puzzlement being difficult in adapt to some state of flight.It it is still approximation rigidity due to wing itself, it is difficult to regulate in real time the aeroperformance of wing according to aircraft flight condition, and front and rear edges chain of command have employed complex hinged system, not only increase aircraft weight to be also easy to cause vibration, noise and structural fatigue to destroy, the maneuverability and the mobility that make aircraft are extremely restricted, and the birds in nature can need to adjust the state of flight of self according to flight at any time, thereby keep higher efficiency.Adaptive wing is exactly that the mankind are inspired by Bird Flight, with smart material and structure, efficiently based on the technology such as actuator, sensor, subject and the technology such as integrated use aerodynamic, modern information technologies, aircraft Multidisciplinary Optimization, modern control theory, aircraft performance is improved to adapt to the change of aircraft flight condition and aerial mission by realizing the requirement of " on-demand deformation ", thus the optimum pneumatic profile needed for remaining flight.
Existing adaptive wing variable camber trailing edge formations there is no the version entering reality application, and major defect is that wing structure is the poorest with the compatibility of eyelid covering, it is difficult to integrated；Deformation pattern many employings mechanical type, mechanism is complicated, weight is big；The flexible covering that can carry the while of having deformation continuous, smooth has bigger defect in structural stability, fatigue properties and compatibility, it is difficult to actual application.Additionally, also with there being a set of stable, reliable driving means, could realize in aircraft flight, wing changes self camber according to state of flight.These requirements realize simultaneously, substantially increase construction weight, add mechanism's complexity, improve development cost and technical difficulty.
Summary of the invention
Technical problem
The technical problem to be solved in the present invention be provide one can realize adaptive wing variable camber trailing edge formations design, it can solve existing adaptive wing exist structure/eyelid covering incompatible, deformation mechanism is complicated, weight is big, development cost is high, the problem of flexible covering poor reliability.
Technical scheme
In order to solve above-mentioned technical problem, the wing with self adaptation variable camber trailing edge of the present invention includes main wing, rim segment after the back rest and variable camber, after described variable camber, rim segment is connected with main wing by the back rest, after described variable camber, rim segment includes upper surface eyelid covering and lower surface eyelid covering, first end of upper surface eyelid covering is connected with the back rest respectively with the first end of lower surface eyelid covering, the other end of upper surface eyelid covering is connected by rigidity trailing edge with the other end of lower surface eyelid covering, upper surface eyelid covering is connected by a slide mechanism near the part of rigidity trailing edge with lower surface eyelid covering, described slide mechanism is connected with the back rest by shape memory actuator.
Further, described slide mechanism is made up of the slide block being slidably connected and guide rail, and wherein slide block is fixed on the upper surface eyelid covering inner side near rigidity trailing edge, and guide rail is fixed on the lower surface eyelid covering inner side near rigidity trailing edge.Described slide block is connected by internal bearing with guide rail, forms linear motion pair.
Further, it is provided with honeycomb core eyelid covering between described lower surface eyelid covering and rigidity trailing edge.When upper and lower surface eyelid covering produces slip or shearing slip relatively by slide block/slide rail, and honeycomb core cover portion is compressed, thus realizes continuous, smooth the deflecting down of trailing edge.
Further, described honeycomb core eyelid covering is 0 Poisson's ratio honeycomb core eyelid covering, is constituted by fibre reinforced elastomer layer and POM honeycomb core are compound.
Further, described shape memory actuator is made up of first, second shape-memory alloy wire, and first described shape-memory alloy wire the first end is connected with the back rest, and the second end is connected with slide block；Second described shape-memory alloy wire the first end is connected with the back rest, and the second end is connected with guide rail.
Further, upper surface eyelid covering and lower surface skin material are Glass/Epoxy Composites.
In technical scheme, utilizing shape-memory alloy wire as the driver of skin morph, drive eyelid covering directly to deform, wherein, upper and lower skin realizes relatively sliding by slide block/guide rail mechanism, finally realizes the variable camber of trailing edge.When shape wing B alloy wire drives upper surface eyelid covering to deflect down, the second shape-memory alloy wire does not works.Meanwhile, by slide block, sliding track mechanism, lower surface eyelid covering is also with deflecting down.Upper and lower surface eyelid covering is produced by slide block/slide rail and relatively slides or shearing slip, then honeycomb skin part is compressed, thus realizes continuous, smooth the deflecting down of trailing edge.Otherwise, it is possible to achieve upward deflecting of trailing edge.
Beneficial effect
The wing with self adaptation variable camber trailing edge of technical solution of the present invention compared with similar wing compare, have that simple in construction, light weight, development cost be low, flying quality advantages of higher, the aeroperformance of aircraft can be greatly improved, improve the pneumatic efficiency of aircraft, oil consumption can be reduced, reduce the use cost of total life cycle.In self adaptation variable camber trailing edge formations designs, one of most important factor is glass/epoxy compound that a kind of yield strength is high with the ratio of elastic modelling quantity, glass/epoxy compound is widely used in Aero-Space, designing technique is ripe, can obtain the version needed for adaptive wing variable camber trailing edge by specialized designs.Meanwhile, the present invention, by existing glass/epoxy compound design means, can be greatly reduced R&D costs, and develop skill feasibility.Standard is selected according to the flexible material that compliant mechanism proposes, glass/epoxy compound that the present invention uses, its yield strength is up to 29 with the ratio of elastic modelling quantity, far above common metal or composite (common iron is 7-8), has the high and low density of reliability and low cost etc. a little.In the long run, use adaptive wing variable camber trailing edge formations, the optimization of aerodynamic characteristic can be ensured in big flight envelope, improve fuel efficiency, improve flight quality, promote security performance, improve lift-drag ratio, reduce radius of turn, improve maneuverability, the frame for movement that tradition rudder face is complicated can also be removed from, reduce aerodynamic noise etc..
Accompanying drawing explanation
Fig. 1 be one embodiment of the invention have self adaptation variable camber trailing edge from wing overview；
Fig. 2 is variable camber trailing edge partial view in embodiment illustrated in fig. 1；
Fig. 3 is the front view of Fig. 2；
Front view when Fig. 4 is that in the embodiment shown in Fig. 1, trailing edge deflects down 10 °.
Detailed description of the invention
Below in conjunction with accompanying drawing, technical scheme is described further.
Such as Fig. 1, shown in Fig. 2, the wing with self adaptation variable camber trailing edge of the present embodiment, including main wing 1, rim segment 3 after the back rest 2 and variable camber, after described variable camber, rim segment 3 is connected with main wing 1 by the back rest 2, after described variable camber, rim segment 3 includes upper surface eyelid covering 5 and lower surface eyelid covering 6, first end of upper surface eyelid covering 5 is connected with the back rest 2 respectively with the first end of lower surface eyelid covering 6, the other end of upper surface eyelid covering 5 is connected by rigidity trailing edge 4 with the other end of lower surface eyelid covering 6, upper surface eyelid covering 5 is connected by a slide mechanism near the part of rigidity trailing edge 4 with lower surface eyelid covering 6, described slide mechanism is connected with the back rest 2 by shape memory actuator.
As shown in Figure 2 and Figure 3, described slide mechanism is made up of the slide block 7 being slidably connected and guide rail 8, and wherein slide block 7 is fixed on the upper surface eyelid covering 5 inner side near rigidity trailing edge 4, and guide rail 8 is fixed on the lower surface eyelid covering 6 inner side near rigidity trailing edge 4.Honeycomb core eyelid covering 9 it is provided with between lower surface eyelid covering 6 and rigidity trailing edge 4.Shape memory actuator is made up of the first shape-memory alloy wire 10 and the second shape-memory alloy wire 11, and the first described shape-memory alloy wire 10 first end is connected with the back rest 2, and the second end is connected with slide block 7；The second described shape-memory alloy wire 11 first end is connected with the back rest 2, and the second end is connected with guide rail 8.
As shown in Figure 3, Figure 4, utilize shape-memory alloy wire 10,11 as the driver of skin morph, driving and directly deformed by the eyelid covering of glass/epoxy compound manufacture, upper surface eyelid covering 5 realizes relative slip with lower surface eyelid covering 6 by slide block/guide rail mechanism, finally realizes the variable camber of trailing edge.As shown in Figure 4, the first shape wing B alloy wire 10 drives upper surface eyelid covering 5 to deflect down, and the second shape-memory alloy wire 11 does not works.Meanwhile, by slide block 7, slide rail 8 mechanism, lower surface eyelid covering 6 is also with deflecting down, and honeycomb core eyelid covering 9 part is compressed, thus realizes continuous, smooth the deflecting down of trailing edge section.Otherwise, continuous, smooth the upward deflecting of trailing edge section can be realized.
Claims (4)
1. there is a wing for self adaptation variable camber trailing edge, including main wing (1), the back rest (2) and variable camber trailing edge
Section (3), after described variable camber, rim segment (3) is connected with main wing (1) by the back rest (2), its feature
Being, after described variable camber, rim segment (3) includes upper surface eyelid covering (5) and lower surface eyelid covering (6),
First end of upper surface eyelid covering (5) is connected with the back rest (2) respectively with the first end of lower surface eyelid covering (6)
Connecing, the other end of upper surface eyelid covering (5) and the other end of lower surface eyelid covering (6) are by rigidity trailing edge (4)
Being connected, upper surface eyelid covering (5) and lower surface eyelid covering (6) pass through near the part of rigidity trailing edge (4)
One slide mechanism is connected, and described slide mechanism is connected with the back rest (2) by shape memory actuator；
Described slide mechanism is made up of the slide block (7) being slidably connected and guide rail (8), and wherein slide block (7) is solid
Being scheduled on the upper surface eyelid covering (5) inner side near rigidity trailing edge (4), guide rail (8) is fixed on lower surface and covers
Skin (6) is near the inner side of rigidity trailing edge (4)；Described lower surface eyelid covering (6) and rigidity trailing edge (4)
Between be provided with honeycomb core eyelid covering (9).
There is the wing of self adaptation variable camber trailing edge the most as claimed in claim 1, it is characterised in that described honeybee
Nest core eyelid covering (9) is 0 Poisson's ratio honeycomb core eyelid covering, by fibre reinforced elastomer layer and POM honeycomb core
Compound composition.
There is the wing of self adaptation variable camber trailing edge the most as claimed in claim 1, it is characterised in that described shape
Shape memory actuator is made up of first, second shape-memory alloy wire (10,11), the first described shape
Shape memory alloys silk (10) first end is connected with the back rest (2), and the second end is connected with slide block (7)；Institute
The second shape-memory alloy wire (11) first end stated is connected with the back rest (2), the second end and guide rail (8)
Connect.
There is the wing of self adaptation variable camber trailing edge the most as claimed in claim 1, it is characterised in that upper surface covers
Skin (5) and lower surface eyelid covering (6) material are Glass/Epoxy Composites.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410677233.5A CN104443354B (en) | 2014-11-21 | 2014-11-21 | A kind of wing with self adaptation variable camber trailing edge |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410677233.5A CN104443354B (en) | 2014-11-21 | 2014-11-21 | A kind of wing with self adaptation variable camber trailing edge |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104443354A CN104443354A (en) | 2015-03-25 |
| CN104443354B true CN104443354B (en) | 2016-10-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410677233.5A Active CN104443354B (en) | 2014-11-21 | 2014-11-21 | A kind of wing with self adaptation variable camber trailing edge |
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| Country | Link |
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| CN (1) | CN104443354B (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105523169B (en) * | 2015-12-28 | 2017-11-03 | 哈尔滨工业大学 | A kind of wing rudder face of Variable-Bend |
| US11174002B2 (en) | 2016-02-29 | 2021-11-16 | Flexsys, Inc. | Edge morphing arrangement for an airfoil |
| CN106005367A (en) * | 2016-05-16 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Flutter model with active flexible front edge |
| CN106827991B (en) * | 2017-02-10 | 2019-09-13 | 哈尔滨工业大学 | A kind of empty amphibious aircraft bistable state wing of water |
| CN108045553A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of variable camber trailing edge |
| CN108100226B (en) * | 2017-11-30 | 2021-06-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Variable radius wing leading edge structure |
| CN108090273B (en) * | 2017-12-13 | 2021-05-28 | 中国飞机强度研究所 | Flexible wing trailing edge structure and flexible wing trailing edge structure design method |
| CN108791811B (en) * | 2018-05-25 | 2020-04-10 | 中国航天空气动力技术研究院 | Thermal self-adaptive variable-configuration wing |
| CN108891577A (en) * | 2018-07-13 | 2018-11-27 | 北京工业大学 | A kind of rear variable camber wing driven with piezoelectric fibre composite material |
| CN109533279B (en) * | 2018-12-28 | 2020-10-27 | 西安交通大学 | Flexible wing of morphing aircraft, variable-stiffness skin structure of flexible wing and preparation method of variable-stiffness skin structure |
| CN110116803B (en) * | 2019-04-30 | 2022-05-03 | 南京航空航天大学 | Variable chord length system for blade |
| CN110304269B (en) * | 2019-07-17 | 2021-09-14 | 北京航空航天大学 | Controllable clamp structure for intelligent material driving control surface to deflect |
| 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 |
| CN111572754B (en) * | 2020-04-30 | 2021-09-03 | 南京理工大学 | Anti-wind-gushing device suitable for fixed wing structure |
| CN111661312B (en) * | 2020-05-20 | 2022-03-29 | 北京航空航天大学 | Flexible trailing edge module for trailing edge camber wing |
| CN111924086B (en) * | 2020-07-07 | 2021-12-10 | 北京机电工程研究所 | Deformable mechanism driven by memory alloy |
| CN113232833B (en) * | 2021-05-14 | 2022-03-25 | 南京航空航天大学 | Shape memory alloy stay wire driven variable camber wing and design method thereof |
| CN113602476B (en) * | 2021-08-16 | 2023-08-25 | 江西洪都航空工业集团有限责任公司 | Continuous deformation structure and deformation method for trailing edge of wing |
| CN114633875B (en) * | 2022-03-11 | 2023-07-21 | 成都飞机工业（集团）有限责任公司 | Flexible control surface capable of continuously changing bending degree |
| CN115452308B (en) * | 2022-11-09 | 2023-03-14 | 中国空气动力研究与发展中心高速空气动力研究所 | Deflection angle adjustable structure for measuring control surface manipulation efficiency in wind tunnel |
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| US4053124A (en) * | 1975-08-22 | 1977-10-11 | The Boeing Company | Variable camber airfoil |
| CN101503113A (en) * | 2009-03-23 | 2009-08-12 | 哈尔滨工业大学 | Shape memory spring driven hinder margin camber variable wing |
| GB0920969D0 (en) * | 2009-11-27 | 2010-01-13 | Airbus Operations Ltd | Trailing edge flap |
| CN102700704A (en) * | 2012-05-30 | 2012-10-03 | 南京航空航天大学 | Deformation skin for aircraft |
| CN104139847B (en) * | 2014-07-25 | 2016-05-18 | 哈尔滨工业大学深圳研究生院 | A kind of for the variable trailing edge of the camber of aircraft wing and the leading edge of a wing |
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- 2014-11-21 CN CN201410677233.5A patent/CN104443354B/en active Active
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| CN104443354A (en) | 2015-03-25 |
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