Distributed thermoelectric element morphing wing SMA driver and method and application

Abstract

The invention discloses a distributed thermoelectric element variant wing SMA driver and method and application, the SMA driver comprises an active cooling layer, an SMA wire driving structure and an elastic supporting layer which are sequentially arranged from top to bottom, each layer is embedded in a flexible material in a sealed mode, the active cooling layer is composed of a plurality of thermoelectric elements arranged in an array mode, and the elastic supporting layer is embedded in the active cooling layer. The thermoelectric element achieves refrigeration of the SMA wire driving structure through the Peltier effect. The cooling efficiency can be remarkably improved, heat accumulation is eliminated, the recovery time of the driver is shortened, the driving frequency is improved, and the service life of the shape memory alloy driver is prolonged. According to the algorithm, an adaptive thermoelectric element layout scheme can be automatically generated in combination with the structural characteristics of the driver, so that heat transfer is accelerated, the uniformity of a temperature field is improved, the application requirements under multiple working conditions and complex environments are met, the algorithm has good universality, the integration requirements of different types of wings are met, and the application prospect is wide. The design process is effectively simplified, and the manufacturing cost is reduced.

Description

Technical Field

[0001] This invention belongs to the field of variator aircraft technology, and particularly relates to a distributed thermoelectric element variator wing SMA actuator, method, and application. Background Technology

[0002] The wing is a key component affecting aircraft performance. Traditional fixed wings are typically designed based on the aerodynamic characteristics of specific flight missions and environmental conditions, achieving optimal aerodynamic performance only at one or a few design points. Facing complex flight environments and missions, aircraft need greater flight flexibility and efficiency to adapt to diverse mission requirements. Therefore, aircraft are evolving towards multi-mission adaptability and high maneuverability, making variator wing technology driven by smart materials a crucial direction for future aircraft design.

[0003] Shape memory alloy (SMA) actuators have attracted widespread attention due to their unique shape memory effect and superelastic properties. When a trained SMA is energized, its temperature rises under the Joule effect. When the temperature exceeds the phase transition temperature, the SMA deforms and drives the skin structure to achieve actuation. After heating is stopped, the SMA cools down and returns to its original shape, and the skin structure also recovers. SMA actuators weigh only 3-10% of traditional actuators, which can reduce aircraft weight and improve fuel efficiency and maneuverability. Furthermore, their rapid response characteristics enable precise deformation of the skin structure, further optimizing the aerodynamic performance of the aircraft. Therefore, SMA actuators have broad application prospects in variator wings.

[0004] The SMA (Speed ​​MA) relies on temperature changes for propulsion. Modulating wings require high-frequency, large-amplitude deformations under multi-task conditions, necessitating effective temperature control of the SMA to ensure rapid actuator response and stable operation. Current technologies primarily cool the SMA using methods such as air cooling, liquid cooling, and radiators. Natural air cooling is simple and easy to implement, but its cooling efficiency is low. Forced ventilation offers high cooling efficiency but requires additional air supply equipment, making the system complex and difficult to integrate. Liquid cooling provides strong cooling capacity, but the system is bulky, poses a leakage risk, and fails to meet the lightweight and compact requirements of modifying wings. Radiators perform well in some applications, but their response lags during high-frequency propulsion, making dynamic temperature control impossible.

[0005] To address the stringent requirements of variator wings regarding system weight, size, and temperature control response speed, it is necessary to introduce active cooling technology with efficient thermal management capabilities and excellent temperature control performance. Thermoelectric elements based on the Peltier effect offer advantages such as small size, fast response, high control precision, and ease of integration. When energized, one side absorbs heat, achieving rapid cooling. To further accelerate heat transfer and improve the uniformity of the overall temperature field distribution of the actuator, the spatial layout of the thermoelectric elements needs to be optimized to meet the application requirements of variator wings in various operating conditions and complex environments. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to provide a distributed thermoelectric element variant wing SMA actuator, method and application to address the above-mentioned shortcomings of the existing technology.

[0007] To achieve the above-mentioned technical objectives, the technical solution adopted by the present invention is as follows:

[0008] The distributed thermoelectric element variant wing SMA actuator includes an active cooling layer, an SMA filament drive structure, and an elastic support layer arranged sequentially from top to bottom. Each layer is sealed and embedded in a flexible material. The active cooling layer consists of several arrayed thermoelectric elements, which cool the SMA filament drive structure through the Peltier effect.

[0009] To optimize the above technical solution, the specific measures also include:

[0010] The aforementioned SMA wire drive structure consists of two end positioning plates and several SMA wires made of single-pass SMA material. The SMA wires are arranged side by side, and the two end positioning plates are fixed to the left and right ends of the elastic support layer, respectively. At the same time, the end positioning plates are also fixedly connected to the left and right ends of the SMA wires. One of the end positioning plates is connected to a power source for heating the SMA wire.

[0011] The aforementioned flexible material is formed by layer-by-layer casting and curing.

[0012] The aforementioned elastic support layer is a single-layer elastic support plate.

[0013] The aforementioned SMA wire is a NiTi shape memory alloy wire, the elastic support plate is a PVC plate, silicone plate or PE plate, the flexible material is PDMS or silicone, and the end positioning plate is an FR-4 plate, PEEK plate or PI plate.

[0014] A method for fabricating a distributed thermoelectric element variant wing SMA actuator includes the following steps: First, an array of thermoelectric elements is placed in a mold, and flexible material is poured; then, two end positioning plates containing SMA wires are placed in the mold, and flexible material is poured, followed by secondary curing; finally, an elastic support plate is laid in the mold, and flexible material is poured again, and after curing, the distributed thermoelectric element variant wing SMA actuator is obtained.

[0015] A design method for a distributed thermoelectric element variant wing SMA actuator is presented, which involves designing the aforementioned distributed thermoelectric element variant wing SMA actuator and calculating and optimizing the arrangement of the thermoelectric elements.

[0016] Step 1: Generate a set of thermoelectric element layouts with random positions and distribution patterns as the initial layout scheme set S = {S1, S2, ..., S...} N}, where each layout scheme S i This represents a specific distribution method for thermoelectric elements, where N is the total number of possible arrangements.

[0017] Step 2: Evaluate different layout schemes S i The cooling effect, specifically, is expressed as follows: the expression for the cooling effect of the thermoelectric element on its surrounding area is: Where A is the cooling intensity coefficient, σ is the thermal effect attenuation scale parameter, (x,y) are the coordinates of the thermoelectric element, and (X,Y) are the coordinates of the grid point in the temperature field; based on the coordinates of all thermoelectric elements and the cooling effect, the new temperature distribution can be expressed as: Where, T0(x) i ,y i (x) represents the initial temperature, and (x) represents the initial temperature. i ,y i ) represents the position of the i-th thermoelectric element, E cooling (x i ,y i Let be the cooling effect of the i-th thermoelectric element, and n be the total number of thermoelectric elements; the uniformity of the temperature field is evaluated by the layout evaluation function, which is expressed as: ΔT=max(T'(x) i ,y i ))-min(T'(x i ,y i )), where max(T′(x i ,y i The maximum value of the new temperature distribution is min(T'(x)). i ,y i The minimum value of the new temperature distribution is ΔT. The smaller the difference between the highest and lowest temperatures in the temperature field, the more uniform the temperature field and the better the layout scheme.

[0018] Step 3: Through a sorting and optimization mechanism, gradually select the layout scheme S with better current temperature control performance. i Moving to the next generation; a layout reorganization operation is used, that is, two layout schemes with good temperature control performance are selected from the current layout set S, local structural features are extracted and combined to generate a new layout scheme S′; in order to expand the solution space and avoid getting trapped in local optima, the algorithm introduces a perturbation mechanism, which adjusts the position parameters of thermoelectric elements in the current layout scheme according to the perturbation rate p, to obtain a new set of perturbed layout schemes; the perturbation rate p gradually decays with the iteration process, and its calculation formula is: Where p is the current perturbation probability, p min p0 is the minimum perturbation rate, n is the initial perturbation rate, and p0 is the minimum perturbation rate. cur Let n be the current iteration number. max The maximum number of iterations is given by α, which is an adjustment factor to control the decay rate of the disturbance rate. Local fine-tuning is introduced to fine-tune the spacing and position of the thermoelectric elements for a better layout scheme. Through multiple generations of iterative optimization, the cooling efficiency of the driver is gradually improved to obtain the optimal thermoelectric element layout scheme.

[0019] The distributed thermoelectric element variant wing SMA actuator is applied to a variable camber wing, which includes an active deformable section connected to a rigid connecting section; the rigid connecting section is used to provide fixed support for the active deformable section; the active deformable section is used to deform the wing; the distributed thermoelectric element variant wing SMA actuator is installed inside the active deformable section.

[0020] The active deformation section is covered with a flexible skin, and the distributed thermoelectric element variant wing SMA actuator is embedded in the flexible skin. The flexible skin can work together with the distributed thermoelectric element variant wing SMA actuator to complete the camber change.

[0021] Multiple distributed thermoelectric element variant wing SMA actuators are distributed along the spanwise direction of the variable camber wing. The distributed thermoelectric element variant wing SMA actuators at different locations are driven independently or in groups. By controlling the directional bending of different regions of the wing spanwise, the complex spanwise variable camber deformation of the variable camber wing is realized.

[0022] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0023] 1. The actuator designed in this invention can significantly improve cooling efficiency, eliminate heat accumulation, shorten actuator recovery time, increase driving frequency, and extend the service life of shape memory alloy actuators by integrating thermoelectric elements in the actuator.

[0024] 2. This invention employs thermoelectric elements based on the Peltier effect as an active cooling device, which has advantages such as small size, easy integration, and fast response speed. Compared with existing air cooling and liquid cooling methods, it does not require an additional air source or piping system, making the system more streamlined, reliable, and stable in operation. It achieves rapid temperature regulation response through current control, thereby realizing efficient thermal management of the variator wing.

[0025] 3. This invention proposes a casting scheme that integrates a flexible material with properties such as light weight, high temperature resistance, strong insulation and hydrophobicity. By incorporating this flexible material into the key arrangement area of ​​the thermoelectric element, direct contact between the thermoelectric element and the shape memory alloy wire is effectively avoided, thereby improving heat dissipation efficiency and electrical safety of the device. Combined with the sealing structure design, condensation is effectively prevented, extending the service life of the thermoelectric element and ensuring the long-term efficient and stable operation of the temperature control system.

[0026] 4. The algorithm of this invention can automatically generate a suitable thermoelectric element layout scheme by combining the structural characteristics of the actuator, so as to accelerate heat transfer, improve the uniformity of temperature field, and meet the application requirements of multiple working conditions and complex environments. The algorithm has good versatility and is suitable for the integration requirements of different types of wings, effectively simplifying the design process and reducing manufacturing costs. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the distributed thermoelectric element variant wing SMA actuator structure of the present invention;

[0028] Figure 2 This is a side view of the distributed thermoelectric element variant wing SMA actuator of the present invention;

[0029] Figure 3 This is a schematic cross-sectional view of the distributed thermoelectric element variant wing SMA actuator of the present invention;

[0030] Figure 4 yes Figure 1 Structural diagram showing the connection method between the SMA wire and the end positioning plate;

[0031] Figure 5 This is a schematic diagram of heat transfer in the distributed thermoelectric element variant wing SMA actuator of the present invention;

[0032] Figure 6 This is a schematic diagram of the bending deformation of the actuator during the phase change of the SMA filament under heating.

[0033] Figure 7 This is a flowchart of the algorithm for optimizing the placement of thermoelectric elements;

[0034] Figure 8 This is a schematic diagram of the installation method of the distributed thermoelectric element variant wing SMA actuator of the present invention on the trailing edge of a variable camber wing;

[0035] Figure 9 This is a schematic diagram of the trailing edge deformation of a variable camber wing equipped with the distributed thermoelectric element variant wing SMA actuator of the present invention.

[0036] 1 is SMA wire, 2 is thermoelectric element, 3 is elastic support plate, 4 is flexible material, 5 is end positioning plate, 6 is rigid connection section, 7 is active deformation section, 8 is flexible skin, and 9 is airfoil section. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this application clearer, the application is described and illustrated below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application. All other embodiments obtained by those skilled in the art based on the embodiments provided in this application without inventive effort are within the scope of protection of this application.

[0038] Obviously, the accompanying drawings described below are merely some examples or embodiments of this application. Those skilled in the art can apply this application to other similar scenarios based on these drawings without any inventive effort. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this application, any changes to design, manufacturing, or production based on the technical content disclosed in this application are merely conventional technical means and should not be construed as insufficient disclosure of the content of this application.

[0039] The distributed thermoelectric element variant wing SMA actuator of the present invention includes, from top to bottom, an active cooling layer, an SMA filament drive structure, and an elastic support layer, each layer being sealed and embedded within a flexible material 4. The active cooling layer consists of several arrayed thermoelectric elements 2. The SMA filament drive structure consists of two end positioning plates 5 and several SMA filaments 1 arranged side by side. The two end positioning plates 5 are respectively fixed to the left and right ends of the elastic support layer, and are also fixedly connected to the left and right ends of the SMA filaments 1. One of the end positioning plates 5 is connected to a power source for heating the SMA filaments 1. The elastic support layer is an elastic support plate 3.

[0040] SMA wire 1 is a NiTi shape memory alloy wire. By resistive heating, SMA wire 1 is heated rapidly. When the temperature reaches the phase transformation temperature, an austenitic phase transformation occurs, thereby achieving active deformation. This material can maintain stable performance in high-frequency cycling and has high shape recovery accuracy.

[0041] Thermoelectric element 2 is made of materials such as bismuth telluride (Bi2Te3), bismuth antimonide (Sb2Te3), or aluminum telluride (Al2Te3); after being energized, thermoelectric element 2 actively absorbs heat, thereby improving the cooling speed of the actuator.

[0042] The elastic support plate 3 can be made of PVC board, silicone board, PE board, etc. The elastic support plate 3 can improve the structural stability of the actuator during the deformation process and provide restoring force during the cooling stage of SMA wire 1, ensuring that the actuator quickly returns to its initial shape, so as to ensure that the actuator has reliable shape recovery capability during long-term use, while improving the overall service life.

[0043] A vertical distance of 2mm is maintained between the SMA wire 1 and the elastic support plate 3. This parameter can be adjusted according to specific application requirements and driver size to further optimize the driving effect.

[0044] The end positioning plate 5 can use FR-4 plate, PEEK plate, PI plate, etc. to stably support the driver structure and provide a reliable fixing base for SMA wire 1.

[0045] Before connecting the SMA wire 1 to the end positioning plate 5, it undergoes repeated loading and energizing training to enhance its fatigue resistance and shape memory effect stability. Figure 4 The SMA wire 1 is connected to the end positioning plate 5 in a parallel manner. The number and length of the SMA wire 1 are set according to the size of the wing; the number of thermoelectric elements 2 is set according to the specific configuration of the SMA wire 1.

[0046] The flexible material 4 can be PDMS, silicone, or other materials. The flexible material and the curing agent are mixed in a 10:1 ratio and then poured to form a uniform sealing layer to improve the impact resistance of the actuator.

[0047] The SMA driver is made of flexible material and sealed by layer-by-layer curing. First, the thermoelectric element 2 is placed in the mold and the flexible material is poured. Then, the end positioning plate 5 with SMA wire 1 is placed in the mold for secondary curing. Finally, the elastic support plate 3 is added and the flexible material is poured again. After curing, the driver is formed as a whole.

[0048] Figure 5 This is a schematic diagram of the heat transfer of the SMA driver of the present invention. The heat is actively absorbed by the thermoelectric element 2 to improve the heat dissipation effect of the driver. The Joule heat generated by the SMA wire 1 after being energized is the heat source, and its heat is uniformly conducted to each part of the driver through the flexible material. When the thermoelectric element 2 is energized, the heat in the driver is dissipated through thermoelectric cooling, natural convection and thermal radiation.

[0049] Depend on Figure 5The energy transfer relationships shown are used to build a thermodynamic model with the SMA actuator as the object. Considering the Joule heat absorbed by the SMA actuator per unit time, natural convection heat dissipation, and the thermal effect of the thermoelectric element, while neglecting thermal radiation, and assuming a uniform heat capacity distribution of the SMA actuator, a lumped parameter modeling approach is used to establish the thermodynamic model, specifically: Where C is the equivalent heat capacity of the SMA actuator; T(t) is the temperature of the SMA actuator at time t; I(t) is the driving current applied to the SMA actuator; R is the resistance of the SMA material; h is the natural convection heat transfer coefficient of air; h is the heat transfer surface area of ​​the actuator in contact with the air; T ambient Q represents ambient temperature; Peltier (t) represents the net thermal power of thermoelectric element 2 to the actuator, including the cooling and heating power it generates and the thermal effects such as Joule heating caused by the current.

[0050] The thermodynamic model described the real-time dynamic process of temperature change in the SMA actuator; its physical meaning is: per unit time, the SMA actuator generates heat (I) due to the resistance current. 2 R), while simultaneously dissipating heat to the outside air hA[T(t)-T abient ], and is affected by the active cooling Q applied by thermoelectric element 2. Peltier The three factors together determine its rate of temperature change. In a practical implementation, I(t) can be adjusted by a current source controller, and Q can be adjusted by controlling the operating current of thermoelectric element 2. Peltier (t), thereby controlling the heating and cooling process of the SMA drive.

[0051] The established thermodynamic model can serve as the basis for quantitative prediction of temperature changes. In subsequent implementation, control methods can be added to this model to further improve control accuracy and response speed. The control methods include, but are not limited to, one or more control strategies such as proportional-integral-derivative (PID) coupled control, model predictive control (MPC), and fuzzy control.

[0052] Figure 6 A schematic diagram of the bending deformation of the actuator after heating the SMA wire 1 to undergo a phase transformation; when the SMA wire 1 is energized, the temperature rises to the austenitic phase transformation temperature, and the elastic support plate 3 bends synchronously with the actuator; when the thermoelectric element 2 is energized, the SMA wire 1 can be cooled and transformed into the martensitic phase, and the elastic support plate 3 provides elastic restoring force for the SMA wire 1, helping the actuator to return to its initial shape.

[0053] To further improve the cooling efficiency and operational stability of the SMA driver, this invention uses an algorithm to calculate and optimize the arrangement of thermoelectric elements 2. The goal of this optimization algorithm is to maximize cooling efficiency and avoid local overheating through a reasonable arrangement of thermoelectric elements 2.

[0054] Figure 7 The flowchart shows the algorithm for optimizing the position of thermoelectric element 2. The algorithm first generates a set of random positions and distribution patterns for thermoelectric element 2 layouts, as the initial layout scheme set S = {S1, S2, ..., S...}. N}, where each layout scheme S i This represents a specific distribution of thermoelectric element 2, where N is the total number of possible layouts; then, different layout schemes S are evaluated. i The cooling effect; specifically: the expression for the cooling effect of thermoelectric element 2 on its surrounding area is: Where A is the cooling intensity coefficient, σ is the thermal effect attenuation scale parameter, (x,y) are the coordinates of the thermoelectric element, and (X,Y) are the coordinates of the grid point in the temperature field; based on the coordinates of all thermoelectric elements 2 and the cooling effect, the new temperature distribution can be expressed as: Where, T0(x) i ,y i (x) represents the initial temperature, and (x) represents the initial temperature. i ,y i ) represents the position of the i-th thermoelectric element 2, E cooling (x i ,y i ) represents the cooling effect of the i-th thermoelectric element 2, and n is the total number of thermoelectric elements; the uniformity of the temperature field is evaluated by the layout evaluation function, which is expressed as: ΔT=max(T'(x i ,y i ))-min(T′(x i ,y i ), where max(T'(x i ,y i The maximum value of the new temperature distribution is min(T'(x)). i ,y i The minimum value of the new temperature distribution is represented by ΔT. The smaller the difference between the highest and lowest temperatures in the temperature field, the more uniform the temperature field and the better the layout scheme. During the optimization process, a sorting and selection mechanism is used to gradually select the layout scheme S with better temperature control performance. iMoving to the next generation; using a layout reorganization operation, two layout schemes with better cooling effects are selected from the existing different layout schemes S. Sub-regions with outstanding temperature control effects are extracted from the two layout schemes, and the sub-regions of one scheme replace the same positions in the other scheme, generating a new position combination S'. The thermoelectric element 2 after layout reorganization must avoid overlapping and exceeding the boundary. To expand the solution space and avoid getting trapped in local optima, the algorithm introduces a perturbation mechanism. In each iteration, several thermoelectric elements are randomly selected from the current layout schemes according to the current perturbation rate p, and their positions are slightly adjusted to obtain the solution set of the new perturbed layout scheme. The perturbed layout schemes cannot overlap and do not exceed the driver boundary, and the uniformity of their temperature field is re-evaluated using the layout evaluation function. The perturbation rate gradually decreases according to the iteration process, and its calculation formula is: Where p is the current perturbation probability, p min p0 is the minimum perturbation rate, n is the initial perturbation rate, and p0 is the minimum perturbation rate. cur Let n be the current iteration number. max The maximum number of iterations is α, which is an adjustment factor to control the decay rate of the disturbance rate. Local fine-tuning is introduced to fine-tune the spacing and position of thermoelectric element 2 for better layout schemes. Through multiple generations of iterative optimization, the cooling efficiency of the driver is gradually improved, and the optimal layout scheme of thermoelectric element 2 is obtained.

[0055] Figure 8 This is a schematic diagram of the installation method of the SMA actuator of the present invention on one side of a variable camber wing. The wing structure on the other side is symmetrical and identical to it. The wing section 9 shows the embedding method of the SMA actuator in the flexible skin 8. The variable camber wing includes a rigid connecting section 6 and an active deformation section 7. The rigid connecting section 6 is used to connect the overall structure and provide fixed support. The active deformation section 7 undertakes the actual deformation task. The SMA actuator is installed inside the active deformation section 7 of the wing and embedded in the flexible skin 8 to realize the variable camber of the wing trailing edge. The flexible skin 8 can be a single-layer or multi-layer composite structure with certain elasticity and thermal conductivity to adapt to the thermal deformation process of the SMA actuator and cooperate to complete the camber change.

[0056] Figure 9 This is a schematic diagram of the trailing edge camber of an airfoil on which the SMA actuator of the present invention is installed. By controlling the current to heat the SMA wire 1, the SMA wire 1 is transformed from the martensitic phase to the austenitic phase. The actuator drives the flexible skin to bend and deform, thereby realizing the camber of the airfoil.

[0057] In this invention, only one SMA actuator is set to realize the local trailing edge camber control of the wing; according to the actual application requirements, multiple SMA actuators can be distributed along the wing spanwise, and the SMA actuators at different positions can be driven independently or in groups. By controlling the directional bending of different regions of the wing spanwise, complex spanwise camber deformation can be further realized.

[0058] The above embodiments are preferred embodiments of the present invention, but the embodiments of the present invention are not limited to the embodiments described above. Any changes, modifications, substitutions, combinations, or simplifications made without departing from the spirit and principle of the present invention shall be considered equivalent substitutions and shall be included within the protection scope of the present invention.

Claims

1. A distributed thermoelectric element variant wing SMA actuator, characterized in that, It includes an active cooling layer, an SMA filament drive structure and an elastic support layer arranged from top to bottom. Each layer is sealed and embedded in a flexible material (4). The active cooling layer is composed of several arrayed thermoelectric elements (2). The thermoelectric elements (2) cool the SMA filament drive structure through the Peltier effect.

2. The distributed thermoelectric element variant wing SMA actuator according to claim 1, characterized in that, The SMA wire drive structure consists of two end positioning plates (5) and several SMA wires (1) made of single-pass SMA material. The SMA wires (1) are arranged side by side. The two end positioning plates (5) are fixed to the left and right ends of the elastic support layer respectively. At the same time, the end positioning plates (5) are also fixedly connected to the left and right ends of the SMA wires (1). One of the end positioning plates (5) is connected to a power source for heating the SMA wires (1).

3. The distributed thermoelectric element variant wing SMA actuator according to claim 1, characterized in that, The flexible material (4) is formed by layer-by-layer casting and curing.

4. The distributed thermoelectric element variant wing SMA actuator according to claim 1, characterized in that, The elastic support layer is a single-layer elastic support plate (3).

5. The distributed thermoelectric element variant wing SMA actuator according to claim 1, characterized in that, The SMA wire (1) is a NiTi shape memory alloy wire, the elastic support plate (3) is a PVC plate, a silicone plate or a PE plate, the flexible material (4) is PDMS or silicone, and the end positioning plate (5) is an FR-4 plate, a PEEK plate or a PI plate.

6. A method for fabricating a distributed thermoelectric element variant wing SMA actuator, characterized in that, The preparation of the distributed thermoelectric element variant wing SMA actuator as described in claim 4 includes the following steps: First, the arrayed thermoelectric elements (2) are placed in a mold and flexible material is poured; then, the two end positioning plates (5) with SMA wires (1) are placed in the mold and flexible material is poured, followed by secondary curing; finally, an elastic support plate (3) is laid in the mold and flexible material is poured again, and after curing, the distributed thermoelectric element variant wing SMA actuator is obtained.

7. A design method for a distributed thermoelectric element variant wing SMA actuator, characterized in that, The distributed thermoelectric element variant wing SMA actuator as described in claim 4 is designed, and the arrangement of the thermoelectric elements (2) is calculated and optimized. Step 1: Generate a set of thermoelectric element (2) layouts with random positions and distribution patterns as the initial layout scheme set S = {S1, S2, ..., S} N }, where each layout scheme S i This represents a specific distribution pattern of thermoelectric element (2), where N is the total number of schemes; Step 2: Evaluate different layout schemes S i The cooling effect is specifically as follows: The expression for the cooling effect of the thermoelectric element (2) on its surrounding area is: Where A is the cooling intensity coefficient, σ is the thermal effect attenuation scale parameter, (x,y) are the coordinates of the thermoelectric element, and (X,Y) are the coordinates of the grid point on the temperature field; based on the coordinates of all thermoelectric elements (2) and the cooling effect, the new temperature distribution can be expressed as: Where, T0(x) i ,y i (x) represents the initial temperature, and (x) represents the initial temperature. i ,y i ) represents the position of the i-th thermoelectric element (2), E cooling (x i ,y i ) represents the cooling effect of the i-th thermoelectric element (2), and n is the total number of thermoelectric elements; the uniformity of the temperature field is evaluated by the layout evaluation function, which is expressed as: ΔT=max(T'(x i ,y i ))-min(T'(x i ,y i ), where max(T'(x i ,y i The maximum value of the new temperature distribution is min(T'(x)). i ,y i The minimum value of the new temperature distribution is ΔT. The smaller the difference between the highest and lowest temperatures in the temperature field, the more uniform the temperature field and the better the layout scheme. Step 3: Through a sorting and optimization mechanism, gradually select the layout scheme S with better current temperature control performance. i Moving to the next generation; using layout reorganization operation, that is, selecting two layout schemes with better temperature control effect from the current layout set S, extracting local structural features and combining them to generate a new layout scheme S′; in order to expand the solution space and avoid getting trapped in local optima, the algorithm introduces a perturbation mechanism, adjusting the position parameters of thermoelectric element (2) in the current layout scheme according to the perturbation rate p, and obtaining the new layout scheme set after perturbation; the perturbation rate p gradually decreases with the iteration process, and its calculation formula is: Where p is the current perturbation probability, p min p0 is the minimum perturbation rate, n is the initial perturbation rate, and p0 is the minimum perturbation rate. cur Let n be the current iteration number. max The maximum number of iterations is α, which is an adjustment factor to control the decay rate of the disturbance rate. Local fine-tuning operation is introduced to fine-tune the spacing and position of the thermoelectric element (2) for a better layout scheme. Through multi-generation iterative optimization, the cooling efficiency of the driver is gradually improved, and the optimal layout scheme of the thermoelectric element (2) is obtained.

8. The application of the distributed thermoelectric element variant wing SMA actuator as described in claim 3, characterized in that: Applied to a variable camber wing, the variable camber wing includes an active deformation section (7) interconnected with a rigid connecting section (6); the rigid connecting section (6) is used to provide fixed support for the active deformation section (7); the active deformation section (7) is used to deform the wing; the distributed thermoelectric element variant wing SMA driver is installed inside the active deformation section (7).

9. The application of the distributed thermoelectric element variant wing SMA actuator according to claim 8, characterized in that: The active deformation segment (7) is covered with a flexible skin (8), and the distributed thermoelectric element variant wing SMA actuator is embedded in the flexible skin (8). The flexible skin (8) can work together with the distributed thermoelectric element variant wing SMA actuator to complete the camber change.

10. The application of the distributed thermoelectric element variant wing SMA actuator according to claim 9, characterized in that: Multiple distributed thermoelectric element variant wing SMA actuators are distributed along the spanwise direction of the variable camber wing. The distributed thermoelectric element variant wing SMA actuators at different locations are driven independently or in groups. By controlling the directional bending of different regions of the wing spanwise, the complex spanwise variable camber deformation of the variable camber wing is realized.

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