Wing trailing edge deflection driving mechanism, wing and aircraft

Abstract

The invention discloses a wing trailing edge deflection driving mechanism, a wing and an aircraft. Relates to the field of aircrafts. The mechanism comprises two supporting devices, and the two supporting devices are hinged and used for being connected with the front edge and the rear edge of a wing correspondingly; the connecting devices are symmetrically arranged above and below a hinge point of the two supporting devices and are connected with the two supporting devices; the connecting device can deform along the length direction of the wing; the driving devices are symmetrically arranged above and below the hinge point of the two supporting devices, the two ends of the driving device located above the hinge point are connected with the parts, located above the hinge point, of the two supporting devices correspondingly, and the two ends of the driving device located below the hinge point are connected with the parts, located below the hinge point, of the two supporting devices correspondingly. The driving device can deform in the length direction of the wings. The weight can be reduced, and the energy consumption can be reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and particularly to a trailing edge deflection drive mechanism, a wing and an aircraft of a wing. Background Art

[0002] A variable configuration aircraft can flexibly adjust its aerodynamic configuration according to changes in flight missions and environments, so as to achieve efficient flight performance within a wide flight envelope, reduce drag, increase range, and exhibit significant advantages in terms of maneuverability, mission adaptability, etc.

[0003] Among numerous variable configuration technologies of variable configuration aircraft, the continuously variable camber wing, as a cutting-edge technology, has received extensive attention. The continuously variable camber wing can smoothly and continuously change the camber of the wing according to real-time flight states and aerodynamic requirements during flight, so as to optimize the aerodynamic performance of the wing. The change of the camber of the wing is achieved by the deflection of the trailing edge of the wing.

[0004] However, from the perspective of improving the performance of the wing, the trailing edge deflection drive mechanism and the trailing edge deflection mechanism of the continuously variable camber wing should possess capabilities such as high precision, high response speed, and high self-adaptability to adapt to complex and changeable flight environments and mission requirements. Achieving this goal poses a challenge to the design of the drive mechanism.

[0005] Currently, there are mainly two solutions for the research on the drive mechanism and the trailing edge deflection mechanism of the continuously variable camber wing: One is the segmented rib mechanism, which adjusts the segmented structure of the ribs and uses a servo motor as the drive to enable the wing to have better aerodynamic performance at different flight stages. The other is the flexible skin structure, which consists of a flexible honeycomb and an elastic film, has good in-plane deformation ability and certain out-of-plane load-bearing ability, and is driven by a distributed stamping tube driver, and can meet the deformation and load-bearing requirements of the trailing edge variable camber wing.

[0006] Although the existing trailing edge deflection drive mechanism and the trailing edge deflection mechanism of the continuously variable camber wing can achieve the deflection of the trailing edge of the wing, they have the following deficiencies: The segmented rib mechanism uses a servo motor for driving, and the intervention of the servo motor and the hydraulic system increases the weight and energy consumption of the wing and requires a relatively high structural strength of the wing. The flexible skin structure is combined with a distributed stamping tube driver. Although it meets the deformation and load-bearing requirements, the driver has a complex structure and high energy consumption.

[0007] Therefore, there is an urgent need to design a technical solution for the trailing edge deflection drive of a wing that can reduce weight and energy consumption. Summary of the Invention

[0008] The object of the present invention is to provide a trailing edge deflection drive mechanism, a wing and an aircraft of a wing to solve the problems existing in the above-mentioned prior art, and can reduce weight and energy consumption.

[0009] To achieve the above object, the present invention provides the following solutions:

[0010] The present invention provides a trailing edge deflection drive mechanism for a wing, comprising:

[0011] Support devices, two of the support devices are hinged, and one end of one of the support devices away from the hinge point is used to connect to the leading edge of the wing, and the other end of the other support device away from the hinge point is used to connect to the trailing edge of the wing;

[0012] Connecting devices, symmetrically arranged above and below the hinge point of the two support devices, and the parts of the two support devices above the hinge point are connected by the connecting device above the hinge point, and the parts of the two support devices below the hinge point are connected by the connecting device below the hinge point; the connecting device can deform along the length direction of the wing;

[0013] Drive devices, symmetrically arranged above and below the hinge point of the two support devices, and the two ends of the drive device above the hinge point are respectively connected to the parts of the two support devices above the hinge point, and the two ends of the drive device below the hinge point are respectively connected to the parts of the two support devices below the hinge point; the drive device can deform along the length direction of the wing.

[0014] Preferably, the support device includes a support frame, one end of the support frame is connected to the leading edge or the trailing edge of the wing, and the other end of the support frame is fixedly provided with two inclined side plates arranged symmetrically up and down. The ends of the two inclined side plates away from the support frame where they are located are fixedly connected, and the connection ends of the two inclined side plates of the support device are hinged to the connection ends of the two inclined side plates of the other support device.

[0015] Preferably, the two support devices are hinged by a flexible hinge.

[0016] Preferably, the connecting device includes a connecting plate capable of generating in-plane deformation; the two ends of the connecting plate are respectively connected to the corresponding support devices.

[0017] Preferably, the connecting plate is formed by connecting a plurality of honeycomb units in sequence. The cross-section of the honeycomb unit forms a polygonal hole, and the sides of the plurality of polygonal holes are connected in sequence to form the connecting plate into a honeycomb structure as a whole.

[0018] Preferably, the connecting device further includes a rigid sliding rod. One rigid sliding rod is respectively penetrated through both sides of the connecting plate, and the connecting plate can generate deformation along the axis direction of the rigid sliding rod.

[0019] Preferably, the driving device includes a shape memory alloy spring, and two ends of the shape memory alloy spring are respectively connected to two inclined side plates located above the hinge point or two inclined side plates located below the hinge point; two ends of the shape memory alloy spring are connected to the corresponding inclined side plates through regulators, and two ends of the shape memory alloy spring are respectively connected to the positive pole and the negative pole of a power supply.

[0020] Preferably, the driving device is a shape memory polymer, a hydraulic micro-driver or a pneumatic micro-driver.

[0021] The present invention also provides a wing, which includes a wing leading edge, a wing trailing edge and the wing trailing edge deflection driving mechanism as described above; the wing leading edge and the wing trailing edge are connected by the wing trailing edge deflection driving mechanism.

[0022] The present invention also provides an aircraft, which includes an aircraft body, and the wings as described above are symmetrically arranged on both sides of the aircraft body.

[0023] The present invention has achieved the following technical effects compared with the prior art:

[0024] The present invention uses two supporting devices to connect the wing leading edge and the wing trailing edge respectively. The two supporting devices are hinged to each other. The parts of the two supporting devices located above the hinge point are connected by a connecting device, and the parts located below the hinge point are connected by another connecting device. The driving device is located between the connecting device and the hinge point, integrating deflection and driving into one. On the premise of ensuring that the wing shape requirements are met, the overall weight of the equipment is greatly reduced, and the direct deformation of the driving device drives the wing trailing edge to deflect around the hinge point, reducing the energy consumption during the driving process. Description of the Drawings

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required to be used in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0026] Figure 1 It is a schematic diagram of the wing trailing edge deflection driving mechanism in one or some embodiments of the present invention;

[0027] Figure 2 It is a schematic diagram of the wing structure with the wing trailing edge deflection driving mechanism in one or some embodiments of the present invention;

[0028] Figure 3 It is a schematic diagram of the plane angle of the wing with the wing trailing edge deflection driving mechanism in one or some embodiments of the present invention;

[0029] Figure 4 Schematic diagram of the connection plate and the rigid sliding rod in one or some embodiments of the present invention;

[0030] Figure 5 Schematic diagram of the deformation direction of the connection plate in one or some embodiments of the present invention.

[0031] In the figure: 1 - leading edge of the wing, 2 - trailing edge of the wing, 3 - connection plate, 301 - honeycomb unit, 4 - driving device, 5 - flexible hinge, 6 - supporting device, 601 - support frame, 602 - inclined side plate, 7 - rigid sliding rod. Specific embodiments

[0032] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0033] The purpose of the present invention is to provide a trailing edge deflection driving mechanism for a wing, a wing and an aircraft, so as to solve the problems existing in the above-mentioned prior art, and can reduce the weight and energy consumption.

[0034] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and understandable, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0035] Referring to Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5 as shown, the present invention provides a trailing edge deflection driving mechanism for a wing, including a supporting device 6. Two supporting devices 6 are hinged, and one end of one supporting device 6 away from the hinge point is used to connect the leading edge 1 of the wing, and the other end of the other supporting device 6 away from the hinge point is used to connect the trailing edge 2 of the wing; two connecting devices are symmetrically arranged above and below the hinge point of the two supporting devices 6, and the parts of the two supporting devices 6 above the hinge point are connected through the connecting device above the hinge point, and the parts of the two supporting devices 6 below the hinge point are connected through the connecting device below the hinge point; the connecting device can deform along the length direction of the wing; two driving devices 4 are symmetrically arranged above and below the hinge point of the two supporting devices 6, and the two ends of the driving device 4 above the hinge point are respectively connected to the parts of the two supporting devices 6 above the hinge point, and the two ends of the driving device 4 below the hinge point are respectively connected to the parts of the two supporting devices 6 below the hinge point; the driving device 4 can deform along the length direction of the wing, Figure 5The arrow in [the figure] indicates the deformation direction that the connecting device can achieve. In the present invention, two support devices 6 are respectively connected to the leading edge 1 and the trailing edge 2 of the wing. The two support devices 6 are hinged to each other. The parts of the two support devices 6 above the hinge point are connected by a connecting device, and the parts below the hinge point are connected by another connecting device. The driving device 4 is located between the connecting device and the hinge point, integrating deflection and driving into one. On the premise of ensuring that the requirements of the wing shape are met, the overall weight of the equipment is greatly reduced. Moreover, the direct deformation of the driving device 4 drives the trailing edge 2 of the wing to deflect around the hinge point, reducing the energy consumption during the driving process.

[0036] Since the wing needs to maintain a smooth and continuous aerodynamic surface during the deflection of the trailing edge to ensure that the aerodynamic performance of the aircraft is not affected at different flight stages, this requires that the driving mechanism must be fully considered in design to perfectly integrate with the wing shape structure, avoiding damaging the overall aerodynamic shape of the wing due to the existence of the driving mechanism. Based on this, the support device 6 in this embodiment is designed to include a support frame 601 with a hollow interior. The upper and lower surfaces of the support frame 601 are correspondingly attached to the upper and lower surfaces of the wing. At the same time, the connecting device also adapts to the upper and lower surfaces of the wing, so that a smooth and complete wing surface structure can be formed after connecting the wing. One end of the support frame 601 is connected to the leading edge 1 or the trailing edge 2 of the wing. At the other end of the support frame 601, two inclined side plates 602 arranged symmetrically up and down are fixedly provided. The ends of the two inclined side plates 602 far from the support frame 601 where they are located are fixedly connected. The connection ends of the two inclined side plates 602 of one support device 6 and the connection ends of the two inclined side plates 602 of another support device 6 are hinged by a flexible hinge 5. The flexible hinge 5 serves as the rotation center when the trailing edge 2 of the wing deflects. It should have a certain supporting ability to ensure the stable connection between the front half and the rear half of the wing, and also have a certain flexibility to ensure that the driving force provided by the driving device 4 can cause it to deform, so that the support device 6 connected to the trailing edge 2 of the wing deflects, and then drives the trailing edge 2 of the wing to deflect up and down. In one embodiment, the specific material of the flexible hinge 5 is TPU, that is, thermoplastic polyurethane elastomer, also known as thermoplastic polyurethane rubber. This material has high tensile strength, flexibility and impact resistance, and is suitable for applications that withstand frequent bending or stretching. In this embodiment, the structure of the flexible hinge 5 is a quadrangular prism. The cross-section of the flexible hinge 5 has four sides. The specific cross-sectional shape is a quadrilateral with a set of opposite sides being arc segments concave towards the center and the other set of opposite sides being straight line segments. And connection parts for connecting the support frame are provided on both sides of the quadrangular prism. The material selected in this embodiment has both a certain strength and sufficient elasticity, so it can rotate through its own deformation while having a certain supporting property; control the thickness of the center of the flexible hinge 5 so that it will not be unable to deform due to being too thick nor lose its supporting property due to being too thin.

[0037] The connecting device includes a connecting plate 3 capable of in-plane deformation, made of TPU, and the material used meets the requirements of a small Young's modulus and a high yield strength; both ends of the connecting plate 3 are respectively connected to the support devices 6 on the corresponding sides. Considering the lightweight design requirements of the aircraft, the drive mechanism itself also needs to minimize its weight under the premise of ensuring sufficient output force and reliability, which poses higher requirements for material selection and the optimal design of the mechanism. In the field of continuously variable camber wing technology, honeycomb structures are widely used in the manufacture of wings. Because honeycomb structures have a high specific strength and specific stiffness, they can reduce the weight of the wing while ensuring the structural strength of the wing. Their unique honeycomb-like internal structure allows the material to have a large deformation space in the in-plane direction. When the wing needs to change its camber, the honeycomb structure can adapt to this deformation requirement through in-plane compression or tension, thus realizing the continuously variable camber function of the wing. Based on this, in order to further reduce the overall weight, the connecting plate 3 in this embodiment is composed of multiple sequentially connected honeycomb cells 301, presenting an overall honeycomb structure.

[0038] In a specific embodiment, the drive device 4 uses a shape memory alloy spring; the front edge 1 of the wing and the support frame 601 of the first support device 6 are connected by bolts. These two parts do not participate in the deformation function of the continuously variable camber wing and mainly play the role of constructing a cross-sectional module that conforms to the aerodynamic shape. The inclined side plates 602 of the two support devices 6 are connected through a flexible hinge 5, a honeycomb-structured connecting plate 3, and a shape memory alloy spring, presenting an overall "X" configuration. Among them, both the flexible hinge 5 and the connecting plate 3 are connected to the corresponding positions of the support device 6 by bolts, and the shape memory alloy spring is connected to the support device 6 through a regulator. The second support device 6 is also connected to the trailing edge 2 of the wing by bolts. The regulator is used to fix the shape memory alloy spring on the support frame. There is a round hole on the regulator through which a wire can pass. The size of the round hole can be adjusted to pass wires of different diameters. This wire is the wire extending from both ends of the shape memory alloy spring for connecting other structures. When the size of the round hole is small enough, the wire can be fixed, and thus the two ends of the shape memory alloy spring can be fixed. The support frame designed in this embodiment has a round hole for passing the wire at the end of the shape memory alloy spring. Pass the wire at one end of the shape memory alloy spring through the round hole of the support frame, and fix the wire on the other side of the round hole of the support frame with a regulator to fix the position of the shape memory alloy spring. The regulator can be replaced with structures such as a limit block or a limit screw.

[0039] The flexible hinge 5 serves as the rotation center when the trailing edge 2 of the wing deflects. It should have a certain supporting ability to ensure the stable connection between the front and rear parts of the wing, and also have a certain flexibility to ensure that the driving force provided by the driving device 4 can cause it to deform, so that the second supporting device 6 deflects, and then drives the trailing edge 2 of the wing to deflect up and down. In addition to serving as a cross-sectional module that constructs an aerodynamic shape, the connecting plate 3 with a honeycomb structure also needs to assist the wing in achieving the function of continuous camber change by generating in-plane deformation (in-plane compression or in-plane tension), which requires it to have a large out-of-plane stiffness and a small in-plane stiffness.

[0040] In one embodiment, the connecting device further includes a rigid slide bar 7. A rigid slide bar 7 is respectively inserted through both sides of the connecting plate 3. The connecting plate 3 can generate deformation along the axis direction of the rigid slide bar 7, preventing out-of-plane deformation and ensuring the continuity and stability of the outer shape structure of the wing during the deformation process. The existing flexible skin structure relies on distributed stamping tubes for driving. Although it can achieve in-plane deformation, the coordinated control of multiple drivers is difficult, and out-of-plane distortion is likely to occur due to inconsistent local deformation. In the present invention, the deformation direction of the connecting plate 3 of the honeycomb structure is restricted by the rigid slide bar 7, forcing the honeycomb cells 301 of the connecting plate 3 to be compressed or stretched only in the plane defined by the axis of the rigid slide bar 7. Combining with the rotational guidance of the flexible hinge 5, the change rate of the surface curvature is smaller when the trailing edge 2 of the wing deflects, and the aerodynamic shape is more continuously smooth than the prior art.

[0041] To meet the performance requirements of the aircraft in different flight states, the drive mechanism needs to have the capabilities of rapid response and precise control, and be able to adjust the deflection angle of the trailing edge according to the changes in flight conditions within a short time. This requirement increases the complexity and energy consumption of the drive device 4. To reduce the complexity and energy consumption of the drive device 4, in one embodiment, the drive device 4 uses a shape memory alloy spring, which has a shape memory effect and can return to a pre-set shape when subjected to specific stimuli (such as temperature changes, current, etc.). The two ends of the shape memory alloy spring are respectively connected to two inclined side plates 602 located above the hinge point or respectively connected to two inclined side plates 602 located below the hinge point; the two ends of the shape memory alloy spring are respectively connected to the positive and negative poles of the power supply, and current can be passed into the corresponding shape memory alloy spring by turning the power supply on and off. The power supply is not limited and can be a storage battery or the power supply of the aircraft itself; the driving force is generated by the shape memory alloy spring, and the deflection of the trailing edge 2 of the wing is directly driven by the deformation of the flexible hinge 5 and the connecting plate 3 of the honeycomb structure, meeting the requirements of lightweight and low energy consumption for the continuously variable camber wing; the shape memory alloy spring adopts a differential layout method, that is, shape memory alloy springs instead of ordinary springs are installed in the corresponding upper and lower parts of the support device 6, so that the energization sequence of the shape memory alloy spring can be adjusted according to needs, and then the upward or downward deflection of the trailing edge 2 of the wing can be controlled. The specific working method is to perform pre-tensioning treatment on the shape memory alloy spring to endow it with initial deformation potential energy. When energized, the original length is restored by using the shape memory effect, maximizing the conversion efficiency of electrical energy-thermal energy-mechanical energy, and at the same time improving the driving response speed through the pre-tightening force. The shape memory alloy springs distributed symmetrically up and down are used as a two-way driving source, and the contraction direction of the shape memory alloy spring is controlled by selective energization to achieve the two-way deflection of the trailing edge 2 of the wing. When neither the upper nor the lower shape memory alloy springs are energized, the wing remains in its original state; when the upper shape memory alloy spring is energized and the lower shape memory alloy spring is not energized, the trailing edge 2 of the wing deflects upward; when the upper shape memory alloy spring is not energized and the lower shape memory alloy spring is energized, the trailing edge 2 of the wing deflects downward.

[0042] The drive device 4 of this embodiment uses a NiTi shape memory alloy spring, that is, a nickel-titanium shape memory alloy spring. The existing segmented wing rib mechanism relies on a servo motor and a hydraulic system for driving, and the energy needs to be transmitted through mechanical transmission chains such as gears and connecting rods, resulting in a loss of transmission efficiency. However, the present invention adopts an integrated design of the drive device 4 and the trailing edge deflection, and directly drives the deformation structure formed by the flexible hinge 5 and the connecting plate 3 of the honeycomb structure through the NiTi shape memory alloy spring, reducing the intermediate transmission links. The servo motor and the hydraulic system are prone to lubrication failure or seal leakage in extreme temperature and vibration environments, while the present invention adopts a fully solid-state drive solution. The NiTi shape memory alloy spring has stable performance in the range of -50°C to 80°C and no wear of moving parts, and theoretically has a long service life.

[0043] The existing segmented wing rib mechanism needs to integrate heavy components such as servo motors, reducers, and hydraulic pipelines, resulting in an increase in the weight of the wing. In the present invention, a differential NiTi shape memory alloy spring layout is used to replace the traditional driving device 4. The density of the NiTi shape memory alloy spring is only about one-third of that of steel, and there is no additional transmission structure. Combining with the high specific stiffness characteristics of the honeycomb structure connecting plate 3, the weight of the driving device 4 is reduced. In addition, the driving device 4, the connecting plate 3 serving as a deflection device, and the flexible hinge 5 are integrated together. The integrated design eliminates redundant connectors and reduces the structural complexity, meeting the requirements of aircraft lightweight and compactness.

[0044] Combined with the efficient electrical energy-mechanical energy conversion mechanism of the pre-stretched NiTi shape memory alloy spring, the overall energy consumption is reduced compared with the segmented wing rib mechanism, solving the problem of energy loss caused by the separation of the driving system and the deformation mechanism in the prior art. In another embodiment, the NiTi shape memory alloy spring can also be replaced with a shape memory polymer, a micro hydraulic actuator or a micro pneumatic actuator. The shape memory polymer can return to a pre-set shape under specific temperature or other external stimuli. A driving device 4 based on the shape memory polymer can be designed, and its deformation can be controlled by heating or cooling, so as to realize the deflection of the trailing edge 2 of the wing. When a micro hydraulic or pneumatic actuator is used to drive the deflection of the trailing edge 2 of the wing, by controlling the pressure change of the hydraulic oil or compressed air, precise driving of the trailing edge 2 of the wing can be achieved. This driving method has the advantages of large driving force and fast response speed; the above functions can also be realized.

[0045] Based on the above scheme, the present invention also provides a wing, as Figure 2 and Figure 3 shown, including a wing leading edge 1, a wing trailing edge 2, and a driving mechanism for deflecting the wing trailing edge 2 as described above; the wing leading edge 1 and the wing trailing edge 2 are connected by the driving mechanism for deflecting the wing trailing edge 2. With the wing structure of the present invention, the present invention also provides an aircraft, including an aircraft body, and the wings as described above are symmetrically arranged on both sides of the aircraft body, so that the wings of the aircraft of the present invention can change the camber, and thus can adapt to various flight environments, and can smoothly and continuously change the camber of the wings according to the real-time flight state and aerodynamic requirements during the flight process, thereby optimizing the aerodynamic performance of the wings.

[0046] In the present invention, specific examples are used to elaborate on the principle and implementation manner of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manner and application scope. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. A wing trailing edge deflection drive mechanism, characterized in that: include: A support device, wherein two of the support devices are hinged, and one end of one of the support devices away from the hinge point is used to connect to the leading edge of the wing, and the other end of the support device away from the hinge point is used to connect to the trailing edge of the wing; The connecting device is symmetrically arranged above and below the hinge point of the two supporting devices, and the parts of the two supporting devices located above the hinge point are connected by the connecting device above the hinge point, and the parts of the two supporting devices located below the hinge point are connected by the connecting device below the hinge point; the connecting device can be deformed along the length direction of the wing; The driving device is symmetrically arranged above and below the hinge points of the two supporting devices, and the two ends of the driving device located above the hinge points are respectively connected to the parts of the two supporting devices located above the hinge points, and the two ends of the driving device located below the hinge points are respectively connected to the parts of the two supporting devices located below the hinge points; the driving device can deform along the length direction of the wing.

2. The wing trailing edge deflection drive mechanism according to claim 1, characterized in that: The supporting device comprises a supporting frame, one end of which is connected to the leading edge or the trailing edge of the wing, and the other end of which is fixedly provided with two inclined side panels which are symmetrically arranged up and down, the two inclined side panels are fixedly connected away from one end of the supporting frame, and the connecting ends of the two inclined side panels of the supporting device are hinged to the connecting ends of the two inclined side panels of another supporting device.

3. The wing trailing edge deflection drive mechanism according to claim 1, characterized in that: The two support devices are hinged by a flexible hinge.

4. The wing trailing edge deflection drive mechanism according to claim 1, characterized in that: The connecting device comprises a connecting plate capable of generating in-plane deformation; both ends of the connecting plate are respectively connected to supporting devices on corresponding sides.

5. The wing trailing edge deflection drive mechanism according to claim 4, characterized in that: The connecting plate is formed by sequentially connecting a plurality of honeycomb units.

6. The wing trailing edge deflection drive mechanism according to claim 4, characterized in that: The connecting device also includes a rigid sliding rod, and one of the rigid sliding rods is respectively passed through the two sides of the connecting plate. The connecting plate can be deformed along the axis direction of the rigid sliding rod.

7. The wing trailing edge deflection drive mechanism according to claim 2, characterized in that: The driving device includes a shape memory alloy spring, and both ends of the shape memory alloy spring are respectively connected to two inclined side plates located above the hinge point or respectively connected to two inclined side plates located below the hinge point; both ends of the shape memory alloy spring are connected to the corresponding inclined side plates through a regulator, and both ends of the shape memory alloy spring are respectively connected to the positive and negative poles of the power supply.

8. The wing trailing edge deflection drive mechanism according to claim 1, characterized in that: The driving device is a shape memory polymer, a hydraulic micro-actuator or a pneumatic micro-actuator.

9. A wing, characterized in that: It comprises a wing leading edge, a wing trailing edge and a wing trailing edge deflection drive mechanism as claimed in any one of claims 1 to 8; the wing leading edge and the wing trailing edge are connected by the wing trailing edge deflection drive mechanism.

10. An aircraft, characterized in that: It comprises an aircraft body, and the wings as claimed in claim 9 are symmetrically arranged on both sides of the aircraft body.

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