CN114476022B - Variable-thickness wing based on memory metal - Google Patents
Variable-thickness wing based on memory metal Download PDFInfo
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- CN114476022B CN114476022B CN202210213159.6A CN202210213159A CN114476022B CN 114476022 B CN114476022 B CN 114476022B CN 202210213159 A CN202210213159 A CN 202210213159A CN 114476022 B CN114476022 B CN 114476022B
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- 229910052751 metal Inorganic materials 0.000 title claims abstract description 28
- 239000002184 metal Substances 0.000 title claims abstract description 28
- 238000010438 heat treatment Methods 0.000 claims abstract description 58
- 208000002197 Ehlers-Danlos syndrome Diseases 0.000 claims abstract description 17
- 229910001285 shape-memory alloy Inorganic materials 0.000 claims description 86
- 210000001015 abdomen Anatomy 0.000 claims description 3
- 230000004323 axial length Effects 0.000 claims 1
- 230000001105 regulatory effect Effects 0.000 abstract description 5
- 238000005516 engineering process Methods 0.000 description 5
- 241000282414 Homo sapiens Species 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000011161 development Methods 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 241001465754 Metazoa Species 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 229910001000 nickel titanium Inorganic materials 0.000 description 1
- HLXZNVUGXRDIFK-UHFFFAOYSA-N nickel titanium Chemical compound [Ti].[Ti].[Ti].[Ti].[Ti].[Ti].[Ti].[Ti].[Ti].[Ti].[Ti].[Ni].[Ni].[Ni].[Ni].[Ni].[Ni].[Ni].[Ni].[Ni].[Ni].[Ni].[Ni].[Ni].[Ni] HLXZNVUGXRDIFK-UHFFFAOYSA-N 0.000 description 1
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- 239000002520 smart material Substances 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a variable-thickness wing based on memory metal, which comprises: the wing comprises an elastic skin, an end support A, an end support B, a connecting plate and a heating regulation and control device arranged on the connecting plate, wherein the elastic skin is coated on the outer sides of the end support A, the heating regulation and control device and the end support B to form a wing, the wing thickness is regulated by stretching and resetting the elastic skin through the heating regulation and control device, the wing is stretched and reset by utilizing different mechanical properties of memory metal at different temperatures, and the wing skin is combined by utilizing a plurality of memory metal modules to realize larger variable thickness of the wing.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to a variable-thickness wing based on memory metal, which is applied to a subsonic aircraft.
Background
The hawk-like spreading wings in the sky is the most romantic dream since the birth of human beings. From the flying dream of Dunhuang mogao hole people over 1600 years ago, the appearance of kites and Kongming lights, and the flying of Davinci's ' flying of Lun bird ', the human beings fail and explore for numerous times, and finally, the first aircraft in the world is manufactured at 12 months and 17 days in 1903, thus opening a new era of human aviation.
The development of aerospace technology plays an extremely important role in national economy and social progress, and the development of the aerospace technology greatly improves the life quality of people. The method is applied to the fields of transportation, aerial photography, agriculture, plant protection, miniature self-timer shooting, disaster relief, wild animal observation, infectious disease monitoring, mapping, news reporting, power inspection, disaster relief, film and television shooting and the like, and the aerospace technology also blooms with the aim of capturing light while the aerospace technology is developed at a high speed.
With the continuous development of the technology of human aerospace, an aircraft needs to realize high-efficiency flight in a larger speed range, and the optimal aerodynamic shapes of the aircraft corresponding to different speeds are different, so that a variant aircraft for researching and designing the aerodynamic shapes adaptively changing along with the flight speed becomes one of research hotspots in recent years, wherein the variable-thickness wing is paid attention to, and the implementation method can be generally divided into two types: firstly, a hinge type actuating mechanism based on mechanical connection; and secondly, the wing skin or the intelligent driver made of the intelligent material is used for directly or indirectly driving the skin to finish the change of the aerodynamic shape.
However, the above method enables the aircraft to obtain better aerodynamic performance without the use of flying speeds by changing the wing profile, but has the following drawbacks:
1. the mechanical actuating mechanism has larger volume and weight, and greatly reduces the effective load of the airplane;
2. the mechanical actuating mechanism is complex, so that the reliability of the mechanical actuating mechanism is greatly reduced;
3. variable thickness airfoils based on smart materials have limited range of variation.
Disclosure of Invention
The invention aims to: the invention aims to solve the defects of the prior art, and provides a variable-thickness wing based on memory metal, which has simpler structure and higher power-weight ratio, can be realized by only using memory metal wires, has a wider variable-thickness range and can realize better aerodynamic performance in wider working conditions.
The technical scheme is as follows: in order to achieve the above object, the present invention provides a memory metal-based variable thickness wing, comprising: the device comprises an elastic skin, an end support A fixedly connected with a fuselage, an end support B positioned at the wing position of an outer section of the wing, connecting plates with two ends vertically fixedly connected with the end support A and the end support B respectively, heating regulating devices vertically fixed on two sides of the connecting plates, wherein the elastic skin is coated on the outer sides of the end support A, the heating regulating devices and the end support B to form the wing, the elastic skin is stretched and reset through the heating regulating devices to realize the adjustment of the thickness of the wing, and the elastic skin is made of nonmetallic silicon adhesive tape glass fiber cloth.
As a further preferred aspect of the present invention, the heating control device includes: the heating device A and the heating device B are symmetrically arranged on two sides of the connecting plate, the ranging device A and the ranging device B are arranged on the heating device A and the heating device B, the supporting bracket A and the supporting bracket B are respectively fixedly arranged on the heating device A and the heating device B, one end of the memory alloy A sleeved on the supporting bracket A is fixedly connected with the heating device A, the other end of the memory alloy A is propped against the inner side of the elastic skin, one end of the memory alloy B sleeved on the supporting bracket B is fixedly connected with the heating device B, and the other end of the memory alloy B is propped against the inner side of the elastic skin. When the aircraft flies, different flying speeds can be corresponding to the optimal wing thickness under the condition, and wings with different thicknesses can be obtained by changing the length of the shape memory alloy to drive the expansion and contraction of the skin.
As a further preferred aspect of the present invention, the heating device a, the heating device B, the distance measuring device a and the distance measuring device B are respectively connected to the single-chip signal processor, the heating device a and the heating device B are used for providing current to heat the memory alloy a and the memory alloy B, and after receiving the energizing signals of the single-chip signal processor, the heating device a and the heating device B are turned on, and then heat the memory alloy a and the memory alloy B; the distance measuring device A and the distance measuring device B are used for receiving the elongation of the memory alloy A and the memory alloy B, sending the received elongation information to the single-chip signal processor, and controlling the on-off of the heating device A and the heating device B by the single-chip signal processor according to the received elongation information and the aircraft flying speed.
Because the memory alloy has the property of double-way memory, when the memory alloy is at different temperatures, the length and the shape can be changed, the shape of a high-temperature phase can be achieved when the memory alloy is heated, the shape of a low-temperature phase can be recovered when the memory alloy is cooled, the memory metal wire is heated by using current, and the stretching amount of the memory alloy is monitored in real time by using a distance measuring sensor, so that the stretching amount of the memory alloy is directly obtained.
As a further preferable mode of the invention, the single-chip signal processor is positioned in an electronic equipment cabin of the front part of the airplane, and an airspeed tube for measuring the airspeed of the airplane is also arranged in the electronic equipment cabin of the front part of the airplane.
As a further preferred aspect of the present invention, the heating control devices are uniformly mounted on the connection plate 5 and have a number of at least 1. Setting the memory alloy A (14) asMemory alloy B (18) is set to +.>Airspeed of the aircraft is set to v, chord length is set to c, and wing is the mostThe major thickness is defined as->The curve of the optimal relative thickness of the wing and the aircraft speed is shown in fig. 5, and the fitting relation between the optimal thickness of the wing and the aircraft speed can be obtained as follows:
as a further preferred aspect of the present invention, the memory alloy strain rate is a ratio of an increase in length of the memory alloy in the axial direction to an original length.
As a further preferred aspect of the present invention, the height difference coefficient of the memory metal A and the memory metal B is a 1 The height difference coefficient of the memory metal A and the memory alloy E is a 2 The height difference coefficient of the memory alloy B and the memory alloy D is B 1 The height difference coefficient of the memory alloy B and the memory alloy F is B 2 ，a 1 、a 2 、b 1 And b 2 The range of the values is as follows:
0≤a 1 ≤1，0≤a 2 ≤1，0≤b 1 ≤a 1 ，0≤b 2 ≤a 2 。
as a further preferred aspect of the present invention, the wing camber is set to f, and the wing camber f and the memory alloy A (14)And memory alloy B (18)>The relation of (2) is:
working principle: the memory alloy is heated by using current, and the length of the memory alloy which is stretched is monitored in real time by using a distance measuring device so as to reach the required stretching amount. The distance measuring sensor transmits electric signals to the single signal processor in the front belly electronic equipment cabin of the airplane through a circuit, and then judges the current stretching amount through frequency after receiving the electric signals, and compares the current stretching amount with the theoretical stretching amount to achieve the theoretical stretching amount. In order to ensure that series requirements such as fatigue strength are met, the memory alloy is made of a nitinol material, and the thickness of the wing can be regulated and controlled in real time through the steps.
The beneficial effects are that: according to the variable-thickness wing based on the memory metal, the memory metal is utilized to show different mechanical properties at different temperatures so as to stretch and reset the wing skin, and the combination of a plurality of memory metal modules is utilized to realize larger variable thickness of the wing.
Drawings
FIG. 1 is a schematic view of the internal structure of a wing;
FIG. 2 is a front view of the internal structure of the wing;
FIG. 3 is a top view of the internal structure of the wing;
FIG. 4 is a bottom view of the wing interior structure;
FIG. 5 is a graph of the variation of the flight speed and the optimal relative thickness of the wing;
FIG. 6 is a schematic diagram of a memory alloy structure in a low temperature state;
FIG. 7 is a schematic diagram of a memory alloy structure in a high temperature state;
FIG. 8 is a graph of shape memory wire temperature versus strain rate;
FIG. 9 is a graph of shape memory wire heating time versus current versus strain;
FIG. 10 is a graph of shape memory wire temperature versus time for natural cooling.
Detailed Description
The invention is further elucidated below in conjunction with the drawings.
As shown in fig. 1, 2, 3 and 4, the memory metal-based variable thickness wing of the present invention includes: the elastic skin 1, the end support A2, the end support B9, the connecting plate 5 and the heating regulation and control device arranged on the connecting plate 5.
The heating regulation and control device comprises: support bracket A6, heating device a11, memory alloy a14, support bracket B17, memory alloy B18, heating device B19, ranging device a26 and ranging device B29.
The end support A2 is fixedly connected with the fuselage, the end support B9 is positioned at the wing position of the outer section of the wing, two ends of the connecting plate 5 are respectively and vertically fixedly connected with the end support A1 and the end support B9, the heating device A11 is vertically fixed on two sides of the connecting plate 5, the distance measuring device A26 and the distance measuring device B29 are positioned on one sides of the heating device A11 and one side of the heating device B19, the elastic skin 1 is coated on the end support A1 and the memory alloy A14, the outer sides of the end support B9 and the memory alloy B18 form the wing, the wing thickness is adjusted by expanding and resetting the elastic skin 2 through the memory alloy A14 and the memory alloy R18, and the heating device A11, the heating device B19, the distance measuring device A26, the distance measuring device B29 and the airspeed speed measuring tube are respectively connected with the single-chip signal processor.
Examples
The two sides of the connecting plate 5 are uniformly distributed with 3 heating regulation devices, as shown in fig. 2, the three heating regulation devices are installed in the same way, and the second heating regulation device comprises: a support bracket C7, a heating device C12, a memory alloy C15, a support bracket D20, a memory alloy D21, a heating device D22, a distance measuring device C27 and a distance measuring device D30; the third heating regulation device comprises: support bracket E8, heating device F13, memory alloy E16, support bracket F23, memory alloy F24, heating device F25, ranging device E28 and ranging device F31.
The aircraft speed is defined herein as v, the chord length as C, and the axial total length of memory alloy A14, memory alloy C15 and memory alloy E16 are respectivelyAnd->The total length of memory alloy B18, memory alloy D21 and memory alloy F24 was +.>And->And->The maximum height of the upper part and the maximum height of the lower part of the end bracket B9 are shown, as shown in fig. 5.
The airspeed of the aircraft can be measured through the airspeed tube, the speed of the aircraft is taken as input, the signal is transmitted into a single-chip signal processor in the cabin of the electronic equipment of the front part of the aircraft, and the following formula is input according to the figure 5 and measured data:
based on chord length c being known, i.e. obtainableIs a value of (2);
assuming that the wing maximum thickness and maximum thickness overlap, the equation can be obtained:
based on the wing camber f being known, a result is obtainedIs a relationship of (3).
Thus, use is made ofAnd->The relation of (a) has been determined (derived from equation 1 and equation 2), is +.>And->I.e. can be solved and an optimal wing thickness at this speed can be obtained +.>
Meanwhile, the length of the remaining memory alloy can be determined according to the following formula:
setting the coefficient a in advance 1 、a 2 、b 1 And b 2 They represent the interrelationship of the difference in axial heights of the memory metals. As further illustrated by way of example in equation 3,for the height difference of memory alloy A14 and memory alloy C15, < >>For the height difference of the memory alloy A and the end bracket B9, a 1 For the proportionality coefficient of these two height differences, a known constant needs to be set in advance; then, since +.>But->Is known, a 1 And is determined in advance as a constant, the height of the memory alloy C15 is +.>Is uniquely determined. The solution ideas of the remaining formulas (4) to (6) are the same as those of the formula (3). To achieve a relative smoothness of the wing surface, a is set to 1 、a 2 、b 1 And b 2 The value range is 0 to a 1 ≤1，0≤a 2 ≤1，0≤b 1 ≤a 1 ，0≤b 2 ≤a 2 . Then, as previously described, according to formulae (3) - (6) and known +.>Can obtain +.>Andthe theoretical elongations of the memory alloy a14, the memory alloy C15, the memory alloy E16, the memory alloy B18, the memory alloy D21 and the memory alloy F24 were confirmed.
Because the memory alloy has the property of double-way memory, when the memory alloy is at different temperatures, the length and the shape can be changed, the shape of the high-temperature phase is achieved when the memory alloy is heated, and the shape of the low-temperature phase can be recovered when the memory alloy is cooled, as shown in fig. 6 and 7.
FIG. 8 shows the temperature dependence of the memory alloy, wherein the strain rate is the ratio of the length increase of the memory metal in the axial direction to the original length. In the invention, the memory metal wire is heated by using current, and the stretching amount of the memory alloy is monitored in real time by using the ranging sensor, so that the stretching amount of the memory alloy is directly obtained. The response time to different elongation of the memory wire is shown in FIG. 9 and the temperature versus time of the shape memory alloy under natural cooling is shown in FIG. 10.
Comparative experiments
The wind speed in the wind tunnel is controlled to increase from 0m/s to 180m/s at a speed increasing rate of 1m/s, wings with different thicknesses are placed in the wind tunnel for testing, the attack angle is changed so that the instantaneous lift coefficient born by the wings is kept the same, the instantaneous resistance coefficient born by the wings is recorded, and the instantaneous resistance coefficient in the whole process is averaged to obtain the total resistance coefficient. The smaller the overall drag coefficient, the higher the flight performance. As can be seen from the following table, the overall drag coefficient of the variable thickness airfoil is smaller, and thus has better aerodynamic performance.
The foregoing embodiments are merely illustrative of the technical concept and features of the present invention, and are intended to enable those skilled in the art to understand the present invention and to implement the same, not to limit the scope of the present invention. All changes and modifications that come within the meaning and range of equivalency of the invention are to be embraced within their scope.
Claims (8)
1. A memory metal-based variable thickness wing, characterized in that: it comprises the following steps: the device comprises an elastic skin (1), an end support A (2) fixedly connected with a fuselage, an end support B (9) positioned at the outer section wing position of the wing, a connecting plate (5) with two ends vertically fixedly connected with the end support A (2) and the end support B (9) respectively, and heating control devices vertically fixed on two sides of the connecting plate (5), wherein the elastic skin (1) is coated on the outer sides of the end support A (2), the heating control devices and the end support B (9) to form the wing, and the expansion and the reset of the elastic skin (1) by the heating control devices are used for realizing the adjustment of the thickness of the wing;
the heating regulation and control device comprises: the heating device A (11) and the heating device B (19) are symmetrically arranged on two sides of the connecting plate (5), the distance measuring device A (26) and the distance measuring device B (29) are arranged on the heating device A (11) and the heating device B (19), the supporting bracket A (6) and the supporting bracket B (17) are respectively fixedly arranged on the heating device A (11) and the heating device B (19), one end of the memory alloy A (14) sleeved on the supporting bracket A (6) is fixed with the heating device A (11), the other end of the memory alloy A (14) is propped against the inner side of the elastic skin (1), one end of the memory alloy B (18) sleeved on the supporting bracket B (17) is fixed with the heating device B (19), and the other end of the memory alloy B (18) is propped against the inner side of the elastic skin (1);
the axial total length of the memory alloy A (14) is set to beThe axial total length of the memory alloy B (18) is set to +.>The airspeed of the aircraft is set to v, the chord length is set to c, and the optimal thickness of the wing is defined as +.>The fitting relation that can obtain the optimal thickness of the airplane speed and the wing is:
2. a memory metal based variable thickness wing as claimed in claim 1, wherein: the heating device A (11), the heating device B (19), the distance measuring device A (26) and the distance measuring device B (29) are respectively connected with the single-chip signal processor.
3. A memory metal based variable thickness wing as claimed in claim 2, wherein: the single-chip signal processor is positioned in the front belly electronic equipment cabin of the airplane.
4. A memory metal based variable thickness wing as claimed in claim 3, wherein: and an airspeed speed measuring tube for measuring the airspeed of the aircraft is also arranged in the front belly electronic equipment cabin of the aircraft.
5. A memory metal based variable thickness wing as claimed in claim 1, wherein: the heating regulation and control devices are uniformly arranged on the connecting plate (5) and the number of the heating regulation and control devices is at least 1.
6. A memory metal based variable thickness wing as claimed in claim 1, wherein: the strain rate of the memory alloy is the ratio of the length increment of the memory alloy along the axial direction to the original length.
7. A memory metal based variable thickness wing as claimed in claim 1, wherein: the height difference coefficient of the memory alloy A (14) and the memory alloy C (15) is a 1 The height difference coefficient of the memory alloy A (14) and the memory alloy E (16) is a 2 The height difference coefficient of the memory alloy B (18) and the memory alloy D (21) is B 1 The height difference coefficient of the memory alloy B (18) and the memory alloy F (24) is B 2 ，a 1 、a 2 、b 1 And b 2 The range of the values is as follows:
0≤a 1 ≤1，0≤a 2 ≤1，0≤b 1 ≤a 1 ，0≤b 2 ≤a 2 。
8. a memory metal based variable thickness wing as claimed in claim 1, wherein: setting the wing camber as f, and setting the total axial length of the wing camber f and the memory alloy A (14)And memory alloy B (18) axial total length +.>The relation of (2) is:
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| CN115806042B (en) * | 2023-02-03 | 2023-04-28 | 北京大学 | Variant wing and aircraft |
| CN116395124B (en) * | 2023-06-07 | 2023-08-11 | 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 | Wing surface deformation mechanism based on shape memory alloy wire drive |
| CN117227964B (en) * | 2023-11-14 | 2024-01-23 | 北京大学 | Multi-connecting-rod variable-structure wing and aircraft |
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| EP0111785A1 (en) * | 1982-12-20 | 1984-06-27 | The Boeing Company | Natural laminar flow, low wave drag airfoil |
| US4611773A (en) * | 1982-12-30 | 1986-09-16 | The Boeing Company | Tapered thickness-chord ratio wing |
| CN107883916A (en) * | 2016-09-29 | 2018-04-06 | 波音公司 | Method and apparatus for sense aircraft areal deformation |
| 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 |
| CN210258812U (en) * | 2019-04-17 | 2020-04-07 | 陶伟灏 | Morphing wing based on active deformation negative Poisson ratio honeycomb structure |
| CN111284679A (en) * | 2020-02-18 | 2020-06-16 | 吉林大学 | Unmanned aerial vehicle deformation wing structure based on memory alloy negative Poisson's ratio cell cube |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020163786A2 (en) * | 2019-02-07 | 2020-08-13 | The Government Of The United States Of America, As Represented By The Secretary Of The Navy | Surface stiffness optimization to improve morphing surface accuracy |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0111785A1 (en) * | 1982-12-20 | 1984-06-27 | The Boeing Company | Natural laminar flow, low wave drag airfoil |
| US4611773A (en) * | 1982-12-30 | 1986-09-16 | The Boeing Company | Tapered thickness-chord ratio wing |
| CN107883916A (en) * | 2016-09-29 | 2018-04-06 | 波音公司 | Method and apparatus for sense aircraft areal deformation |
| 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 |
| CN210258812U (en) * | 2019-04-17 | 2020-04-07 | 陶伟灏 | Morphing wing based on active deformation negative Poisson ratio honeycomb structure |
| CN111284679A (en) * | 2020-02-18 | 2020-06-16 | 吉林大学 | Unmanned aerial vehicle deformation wing structure based on memory alloy negative Poisson's ratio cell cube |
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