CN101503113A - Shape memory spring driven hinder margin camber variable wing - Google Patents
Shape memory spring driven hinder margin camber variable wing Download PDFInfo
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- CN101503113A CN101503113A CNA2009100716133A CN200910071613A CN101503113A CN 101503113 A CN101503113 A CN 101503113A CN A2009100716133 A CNA2009100716133 A CN A2009100716133A CN 200910071613 A CN200910071613 A CN 200910071613A CN 101503113 A CN101503113 A CN 101503113A
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Abstract
The invention provides a wing with changeable trailing edge camber driven by a shape memory spring, relating to a wing with a changeable trailing edge camber, and aiming at the problems of traditional airplanes that a mechanism is complex and heavy, airflow breakaway is quite early and aerodynamic efficiency is low. The front end face and the back end face of an upper metal plate are fixedly connected with the front end faces of a connecting plate and the trailing edge; the front end face and the back end face of the lower metal plate are fixedly connected with the front end face of the connecting plate and the trailing edge; the same side surface of the upper metal plate and the lower metal plate are fixed with an upper prop stay and a lower prop stay; the two ends of a first shape memory spring are fixedly connected with a fixed plate and the upper metal plate; the two ends of a second shape memory spring are fixedly connected with the front end faces of the upper prop stay and the trailing edge; the two ends of a third shape memory spring are fixedly connected with the fixed plate and the lower metal plate; and the two ends of a fourth shape memory spring are fixedly connected with the front end faces of the lower prop stay and the trailing edge. The invention has the advantages of light weight, simple structure and high aerodynamic efficiency.
Description
Technical field
The present invention relates to a kind of variable trailing edge camber wing.
Background technology
At present, the control surface of most of aircrafts (as aileron and wing flap) all changes wing camber by mechanical driving mechanism, handles required aerodynamic force for aircraft provides.But the control surface of this employing mechanical driving mechanism exists mechanism's complexity, heaviness, burbling is too early, pneumatic efficiency is low problem.
Summary of the invention
The purpose of this invention is to provide the variable trailing edge camber wing that a kind of shape memory spring drives, replace traditional mechanical driving mechanism, to solve existing aircraft control surface mechanism complexity, heaviness, burbling is too early, pneumatic efficiency is low problem.
The present invention solves the problems of the technologies described above the technical scheme of taking to be: variable trailing edge camber wing of the present invention comprises trailing edge; Variable trailing edge camber wing of the present invention also comprises sheet metal, first shape memory spring, upper supporting column, second shape memory spring, the 3rd shape memory spring, lower supporting rod, the 4th shape memory spring, following sheet metal and connecting panel; The described front end face of going up sheet metal is captiveed joint with the upper end of connecting panel, the aft end face of last sheet metal is captiveed joint with the upper end of the front end face of trailing edge, the described front end face of sheet metal is down captiveed joint with the lower end of connecting panel, the aft end face of following sheet metal is captiveed joint with the lower end of the front end face of trailing edge, the surface, the same side of last sheet metal and following sheet metal is vertically gone up and is fixed with upper supporting column and lower supporting rod respectively, captive joint with last sheet metal with adapter plate respectively in the two ends of described first shape memory spring, captive joint with the front end face of upper supporting column and trailing edge respectively in the two ends of described second shape memory spring, captiveing joint with following sheet metal with adapter plate respectively in the two ends of described the 3rd shape memory spring, captives joint with the front end face of lower supporting rod and trailing edge respectively in the two ends of described the 4th shape memory spring.
The invention has the beneficial effects as follows: but smooth, continuous variable camber wing technology adopted in the present invention, cancelled the mechanical type hinge, make wing in deformation process, the aerofoil surface smooth and continuous is seamless, when avoiding control surface deflection like this, because the aerofoil surface slope is undergone mutation, produce burbling, thereby improve the distribution of pressure of wing.The smooth and continuous of wing camber changes the 1ift-drag ratio that can also improve under the existing flying condition, by adjusting maximum lift-drag ratio, has improved maximum lift coefficient, thereby has expanded cruising rang.Another effect that changes wing camber is that the buffet boundary in cruise Mach range has been widened, and makes aircraft can obtain higher lift coefficient awing.Aircraft is flown on higher sea level elevation, and avoid wing when design to adopt the low wing load restriction excessive weight.In addition, it is seamless that variable trailing edge camber wing aerofoil surface in deformation process remains smooth and continuous, reduced radar returns widely, fundamentally improved the stealthy performance of aircraft.For scout, adopt variable trailing edge camber wing can improve its cruising ability and increase voyage, its stealthy performance also greatly improves simultaneously; For seating plane, adopt variable trailing edge camber wing to reduce its fuel oil consumption, improved the economy of passenger plane.Therefore, the present invention compares with the mechanical driving mechanism that extensively adopts now, advantage with light weight, simple in structure, easy to maintenance, continuous deflection of trailing edge, thereby the operational mobility and the safety that can reduce the aircraft maintenance cost widely, improve armament systems have reduced the weaponry risk in the process under arms.In the long run, the variation on this aircraft configuration can make aircraft reach bigger 1ift-drag ratio, and has high fuel efficiency, high flight quality, high safety performance and better operability, landing speed faster, adapts to the liftoff site of various conditions.
Description of drawings
Fig. 1 is that integral structure master of the present invention looks scheme drawing (trailing edge 5 not deformation state under), and Fig. 2 is that integral structure master of the present invention looks scheme drawing (under trailing edge 5 deformation states).
The specific embodiment
The specific embodiment one: in conjunction with Fig. 1 present embodiment is described, the variable trailing edge camber wing of present embodiment comprises trailing edge 5; Described variable trailing edge camber wing also comprises sheet metal 1, first shape memory spring 2, upper supporting column 3, second shape memory spring 4, the 3rd shape memory spring 6, lower supporting rod 7, the 4th shape memory spring 8, following sheet metal 9 and connecting panel 10; The described front end face of going up sheet metal 1 is captiveed joint with the upper end of connecting panel 10, the aft end face of last sheet metal 1 is captiveed joint with the upper end of the front end face of trailing edge 5, the described front end face of sheet metal 9 is down captiveed joint with the lower end of connecting panel 10, the aft end face of following sheet metal 9 is captiveed joint with the lower end of the front end face of trailing edge 5, the surface, the same side of last sheet metal 1 and following sheet metal 9 is vertically gone up and is fixed with upper supporting column 3 and lower supporting rod 7 respectively, captive joint with last sheet metal 1 with adapter plate 10 respectively in the two ends of described first shape memory spring 2, captive joint with the front end face of trailing edge 5 with upper supporting column 3 respectively in the two ends of described second shape memory spring 4, captiveing joint with following sheet metal 9 with adapter plate 10 respectively in the two ends of described the 3rd shape memory spring 6, captives joint with the front end face of trailing edge 5 with lower supporting rod 7 respectively in the two ends of described the 4th shape memory spring 8.
The specific embodiment two: present embodiment is described in conjunction with Fig. 1, present embodiment with the difference of the specific embodiment one is: captive joint with the middle part of last sheet metal 1 in the two ends of first shape memory spring 2 of the present embodiment middle part of adapter plate 10 respectively, captive joint with the middle part of the front end face of trailing edge 5 with the upper end of upper supporting column 3 respectively in the two ends of described second shape memory spring 4, captiveing joint with the middle part of following sheet metal 9 with the middle part of adapter plate 10 respectively in the two ends of described the 3rd shape memory spring 6, captives joint with the middle part of the front end face of trailing edge 5 with the lower end of lower supporting rod 7 respectively in the two ends of described the 4th shape memory spring 8.So be provided with, can make trailing edge 5 cambers reach optimum regime, and the easiest flexural deformation.
The specific embodiment three: present embodiment is described in conjunction with Fig. 1, the material of first shape memory spring 2, second shape memory spring 4, the 3rd shape memory spring 6 and the 4th shape memory spring 8 of present embodiment is the TiNi marmem, has shape memory effect preferably.Other is identical with the specific embodiment one or two.
The specific embodiment four: in conjunction with Fig. 1 present embodiment is described, the last sheet metal 1 of present embodiment and the material of following sheet metal 9 are steel, iron or aluminum metallic material, can select according to the needs that use.Other is identical with the specific embodiment one or two.
The specific embodiment five: in conjunction with Fig. 1 present embodiment is described, the thickness of the last sheet metal 1 of present embodiment and the thickness of following sheet metal 9 are equal and be 0.1mm～0.5mm.So be provided with, can satisfy the requirement of strength of variable trailing edge camber wing.Other is identical with the specific embodiment one, two, three or four.
The specific embodiment six: in conjunction with Fig. 1 present embodiment is described, the thickness of the last sheet metal 1 of present embodiment and the thickness of following sheet metal 9 are 0.3mm.Under the prerequisite of the requirement of strength that guarantees variable trailing edge camber wing, also can alleviate overall weight.Other is identical with the specific embodiment five.
The specific embodiment seven: in conjunction with Fig. 1 present embodiment is described, the upper supporting column 3 and the lower supporting rod 7 of present embodiment are coaxial.So be provided with, be convenient to the wing bending.Other is identical with the specific embodiment one.
Principle of work: the process of a complete Variable Geometry Wing variable camber is: 1. the 3rd shape memory spring 6 is heated; 2. after heating after a while, the 3rd shape memory spring 6 begins shrinkage distortions; 3. descend sheet metal 9 under the effect of the 3rd shape memory spring 6 convergent forces, produce flexural deformation; 4. go up sheet metal 1 and will make curvilinear movement, thereby make trailing edge 5 that downward deflection (referring to accompanying drawing 2) take place around upper supporting column 3.Otherwise, if want to make trailing edge 5 that deflection upwards takes place, only need first shape memory spring 2 is heated, after heating after a while, the 2 beginning shrinkage distortions of first shape memory spring, last sheet metal 1 produces flexural deformation under the effect of first shape memory spring, 2 convergent forces, following sheet metal 9 will be made curvilinear movement around lower supporting rod 7, thereby make trailing edge 5 that deflection upwards take place.
Claims (6)
1, a kind of variable trailing edge camber wing of shape memory spring driving, described variable trailing edge camber wing comprises trailing edge (5); It is characterized in that: described variable trailing edge camber wing also comprises sheet metal (1), first shape memory spring (2), upper supporting column (3), second shape memory spring (4), the 3rd shape memory spring (6), lower supporting rod (7), the 4th shape memory spring (8), following sheet metal (9) and connecting panel (10); The described front end face of going up sheet metal (1) is captiveed joint with the upper end of connecting panel (10), the aft end face of last sheet metal (1) is captiveed joint with the upper end of the front end face of trailing edge (5), the described front end face of sheet metal (9) is down captiveed joint with the lower end of connecting panel (10), the aft end face of following sheet metal (9) is captiveed joint with the lower end of the front end face of trailing edge (5), the surface, the same side of last sheet metal (1) and following sheet metal (9) is vertically gone up and is fixed with upper supporting column (3) and lower supporting rod (7) respectively, captive joint with last sheet metal (1) with adapter plate (10) respectively in the two ends of described first shape memory spring (2), captive joint with the front end face of trailing edge (5) with upper supporting column (3) respectively in the two ends of described second shape memory spring (4), captiveing joint with following sheet metal (9) with adapter plate (10) respectively in the two ends of described the 3rd shape memory spring (6), captives joint with the front end face of trailing edge (5) with lower supporting rod (7) respectively in the two ends of described the 4th shape memory spring (8).
2, the variable trailing edge camber wing of a kind of shape memory spring driving according to claim 1, it is characterized in that: the material of described first shape memory spring (2), second shape memory spring (4), the 3rd shape memory spring (6) and the 4th shape memory spring (8) is the TiNi marmem.
3, the variable trailing edge camber wing of a kind of shape memory spring driving according to claim 1 is characterized in that: the described material that goes up sheet metal (1) and following sheet metal (9) is steel, iron or aluminum metallic material.
4, the variable trailing edge camber wing that drives according to claim 1,2 or 3 described a kind of shape memory spring is characterized in that: the thickness of the described thickness of going up sheet metal (1) and following sheet metal (9) is equal and be 0.1mm～0.5mm.
5, the variable trailing edge camber wing of a kind of shape memory spring driving according to claim 4 is characterized in that: the thickness of described upward sheet metal (1) and the thickness of following sheet metal (9) are 0.3mm.
6, the variable trailing edge camber wing of a kind of shape memory spring driving according to claim 1, it is characterized in that: described upper supporting column (3) and lower supporting rod (7) are coaxial.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2009100716133A CN101503113A (en) | 2009-03-23 | 2009-03-23 | Shape memory spring driven hinder margin camber variable wing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2009100716133A CN101503113A (en) | 2009-03-23 | 2009-03-23 | Shape memory spring driven hinder margin camber variable wing |
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| CN101503113A true CN101503113A (en) | 2009-08-12 |
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| CNA2009100716133A Pending CN101503113A (en) | 2009-03-23 | 2009-03-23 | Shape memory spring driven hinder margin camber variable wing |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103387048A (en) * | 2013-07-27 | 2013-11-13 | 哈尔滨工业大学 | Variant flexible tail edge structure based on bionic conception |
| CN103419925A (en) * | 2012-05-16 | 2013-12-04 | 波音公司 | Shape memory alloy active spars for blade twist |
| 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 |
| CN104379445A (en) * | 2012-04-30 | 2015-02-25 | 空中客车营运有限公司 | Morphing aerofoil |
| CN104443354A (en) * | 2014-11-21 | 2015-03-25 | 南京航空航天大学 | Wing with self-adaptive variable camber trailing edge |
| US9457887B2 (en) | 2014-03-05 | 2016-10-04 | Toyota Motor Engineering & Manufacturing North America, Inc. | Smart material trailing edge variable chord morphing wing |
| 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 |
| US9856012B2 (en) | 2012-06-21 | 2018-01-02 | Bombardier Inc. | Morphing wing for an aircraft |
| CN107628228A (en) * | 2017-08-28 | 2018-01-26 | 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 continuously bent structure |
| CN107628229A (en) * | 2017-08-28 | 2018-01-26 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of continuous variable camber structure of the truss-like leading edge of a wing |
| CN108100228A (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 active flexible Telescopic truss structure |
| CN108839788A (en) * | 2018-07-05 | 2018-11-20 | 西北工业大学 | A kind of variable camber trailing edge based on compliant mechanism |
| CN109572997A (en) * | 2018-11-19 | 2019-04-05 | 南京航空航天大学 | Using the aircraft wing of marmem and motor composite drive |
| 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 |
| CN110758715A (en) * | 2019-12-06 | 2020-02-07 | 中国民航大学 | Deformable wing based on shape memory alloy driving |
| CN111717368A (en) * | 2020-07-01 | 2020-09-29 | 电子科技大学 | Flexible wing structure based on shape memory alloy and manufacturing method thereof |
| 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 |
| CN113247237A (en) * | 2020-02-11 | 2021-08-13 | 波音公司 | Adaptive airfoil |
-
2009
- 2009-03-23 CN CNA2009100716133A patent/CN101503113A/en active Pending
Cited By (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104379445A (en) * | 2012-04-30 | 2015-02-25 | 空中客车营运有限公司 | Morphing aerofoil |
| CN104379445B (en) * | 2012-04-30 | 2016-05-11 | 空中客车营运有限公司 | Distortion aerofoil |
| CN103419925A (en) * | 2012-05-16 | 2013-12-04 | 波音公司 | Shape memory alloy active spars for blade twist |
| CN103419925B (en) * | 2012-05-16 | 2018-12-28 | 波音公司 | Marmem active spar for blade twist |
| US9856012B2 (en) | 2012-06-21 | 2018-01-02 | Bombardier Inc. | Morphing wing for an aircraft |
| CN103387048A (en) * | 2013-07-27 | 2013-11-13 | 哈尔滨工业大学 | Variant flexible tail edge structure based on bionic conception |
| CN103387048B (en) * | 2013-07-27 | 2016-01-06 | 哈尔滨工业大学 | The variant flexible trailing edge structure of pneumatic actuation/distortion/carrying integration |
| US9457887B2 (en) | 2014-03-05 | 2016-10-04 | Toyota Motor Engineering & Manufacturing North America, Inc. | Smart material trailing edge variable chord morphing wing |
| 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 |
| 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 |
| CN104443354A (en) * | 2014-11-21 | 2015-03-25 | 南京航空航天大学 | Wing with self-adaptive variable camber trailing edge |
| 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 |
| CN107628229A (en) * | 2017-08-28 | 2018-01-26 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of continuous variable camber structure of the truss-like leading edge of a wing |
| CN107628228A (en) * | 2017-08-28 | 2018-01-26 | 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 continuously bent structure |
| CN108100228A (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 active flexible Telescopic truss structure |
| CN108839788A (en) * | 2018-07-05 | 2018-11-20 | 西北工业大学 | A kind of variable camber trailing edge based on compliant mechanism |
| CN108839788B (en) * | 2018-07-05 | 2021-08-03 | 西北工业大学 | Variable camber wing trailing edge based on compliant mechanism |
| CN109572997A (en) * | 2018-11-19 | 2019-04-05 | 南京航空航天大学 | Using the aircraft wing of marmem and motor composite drive |
| 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 |
| CN110758715A (en) * | 2019-12-06 | 2020-02-07 | 中国民航大学 | Deformable wing based on shape memory alloy driving |
| CN110758715B (en) * | 2019-12-06 | 2022-11-25 | 中国民航大学 | Deformable wing based on shape memory alloy drive |
| CN113247237A (en) * | 2020-02-11 | 2021-08-13 | 波音公司 | Adaptive airfoil |
| CN111717368A (en) * | 2020-07-01 | 2020-09-29 | 电子科技大学 | Flexible wing structure based on shape memory alloy and manufacturing method thereof |
| CN111717368B (en) * | 2020-07-01 | 2024-04-02 | 电子科技大学 | Flexible wing structure based on shape memory alloy and manufacturing method thereof |
| 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 |
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Open date: 20090812 |