CN114476022A - Variable-thickness wing based on memory metal - Google Patents

Variable-thickness wing based on memory metal Download PDF

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CN114476022A
CN114476022A CN202210213159.6A CN202210213159A CN114476022A CN 114476022 A CN114476022 A CN 114476022A CN 202210213159 A CN202210213159 A CN 202210213159A CN 114476022 A CN114476022 A CN 114476022A
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wing
memory alloy
memory
memory metal
heating device
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CN114476022B (en
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刘洪�
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Shanghai Lihong Aviation Technology Co ltd
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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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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 installed 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 the wing, the heating regulation and control device is used for opening and resetting the elastic skin to adjust the thickness of the wing, the wing stretches and resets the wing skin by utilizing different mechanical properties of memory metal at different temperatures, and the combination of a plurality of memory metal modules is used for realizing larger variable thickness of the wing.

Description

Variable-thickness wing based on memory metal
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
Spreading its wings in the sky like a hawk is the most romantic dream since its birth. From the flying dream of people in Dunhuang Mogao Grottoes more than 1600 years ago, to the appearance of kites and Kongming lantern and then to the flight of theoretical birds in DaVinci, the first plane in the world is manufactured after numerous failures and explorations of human beings and finally within 12 and 17 months in 1903, and the era creates a new era of human aviation.
The development of aerospace technology plays an important role in national economy and social progress, and the development of aerospace technology greatly improves the quality of life of people. The system is applied to the fields of transportation, aerial photography, agriculture, plant protection, miniature self-timer, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, movie and television shooting and the like, and the aerospace technology blooms target-capturing brilliance while the aviation technology is developed at a high speed.
With the continuous development of the aerospace technology, the aircraft needs to fly efficiently in a large speed range, and the optimal aerodynamic profiles of the aircraft corresponding to different speeds are greatly different, so that the research and design of a variant aircraft with an aerodynamic profile adaptively changing along with the flying speed becomes one of the research hotspots in recent years, wherein the variable-thickness wing is concerned by people, and the implementation methods thereof can be generally divided into two types: firstly, a hinge type actuating mechanism based on mechanical connection; and secondly, the change of the aerodynamic shape is completed by directly or indirectly driving the skin by using the wing skin made of intelligent materials or an intelligent driver.
However, the above method enables the aircraft to obtain better aerodynamic performance without flying speed by changing the wing profile, but has the following disadvantages:
1. the mechanical actuating mechanism has larger volume and weight, so that the effective load of the airplane is greatly reduced;
2. the mechanical actuating mechanism is complex, so that the reliability of the mechanical actuating mechanism is greatly reduced;
3. the variable thickness wing based on the intelligent material has limited variation range.
Disclosure of Invention
The purpose of the invention is as follows: the variable-thickness wing based on the memory metal is simpler in structure and higher in power-weight ratio, can be realized only by the memory metal wire, is large in variable-thickness range, and can realize excellent pneumatic performance in a wider working condition.
The technical scheme is as follows: in order to achieve the above object, the present invention provides a variable thickness wing based on memory metal, which comprises: the aircraft comprises an elastic skin, an end support A fixedly connected with an aircraft body, an end support B located at the position of an outer wing section of an airfoil, a connecting plate fixedly connected with the end support A and the end support B at two ends respectively, and heating regulation and control devices vertically fixed on two sides of the connecting plate, wherein the elastic skin is coated on the outer sides of the end support A, the heating regulation and control devices and the end support B to form the airfoil, the elastic skin is expanded and reset through the heating regulation and control devices to realize the regulation of the thickness of the airfoil, and the elastic skin is made of nonmetal silica gel cloth and glass fiber cloth.
As a further preferred aspect of the present invention, the heating control device comprises: heating device A and heating device B are installed at the connecting plate both sides symmetrically, install range unit A and range unit B on heating device A and heating device B to and set firmly support holder A and support holder B on heating device A and heating device B respectively, the cover is established the one end and the heating device A of memory alloy A on support holder A and is fixed, the other end and the inboard of elastic skin of memory alloy A offset, the cover is established the one end and the heating device B of memory alloy B on support holder B and is fixed, the other end and the inboard of elastic skin of memory alloy B offset. When the airplane flies, different flying speeds can correspond to the optimal wing thickness under the condition, and the length of the shape memory alloy is changed to drive the skin to expand and contract so as to obtain the wings with different thicknesses.
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 monolithic 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 the heating device a and the heating device B receive the power-on signal of the monolithic signal processor, the heating device a and the heating device B are turned on, and then the memory alloy a and the memory alloy B are heated; 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 and sending the received elongation information to the single-chip signal processor, and the single-chip signal processor controls the on-off of the heating device A and the heating device B according to the received elongation information and the flight speed of the airplane.
Because the memory alloy has the property of two-way memory, when the memory alloy is at different temperatures, the length and the shape can be changed, the memory alloy can reach a high-temperature phase shape when being heated, and can recover a low-temperature phase shape when being 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 present invention, the single-chip signal processor is located in an electronic equipment cabin of a front belly of the aircraft, and an airspeed speed measurement tube for measuring an airspeed of the aircraft is further provided in the electronic equipment cabin of the front belly of the aircraft.
As a further preferred embodiment of the present invention, the heating control devices are uniformly installed on the connecting plate 5 and the number of the heating control devices is at least 1. Setting the memory alloy A (14) to
Figure BDA0003531634950000021
Memory alloy B (18) is set to
Figure BDA0003531634950000022
The airspeed of the airplane is set as v, the chord length is set as c, and the optimal thickness of the wing is defined as
Figure BDA0003531634950000023
The curve of the aircraft speed and the optimal relative thickness of the wing is shown in fig. 5, and the fitting relation of the aircraft speed and the optimal thickness of the wing can be obtained as follows:
Figure BDA0003531634950000024
in a further preferred embodiment of the present invention, the strain rate of the memory alloy is a ratio of an increase in length of the memory alloy in the axial direction to an original length of the memory alloy.
In a further preferred embodiment of the present invention, the height difference coefficient between the memory metal A and the memory metal B is a1The coefficient of height difference between the memory metal A and the memory alloy E is a2The height difference coefficient of the memory alloy B and the memory alloy D is B1The height difference coefficient of the memory alloy B and the memory alloy F is B2，a1、a2、b1And b2The value range is as follows:
0≤a1≤1，0≤a2≤1，0≤b1≤a1，0≤b2≤a2。
as a further preferred aspect of the present invention, the wing camber is set to f, and the wing camber f is in contact with a memory alloy A (14)
Figure BDA0003531634950000031
And memory alloy B (18)
Figure BDA0003531634950000032
The relationship of (1) is:
Figure BDA0003531634950000033
the working principle is as follows: the memory alloy is heated by current, and the length of the memory alloy after being stretched is monitored in real time by a distance measuring device, so that the required stretching amount is achieved. The distance measuring sensors under different distances transmit back electric signal processors with different frequencies to a single-chip signal processor positioned in an electronic equipment cabin of the front belly of the airplane through the circuits, and after the electric signal processors receive electric signals, the current stretching amount is judged through the frequencies and compared with the theoretical stretching amount, so that the theoretical stretching amount is achieved. In order to meet series requirements such as fatigue strength and the like, 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.
Has the advantages that: according to the variable-thickness wing based on the memory metal, disclosed by the invention, the memory metal shows different mechanical properties at different temperatures so as to stretch and restore 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 an airfoil;
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 internal structure of the wing;
FIG. 5 is a graph of the change in flying speed and the optimum relative thickness of the airfoil;
FIG. 6 is a schematic structural diagram of a memory alloy in a low temperature state;
FIG. 7 is a schematic structural diagram of a memory alloy in a high temperature state;
FIG. 8 is a graph of shape memory wire temperature versus strain rate;
FIG. 9 is a graph of the shape memory wire heating time-current-strain relationship;
FIG. 10 is a graph of shape memory wire temperature versus time as it cools naturally.
Detailed Description
The invention will be further elucidated with reference to the drawing.
As shown in fig. 1, 2, 3 and 4, the invention relates to a variable thickness wing based on memory metal, which comprises: the elastic skin 1, an end bracket A2, an end bracket B9, a connecting plate 5 and a heating regulation device arranged on the connecting plate 5.
The heating regulation and control device comprises: a supporting bracket A6, a heating device A11, a memory alloy A14, a supporting bracket B17, a memory alloy B18, a heating device B19, a distance measuring device A26 and a distance measuring device B29.
An end support A2 is fixedly connected with a fuselage, an end support B9 is located at the position of an outer section wing of the wing, two ends of a connecting plate 5 are respectively and fixedly connected with an end support A1 and an end support B9 vertically, a heating device A11 is vertically fixed on two sides of the connecting plate 5, a distance measuring device A26 and a distance measuring device B29 are located on one side of the heating device A11 and one side of the heating device B19, the elastic skin 1 covers the end support A1 and the memory alloy A14, the end support B9 and the memory alloy B18 to form the wing, the thickness of the wing 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 head are respectively connected with a single-chip signal processor.
Examples
Evenly arrange 3 vertical fixation's heating regulation and control devices in the both sides of connecting plate 5, as shown in fig. 2, three heating regulation and control device's mounting means is the same, and second heating regulation and control device includes: a supporting bracket C7, a heating device C12, a memory alloy C15, a supporting 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 and control device comprises: a supporting bracket E8, a heating device F13, a memory alloy E16, a supporting bracket F23, a memory alloy F24, a heating device F25, a distance measuring device E28 and a distance measuring device F31.
Here, the aircraft velocity is defined as v, the chord length is defined as c, and the memory alloy A14The total axial length of the memory alloy C15 and the memory alloy E16 is respectively
Figure BDA0003531634950000041
And
Figure BDA0003531634950000042
the total length of the memory alloy B18, the memory alloy D21 and the memory alloy F24 is respectively
Figure BDA0003531634950000043
And
Figure BDA0003531634950000044
and
Figure BDA0003531634950000045
showing the maximum height of the upper portion and the maximum height of the lower portion of end bracket B9, as shown in particular in fig. 5.
The airspeed of the airplane can be measured through the airspeed speed measuring tube, the speed of the airplane is used as input, the signal is transmitted into a single-chip signal processor in an electronic equipment cabin of a belly at the front part of the airplane, and the following formula is input according to the graph 5 and measured data:
Figure BDA0003531634950000046
based on the chord length c, is known, i.e. is obtained
Figure BDA0003531634950000047
A value of (d);
assuming that the maximum thickness of the wing coincides with the maximum thickness, the formula can be obtained:
Figure BDA0003531634950000051
based on the wing camber f being known, obtaining
Figure BDA0003531634950000052
The relationship (2) of (c).
Thus, utilize
Figure BDA0003531634950000053
And
Figure BDA0003531634950000054
has been determined (derived from equations 1 and 2),
Figure BDA0003531634950000055
and
Figure BDA0003531634950000056
i.e. can be solved and the optimum wing thickness at this speed can be obtained
Figure BDA0003531634950000057
Meanwhile, the lengths of the remaining memory alloys can be determined according to the following formula:
Figure BDA0003531634950000058
Figure BDA0003531634950000059
Figure BDA00035316349500000510
Figure BDA00035316349500000511
setting the coefficient a in advance1、a2、b1And b2They represent the correlation of the difference in the axial height of the memory metal. Further explanation is made by taking the formula 3 as an example,
Figure BDA00035316349500000512
is the height difference between the memory alloy A14 and the memory alloy C15,
Figure BDA00035316349500000513
is the difference in height between memory alloy A and end bracket B9, a1For the proportionality coefficient of the two height differences, a known constant needs to be set in advance; then, since it has already been solved in the previous calculation
Figure BDA00035316349500000514
While
Figure BDA00035316349500000515
Is known as a1And is predetermined as a constant, the height of the memory alloy C15
Figure BDA00035316349500000516
Is uniquely determined. The solution idea of the remaining equations (4) to (6) is the same as that of equation (3). To achieve a relatively smooth surface of the wing, a is set1、a2、b1And b2A is greater than or equal to 01≤1，0≤a2≤1，0≤b1≤a1，0≤b2≤a2. Then, as previously described, according to equations (3) - (6) and as known
Figure BDA00035316349500000517
Can find out
Figure BDA00035316349500000518
And
Figure BDA00035316349500000519
thus, the theoretical elongation 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 was confirmed.
Because the memory alloy has the property of two-way memory, when the memory alloy is at different temperatures, the length and the shape of the memory alloy can be changed, the memory alloy can reach a high-temperature phase shape when being heated, and can recover a low-temperature phase shape when being cooled, as shown in fig. 6 and 7.
FIG. 8 shows the temperature dependence of a memory alloy, wherein the strain rate is the ratio of the increase in length 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 distance measuring sensor, so that the stretching amount of the memory alloy is directly obtained. The response time of the memory wire to different elongation rates is shown in fig. 9, and the temperature-time relationship curve of the shape memory alloy in the natural cooling state is shown in fig. 10.
Comparative experiment
Controlling the wind speed in the wind tunnel to increase from 0m/s to 180m/s at the speed increase of 1m/s/min, placing wings with different thicknesses in the wind tunnel for testing, changing an attack angle to keep the instantaneous lift coefficient on the wings the same, recording the instantaneous resistance coefficient on the wings, and averaging the instantaneous resistance coefficient in the whole process to obtain the total resistance coefficient. The smaller the overall drag coefficient, the higher the flight performance. As can be seen from the table below, the overall coefficient of drag of the variable thickness wing is smaller and therefore has better aerodynamic performance.
Figure BDA0003531634950000061
The above embodiments are merely illustrative of the technical concepts and features of the present invention, and the purpose of the embodiments is to enable those skilled in the art to understand the contents of the present invention and implement the present invention, and not to limit the protection scope of the present invention. All equivalent changes or modifications made according to the spirit of the present invention should be covered within the protection scope of the present invention.

Claims (10)

1. A variable thickness wing based on memory metal, characterized in that: it includes: elastic skin (1), tip support A (2) that links firmly with the fuselage, be located tip support B (9) of wing outer segment wing position department, both ends respectively with tip support A (1) and tip support B (9) perpendicular connecting plate (5) that link firmly, the heating regulation and control device of vertical fixation in connecting plate (5) both sides, elastic skin (1) cladding form the wing in the outside of tip support A (1), heating regulation and control device and tip support B (9), strut and reset through heating regulation and control device to elastic skin (1) and realize the regulation of wing thickness.
2. A memory metal based variable thickness wing as claimed in claim 1, wherein: the heating regulation and control device comprises: the device comprises a heating device A (11) and a heating device B (19) which are symmetrically arranged on two sides of a connecting plate (5), a distance measuring device A (26) and a distance measuring device B (29) which are arranged on the heating device A (11) and the heating device B (19), a supporting bracket A (6) and a supporting bracket B (17) which are fixedly arranged on the heating device A (11) and the heating device B (19) respectively, one end of a 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 abutted against the inner side of an elastic skin (1), one end of a 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 abutted against the inner side of the elastic skin (1).
3. A memory metal based variable thickness wing as claimed in claim 2, wherein: and 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.
4. A memory metal based variable thickness wing as claimed in claim 3, wherein: the single-chip signal processor is positioned in an electronic equipment cabin of the front part of the airplane.
5. A variable thickness wing based on memory metal as claimed in claim 4, wherein: the electronic equipment cabin at the front part of the airplane belly is also internally provided with an airspeed speed measuring tube for measuring the airspeed of the airplane.
6. 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.
7. A memory metal based variable thickness wing as claimed in claim 2, wherein: setting the memory alloy A (14) to
Figure FDA0003531634940000011
Memory alloy B (18) is set to
Figure FDA0003531634940000012
The airspeed of the airplane is set as v, the chord length is set as c, and the optimal thickness of the wing is defined as
Figure FDA0003531634940000013
The curve of the aircraft speed and the optimal relative thickness of the wing is shown in fig. 5, and the fitting relation of the aircraft speed and the optimal thickness of the wing can be obtained as follows:
Figure FDA0003531634940000014
8. a memory metal based variable thickness wing as claimed in claim 7, 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.
9. A memory metal based variable thickness wing as claimed in claim 7, wherein: the height difference coefficient of the memory metal A (14) and the memory metal C (15) is a1The coefficient of height difference between the memory metal A (14) and the memory alloy E (16) is a2The coefficient of difference in height between the memory alloy B (18) and the memory alloy D (21) is B1The coefficient of height difference between the memory alloy B (18) and the memory alloy F (24) is B2，a1、a2、b1And b2The value range is as follows:
0≤a1≤1，0≤a2≤1，0≤b1≤a1，0≤b2≤a2。
10. a memory metal based variable thickness wing as claimed in claim 2, wherein: setting the wing camber as f, the wing camber f and the memory alloy A (14)
Figure FDA0003531634940000021
And memory alloy B (18)
Figure FDA0003531634940000022
The relationship of (1) is:
Figure FDA0003531634940000023
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115806042A (en) * 2023-02-03 2023-03-17 北京大学 Morphing wing and aircraft
CN116395124A (en) * 2023-06-07 2023-07-07 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
CN117227964A (en) * 2023-11-14 2023-12-15 北京大学 Multi-connecting-rod variable-structure wing and aircraft

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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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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
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115806042A (en) * 2023-02-03 2023-03-17 北京大学 Morphing wing and aircraft
CN115806042B (en) * 2023-02-03 2023-04-28 北京大学 Variant wing and aircraft
CN116395124A (en) * 2023-06-07 2023-07-07 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
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
CN117227964A (en) * 2023-11-14 2023-12-15 北京大学 Multi-connecting-rod variable-structure wing and aircraft
CN117227964B (en) * 2023-11-14 2024-01-23 北京大学 Multi-connecting-rod variable-structure wing and aircraft

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