Integrated variable camber wing based on piezoelectric driving pressure-torsion cubic superstructure

Abstract

This invention relates to an integrated variable camber wing based on a piezoelectric-driven torsional cubic superstructure, comprising a wing skeleton and a skin. The wing skeleton includes multiple torsional cubic superstructures arrayed along the wing chord direction. Each torsional cubic superstructure is a cube formed by an array of multiple unit-cell torsional superstructures. Adjacent unit-cell torsional superstructures in the wing length and thickness directions share a straight rod, while adjacent unit-cell torsional superstructures in the wing width direction share four Z-shaped piezoelectric rods. Each unit-cell torsional superstructure is a cube formed by an array of four cell units, with adjacent cell units sharing a straight rod. Each cell unit includes Z-shaped piezoelectric rods and straight rods. Two Z-shaped piezoelectric rods are connected to the two ends of two straight rods. Each Z-shaped piezoelectric rod at both ends of the torsional cubic superstructure is connected to the skin. When all the Z-shaped piezoelectric rods of the unit-cell torsional superstructure undergo compressive deformation in the height direction, the unit-cell torsional superstructure undergoes torsional deformation, thus causing the torsional cubic superstructure to undergo torsional deformation. By converting the compressive deformation of the cellular unit into the torsional deformation of the compressive-torsional cubic superstructure, the wing camber is changed, and the drive components are eliminated, thus realizing the lightweight design of the morphing wing.

Description

Technical Field

[0001] This invention belongs to the field of variator wing technology, specifically an integrated variable camber wing based on a piezoelectrically driven torsion cubic superstructure. Background Technology

[0002] Traditional aircraft have fixed wings, with their wingspan and airfoil remaining constant throughout flight, making them unsuitable for complex and ever-changing flight environments and missions. Variable-camber wings, on the other hand, are variant wings that can alter their wingspan and airfoil by changing their camber. This allows for adjustments based on flight requirements, improving the aircraft's aerodynamic performance and maneuverability. For wingspan adjustment, increasing wingspan during takeoff and landing provides greater lift, making takeoff and landing easier; while decreasing wingspan during cruise reduces drag, improving speed and fuel efficiency. By adjusting the airfoil, variable-camber wings can provide different lift and drag characteristics at different flight phases. For example, a thinner airfoil is used for high-speed flight to reduce drag, while a thicker airfoil is used for low-speed flight to increase lift.

[0003] Existing variable-camber wings typically consist of multiple independent wing segments, each of which can independently adjust its wingspan and airfoil. The aircraft can use different wingspans and airfoils at different flight phases to adapt to varying flight conditions and mission requirements. However, this split design severely impacts the compliance of the variable-camber wing. For example, invention patent CN 117566088 A, published on February 20, 2024, discloses a variable-camber wing rib, mainly comprising a fixed side rib, a movable side rib, and a drive shaft. A drive system moves the drive shaft, causing the movable side rib to rotate around the fixed side rib, thereby controlling the wing camber. This rib uses a split design, which, while enabling variable camber, sacrifices the compliant deformation characteristics of the variable-camber wing, severely affecting the improvement and optimization of its aerodynamic efficiency. Summary of the Invention

[0004] In view of the shortcomings of the existing technology, the technical problem to be solved by the present invention is to provide an integrated variable camber wing based on a piezoelectric driven torsion cubic superstructure.

[0005] The technical solution of the present invention to solve the aforementioned technical problem is:

[0006] An integrated variable camber wing based on a piezoelectrically driven torsional cubic superstructure includes a wing skeleton and a skin; characterized in that the wing skeleton comprises multiple torsional cubic superstructures arrayed along the wing chord direction, each torsional cubic superstructure being a cube formed by multiple unit cell torsional superstructures arrayed together, adjacent unit cell torsional superstructures in the x and z directions sharing a straight rod, and adjacent unit cell torsional superstructures in the y direction sharing four Z-shaped piezoelectric rods; wherein the x, y, and z directions are along the length, width, and thickness directions of the wing, respectively;

[0007] The single-cell compression-torsion superstructure is a cube composed of four cell units arrayed together, with adjacent cell units sharing a single straight rod. Each cell unit includes a Z-shaped piezoelectric rod and a straight rod, with two Z-shaped piezoelectric rods connected to the two ends of two straight rods. Each Z-shaped piezoelectric rod located at both ends of the compression-torsion cubic superstructure is connected to the skin. When all the Z-shaped piezoelectric rods of the single-cell compression-torsion superstructure undergo compressive deformation in the height direction, the single-cell compression-torsion superstructure undergoes torsional deformation. When all the single-cell compression-torsion superstructures of the compression-torsion cubic superstructure undergo torsional deformation, the compression-torsion cubic superstructure undergoes torsional deformation, thus achieving variable camber of the wing.

[0008] Furthermore, the Z-shaped piezoelectric rod is divided into a first piezoelectric short rod, a piezoelectric long rod, and a second piezoelectric short rod; one end of the first piezoelectric short rod is connected to a straight rod of the cell unit, the two ends of the piezoelectric long rod are respectively connected to the other end of the first piezoelectric short rod and one end of the second piezoelectric short rod, and the other end of the second piezoelectric short rod is connected to another straight rod of the cell unit. The piezoelectric long rod and the first piezoelectric short rod form an angle that is concave towards the inside of the cell unit, and the piezoelectric long rod and the second piezoelectric short rod form an angle that is convex towards the outside of the cell unit.

[0009] Furthermore, the Z-shaped piezoelectric rod is made of piezoelectric metamaterial.

[0010] Furthermore, the dimensions of each compression-torsion cubic superstructure of the wing skeleton vary gradually along the wing chord direction, with the compression-torsion cubic superstructure closer to the wingtip having a smaller dimension.

[0011] Furthermore, the number of unit cell compression-torsion superstructures in the x and z directions is the same, while the number of unit cell compression-torsion superstructures in the y direction is greater than the number of unit cell compression-torsion superstructures in the other two directions.

[0012] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0013] The variable camber wing of this invention employs multiple compression-torsion cubic superstructures integrally filled within the skin, eliminating the need for rib structure design as required by traditional variable camber wings. The Z-shaped piezoelectric rods of the unit cell compression-torsion superstructure are made of piezoelectric material. Piezoelectric drive causes the Z-shaped piezoelectric rods to bend and deform, converting the compressive deformation of the cell unit into torsional deformation of the unit cell compression-torsion superstructure, thereby inducing torsional deformation of the compression-torsion cubic superstructure. Through dimensional gradient design of each compression-torsion cubic superstructure along the wing chord direction, different torsional angles are generated by each superstructure, achieving variable camber of the wing. The compression-torsion cubic superstructure possesses high strength and load-bearing capacity, helping to overcome the shortcomings of traditional variable camber wings, such as low strength and large mass. This invention innovatively integrates piezoelectric supermaterials and compression-torsion cubic superstructures into the variator wing design, eliminating the drive components found in traditional variator wings, significantly reducing the wing's weight, and achieving lightweight wing design. This invention utilizes the compression-torsion characteristics of a compression-torsion cubic superstructure to achieve variable camber of the wing, enabling large-angle bending deformation under relatively small driving loads. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the overall structure of the present invention with part of the skin removed;

[0015] Figure 2 This is a schematic diagram of the compression-torsion cubic superstructure of the present invention;

[0016] Figure 3 This is a schematic diagram of the unit cell compression-torsion superstructure of the present invention;

[0017] Figure 4 This is a schematic diagram of the Z-shaped piezoelectric rod of the present invention;

[0018] Figure 5 This is the curve showing the relationship between strain and wing bending angle in this invention;

[0019] In the figure, 100 is a pressure-torsion cubic superstructure; 200 is a skin; 110 is a unit cell pressure-torsion superstructure; 110a is a Z-shaped piezoelectric rod; 110b is a straight rod; 110a-1 is the first piezoelectric short rod; 110a-2 is the piezoelectric long rod; and 110a-3 is the second piezoelectric short rod. Detailed Implementation

[0020] Specific embodiments are given below with reference to the accompanying drawings. These specific embodiments are only used to further describe the technical solution of the present invention in detail and do not limit the scope of protection of this application.

[0021] This invention provides an integrated variable camber wing based on a piezoelectric-driven torsion cubic superstructure (hereinafter referred to as variable camber wing, see below). Figures 1-5The wing includes a wing skeleton and a skin 200 covering the wing skeleton. The wing skeleton is formed by an array of multiple compression-torsion cubic superstructures 100 along the wing chord direction. The size of each compression-torsion cubic superstructure 100 (including the size of the unit cell compression-torsion superstructure and the thickness of the rod wall) changes with the overall shape of the wing. That is, the size of the compression-torsion cubic superstructure closer to the wingtip is smaller. The purpose of variable camber is achieved through this design of size gradient change.

[0022] like Figure 2 As shown, the pressure-torsion cubic superstructure 100 is a cube formed by an array of multiple unit-cell pressure-torsion superstructures 110. Adjacent unit-cell pressure-torsion superstructures in the x and z directions share a single straight rod 110b, while adjacent unit-cell pressure-torsion superstructures in the y direction share four Z-shaped piezoelectric rods 110a. The number of unit-cell pressure-torsion superstructures 110 in the x and z directions is the same, while the number of unit-cell pressure-torsion superstructures 110 in the y direction is greater than the number of unit-cell pressure-torsion superstructures 110 in the other two directions. The x, y, and z directions are along the length, width, and thickness directions of the wing, respectively.

[0023] like Figure 3 As shown, the single-cell compressive-torsional superstructure 110 is a cube composed of an array of four cell units, with adjacent cell units sharing a single straight rod 110b. Each cell unit includes two Z-shaped piezoelectric rods 110a and two straight rods 110b. The two Z-shaped piezoelectric rods 110a are connected to the two ends of the two straight rods 110b. The straight rods 110b are non-deformable, ensuring the strength and stability of the single-cell compressive-torsional superstructure 110. The Z-shaped piezoelectric rods 110a are made of piezoelectric metamaterials. When energized, the Z-shaped piezoelectric rods 110a bend and deform, driving the cell units to compress and deform, thereby causing the single-cell compressive-torsional superstructure 110 to undergo torsional deformation.

[0024] like Figure 4As shown, the Z-shaped piezoelectric rod 110a is divided into three segments: a first piezoelectric short rod 110a-1, a piezoelectric long rod 110a-2, and a second piezoelectric short rod 110a-3. One end of the first piezoelectric short rod 110a-1 is connected to a straight rod 110b of the cell unit. The two ends of the piezoelectric long rod 110a-2 are respectively connected to the other end of the first piezoelectric short rod 110a-1 and one end of the second piezoelectric short rod 110a-3. The other end of the second piezoelectric short rod 110a-3 is connected to the cell unit. Another straight rod 110b of the body unit is connected. The piezoelectric long rod 110a-2 forms an inward (concave towards the inside of the cell unit) angle with the first piezoelectric short rod 110a-1, and forms an outward (convex towards the outside of the cell unit) angle with the second piezoelectric short rod 110a-3. The connection positions of the piezoelectric long rod 110a-2 and the second piezoelectric short rod 110a-3 of each Z-shaped piezoelectric rod 110a at both ends of the twisted cubic superstructure 100 are simultaneously connected to the skin 200. When voltages of the same magnitude but opposite directions are applied to the upper and lower surfaces of the Z-shaped piezoelectric rod 110a, the first piezoelectric short rod 110a-1, the piezoelectric long rod 110a-2, and the second piezoelectric short rod 110a-3 all undergo bending deformation. The first piezoelectric short rod 110a-1 and the second piezoelectric short rod 110a-3 undergo bending deformation similar to that of a cantilever beam subjected to force at one end, while the piezoelectric long rod 110a-2 undergoes a centrally symmetrical bending deformation with its center as the center of symmetry. Relating this to the Z-shaped piezoelectric rod 110a, the Z-shaped piezoelectric rod 110a undergoes bending deformation with the first piezoelectric short rod 110a-1 as the center of symmetry. The upward bending deformation, with the connection point between a-1 and the piezoelectric long rod 110a-2 as the point of application, and the downward bending deformation, with the connection point between the piezoelectric long rod 110a-2 and the second piezoelectric short rod 110a-3 as the point of application, causes the height of the Z-shaped piezoelectric rod 110a to decrease and its length to increase. The identical bending deformation of all Z-shaped piezoelectric rods 110a in the unit cell torsion superstructure 110 causes torsional deformation in the unit cell torsion superstructure 110, which in turn causes torsion in the torsion cubic superstructure 100, achieving torsional deformation and variable camber of the entire wing. Due to the gradient change in the wall thickness of the rods of each torsion cubic superstructure 100 along the wing chord direction, each torsion cubic superstructure 100 produces a different torsion angle under the same voltage drive, with the torsion angle of the torsion cubic superstructure 100 closer to the wingtip being larger, thus achieving variable camber of the wing. Furthermore, the size of the compression-torsion cubic superstructure 100 closer to the wingtip is smaller, resulting in a smaller Young's modulus and a smaller resistance to deformation. Therefore, under the same size drive, the compression-torsion cubic superstructure 100 deforms first and the degree of deformation is also larger.

[0025] To verify the effectiveness of the bending deformation, a wing simulation model with a length of 450 mm was constructed. The relationship curve between strain and wing bending angle was obtained (see [reference needed]). Figure 5When the compressive strain of the 100-cell torsion cubic superstructure exceeds 2%, the wing exhibits significant bending deformation, reaching approximately 22° / m.

[0026] The working principle and workflow of this invention are as follows:

[0027] The Z-shaped piezoelectric rod 110a of the unit cell compression-torsion superstructure 110 is made of piezoelectric material. Piezoelectric material is a crystalline material that generates a voltage between its two end faces when subjected to pressure. When voltages of the same magnitude but opposite directions are applied to the upper and lower surfaces of the Z-shaped piezoelectric rod 110a, the Z-shaped piezoelectric rod 110a will bend and deform, causing the cell unit composed of the Z-shaped piezoelectric rod 110a and the straight rod 110b to deform in both length and width directions. This deformation is reflected in the unit cell compression-torsion superstructure 110 and exhibits torsional characteristics, thereby converting the compressive deformation of the cell unit into the torsional deformation of the unit cell compression-torsion superstructure 110, realizing the torsional deformation of the compression-torsion cubic superstructure 100, which is the basis for realizing the variable camber of the wing. Because the dimensions of each compression-torsion cubic superstructure 100 (including the size of the unit cell compression-torsion superstructure and the wall thickness of the rods) vary gradient along the chord direction with the overall shape of the wing, this gradient design ensures that each compression-torsion cubic superstructure 100 produces the same torsional deformation when subjected to the same load. The compression-torsion cubic superstructure 100 closer to the wingtip has fewer unit cell compression-torsion superstructures 110, smaller rod wall thickness, smaller Young's modulus, and less resistance to deformation, resulting in greater deformation. Therefore, the compression-torsion cubic superstructure 100 closer to the wingtip has a larger torsion angle, and thus the torsion angle produced by each compression-torsion cubic superstructure 100 differs, causing the wing to exhibit camber deformation characteristics.

[0028] Any aspects not covered in this invention are applicable to existing technologies.

Claims

1. An integrated variable camber wing based on a piezoelectric-driven torsional cubic superstructure, comprising a wing frame and skin; characterized in that, The wing skeleton comprises multiple compression-torsion cubic superstructures arrayed along the wing chord direction. Each compression-torsion cubic superstructure is a cube formed by an array of multiple unit-cell compression-torsion superstructures. x and z Adjacent unit cell compression-torsion superstructures share a single straight rod. y Four Z-shaped piezoelectric rods are shared between adjacent unit cell compression-torsion superstructures. in, x , y , z The directions are along the length, width, and thickness of the wing, respectively; The single-cell compression-torsion superstructure is a cube composed of four cell units arrayed together, with adjacent cell units sharing a single straight rod. Each cell unit includes a Z-shaped piezoelectric rod and a straight rod, with two Z-shaped piezoelectric rods connected to the two ends of two straight rods. Each Z-shaped piezoelectric rod located at both ends of the compression-torsion cubic superstructure is connected to the skin. When all the Z-shaped piezoelectric rods of the single-cell compression-torsion superstructure undergo compressive deformation in the height direction, the single-cell compression-torsion superstructure undergoes torsional deformation. When all the single-cell compression-torsion superstructures of the compression-torsion cubic superstructure undergo torsional deformation, the compression-torsion cubic superstructure undergoes torsional deformation, thus achieving variable camber of the wing. The Z-shaped piezoelectric rod is divided into a first piezoelectric short rod, a piezoelectric long rod, and a second piezoelectric short rod. One end of the first piezoelectric short rod is connected to a straight rod of the cell unit. The two ends of the piezoelectric long rod are respectively connected to the other end of the first piezoelectric short rod and one end of the second piezoelectric short rod. The other end of the second piezoelectric short rod is connected to another straight rod of the cell unit. The piezoelectric long rod and the first piezoelectric short rod form an angle that is concave inward towards the cell unit, and the piezoelectric long rod and the second piezoelectric short rod form an angle that is convex outward towards the cell unit. When voltages of the same magnitude but opposite directions are applied to the upper and lower surfaces of the Z-shaped piezoelectric rod, the first piezoelectric short rod, the piezoelectric long rod, and the second piezoelectric short rod all undergo bending deformation. The first piezoelectric short rod and the second piezoelectric short rod undergo bending deformation similar to that of a cantilever beam subjected to force at one end, while the piezoelectric long rod undergoes bending deformation that is centrally symmetrical with its center as the center of symmetry. The dimensions of each compression-torsion cubic superstructure of the wing skeleton vary gradually along the wing chord direction, with the compression-torsion cubic superstructure closer to the wingtip having a smaller size.

2. The integrated variable camber wing based on a piezoelectric-driven torsion cubic superstructure according to claim 1, characterized in that, The Z-shaped piezoelectric rod is made of piezoelectric metamaterial.

3. The integrated variable camber wing based on a piezoelectric-driven torsion cubic superstructure according to claim 1, characterized in that, The compression-torsion cubic superstructure in x and z The number of unit cell compression-torsional superstructures in the direction is the same. y The number of unit cell compression-torsion superstructures in the direction is greater than the number of unit cell compression-torsion superstructures in the other two directions.

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