CN104443354A - Wing with self-adaptive variable camber trailing edge - Google Patents
Wing with self-adaptive variable camber trailing edge Download PDFInfo
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- CN104443354A CN104443354A CN201410677233.5A CN201410677233A CN104443354A CN 104443354 A CN104443354 A CN 104443354A CN 201410677233 A CN201410677233 A CN 201410677233A CN 104443354 A CN104443354 A CN 104443354A
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Abstract
The invention discloses a wing with a self-adaptive variable camber trailing edge. The wing comprises a main wing, a rear beam and a variable camber trailing edge section, wherein the variable camber trailing edge section is connected with the main wing through the rear beam; the variable camber trailing edge section comprises an upper surface skin and a lower surface skin; the first end of the upper surface skin and the first end of the lower surface skin are respectively connected with the rear beam; the other end of the upper surface skin and the other end of the lower surface skin are connected through a rigid trailing edge; the parts, close to the rigid trailing edge, of the upper surface skin and the other end of the lower surface skin, are connected through a sliding mechanism; the sliding mechanism is connected with the rear beam through a shape memory driving part. By adopting the technical scheme, compared with a conventional similar wing, the wing with the self-adaptive variable camber trailing edge has the advantages of simple structure, light weight, low research and manufacturing cost, high flying performance and the like, the aerodynamic performance of an aircraft is greatly improved, the aerodynamic efficiency of the aircraft is improved, the oil consumption is reduced, and the use cost of the aircraft in the whole service life is lowered.
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 efficient, flexible, safe flight and always be the emphasis that airplane design personnel study, along with the raising of vehicle flight speeds and the variation of aerial mission, the rudder faces such as the front and rear edges wing flap that control surface is commonly used from early stage deformable controlsurface replace.Even to this day, utilize rudder face to handle and be also faced with the puzzlement being difficult to adapt to some state of flight.Because wing itself is still approximate rigidity, be difficult to the aeroperformance regulating wing according to aircraft flight condition in real time, and front and rear edges control surface have employed comparatively complicated hinged system, not only increasing aircraft weight also easily causes vibration, noise and structural fatigue to destroy, the road-holding property of aircraft and manoevreability are extremely restricted, and the birds of occurring in nature can need according to flight the state of flight adjusting self at any time, keep higher efficiency by this.Adaptive wing is exactly the inspirations of the mankind by Bird Flight, with smart material and structure, based on efficient actuator, sensor technology, subject and the technology such as integrated use aerodynamics, modern information technologies, aircraft Multidisciplinary Optimization, modern control theory, improve aircraft performance to adapt to the change of aircraft flight condition and aerial mission by the requirement realizing " being out of shape as required ", thus remain the optimum pneumatic profile needed for flight.
Existing adaptive wing variable camber trailing edge formations there is no the version entering practical application, and major defect is that the compatibility of wing structure and covering is too poor, is difficult to integrated; Deformation pattern many employings mechanical type, mechanism is complicated, weight is large; The flexible covering that can carry the while of having continuous, smooth distortion has larger defect in structural stability, fatigue characteristic and compatibility, is difficult to practical application.In addition, also with there being a set of stable, failure-free actuating device, could realize in aircraft flight, wing changes self camber according to state of flight.These requirements realize simultaneously, substantially increase structural weight, add mechanism's complexity, improve development cost and technical risk.
Summary of the invention
technical matters
The technical problem to be solved in the present invention is to provide one can realize the design of adaptive wing variable camber trailing edge formations, and it can solve, and structure/covering that existing adaptive wing exists is incompatible, deformation mechanism is complicated, weight is large, development cost is high, the problem of flexible covering poor reliability.
technical scheme
In order to solve above-mentioned technical matters, the wing with self adaptation variable camber trailing edge of the present invention comprises main wing, the back rest and variable camber trailing edge section, described variable camber trailing edge section is connected with main wing by the back rest, described variable camber trailing edge section comprises upper surface covering and lower surface covering, the first end of upper surface covering is connected with the back rest respectively with the first end of lower surface covering, the other end of upper surface covering is connected by rigidity trailing edge with the other end of lower surface covering, upper surface covering is connected by a slide mechanism with the part of lower surface covering near rigidity trailing edge, described slide mechanism is connected with the back rest by shape memory actuator.
Further, described slide mechanism is made up of the slide block of sliding block joint and guide rail, and wherein slide block is fixed on the inner side of upper surface covering near rigidity trailing edge, and guide rail is fixed on the inner side of lower surface covering near rigidity trailing edge.Described slide block is connected by inner bearing with guide rail, forms straight-line motion secondary.
Further, honeycomb core covering is provided with between described lower surface covering and rigidity trailing edge.When upper and lower surface covering produces relative sliding or shearing slip by slide block/slide rail, honeycomb core cover portion is compressed, thus realizes continuous, smooth the deflecting down of trailing edge.
Further, described honeycomb core covering is 0 Poisson's ratio honeycomb core covering, is made up of fibre reinforced elastomer layer and POM honeycomb core compound.
Further, described shape memory actuator is made up of first, second shape-memory alloy wire, and the first described shape-memory alloy wire first end is connected with the back rest, and the second end is connected with slide block; The second described shape-memory alloy wire first end is connected with the back rest, and the second end is connected with guide rail.
Further, upper surface covering and lower surface skin material are Glass/Epoxy Composites.
In technical scheme of the present invention, utilize shape-memory alloy wire as the actuator of skin morph, drive covering to be directly out of shape, wherein, upper and lower skin realizes relative sliding by slide block/guide rail mechanism, finally realizes the variable camber of trailing edge.When shape wing B alloy wire drives upper surface covering to deflect down, the second shape-memory alloy wire does not work.Meanwhile, by slide block, sliding track mechanism, lower surface covering is also along with deflecting down.Upper and lower surface covering produces relative sliding or shearing slip by slide block/slide rail, then honeycomb skin part is compressed, thus realizes continuous, smooth the deflecting down of trailing edge.Otherwise, upward deflecting of trailing edge can be realized.
beneficial effect
The wing with self adaptation variable camber trailing edge of technical solution of the present invention is compared with existing similar wing, have that structure is simple, quality is light, development cost is low, airworthiness advantages of higher, significantly can improve the aeroperformance of aircraft, improve the pneumatic efficiency of aircraft, can oil consumption be reduced, reduce the use cost of total life cycle.In the design of self adaptation variable camber trailing edge formations, one of most important factor is a kind of yield strength glass/epoxy compound high with the ratio of modulus of elasticity, glass/epoxy compound is widely used in aerospace, designing technique is ripe, can obtain the version needed for adaptive wing variable camber trailing edge by customized design.Meanwhile, the present invention, by existing glass/epoxy compound design means, significantly can reduce R&D costs, and develop skill feasibility.According to the flexible material choice criteria that compliant mechanism proposes, glass/epoxy compound that the present invention adopts, the ratio of its yield strength and modulus of elasticity, up to 29, far above common metal or composite material (common iron is 7-8), has the high and low density of reliability and low cost etc. a little.In the long run, adopt adaptive wing variable camber trailing edge formations, the optimization of aerodynamic characteristic can be ensured in large flight envelope, improve fuel efficiency, improve flight quality, promote safety performance, improve 1ift-drag ratio, reduce turn radius, improve road-holding property, the physical construction of traditional rudder face complexity can also be removed from, reduce aerodynamics 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 middle variable camber trailing edge partial view embodiment illustrated in fig. 1;
Fig. 3 is the front elevation of Fig. 2;
Fig. 4 is front elevation when trailing edge deflects down 10 ° in the embodiment shown in Fig. 1.
Detailed description of the invention
Below in conjunction with accompanying drawing, technical scheme of the present invention is described further.
As Fig. 1, shown in Fig. 2, the wing with self adaptation variable camber trailing edge of the present embodiment, comprise main wing 1, the back rest 2 and variable camber trailing edge section 3, described variable camber trailing edge section 3 is connected with main wing 1 by the back rest 2, described variable camber trailing edge section 3 comprises upper surface covering 5 and lower surface covering 6, the first end of upper surface covering 5 is connected with the back rest 2 respectively with the first end of lower surface covering 6, the other end of upper surface covering 5 is connected by rigidity trailing edge 4 with the other end of lower surface covering 6, upper surface covering 5 is connected by a slide mechanism with the part of lower surface covering 6 near rigidity trailing edge 4, 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 of sliding block joint and guide rail 8, and wherein slide block 7 is fixed on the inner side of upper surface covering 5 near rigidity trailing edge 4, and guide rail 8 is fixed on the inner side of lower surface covering 6 near rigidity trailing edge 4.Honeycomb core covering 9 is provided with between lower surface 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 actuator of skin morph, drive and be directly out of shape by the covering of glass/epoxy compound manufacture, upper surface covering 5 and lower surface covering 6 realize relative sliding by slide block/guide rail mechanism, finally realize the variable camber of trailing edge.As shown in Figure 4, the first shape wing B alloy wire 10 drives upper surface covering 5 to deflect down, and the second shape-memory alloy wire 11 does not work.Meanwhile, by slide block 7, slide rail 8 mechanism, lower surface covering 6 is also along with deflecting down, and honeycomb core 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 (6)
1. one kind has the wing of self adaptation variable camber trailing edge, comprise main wing (1), the back rest (2) and variable camber trailing edge section (3), described variable camber trailing edge section (3) is connected with main wing (1) by the back rest (2), it is characterized in that, described variable camber trailing edge section (3) comprises upper surface covering (5) and lower surface covering (6), the first end of upper surface covering (5) is connected with the back rest (2) respectively with the first end of lower surface covering (6), the other end of upper surface covering (5) is connected by rigidity trailing edge (4) with the other end of lower surface covering (6), upper surface covering (5) is connected by a slide mechanism with the part of lower surface covering (6) near rigidity trailing edge (4), described slide mechanism is connected with the back rest (2) by shape memory actuator.
2. there is the wing of self adaptation variable camber trailing edge as claimed in claim 1, it is characterized in that, described slide mechanism is made up of the slide block (7) of sliding block joint and guide rail (8), wherein slide block (7) is fixed on the inner side of upper surface covering (5) near rigidity trailing edge (4), and guide rail (8) is fixed on the inner side of lower surface covering (6) near rigidity trailing edge (4).
3. there is the wing of self adaptation variable camber trailing edge as claimed in claim 1 or 2, it is characterized in that, between lower surface covering (6) and rigidity trailing edge (4), be provided with honeycomb core covering (9).
4. have the wing of self adaptation variable camber trailing edge as claimed in claim 3, it is characterized in that, described honeycomb core covering (9) is 0 Poisson's ratio honeycomb core covering, is made up of fibre reinforced elastomer layer and POM honeycomb core compound.
5. there is the wing of self adaptation variable camber trailing edge as claimed in claim 1, it is characterized in that, described shape memory actuator is made up of first, second shape-memory alloy wire (10,11), described the first shape-memory alloy wire (10) first end is connected with the back rest (2), and the second end is connected with slide block (7); Described the second shape-memory alloy wire (11) first end is connected with the back rest (2), and the second end is connected with guide rail (8).
6. have the wing of self adaptation variable camber trailing edge as claimed in claim 1, it is characterized in that, upper surface covering (5) and lower surface covering (6) material are Glass/Epoxy Composites.
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| CN201410677233.5A CN104443354B (en) | 2014-11-21 | 2014-11-21 | A kind of wing with self adaptation variable camber trailing edge |
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| CN201410677233.5A CN104443354B (en) | 2014-11-21 | 2014-11-21 | A kind of wing with self adaptation variable camber trailing edge |
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| CN104443354B CN104443354B (en) | 2016-10-12 |
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Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105523169A (en) * | 2015-12-28 | 2016-04-27 | 哈尔滨工业大学 | Bendable wing control surface |
| 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 |
| CN106827991A (en) * | 2017-02-10 | 2017-06-13 | 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 |
| CN108090273A (en) * | 2017-12-13 | 2018-05-29 | 中国飞机强度研究所 | A kind of flexible wing trailing edge formations and flexible wing trailing edge formations design method |
| CN108100226A (en) * | 2017-11-30 | 2018-06-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of leading edge of a wing support frame and variable radius leading edge of a wing structure |
| CN108698684A (en) * | 2016-02-29 | 2018-10-23 | 弗莱克斯塞思股份有限公司 | Edge deformation device for aerofoil |
| CN108791811A (en) * | 2018-05-25 | 2018-11-13 | 中国航天空气动力技术研究院 | A kind of adaptive strain configuration wing of heat |
| 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 |
| CN109533279A (en) * | 2018-12-28 | 2019-03-29 | 西安交通大学 | A kind of variant aircraft flexible wing and its variation rigidity stressed-skin construction and preparation method |
| CN110116803A (en) * | 2019-04-30 | 2019-08-13 | 南京航空航天大学 | A kind of change chord length system for blade |
| CN110304269A (en) * | 2019-07-17 | 2019-10-08 | 北京航空航天大学 | A kind of controllable clamp structure of intellectual material driving control surface deflection |
| 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 |
| CN111572754A (en) * | 2020-04-30 | 2020-08-25 | 南京理工大学 | Anti-wind-gushing device suitable for fixed wing structure |
| CN111661312A (en) * | 2020-05-20 | 2020-09-15 | 北京航空航天大学 | Flexible trailing edge module for trailing edge camber wing |
| CN111924086A (en) * | 2020-07-07 | 2020-11-13 | 北京机电工程研究所 | Deformable mechanism driven by memory alloy |
| CN113232833A (en) * | 2021-05-14 | 2021-08-10 | 南京航空航天大学 | Shape memory alloy stay wire driven variable camber wing and design method thereof |
| CN113602476A (en) * | 2021-08-16 | 2021-11-05 | 江西洪都航空工业集团有限责任公司 | Continuous deformation structure and deformation method for wing trailing edge |
| CN114633875A (en) * | 2022-03-11 | 2022-06-17 | 成都飞机工业（集团）有限责任公司 | Flexible control surface capable of continuously changing camber |
| CN115452308A (en) * | 2022-11-09 | 2022-12-09 | 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| US20110127385A1 (en) * | 2009-11-27 | 2011-06-02 | Airbus Operations Limited | Trailing edge flap |
| CN102700704A (en) * | 2012-05-30 | 2012-10-03 | 南京航空航天大学 | Deformation skin for aircraft |
| CN104139847A (en) * | 2014-07-25 | 2014-11-12 | 哈尔滨工业大学深圳研究生院 | Trailing edge and leading edge with adjustable degrees of curvature for aircraft wing |
-
2014
- 2014-11-21 CN CN201410677233.5A patent/CN104443354B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| US20110127385A1 (en) * | 2009-11-27 | 2011-06-02 | Airbus Operations Limited | Trailing edge flap |
| CN102700704A (en) * | 2012-05-30 | 2012-10-03 | 南京航空航天大学 | Deformation skin for aircraft |
| CN104139847A (en) * | 2014-07-25 | 2014-11-12 | 哈尔滨工业大学深圳研究生院 | Trailing edge and leading edge with adjustable degrees of curvature for aircraft wing |
Non-Patent Citations (1)
| Title |
|---|
| 刘力搏: "基于可变形蒙皮的柔性后缘力学分析", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (30)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105523169A (en) * | 2015-12-28 | 2016-04-27 | 哈尔滨工业大学 | Bendable wing control surface |
| CN108698684A (en) * | 2016-02-29 | 2018-10-23 | 弗莱克斯塞思股份有限公司 | Edge deformation device for aerofoil |
| 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 |
| CN106827991A (en) * | 2017-02-10 | 2017-06-13 | 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 |
| CN108100226A (en) * | 2017-11-30 | 2018-06-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of leading edge of a wing support frame and variable radius leading edge of a wing structure |
| CN108090273A (en) * | 2017-12-13 | 2018-05-29 | 中国飞机强度研究所 | A kind of flexible wing trailing edge formations and flexible wing trailing edge formations design method |
| 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 |
| CN108791811A (en) * | 2018-05-25 | 2018-11-13 | 中国航天空气动力技术研究院 | A kind of adaptive strain configuration wing of heat |
| 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 |
| CN109533279A (en) * | 2018-12-28 | 2019-03-29 | 西安交通大学 | A kind of variant aircraft flexible wing and its variation rigidity stressed-skin construction and preparation method |
| 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 |
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| 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 |
| CN110304269A (en) * | 2019-07-17 | 2019-10-08 | 北京航空航天大学 | A kind of controllable clamp structure of intellectual material driving control surface deflection |
| 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 |
| 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 |
| CN111572754A (en) * | 2020-04-30 | 2020-08-25 | 南京理工大学 | Anti-wind-gushing device suitable for fixed wing structure |
| CN111661312A (en) * | 2020-05-20 | 2020-09-15 | 北京航空航天大学 | Flexible trailing edge module for trailing edge camber wing |
| 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 |
| CN111924086A (en) * | 2020-07-07 | 2020-11-13 | 北京机电工程研究所 | Deformable mechanism driven by memory alloy |
| CN113232833A (en) * | 2021-05-14 | 2021-08-10 | 南京航空航天大学 | Shape memory alloy stay wire driven variable camber wing and design method thereof |
| CN113602476A (en) * | 2021-08-16 | 2021-11-05 | 江西洪都航空工业集团有限责任公司 | Continuous deformation structure and deformation method for wing trailing edge |
| 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 |
| CN114633875A (en) * | 2022-03-11 | 2022-06-17 | 成都飞机工业（集团）有限责任公司 | Flexible control surface capable of continuously changing camber |
| 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 |
| CN115452308A (en) * | 2022-11-09 | 2022-12-09 | 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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