CN111284679B - Unmanned aerial vehicle deformation wing structure based on memory alloy negative Poisson's ratio cell cube - Google Patents

Unmanned aerial vehicle deformation wing structure based on memory alloy negative Poisson's ratio cell cube Download PDF

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CN111284679B
CN111284679B CN202010098558.3A CN202010098558A CN111284679B CN 111284679 B CN111284679 B CN 111284679B CN 202010098558 A CN202010098558 A CN 202010098558A CN 111284679 B CN111284679 B CN 111284679B
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memory alloy
wing
niti
negative poisson
unmanned aerial
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CN111284679A (en
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于征磊
信仁龙
张志辉
谢鑫宇
郭雪
任露泉
闫维
张晓龙
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Jilin University
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Jilin University
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/061—Frames
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/40—Sound or heat insulation, e.g. using insulation blankets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Toys (AREA)

Abstract

The invention belongs to the technical field of structural materials of unmanned aerial vehicles, and particularly relates to a deformable wing structure of an unmanned aerial vehicle based on a memory alloy negative Poisson's ratio unit body. It includes the fuselage, has NiTi memory alloy skeleton texture, wing covering, interior heating system, insulating layer, intelligent perception system and temperature sensor, the wing that NiTi memory alloy skeleton texture is the main part is installed to the both sides of fuselage, there is outer cladding of NiTi memory alloy skeleton texture to have the wing covering, there is the inside of NiTi memory alloy skeleton texture to be provided with and be used for having the interior heating system of NiTi memory alloy skeleton texture heating. The invention has the advantages that the traditional mechanical deformation modes such as the traditional motor-driven link mechanism are changed, and the traditional mechanical action of the trailing edge of each discrete wing is cancelled, so that the resistance and the noise are reduced, the structure of the wing is simple, the difficulty and the cost of wing maintenance are reduced, and the fixed wing structure can be replaced.

Description

Unmanned aerial vehicle deformation wing structure based on memory alloy negative Poisson's ratio unit body
Technical Field
The invention belongs to the technical field of structural materials of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle deformation wing structure based on a memory alloy negative Poisson's ratio unit body.
Background
At present, parameters such as height, weight and speed of an airplane are not fixed and unchanged in the flying process, different wing shapes are expected to be adjusted according to different parameter changes when the wing shape is designed in order to enable the airplane to have better aerodynamics, and researches show that fuel of several percent can be saved for the airplane by changing the wing shape in the flying process. Meanwhile, the deformation of the shape of the wing has important significance for reducing noise.
During the deformation of the aircraft, the aerodynamic properties are taken into account, so that the deformation should be as little as possible, with an excessively rough, intermittent shape. Currently, in the research of wing deformation structures, the most studied deformation forms include variable span length, variable chord length, variable thickness, variable sweep, variable camber and the like. The traditional deformation mode is mainly that a connecting rod mechanism is driven to deform the wing area, the wing aspect ratio, the sweep angle, the wing camber and the like in a mechanical mode. However, the transmission system of the traditional mechanical driving mode is complex, occupies a large space and can affect the maneuverability of the airplane. Because the shape memory alloy has the advantages of large power-weight ratio, low driving condition, simple driving structure and the like, the shape memory alloy can play an increasingly large role as a high-efficiency and clean driving element in the driving research of the morphing wing.
A mechanical analysis model of a flexible Honeycomb skin Structure is established in a document aiming at the Application of a Negative Poisson's Ratio Honeycom Structure and It's Application Structure and It's Applications in the Structure Design of moving Aircraft, and the Negative Poisson Ratio Honeycomb Structure has larger in-vivo deformation capability after research, namely the internal Structure space is enough to allow stretching and in-plane recess, and the variant Aircraft wing adopting the Negative Poisson Ratio flexible Honeycomb Structure has the potential of improving the takeoff and landing performance of an unmanned aerial vehicle due to the special stretching characteristic of the Structure.
Wing deformation requires that the wing structure be able to deform easily while being able to withstand aerodynamic loads. Control of the airfoil shape may be achieved using shape memory alloys. The shape memory alloy with the two-way shape memory effect can recover the shape of a high-temperature phase when heated and recover the shape of a low-temperature phase when cooled, so that the conversion between the shapes of the high-temperature phase and the low-temperature phase can be realized by controlling the change of temperature; under the condition of meeting the requirements of the wings for bearing stress and strain of certain load, the negative Poisson's ratio unit body structure is adopted, so that enough load bearing capacity can be ensured, and the light weight of the wing structure can be realized.
And because the materials of the wings and the fuselage are different, the existing wings are inconvenient to be fixedly installed with the fuselage, are difficult to disassemble and are inconvenient to maintain and replace, so that the existing assembly, disassembly and maintenance of the morphing wings are also important problems to be overcome by the morphing wings.
Disclosure of Invention
Technical problem to be solved
Aiming at the existing technical problems, the invention provides an unmanned aerial vehicle deformed wing structure based on a memory alloy negative Poisson's ratio unit body
(II) technical scheme
In order to achieve the purpose, the invention adopts the main technical scheme that: an unmanned aerial vehicle deformation wing structure based on a memory alloy negative Poisson ratio unit body comprises a fuselage, a NiTi memory alloy framework structure, a wing skin, an internal heating system, a heat insulation layer, an intelligent sensing system and a temperature sensor;
wings with a NiTi memory alloy framework structure as a main body are arranged on two sides of the fuselage;
the outer layer of the NiTi memory alloy framework structure is coated with the wing skin;
an internal heating system for heating the NiTi memory alloy skeleton structure is arranged inside the NiTi memory alloy skeleton structure;
a temperature sensor convenient for testing the temperature of the NiTi memory alloy framework structure is arranged in the NiTi memory alloy framework structure;
the signal of the temperature sensor is transmitted to the intelligent sensing system through an electric signal;
the heat insulation layer is arranged on an interlayer between the NiTi memory alloy framework structure and the internal heating system;
the skeleton structure of the memory alloy with NiTi is Ni 50.9 Ti 49.1 The deformed wing structure of the shape memory alloy negative Poisson ratio unit body;
wing mounting structures are arranged at the mounting positions of the NiTi memory alloy framework structure and the two sides of the fuselage, so that the wings and the fuselage can be conveniently mounted and matched;
the wing mounting structure comprises an insertion block and an insertion groove;
the front end and the rear end of the left side and the right side of the outer wall of the airplane body are respectively provided with an inserting block which is convenient for the installation of wings;
the inner sides of the left and right sheets with the NiTi memory alloy framework structure are provided with insertion grooves which are arranged in the front and back and are convenient for insertion of insertion blocks;
the inner side of the insertion block is provided with a clamping groove;
the inner sides of the front and the rear insertion grooves are provided with clamping structures for mounting wings;
the clamping structure comprises a supporting plate;
the top end of the supporting plate is connected with a rotating plate through a bearing in a shaft way;
the inner walls of the left side and the right side of the supporting plate are fixedly connected with guide rods;
clamping blocks matched with the clamping grooves in an inserting manner are sleeved on the front side and the rear side of the outer wall of the guide rod;
the center position of the top end of the inner side of each clamping block is connected with one end of a push rod in a shaft mode;
the other end of the push rod is respectively connected with the outer walls at the left end and the right end of the top end of the rotating plate in a shaft mode;
the center position of the rotating plate is fixedly connected with a rotating rod which is convenient for driving the rotating plate to rotate;
a NiTi memory alloy framework structure penetrates through the top end of the rotating rod, and a rotating disc for rotating the rotating rod is arranged;
a groove is formed in the side wall of the rotary table;
and the inner side of the groove is contacted with a telescopic mechanism for clamping the rotary disc.
According to the invention, a second conductor is arranged on the inner side of the insertion groove;
and a first conductor which is contacted with the second conductor and enables the NiTi memory alloy framework structure to form circuit connection with the machine body is arranged on the outer side of the inserting block.
According to the invention, the telescopic mechanism comprises a fixed block;
the bottom end of the fixed block is fixedly connected with a NiTi memory alloy framework structure;
a cross rod is inserted into the inner cavity of the fixed block;
a pull handle is arranged on the outer side of the cross rod;
the inner side of the cross rod is provided with a convex block;
the lug is embedded with the groove;
the outer wall of the cross rod is sleeved with a spring;
one end of the spring is abutted against the inner wall of the fixed block, and the other end of the spring is abutted against the inner wall of the lug.
According to the invention, the inner cavity with the NiTi memory alloy framework structure is provided with an electric heating groove;
the internal heating system is embedded in the NiTi memory alloy framework structure through the electric heating groove;
the internal heating system is an electric heating wire;
the material around the groove is Cu-Al-Ni alloy
According to the invention, the number of the grooves formed in the side wall of the turntable is even, and the grooves are uniformly and symmetrically distributed on the side wall of the turntable.
According to the invention, the rotating plate is an elliptical rotating plate.
According to the invention, the wing skin is integrally formed by the polyether-ether-ketone flexible high polymer and the fiber composite material, and the wing skin is a flexible curved surface skin.
According to the invention, the electric heating grooves are uniformly distributed in the NiTi memory alloy framework structure in a net shape.
According to the invention, the heat insulation layer material adopts basalt fiber or HPS static composite heat insulation paste.
(III) advantageous effects
The invention has the beneficial effects that:
(1) the mechanical deformation modes such as the traditional mode that a connecting rod mechanism is driven by a motor are changed, the weight of the airplane body is reduced, the structure of the airplane body is simplified, the adaptability of the working environment of the wings is enhanced, and the working reliability and the safety factor of the wings are improved.
(2) The traditional mechanical action of each discrete wing trailing edge is cancelled, (such as the extension and retraction of a flap, and the aerodynamic characteristics of the wing are changed by changing the area of the wing), so that the drag and the noise are reduced, and meanwhile, the energy efficiency is improved, and the energy saving is facilitated.
(3) The wing has a simple structure, does not have a complex mechanical transmission structure, and reduces the difficulty and cost of wing maintenance.
(4) The fixed wing structure can replace a traditional fixed wing structure, wing deformation is realized under the condition of bearing normal load, and the flying performance of the airplane is improved. On the basis, the aim of improving the speed, protecting the environment, being more efficient and saving energy can be fulfilled by carrying out targeted design.
(5) The problem of fixation of the wings and the fuselage due to the fact that the wings and the fuselage are made of different materials can be solved, the wing fixing device is easy to disassemble, and maintenance and replacement are convenient.
Drawings
FIG. 1 is an isometric view of the present invention;
FIG. 2 is a schematic diagram of the framework unit structure of the present invention;
FIG. 3 is a diagram of the effect of the invention after deformation of the airfoil;
FIG. 4 is a view showing the construction of the internal heating apparatus of the present invention;
FIG. 5 is a top view of the present invention;
FIG. 6 is a schematic view showing the connection relationship between the frame structure of the memory alloy with NiTi and the body according to the present invention;
FIG. 7 is an enlarged view taken at A of FIG. 6;
FIG. 8 is a schematic sectional front view of a connection portion between a framework structure of a NiTi memory alloy and a body according to the present invention;
FIG. 9 is a schematic sectional top view of a surface mounting block with a NiTi memory alloy skeleton structure according to the present invention;
Detailed Description
For the purpose of better explaining the present invention and to facilitate understanding, the present invention will be described in detail by way of specific embodiments with reference to the accompanying drawings.
The invention provides an unmanned aerial vehicle deformation wing structure based on a memory alloy negative Poisson's ratio unit body, which comprises a fuselage 5, a NiTi memory alloy framework structure 3, a wing skin 1, an internal heating system, a heat insulation layer 2, an intelligent sensing system and a temperature sensor, wherein the NiTi memory alloy framework structure is arranged on the fuselage;
wings with a NiTi memory alloy framework structure 3 as a main body are arranged on two sides of the fuselage;
the outer layer of the NiTi memory alloy skeleton structure 3 is coated with a wing skin 1, and the wing skin 1 plays a role in protecting the internal structure;
an internal heating system for heating the NiTi memory alloy skeleton structure 3 is arranged in the NiTi memory alloy skeleton structure 3, and the internal heating system is used for controlling the temperature in the NiTi memory alloy skeleton structure 3;
a temperature sensor which is convenient for testing the temperature of the NiTi memory alloy framework structure 3 is arranged in the NiTi memory alloy framework structure, and the temperature sensor is used for conveniently testing the temperature of the NiTi memory alloy framework structure 3;
the signal of the temperature sensor is transmitted to the intelligent sensing system through an electric signal, and the intelligent sensing system plays a role in controlling the internal heating system;
a heat insulation layer 2 is arranged between the NiTi memory alloy framework structure 3 and the interlayer of the internal heating system, and the heat insulation layer 2 plays a role in heat insulation;
the NiTi memory alloy skeleton structure 3 is Ni 50.9 Ti 49.1 The deformed wing structure of the shape memory alloy negative Poisson ratio unit body;
the raw materials of the composite material comprise 49.1 wt.% of Ti powder and 50.9 wt.% of Ni powder; in the traditional nickel-titanium alloy preparation process, due to the influence of factors such as component segregation and impurities, the alloy components are uneven, the structure properties such as the moulding forming and the alloy density of the alloy are influenced, and the shape memory effect of the printed sample piece is not ideal. Material Ni we used 50.9 Ti 49.1 The shape memory effect is relatively good after the research and the experimental verification of other people, and the structure is obtainedWhen a compression recovery experiment is carried out, the recovery effect can reach about 75 percent at most. The printed finished sample piece has high compactness and good fatigue resistance.
The NiTi memory alloy skeleton structure adopts a full-coverage type skeleton with a negative Poisson ratio, the memory alloy negative Poisson ratio unit body skeleton structure is manufactured by an additive manufacturing method, the adopted skeleton structures are different from the traditional wing skeletons, a truss type beam structure is not adopted, but the full-coverage type skeleton with the negative Poisson ratio is adopted, a negative Poisson ratio test piece can bear higher load than a positive Poisson ratio test piece when initial damage occurs, more energy can be absorbed when the test piece finally fails, delamination damage is limited in a relatively small local area, and the area of the test piece needing to be repaired is greatly reduced. Therefore, compared with the application limit of the traditional paving mode positive poisson ratio composite material in the field of aviation industry, the negative poisson ratio composite material has obvious advantages. Not only the purpose of light weight is achieved, but also the bearing performance of the wing is improved.
Wing mounting structures are arranged at the mounting positions of the NiTi memory alloy framework structure 3 and the two sides of the fuselage 5, so that the wings and the fuselage 5 can be conveniently mounted and matched.
Specifically, the wing mounting structure comprises an insertion block 6 and an insertion groove 14, wherein the insertion block 6 of the fuselage 5 is inserted into the insertion groove 14 of the wing, and the fuselage 5 and the wing are mounted in a matched manner;
a second electric conductor 16 is arranged on the inner side of the inserting groove 14;
the front end and the rear end of the left side and the right side of the outer wall of the fuselage 5 are respectively provided with an inserting block 6 which is convenient for the installation of wings;
the inner sides of the left and right sheets with the NiTi memory alloy framework structures 3 are provided with inserting grooves 14 which are arranged in the front and back and are convenient for inserting the inserting blocks 6;
the inner side of the insertion block 6 is provided with a clamping groove 7, and the clamping groove 7 is conveniently matched and inserted with a clamping block 12 to be described later;
a first conductor 8 which is contacted with a second conductor 16 and enables the NiTi memory alloy framework structure 3 and the fuselage 5 to form circuit connection is arranged on the outer side of the insertion block 6, and the first conductor 8 and the second conductor 16 are used for facilitating the electrification of the wing;
the inner sides of the front and the rear insertion grooves 14 are provided with clamping structures for mounting wings.
Furthermore, the clamping structure comprises a supporting plate 9, and the supporting plate 9 plays a supporting role on the top mechanism;
the top end of the supporting plate 9 is connected with a rotating plate 10 through a bearing shaft, and the rotating plate 10 can rotate relative to the supporting plate 9;
the inner walls of the left side and the right side of the supporting plate 9 are fixedly connected with guide rods 11, and the guide rods 11 play a role in guiding the movement of the fixture blocks 12;
the front side and the rear side of the outer wall of the guide rod 11 are respectively sleeved with a clamping block 12 which is in inserted fit with the clamping groove 7, and when the clamping blocks 12 enter the clamping grooves 7, the connection between the fuselage 5 and the wings is realized;
the center position of the top end of the inner side of each clamping block 12 is connected with one end of a push rod 13 in a shaft mode;
the other end of the push rod 13 is respectively coupled with the outer walls at the left and right ends of the top end of the rotating plate 10, and the rotating plate 10 rotates to drive the front and rear clamping blocks 12 to be inserted into the clamping grooves 7 through the push rod 13;
the central position of the rotating plate 10 is fixedly connected with a rotating rod 15 which is convenient for driving the rotating plate 10 to rotate, and the rotating rod 15 drives the rotating plate 10 to rotate;
the top end of the rotating rod 15 is penetrated with a NiTi memory alloy framework structure 3 and is provided with a rotating disk 17 for rotating the rotating rod;
a groove 18 is formed in the side wall of the turntable 17;
the inner side of the groove 18 is contacted with a telescopic mechanism clamped with the rotary disc 17.
Further, the telescopic mechanism comprises a fixed block 19, and the fixed block 19 is used for supporting the internal devices of the telescopic mechanism;
the bottom end of the fixed block 19 is fixedly connected with the NiTi memory alloy framework structure 3;
a cross rod 20 is inserted into the inner cavity of the fixed block 19;
a pull handle 21 is arranged on the outer side of the cross rod 20, and the pull handle 21 is used for pulling the cross rod 20;
the inner side of the cross rod 20 is provided with a lug 23;
the lug 23 is embedded with the groove 18, and the lug 23 enters the groove 18 to fix the turntable 17;
the outer wall of the cross rod 20 is sleeved with a spring 22;
one end of the spring 22 abuts against the inner wall of the fixed block 19, and the other end abuts against the inner wall of the projection 23.
Further, an electric heating groove is formed in the inner cavity of the NiTi memory alloy framework structure 3;
the internal heating system is embedded and connected inside the NiTi memory alloy framework structure 3 through the electric heating groove;
the internal heating system is a heating wire 4;
the material around the groove is Cu-Al-Ni alloy which is a material capable of being well matched with a deformation material
Furthermore, the number of the grooves 18 formed in the side wall of the turntable 17 is even, and the grooves are uniformly and symmetrically distributed on the side wall of the turntable 17, and the projections 23 and the grooves 18 fix the turntable 17.
Further, the rotating plate 10 is an elliptical rotating plate, and the rotating plate 10 is used for pushing the latch 12 to move through the push rod 13.
Further, the wing skin 1 is formed by integrally molding a polyether-ether-ketone flexible high polymer and a fiber composite material, and the wing skin 1 is a flexible curved surface skin.
Furthermore, the electric heating grooves are evenly distributed in the NiTi memory alloy framework structure 3 in a net shape.
Furthermore, the thermal insulation layer 2 is made of basalt fiber or HPS static composite thermal insulation paste, so that the thermal insulation performance is good, the weight is light, and deformation is not influenced.
The heat insulation layer 2 has the functions: at present, equipment and a heat supply line are coated with a single-layer or double-layer heat insulation layer, so that on one hand, the heat dissipation loss of a heat medium in the conveying process is reduced, and on the other hand, the stable temperature in wing deformation is ensured to prevent the deformation from not being in place.
According to the unit body framework of the unmanned aerial vehicle morphing wing, a negative Poisson ratio unit model required by the unmanned aerial vehicle morphing wing is established by using CATIA modeling software, and then the unit body can be re-entered, as shown in FIG. 2; then, the unit bodies are arranged to form the shape of the wing, and an electric heating groove is designed in the framework of the wing so as to be convenient for embedding a heating wire; and finally, establishing a curved surface on the outer layer of the wing framework, namely a flexible wing skin. Finally, establishing a three-dimensional model in a computer;
then, printing the wing structure by using an SLM (selective laser melting) technology, dividing the skeleton structure into five parts based on the actual printing capacity of a printer, and assembling after printing respectively; and the equipment controls the laser beam to selectively melt the metal powder materials of each layer according to the filling scanning lines and gradually stacks the metal powder materials into a three-dimensional wing skeleton structure. Before the laser beam starts scanning, a powder spreading device firstly pushes metal powder to a substrate of a forming cylinder, the laser beam selectively melts the powder on the substrate according to a filling scanning line of a current layer to process the current layer, then the forming cylinder descends by a distance of one layer thickness, a powder material cylinder ascends by a distance of a certain thickness, the powder spreading device spreads the metal powder on the processed current layer, equipment is adjusted to data of the profile of the next layer to process, and the layer-by-layer processing is carried out until the framework structure is processed.
The working principle is as follows: ni 50.9 Ti 49.1 The alloy obtains a two-way shape memory effect through training, and the one-way memory effect is obtained firstly, namely the wing skeleton can be deformed through temperature, the wing can be restored to a bendable limit position, and then Ni is subjected to Ni-based annealing at a temperature Ms lower than the temperature at which the martensite of the material starts to change phase 50.9 Ti 49.1 The alloy is subjected to a deformation recovery, i.e. the airfoil retains its original shape, and is then heated to a temperature at which the martensite transforms into austenite As, Ni 50.9 Ti 49.1 The alloy recovers the bendable extreme position state, namely the wing changes to the shape adapting to the motion state of the wing; further reducing the temperature below Ms to deform Ni again 50.9 Ti 49.1 Alloying the alloy to an initial state. Through the repeated training, Ni is enabled 50.9 Ti 49.1 The alloy obtains the needed two-way memory effect, thereby realizing the function of controlling the deformation of the wing through the temperature change, and when the wing needs to be installed, firstly, the inserting slot 14 of the wing is aligned with the inserting block 6 on the side surface of the fuselage 5, the inserting block 6 is inserted into the inner cavity of the inserting slot 14, at the moment, the cross bar 20 is pulled outwards through the pull handle 21, and the cross bar 20 is provided with a beltAfter the movable lug 23 is separated from the groove 18 on the side wall of the rotary disc 17, the rotary disc 17 rotates anticlockwise, at the moment, the rotary disc 17 drives the rotary rod 15 to rotate anticlockwise, the rotary rod 15 drives the rotary plate 10 to rotate anticlockwise, the rotary plate 10 pushes the fixture block 12 into the clamping groove 7 through the push rod 13, after the fixture block 12 completely enters the clamping groove 7, the rotary disc 17 stops rotating, the pull handle 21 is loosened, and at the moment, the spring 22 resets to push the lug 23 into the groove 18 again to complete the installation of the wing.
The technical principles of the present invention have been described above in connection with specific embodiments, which are intended to explain the principles of the present invention and should not be construed as limiting the scope of the present invention in any way. Based on the explanations herein, those skilled in the art will be able to conceive of other embodiments of the invention without inventive step, which shall fall within the scope of the invention.

Claims (9)

1. An unmanned aerial vehicle deformation wing structure based on a memory alloy negative Poisson ratio unit body comprises a fuselage (5), a NiTi memory alloy framework structure (3), a wing skin (1), an internal heating system, a heat insulation layer (2), an intelligent sensing system and a temperature sensor;
wings with a NiTi memory alloy framework structure (3) as a main body are arranged on two sides of the fuselage;
the outer layer of the NiTi memory alloy skeleton structure (3) is wrapped with the wing skin (1);
an internal heating system for heating the NiTi memory alloy framework structure (3) is arranged inside the NiTi memory alloy framework structure (3);
a temperature sensor convenient for testing the temperature of the NiTi memory alloy framework structure (3) is arranged inside the NiTi memory alloy framework structure;
the signal of the temperature sensor is transmitted to the intelligent sensing system through an electric signal;
the interlayer that has NiTi memory alloy skeleton texture (3) and interior heating system sets up insulating layer (2), its characterized in that:
the NiTi memory alloy framework structure (3) is Ni 50.9 Ti 49.1 The deformation wing structure of the shape memory alloy negative Poisson's ratio unit body;
wing mounting structures are arranged at the mounting positions of the NiTi memory alloy framework structure (3) and the two sides of the fuselage (5), so that the wings and the fuselage (5) can be conveniently mounted and matched;
the wing mounting structure comprises an insertion block (6) and an insertion groove (14);
the front end and the rear end of the left side and the rear side of the outer wall of the airplane body (5) are provided with inserting blocks (6) which are convenient for mounting wings;
the inner sides of the left and right sheets of the NiTi memory alloy framework structures (3) are provided with insertion grooves (14) which are arranged in the front and back and are convenient for insertion of the insertion blocks (6);
a clamping groove (7) is formed in the inner side of the insertion block (6);
clamping structures for mounting wings are arranged on the inner sides of the front and the rear inserting grooves (14);
the clamping structure comprises a support plate (9);
the top end of the supporting plate (9) is connected with a rotating plate (10) through a bearing in a shaft way;
the inner walls of the left side and the right side of the supporting plate (9) are fixedly connected with guide rods (11);
clamping blocks (12) which are in plug-in fit with the clamping grooves (7) are sleeved on the front side and the rear side of the outer wall of the guide rod (11);
the center position of the top end of the inner side of each clamping block (12) is connected with one end of a push rod (13) in a shaft mode;
the other end of the push rod (13) is respectively connected with the outer walls at the left end and the right end of the top end of the rotating plate (10) in a shaft mode;
the center of the rotating plate (10) is fixedly connected with a rotating rod (15) which is convenient for driving the rotating plate (10) to rotate;
a NiTi memory alloy framework structure (3) penetrates through the top end of the rotating rod (15) and is provided with a rotating disk (17) for rotating the rotating rod;
a groove (18) is formed in the side wall of the rotary table (17);
the inner side of the groove (18) is contacted with a telescopic mechanism which is clamped with the turntable (17).
2. The deformable wing structure of drone based on negative poisson's ratio memory alloy unit cell of claim 1, wherein:
a second electric conductor (16) is arranged on the inner side of the inserting groove (14);
and a first conductor (8) which is contacted with the second conductor (16) and enables the NiTi memory alloy framework structure (3) and the machine body (5) to form circuit connection is arranged on the outer side of the insertion block (6).
3. The deformable wing structure of unmanned aerial vehicle based on memory alloy negative poisson's ratio unit body of claim 1, wherein:
the telescopic mechanism comprises a fixed block (19);
the bottom end of the fixed block (19) is fixedly connected with the NiTi memory alloy framework structure (3);
a cross rod (20) is inserted into the inner cavity of the fixed block (19);
a pull handle (21) is arranged on the outer side of the cross rod (20);
a lug (23) is arranged on the inner side of the cross rod (20);
the lug (23) is embedded with the groove (18);
the outer wall of the cross rod (20) is sleeved with a spring (22);
one end of the spring (22) is abutted against the inner wall of the fixing block (19), and the other end of the spring is abutted against the inner wall of the bump (23).
4. The morphing wing structure of unmanned aerial vehicle based on memory alloy negative poisson's ratio unit cell of any one of claims 1-3, wherein:
an electric heating groove is formed in the inner cavity of the NiTi memory alloy framework structure;
the internal heating system is embedded in the NiTi memory alloy framework structure through the electric heating groove;
the internal heating system is an electric heating wire (4);
the peripheral material of the groove is Cu-Al-Ni alloy.
5. The morphing wing structure of unmanned aerial vehicle based on memory alloy negative poisson's ratio cell body of any one of claims 1 or 3, wherein:
the number of the grooves (18) formed in the side wall of the rotary table (17) is even, and the grooves are uniformly and symmetrically distributed in the side wall of the rotary table (17).
6. The morphing wing structure of unmanned aerial vehicle based on memory alloy negative poisson's ratio cell body of any one of claims 1 or 3, wherein:
the rotating plate (10) is an oval rotating plate.
7. The deformable wing structure of unmanned aerial vehicle based on memory alloy negative poisson's ratio unit body of claim 1, wherein:
the wing skin is integrally formed by a polyether-ether-ketone flexible high polymer and a fiber composite material, and is a flexible curved surface skin.
8. The deformable wing structure of unmanned aerial vehicle based on memory alloy negative poisson's ratio unit body of claim 4, wherein:
the electrothermal grooves are uniformly distributed in the NiTi memory alloy framework structure in a mesh shape.
9. The deformable wing structure of unmanned aerial vehicle based on memory alloy negative poisson's ratio unit body of claim 1, wherein:
the heat insulation layer material adopts basalt fiber or HPS static composite heat insulation paste.
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