Biomimetic morphing wing

Abstract

The application discloses a bionic morphing wing, which comprises a main wing, two first ailerons, two second ailerons, a first control assembly, a second control assembly and a main controller. The two first ailerons are arranged at two ends of the main wing and can rotate relative to the main wing; the first control assembly is used for controlling the rotation of the first ailerons relative to the main wing; the two second ailerons are arranged on one side of each first aileron and can make folding movement relative to the first aileron; the second control assembly is used for controlling the folding of the second ailerons relative to the first aileron; and the main controller is arranged in the main wing and is in communication connection with the first control assembly and the second control assembly so as to control the first control assembly and the second control assembly. The bionic morphing wing has simple wing structure, the first ailerons can rotate, the second ailerons can fold, and the bionic morphing wing has strong stability and flexibility.

Description

Technical Field

[0001] This invention relates to the field of aircraft, and in particular to a biomimetic deformable wing. Background Technology

[0002] The wing is a crucial component of an aircraft, providing lift, stability, roll, and pitch torque. The aerodynamic performance of the wing determines an aircraft's flight performance and environmental adaptability. To balance these performance aspects, deformable or folding wings are typically employed. Compared to traditional wings, deformable wings offer advantages such as improved aerodynamic characteristics, enhanced handling, and expanded application range. Wing deformation primarily includes in-plane deformation with variable span, chord length, and sweep; out-of-plane deformation with spanwise curvature, variable dihedral angle, wing twist, and wing folding; and airfoil deformation with variable camber and thickness.

[0003] However, existing morphing wings typically consist of several morphing mechanisms, which are inconvenient to assemble and disassemble, heavy, require high actuator output force, and generate drag during morphing, reducing efficiency. They are also difficult to install and adjust, have high environmental requirements, and experience significant transmission vibration. Some wings can only morph in one direction, resulting in low turbine transmission efficiency, heat generation, high axial force, and significant energy loss in the secondary transmission. Their complex structure makes installation and maintenance inconvenient and occupies a large space. Furthermore, installing folding wings affects the size and position of ailerons. For example, moving the aileron inward reduces its lever arm or area, thus decreasing the aircraft's roll speed and roll moment, impacting its handling performance and maneuverability.

[0004] The information disclosed in this background section is intended only to enhance the understanding of the overall background of the invention and should not be construed as an admission or in any way implying that the information constitutes prior art known to those skilled in the art. Summary of the Invention

[0005] The purpose of this invention is to provide a biomimetic deformable wing with a simple structure, a first aileron that can rotate, and a second aileron that can fold, giving the biomimetic deformable wing strong stability and flexibility.

[0006] To achieve the above objectives, embodiments of the present invention provide a biomimetic deformable wing, comprising: a main wing, two first ailerons, two second ailerons, a first control component, a second control component, and a main controller. The two first ailerons are respectively disposed at both ends of the main wing and are rotatable relative to the main wing; the first control component controls the rotation of the first ailerons relative to the main wing; the two second ailerons are respectively disposed on one side of each first aileron and are folding relative to the first ailerons; the second control component controls the folding of the second ailerons relative to the first ailerons; the main controller is disposed within the main wing and is communicatively connected to the first and second control components to control the first and second control components.

[0007] In one or more embodiments of the present invention, the first control component is disposed at one end of the main wing near the first aileron; the second control component is disposed on the second aileron.

[0008] In one or more embodiments of the present invention, the first control component includes: a torsion servo, a torsion servo gear, a torsion output gear, and a torsion shaft. The torsion servo gear is connected to and driven by the torsion servo; the torsion output gear meshes with the torsion servo gear; one end of the torsion shaft is fixedly connected to the torsion output gear, and the other end is fixedly connected to the first aileron, the first aileron being rotatable around the torsion shaft.

[0009] In one or more embodiments of the present invention, the torsion shaft is disposed at the pressure center of the first aileron.

[0010] In one or more embodiments of the present invention, the second control component includes: a folding servo, a folding servo gear, a folding output gear, and a folding shaft. The folding servo gear is connected to and driven by the folding servo; the folding output gear meshes with the folding servo gear; the folding shaft is inserted into the folding output gear and fixed relative to the folding output gear; the folding shaft passes through the first aileron and the second aileron and is fixed relative to the first aileron and the second aileron.

[0011] In one or more embodiments of the present invention, the second control component includes: a folding shaft, a folding control block, and a shape memory alloy control assembly. The folding shaft passes through the first aileron and the second aileron and is fixed relative to the first aileron and the second aileron; the folding control block is sleeved on the folding shaft and fixed relative to the folding shaft; the shape memory alloy control assembly is connected to the folding control block and is used to control the rotation of the folding control block.

[0012] In one or more embodiments of the present invention, the shape memory alloy control assembly includes: a first shape memory alloy wire and a second shape memory alloy wire. One end of the first shape memory alloy wire is connected to the first aileron, and the other end is connected to the folding control block; the second shape memory alloy wire is disposed below the first shape memory alloy wire, one end of the second shape memory alloy wire is connected to the first aileron, and the other end is connected to the folding control block.

[0013] In one or more embodiments of the present invention, the first shape memory alloy wire includes a first control segment and a second control segment. One end of the first control segment is provided with a fixed bushing for connecting the first control segment to the first aileron. One end of the second control segment is provided with a fixed bushing for connecting the second control segment to the folding control block. A coupling is provided between the first control segment and the second control segment for connecting the first control segment and the second control segment.

[0014] In one or more embodiments of the present invention, the second shape memory alloy wire includes a third control segment and a fourth control segment. One end of the third control segment is provided with a fixed bushing for connecting the third control segment to the first aileron. One end of the fourth control segment is provided with a fixed bushing for connecting the fourth control segment to the folding control block. A coupling is provided between the third control segment and the fourth control segment for connecting the third control segment and the fourth control segment.

[0015] In one or more embodiments of the present invention, the folding control block has two through holes, which are located on both sides of the folding shaft, and one end of the first memory alloy wire and the second memory alloy wire are respectively inserted into the two through holes.

[0016] Compared with existing technologies, the biomimetic deformable wing according to the embodiments of the present invention, by setting a first aileron and a second aileron, can realize various motion modes of the aircraft, such as pitch and roll. Furthermore, the first and second control components of this biomimetic deformable wing have simple structures and better handling performance, thereby improving the aircraft's handling performance and flexibility. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of a biomimetic deformable wing according to an embodiment of the present invention;

[0018] Figure 2 This is a second schematic diagram of a biomimetic deformable wing according to an embodiment of the present invention;

[0019] Figure 3 This is a schematic diagram of a first control component and a second control component according to an embodiment of the present invention;

[0020] Figure 4This is a schematic diagram of the second control component of a biomimetic deformable wing according to another embodiment of the present invention;

[0021] Figure 5 This is a schematic diagram of the internal structure of the second control component according to another embodiment of the present invention.

[0022] Explanation of key figure labels:

[0023] 1-Main wing, 2-First aileron, 3-Second aileron, 4-First control assembly, 41-Torsion servo, 42-Torsion servo gear, 43-Torsion output gear, 44-Torsion shaft, 5-Second control assembly, 51-Folding servo, 52-Folding servo gear, 53-Folding output gear, 54-Folding shaft, 55-Folding control block, 551-Through hole, 56-Memory alloy control group, 561-First memory alloy wire, 5611-First control section, 5612-Second control section, 562-Second memory alloy wire, 5621-Third control section, 5622-Fourth control section, 563-Fixed bushing, 564-Coupling. Detailed Implementation

[0024] The specific embodiments of the present invention will now be described in detail with reference to the accompanying drawings, but it should be understood that the scope of protection of the present invention is not limited to the specific embodiments.

[0025] Unless otherwise expressly stated, throughout the specification and claims, the term "comprising" or its variations such as "including" or "comprises" shall be understood to include the stated elements or components without excluding other elements or other components.

[0026] like Figures 1 to 5 As shown, a biomimetic deformable wing according to a preferred embodiment of the present invention includes: a main wing 1, two first ailerons 2, two second ailerons 3, a first control component 4, a second control component 5, and a main controller. The two first ailerons 2 are respectively disposed at both ends of the main wing 1 and are rotatable relative to the main wing 1. The first control component 4 is used to control the rotation of the first ailerons 2 relative to the main wing 1. The two second ailerons 3 are respectively disposed on one side of each first aileron 2 and are foldable relative to the first aileron 2, and the second ailerons 3 can follow the rotation of the first ailerons 2 relative to the main wing 1. The second control component 5 is used to control the folding of the second ailerons 2 relative to the first ailerons 2. The main controller is disposed within the main wing 1 and is communicatively connected to the first control component 4 and the second control component 5 to control the first control component 4 and the second control component 5, thereby controlling the first ailerons 2 and the second ailerons 3. The main controller can be a chip or a control board, etc.

[0027] In the above embodiment, the biomimetic deformable wing can control the aircraft's pitch and roll movements. The identical movement of the first ailerons 2 on both sides allows the wing to function like an elevator, i.e., pitch. Different movements of the first ailerons 2 on both sides can alter the lift of the wings, generating roll torque and causing the aircraft to roll. When the twisting directions are the same but the angles are different, the aircraft exhibits both roll and pitch movements. Folding the second ailerons 3 relative to the first ailerons 2 controls the aircraft's yaw movement. Different movements of the second ailerons 3 can alter the drag on both sides of the second ailerons 3, thereby generating yaw torque. This biomimetic deformable wing, by setting a pair of first ailerons 2 that can rotate circumferentially relative to the main wing 1 and a pair of second ailerons 3 that can fold relative to the first ailerons 2, can achieve changes in the aircraft's flight direction and can realize pitch and roll movements. Compared to existing biomimetic wings, this biomimetic deformable wing has a simpler structure and better handling performance. Furthermore, the arrangement of the first ailerons 2 and the second ailerons 3 can improve the aircraft's handling performance and flexibility.

[0028] This biomimetic morphing wing exhibits multiple flight states, including: roll, pitch, yaw, pitch and roll, pitch and yaw, roll and yaw, and pitch, roll and yaw. The flight states of the biomimetic morphing wing are as follows:

[0029] Roll: The left first aileron 2 and the second aileron 3 twist downwards, and the right first aileron 2 and the second aileron 3 twist upwards with the same twist angle for both ailerons 2, resulting in a left roll; the left first aileron 2 and the second aileron 3 twist upwards, and the right first aileron 2 and the second aileron 3 twist downwards with the same twist angle for both ailerons 2, resulting in a right roll.

[0030] Pitch: Both the first aileron 2 and the second aileron 3 on both sides twist upward at the same angle, and the aircraft pitches up and climbs; both the first aileron 2 and the second aileron 3 on both sides twist downward at the same angle, and the aircraft pitches down and dives.

[0031] Yaw: When the left second aileron 3 folds upward and the right second aileron 3 folds downward at the same angle, the drag of the right second aileron 3 decreases and the drag of the left second aileron 3 increases, generating a yaw torque that makes the aircraft yaw to the left; when the right second aileron 3 folds upward and the left second aileron 3 folds downward at the same angle, the aircraft yaws to the right.

[0032] Pitch + Roll: When both first ailerons 2 are twisted upwards, if the twist angle of the right first aileron 2 is less than that of the left first aileron 2, the aircraft pitches up and rolls to the right; if the twist angle of the right first aileron 2 is greater than that of the left first aileron 2, the aircraft pitches up and rolls to the left. Conversely, when both first ailerons 2 are twisted downwards, if the twist angle of the right first aileron 2 is less than that of the left first aileron 2, the aircraft nose-dives and rolls to the right; if the twist angle of the right first aileron 2 is greater than that of the left first aileron 2, the aircraft nose-dives and rolls to the left.

[0033] Pitch + Yaw: When both first ailerons 2 on both sides are twisted upwards at the same angle, if the right second aileron 3 folds downwards and the left second aileron 3 folds upwards, the aircraft will pitch up and climb, yaw to the left; if the right second aileron 3 folds upwards and the left second aileron 3 folds downwards, the aircraft will pitch up and climb, yaw to the right. When both first ailerons 2 on both sides are twisted downwards at the same angle, if the right second aileron 3 folds downwards and the left second aileron 3 folds upwards, the aircraft will nose-dive and yaw to the left; if the right second aileron 3 folds upwards and the left second aileron 3 folds downwards, the aircraft will nose-dive and yaw to the right.

[0034] Roll + Yaw: With the left first aileron 2 twisting downwards and the right first aileron 2 twisting upwards at the same angle, the left second aileron 3 folds upwards and the right second aileron 3 folds downwards, causing the aircraft to roll left and yaw to the left; with the left second aileron 3 folding downwards and the right second aileron 3 folding upwards, the aircraft rolls left and yaws to the right. With the left first aileron 2 twisting upwards and the right first aileron 2 twisting downwards at the same angle, the left second aileron 3 folds upwards and the right second aileron 3 folds downwards, causing the aircraft to roll right and yaw to the left; with the left second aileron 3 folding downwards and the right second aileron 3 folding upwards, the aircraft rolls right and yaws to the right.

[0035] Pitch + Roll + Yaw: Both first ailerons 2 on both sides twist upwards, with the right first aileron 2 twisting at a smaller angle than the left first aileron 2. The left second aileron 3 folds upwards and the right second aileron 3 folds downwards at the same angle, causing the aircraft to pitch up, roll to the right, and yaw to the left. The left second aileron 3 folds downwards and the right second aileron 3 folds upwards at the same angle, causing the aircraft to pitch up, roll to the right, and yaw to the right. The right first aileron 2 twists at a greater angle than the left first aileron 2. The left second aileron 3 folds upwards and the right second aileron 3 folds downwards at the same angle, causing the aircraft to pitch up, roll to the left, and yaw to the left. The left second aileron 3 folds downwards and the right second aileron 3 folds downwards at the same angle, causing the aircraft to pitch up, roll to the right, and yaw to the right.

[0036] When both first ailerons 2 on both sides are twisted downwards, and the twist angle of the right first aileron 2 is less than that of the left first aileron 2, the left second aileron 3 folds upwards and the right second aileron 3 folds downwards at the same angle, causing the aircraft to pitch down, roll to the right, and yaw to the left; when the left second aileron 3 folds downwards and the right second aileron 3 folds upwards at the same angle, the aircraft pitch down, roll to the right, and yaw to the right; when the twist angle of the right first aileron 2 is greater than that of the left first aileron 2, the left second aileron 3 folds upwards and the right second aileron 3 folds downwards at the same angle, causing the aircraft to pitch down, roll to the left, and yaw to the left; when the left second aileron 3 folds downwards and the right second aileron 3 folds downwards at the same angle, the aircraft pitch down, roll to the right, and yaw to the right.

[0037] In one implementation, such as Figure 2 and Figure 3 As shown, to achieve the rotation of the first aileron 2 relative to the main wing 1, a first control component 4 is provided at the end of the main wing 1 near the first aileron 2. This component controls the rotation of the first aileron 2 relative to the main wing 1, allowing the first aileron 2 to twist upwards or downwards relative to the main wing 1. The first control component 4 includes a torsion servo 41, a torsion servo gear 42, a torsion output gear 43, and a torsion shaft 44. The torsion servo gear 42 is connected to and driven by the torsion servo 41. The torsion output gear 43 meshes with the torsion servo gear 42. One end of the torsion shaft 44 is fixedly connected to the torsion output gear 43, and the other end is fixedly connected to the first aileron 2, enabling the first aileron 2 to rotate around the torsion shaft 44.

[0038] The torsion servo 41 and the main wing 1, the torsion servo gear 42 and the torsion servo 41, the torsion output gear 43 and the torsion shaft 44, and the torsion shaft 44 and the first aileron 2 can be fixed with bolts to ensure stable connection between the components. The torsion shaft 44 and the main wing 1 can be connected with bearings to reduce friction. The torsion servo gear 42 can mesh with the torsion output gear 43, where the torsion servo gear 42 is the driving gear and the torsion output gear 43 is the driven gear. The torsion output gear 43 can only rotate about its axial direction, and its other degrees of freedom are restricted by the main wing 1 and the torsion shaft 44.

[0039] The main wing 1 and the first aileron 2 are connected by a torsion shaft 44, which is located at the pressure center of the first aileron 2 to balance the torsional force generated by the weight of the first aileron 2. One end of the torsion shaft 44 is connected to a torsion output gear 43, which transmits torque and prevents the torsion shaft 44 from slipping off the main wing 1. The other end is fixed to the first aileron 2 with bolts. The working principle of the first control component 4 is as follows: the torsion servo 41 drives the torsion servo gear 42 to rotate, which in turn drives the torsion output gear 43 to rotate together with the torsion shaft 44, which in turn drives the first aileron 2 to rotate. To make the first aileron 2 rotate in the opposite direction, the torsion servo 41 is reversed.

[0040] To achieve the folding of the second aileron 3 relative to the first aileron 2, a second control component 5 is provided on the first aileron 2 for controlling the folding of the second aileron 3 relative to the first aileron 2. The second control component 5 includes: a folding servo 51, a folding servo gear 52, a folding output gear 53, and a folding shaft 54. The folding servo gear 52 is connected to and driven by the folding servo 51. The folding output gear 53 meshes with the folding servo gear 52. The folding shaft 54 ​​is inserted into the folding output gear 53 and fixed relative to the folding output gear 53; the folding shaft 54 ​​passes through the first aileron 2 and the second aileron 3 and is fixed relative to the first aileron 2 and the second aileron 3.

[0041] The folding servo 51 and the first aileron 2, the folding output gear 53 and the folding shaft 54, and the folding shaft 54 ​​and the second aileron 3 can be fixed with bolts to ensure stable connection between the components. The folding shaft 54 ​​and the first aileron 2 can be connected with bearings to reduce friction. The folding servo gear 52 and the folding output gear 53 mesh, with the folding servo gear 52 being the driving gear and the folding output gear 53 being the driven gear. The working principle of the second control component 5 is as follows: the folding servo 51 drives the folding servo gear 52 to rotate, which in turn drives the folding output gear 53 and the folding shaft 54 ​​to rotate together. The folding shaft 54 ​​then drives the second aileron 3 to fold relative to the first aileron 2. To fold the second aileron 3 in the opposite direction, the folding servo 51 can be reversed.

[0042] The present invention also provides another embodiment of the second control component 5, such as... Figure 4 and Figure 5 As shown, the second control component 5 includes a folding shaft 54, a folding control block 55, and a shape memory alloy control assembly 56. The folding shaft 54 ​​passes through the first aileron 2 and the second aileron 3 and is fixed relative to the first aileron 2 and the second aileron 3. The folding control block 55 is sleeved on the folding shaft 54 ​​and fixed relative to the folding shaft 54. The shape memory alloy control assembly 56 is connected to the folding control block 55 and is used to control the rotation of the folding control block 55.

[0043] The shape memory alloy control assembly 56 includes a first shape memory alloy wire 561 and a second shape memory alloy wire 562. One end of the first shape memory alloy wire 561 is connected to the first aileron 2, and the other end is connected to the folding control block 55. The second shape memory alloy wire 562 is located below the first shape memory alloy wire 561, with one end connected to the first aileron 2 and the other end connected to the folding control block 55. The first shape memory alloy wire 561 and the second shape memory alloy wire 562 are arranged vertically. By controlling the contraction and relaxation of the first shape memory alloy wire 561 and the second shape memory alloy wire 562, the second aileron 3 can be controlled to fold upward or downward.

[0044] Specifically, the first shape memory alloy wire 561 includes a first control segment 5611 and a second control segment 5612. One end of the first control segment 5611 is provided with a fixed bushing 563 for connecting the first control segment 5611 to the first aileron 2. One end of the second control segment 5612 is provided with a fixed bushing 563 for connecting the second control segment 5612 to the folding control block 55. A coupling 564 is provided between the first control segment 5611 and the second control segment 5612 for connecting the first control segment 5611 and the second control segment 5612. The second shape memory alloy wire 562 includes a third control segment 5621 and a fourth control segment 5622. One end of the third control segment 5621 is provided with a fixed bushing 563 for connecting the third control segment 5621 to the first aileron 2. One end of the fourth control segment 5622 is provided with a fixed bushing 563 for connecting the fourth control segment 5622 to the folding control block 55. A coupling 564 is provided between the third control segment 5621 and the fourth control segment 5622 for connecting the third control segment 5621 and the fourth control segment 5622.

[0045] The control principle of the first shape memory alloy wire 561 and the second shape memory alloy wire 562 is as follows: In the initial state, the first control segment 5611 and the fourth control segment 5622 are in a contracted state, while the second control segment 5612 and the third control segment 5621 are in a relaxed state. When the second aileron 3 needs to be folded downwards, the third control segment 5621 is energized to contract, the folding control block 55 rotates downwards, pulling the first control segment 5611, causing it to relax. At this time, both the third control segment 5621 and the fourth control segment 5622 are in a contracted state, while the first control segment 5611 and the second control segment 5612 are in a relaxed state, and the second aileron 3 will move downwards. Conversely, the second aileron 3 will fold upwards.

[0046] In one embodiment, the folding control block 55 has two through holes 551, which are located on both sides of the folding shaft 54. One end of the first memory alloy wire 561 and the second memory alloy wire 562 are respectively inserted into the two through holes 551. Thus, the folding control block 55 can be rotated by the contraction and relaxation of the first memory alloy wire 561 and the second memory alloy wire 562 to realize the folding of the second aileron 3.

[0047] In summary, this biomimetic deformable wing, by incorporating a first aileron 2 and a second aileron 3, enables the aircraft to change its flight direction and achieve various motion modes such as pitch and roll. Furthermore, the first control component 4 and the second control component 5 of this biomimetic deformable wing have simple structures and better handling performance; therefore, the placement of the first aileron 2 and the second aileron 3 can improve the aircraft's handling performance and flexibility.

[0048] The foregoing description of specific exemplary embodiments of the invention is for illustrative and explanatory purposes. These descriptions are not intended to limit the invention to the precise forms disclosed, and it will be apparent that many changes and variations can be made in accordance with the foregoing teachings. The exemplary embodiments were chosen and described in order to explain the specific principles of the invention and its practical application, thereby enabling those skilled in the art to implement and utilize various different exemplary embodiments of the invention, as well as various different choices and variations. The scope of the invention is intended to be defined by the claims and their equivalents.

Claims

1. A biomimetic morphing wing, characterized in that, The utility model relates to a kind of wing control system, including: Main wing; Two first ailerons, respectively set in the two ends of the main wing and can be twisted relative to the main wing; First control assembly, for controlling the first aileron relative to the main wing twist; Two second ailerons, respectively set in one side of each first aileron and can be folded in up-down direction relative to the first aileron; Second control assembly, for controlling the second aileron relative to the first aileron folding in up-down direction; And Main controller, set in the main wing and with the first control assembly and second control assembly communication, to control the first control assembly and second control assembly.

2. The biomimetic morphing airfoil of claim 1, wherein, The first control assembly is set in the end of the main wing close to the first aileron;The second control assembly is set in the second aileron.

3. The biomimetic morphing airfoil of claim 2, wherein, The first control assembly includes: Twist rudder machine; Twist rudder machine gear, connect with the twist rudder machine and be driven by the twist rudder machine; Twist output gear, engage with the twist rudder machine gear;And Twist shaft, one end is fixedly connected with the twist output gear, the other end is fixedly connected with the first aileron, and the first aileron can rotate around the twist shaft.

4. The biomimetic morphing airfoil of claim 3, wherein, The twist shaft is set in the pressure center of the first aileron.

5. The biomimetic morphing airfoil of claim 1, wherein, The second control assembly includes: Folding rudder machine; Folding rudder machine gear, connect with the folding rudder machine and be driven by the folding rudder machine; Folding output gear, engage with the folding rudder machine gear;And Folding shaft, insert in the folding output gear and relative to the folding output gear fixed;The folding shaft is inserted in the first aileron and second aileron, and relative to the first aileron and second aileron fixed.

6. The biomimetic morphing airfoil of claim 1, wherein, The second control assembly includes: Folding shaft, insert in the first aileron and second aileron, and relative to the first aileron and second aileron fixed; Folding control block, cover in the folding shaft and relative to the folding shaft fixed;And Memory alloy control group, connect with the folding control block, for controlling the rotation of the folding control block.

7. The biomimetic morphing airfoil of claim 6, wherein, The memory alloy control group includes: First memory alloy wire, one end is connected with the first aileron, the other end is connected with the folding control block;And Second memory alloy wire, set in the lower of the first memory alloy wire, one end of the second memory alloy wire is connected with the first aileron, the other end is connected with the folding control block.

8. The biomimetic morphing airfoil of claim 7, wherein, The first memory alloy wire includes first control section and second control section, one end of the first control section is provided with fixed shaft sleeve, for connecting the first control section to first aileron;One end of the second control section is provided with fixed shaft sleeve for connecting the second control section to the folding control block;Coupling is arranged between the first control section and the second control section, for connecting the first control section and the second control section.

9. The biomimetic morphing airfoil of claim 7, wherein, The second memory alloy wire includes third control section and fourth control section, one end of the third control section is provided with fixed shaft sleeve, for connecting the third control section to first aileron;One end of the fourth control section is provided with fixed shaft sleeve for connecting the fourth control section to the folding control block;Coupling is arranged between the third control section and the fourth control section, for connecting the third control section and the fourth control section.

10. The biomimetic morphing airfoil of claim 7, wherein, The folding control block is provided with two through holes, which are arranged on the two sides of the folding shaft, and one end of the first memory alloy wire and the second memory alloy wire is respectively arranged in the two through holes.

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