阅读说明：本技术 一种机翼后缘连续变形结构及变形方法 (Continuous deformation structure and deformation method for wing trailing edge ) 是由 王震 杜龙 王红飞 项小平 李彬 张海东 余凌晶 岳鹏阳 刘志远 张宁 于 2021-08-16 设计创作，主要内容包括：一种机翼后缘连续变形结构,包括机翼、蒙皮、后缘骨架及控制电路,其中,所述梁、肋与长桁组成后缘骨架,所述蒙皮包裹在后缘骨架外层,所述后缘骨架上平行设置有多个肋,并将每个肋分成多个肋段,且所述后缘骨架固定在机翼后缘上,所述控制电路与设置在每个肋段上的驱动组件连接,所述驱动组件中的驱动绳索、连接点均为NiTi形状记忆合金制成；本发明利用形状记忆合金材料的形状记忆效应,对机翼后缘结构进行多点驱动,促使机翼后缘连续柔顺变形,以实现机翼后缘的无缝过渡；有效提高机翼的气动效率和飞行器的机动性,减少噪声和耗油率。(A wing trailing edge continuous deformation structure comprises a wing, a skin, a trailing edge framework and a control circuit, wherein the trailing edge framework is formed by beams, ribs and stringers, the skin wraps the outer layer of the trailing edge framework, a plurality of ribs are arranged on the trailing edge framework in parallel, each rib is divided into a plurality of rib sections, the trailing edge framework is fixed on the trailing edge of the wing, the control circuit is connected with a driving assembly arranged on each rib section, and driving ropes and connecting points in the driving assembly are made of NiTi shape memory alloy; the invention utilizes the shape memory effect of the shape memory alloy material to drive the structure of the trailing edge of the wing at multiple points, so as to promote the continuous flexible deformation of the trailing edge of the wing, thereby realizing the seamless transition of the trailing edge of the wing; the aerodynamic efficiency of the wing and the maneuverability of the aircraft are effectively improved, and the noise and the oil consumption rate are reduced.)

1. The utility model provides a wing trailing edge continuous deformation structure, includes wing, covering, trailing edge skeleton and control circuit, its characterized in that, the trailing edge skeleton is constituteed with the stringer to roof beam, rib, the covering parcel is outer at the trailing edge skeleton, parallel arrangement has a plurality of ribs on the trailing edge skeleton to divide into a plurality of rib sections with every rib, just the trailing edge skeleton is fixed on the wing trailing edge, control circuit is connected with the drive assembly who sets up on every rib section, drive rope, tie point among the drive assembly are NiTi shape memory alloy and make.

2. The wing trailing edge continuous deformation structure according to claim 1, wherein the specific structure is as follows:

the middle parts of the rib sections are connected through a fixing piece, each rib section can rotate around the fixing piece, and meanwhile, the upper part and the lower part of each rib section are respectively provided with a driving assembly which is used for controlling the rib section to deflect;

the control circuit comprises a power supply, a control switch and a driving assembly, the driving assembly comprises a driving rope, a connecting point and a cable, the connecting point comprises a connecting base body and a cable, the connecting base body is made of NiTi shape memory alloy, the connecting base body penetrates through an oval hole formed in the rib section and is fixed on the rib section, the cable connected with the control switch is welded at two ends of the connecting base body, the driving rope is wound on the connecting base body, the cable connected with the control switch is welded at two ends of the driving rope, the control switch is provided with an upper state, a neutral state and a lower state, and the control switch is connected with the power supply.

3. The wing trailing edge continuous deformation structure according to claim 2, wherein a circular hole for fixing a driving rope and capable of deforming by energization is provided on the connection base, and the driving rope is wound on the connection base through the circular hole.

4. The wing trailing edge continuous deformation structure of claim 2, wherein the ratio of the distance between the adjacent connection points to the rib section height is equal.

5. The wing trailing edge continuous deformation structure according to claim 2, wherein the driving rope comprises an upper driving rope and a lower driving rope, the connecting points comprise an upper connecting point and a lower connecting point, the upper portion divided into the first rib section is connected with the beam through the upper driving rope and the upper connecting point, and the lower portion is connected with the beam through the lower driving rope and the lower connecting point; the upper part of each subsequent rib section is connected with the previous rib section through an upper driving rope and an upper connecting point, and the lower part of each subsequent rib section is connected with the previous rib section through a lower driving rope and a lower connecting point.

6. The wing trailing edge continuous deformation structure of claim 5, wherein the upper driving rope and the lower driving rope are identical in structure, length and diameter, and the upper connecting point and the lower connecting point are identical in structure, length and diameter.

7. The wing trailing edge continuous deformation structure according to claim 6, wherein the upper driving rope is connected in series and then connected in parallel with the upper driving rope of the other parallel rib, and the lower connecting point is connected in series and then connected in parallel with the lower connecting point of the other parallel rib and then connected to a power supply through a control switch; the lower driving ropes are connected in series and then connected in parallel with the lower driving ropes of other parallel ribs, and the upper connecting points are connected in series and then connected in parallel with the upper connecting points of other parallel ribs and then connected with a power supply through a control switch.

8. The wing trailing edge continuous deformation structure according to claim 1, wherein the skin comprises an upper wall plate, a lower wall plate and a honeycomb sandwich layer, wherein the upper wall plate and the lower wall plate are connected with the honeycomb sandwich layer through gluing, and the honeycomb sandwich layer is a zero-Poisson ratio honeycomb structure.

9. A deformation method of a wing trailing edge continuous deformation structure is characterized in that when a control switch is adjusted to an upper state, an upper driving rope and a lower connecting point are connected with a power supply, the upper driving rope contracts and deforms to generate driving tension, the section of the lower connecting point becomes circular, the lower connecting point rotates to enable the lower driving rope to relax and not bear load, and the wing trailing edge deflects upwards and deforms; when the control switch is adjusted to a lower position, the lower driving rope and the upper connecting point are connected with a power supply, the lower driving rope contracts and deforms to generate driving tension, the section of the upper connecting point is changed into a circular shape, the upper connecting point rotates to enable the upper driving rope to be loosened and not bear load, and the trailing edge of the wing deflects downwards to deform; when the control switch is adjusted to be in a neutral state, the circuit is broken, the upper connecting point and the lower connecting point cannot rotate, the rope is driven to bear load, and the rear edge framework is promoted to be in the neutral state; thereby realizing continuous deformation of the trailing edge of the wing.

10. The method for deforming the continuous wing trailing edge deformation structure of claim 9, wherein the ratio of the distance between the adjacent connection points to the height of the rib section is equal, and since the unit length deformation of the driving rope is the same, when the ratio of the distance between the adjacent connection points to the height of the rib section is the same, the driving rope is electrically deformed, and the deflection angle of each rib section is the same, the deflection angle of the rib section is only proportional to the electrical heating time, and the coordinated deformation of the plurality of driving ropes can be controlled only by a simple circuit, so as to ensure the continuous wing trailing edge deformation.

Technical Field

The invention relates to the technical field of wing structures, in particular to a wing trailing edge continuous deformation structure and a wing trailing edge continuous deformation method.

Background

The wing is the most important part of the aircraft lift source, and the shape of the wing directly influences the flight performance of the aircraft. Since the first powered and steerable aircraft came into the world, engineers developed many aircraft with the inspiration of bird flight. It has been found that birds continuously adjust their wing shape and size to accommodate different flight missions during flight, thereby modifying aerodynamic performance through wing deformation pairs to achieve better flight performance.

Compared with the prior aircraft, engineers approach the wings of the aircraft as much as possible to obtain the aerodynamic performance as excellent as the wings of the birds, thus a series of movable control surfaces and auxiliary devices such as flaps, ailerons, slats, spoilers and the like of the aircraft are created, the movable parts enable the wings of the aircraft to change in shape and size and accordingly change the influence caused by the aerodynamic force in the flight process, but the wings of the design cannot deform continuously, and the wing deformation is realized at the present stage by mainly adopting intelligent deformation materials to replace the trailing edge of the whole wing or using a device for wing bending deformation, the former has the defects that the adopted material deformation response speed is slow or the adopted material cannot bear large air load (such as rubber elastic flexible skin and composite material bistable plate shell), the existing bistable plate shell is limited by materials and preparation methods, the device mainly adopts a motor to drive devices such as a connecting rod, a sliding block and the like to perform translation and rotation motions, but because the space in the wing is narrow, the performance of a driving element of the deformation device is often limited, the mechanism can only be arranged flatly according to the shape of the wing, the transmission performance is generally poor, in addition, the positions of all components in the movement process of the mechanism are usually changed, the gravity center of the whole wing is changed greatly, and the structural characteristics of the wing are influenced.

Meanwhile, the existing fixed wing aircraft usually adopts a control surface to carry out flight control, the deflection of the control surface easily causes discontinuous air flow on the surface of the wing, and airflow separation can be caused when the deflection angle is large, so that the aerodynamic performance of the wing is reduced, and the noise and oil consumption of the aircraft are increased. Therefore, the wing capable of continuously yielding and deforming in the flying process is designed to realize seamless transition of the trailing edge of the wing, efficiently change the wing profile, improve the aerodynamic characteristics and reduce wind noise and fuel consumption, and is an important feature and development direction of future advanced aviation aircrafts. With the development of shape memory alloy technology, the application of the shape memory alloy to the wings of the airplane becomes a technical problem to be solved urgently by those skilled in the art.

Disclosure of Invention

The present invention provides a continuous deformation structure and a deformation method for a trailing edge of an airfoil to solve the above problems in the background art.

The technical problem solved by the invention is realized by adopting the following technical scheme:

the utility model provides a wing trailing edge continuous deformation structure, includes wing, covering, trailing edge skeleton and control circuit, wherein, the trailing edge skeleton is constituteed with the stringer to roof beam, rib, the last parallel arrangement of trailing edge skeleton has a plurality of ribs to divide into a plurality of rib sections with every rib, and the trailing edge skeleton passes through fix with rivet on the wing trailing edge, control circuit is connected with the drive assembly who sets up on every rib section, drive rope, the tie point in the drive assembly are NiTi shape memory alloy and make, utilize the specific temperature of NiTi shape memory alloy to restore the characteristic of specific shape, and the drive rope can contract after the circular telegram heats to specific temperature, and then produces the drive pulling force, thereby drives drive trailing edge structure continuous deformation to transmit wing trailing edge load to the wing, the covering parcel is in the outer layer of trailing edge skeleton, and specific structure is as follows:

the middle of each rib section is connected through a bolt, each rib section can rotate around the bolt, the upper part and the lower part of each rib section are respectively provided with a driving assembly, and the deflection of the rib sections is controlled through the driving assemblies, so that only one section of the original control surface can be deflected, the rib sections are changed into multi-section continuous deflection, each section only needs to deflect a small angle, and the wing shapes can be effectively bent after accumulation, so that the control load is generated; because the deflection angles of all the sections are smaller, the deformation of the trailing edge of the wing is more flexible, the airflow is smoother, the aerodynamic efficiency of the wing is higher, and the noise and the oil consumption are lower;

the skin comprises an upper wall plate, a lower wall plate and a honeycomb interlayer, wherein the upper wall plate and the lower wall plate are connected with the honeycomb interlayer through gluing;

the upper wall plate and the lower wall plate are made of silicon rubber and can bear larger deformation;

the honeycomb sandwich layer is of a zero-Poisson ratio honeycomb structure, can be stretched and deformed, and can bear loads vertical to the honeycomb sandwich layer, so that the skin can generate larger stretching deformation and can bear aerodynamic loads vertical to the skin, then the loads are transmitted to the trailing edge framework, and the trailing edge framework transmits the trailing edge loads of the wings to the wings;

the control circuit comprises a power supply, a control switch and a drive assembly, the drive assembly comprises a drive rope, a connection point and a cable, the connection point comprises a connection base body and a cable, the connection base body is made of NiTi shape memory alloy, the connection base body penetrates through an oval hole of a rib section and is fixed on the rib section, the cable is welded at two ends of the connection base body, the drive rope is wound on the connection point, the cable connected with the control switch is welded at two ends of the drive rope, the control switch is provided with an upper control state, a middle control state and a lower control state, and the control switch is connected with the power supply;

the driving ropes comprise upper driving ropes and lower driving ropes, the connecting points comprise upper connecting points and lower connecting points, the upper part divided into the first rib section is connected with the beam through the upper driving ropes and the upper connecting points, and the lower part is connected with the beam through the lower driving ropes and the lower connecting points; the upper part of each subsequent rib section is connected with the previous rib section through an upper driving rope and an upper connecting point, the lower part of each subsequent rib section is connected with the previous rib section through a lower driving rope and a lower connecting point, the upper driving rope and the lower driving rope are identical in structure, length and diameter, and the upper connecting point and the lower connecting point are identical in structure, length and diameter.

In the invention, the upper driving ropes are connected in series and then connected in parallel with the upper driving ropes of other parallel ribs, and the lower connecting points are connected in series and then connected in parallel with the lower connecting points of other parallel ribs and then connected with a power supply through a control switch; the lower driving ropes are connected in series and then connected in parallel with the lower driving ropes of other parallel ribs, and the upper connecting points are connected in series and then connected in parallel with the upper connecting points of other parallel ribs and then connected with a power supply through a control switch.

When a control switch is adjusted to an upper state, an upper driving rope and a lower connecting point are connected with a power supply, the upper driving rope contracts and deforms to generate driving tension, the section of the lower connecting point becomes circular, the lower connecting point rotates to enable the lower driving rope to relax and not bear load, and the trailing edge of the wing deflects and deforms upwards; when the control switch is adjusted to a lower position, the lower driving rope and the upper connecting point are connected with a power supply, the lower driving rope contracts and deforms to generate driving tension, the section of the upper connecting point is changed into a circular shape, the upper connecting point rotates to enable the upper driving rope to be loosened and not bear load, and the trailing edge of the wing deflects downwards to deform; when the control switch is adjusted to the neutral state, the circuit is broken, the upper connecting point and the lower connecting point cannot rotate, and the driving rope can bear load to promote the trailing edge framework to keep the neutral state; thereby realizing continuous deformation of the trailing edge of the wing.

In the invention, each rib section is provided with a bolt mounting hole.

In the invention, a round hole which is used for fixing the driving rope and can be deformed by electrifying is arranged on the connecting base body, and the driving rope passes through the round hole and is wound on the connecting base body.

In the invention, when not electrified, the section of the connection base body matched with the rib plate oval open hole is oval, so that the connection base body cannot rotate, the driving rope is tightly wound on the connection base body at the moment, and the driving rope can bear tension; the cross section recovers to be circular after being electrified and heated, the connecting base body can rotate, the driving rope wound on the connecting base body is loosened, and the driving rope cannot bear tension.

In the invention, the ratio of the distance between the adjacent connection points to the height of the rib sections is equal, because the unit length deformation of the driving ropes is the same, when the distance between the adjacent connection points of each rib section is equal to the ratio of the height of the rib section, the driving ropes are electrified to deform, the deflection angles of the rib sections are the same, and the deflection angles of the rib sections are only in direct proportion to the electrified heating time, so that the operation is simplified, and a plurality of driving ropes can be controlled to deform in a coordinated manner by a simple circuit to ensure the continuous deformation of the trailing edge of the wing.

Has the advantages that:

1. the invention utilizes the shape memory effect of the shape memory alloy material to manufacture the shape memory alloy material into a driving rope and a connecting point so as to realize multipoint driving of the trailing edge structure of the wing and promote the continuous flexible deformation of the trailing edge of the wing; the aerodynamic efficiency of the wings and the maneuverability of the aircraft are effectively improved, and the noise and the oil consumption rate are reduced;

2. the invention adopts multi-point drive, effectively disperses the drive load, simplifies the drive mechanism and greatly reduces the structural weight;

3. the invention has the advantages of simple structure, simple operation, clear principle, convenient production, strong practicability, easy popularization and application and great value.

Drawings

FIG. 1 is an assembly view of a trailing edge frame and wing in accordance with a preferred embodiment of the present invention.

FIG. 2 is a schematic view of the trailing edge skeleton structure in the preferred embodiment of the present invention.

Fig. 3 is an assembly view of a single rib in a preferred embodiment of the present invention.

Fig. 4 is a schematic view of a beam structure in a preferred embodiment of the invention.

FIG. 5 is a schematic view of a single rib segment in a preferred embodiment of the present invention.

FIG. 6 is a schematic diagram of a single driving assembly according to a preferred embodiment of the present invention.

FIG. 7 is a schematic view of a single connection point structure in a preferred embodiment of the present invention.

FIG. 8 is a cross-sectional view of a single connection point variation in the preferred embodiment of the present invention.

FIG. 9 is a schematic view of a skin structure according to a preferred embodiment of the present invention.

FIG. 10 is a schematic diagram of the connection of the control circuit in the preferred embodiment of the invention.

FIG. 11 is a schematic view of the trailing edge deformation of a preferred embodiment of the present invention.

Detailed Description

In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below by combining the specific drawings.

Referring to fig. 1 to 11, a wing trailing edge continuous deformation structure includes a wing 1, a beam 2, a rib 3, a skin 4, a stringer 5, and a control circuit 6, the beam 2, the rib 3, and the stringer 5 form a trailing edge skeleton, the trailing edge skeleton is fixed on the trailing edge of the wing 1 by rivets, the control circuit 6 is connected to a driving assembly disposed on the rib 3, a driving rope in the driving assembly is made of a NiTi shape memory alloy, the driving rope can be contracted after being electrified and heated to a specific temperature by using the characteristic that the specific temperature of the NiTi shape memory alloy can recover to a specific shape, and then a driving pulling force is generated, so as to drive the driving wing trailing edge structure to continuously deform, so as to transmit the wing trailing edge load to the wing 1, and the specific structure is as follows:

the rear edge framework is provided with a plurality of ribs 3 in parallel, each rib 3 is divided into 4 sections, namely a first rib section 9, a second rib section 10, a third rib section 11 and a fourth rib section 12, each rib section is provided with a bolt mounting hole and is connected with the front structure through a bolt, each rib section can rotate around the bolt, and meanwhile, the rib sections are controlled to deflect through a driving assembly between the rib sections, so that the original control surface only deflects for one section and is changed into four sections to deflect continuously, each section only needs to deflect for a small angle, and the wing shape can be effectively bent after being accumulated, so that the control load is generated; because the deflection angles of all the sections are smaller, the deformation of the trailing edge of the wing is more flexible, the airflow is smoother, the aerodynamic efficiency of the wing is higher, and the noise and the oil consumption are lower; here each rib 3 is divided into 4 sections, the first rib section 9 is the first rib section, and so on;

the skin 4 comprises an upper wall plate 21, a lower wall plate 22 and a honeycomb sandwich 23, wherein the upper wall plate 21 and the lower wall plate 22 are connected with the honeycomb sandwich 23 through gluing, and the skin 4 is wrapped on the outer layer of the rear edge framework and is connected through rivets;

the upper wall plate 21 and the lower wall plate 22 are made of silicon rubber and can bear large deformation;

the honeycomb interlayer 23 is of a zero-Poisson ratio honeycomb structure, can be stretched and deformed, and can bear the load vertical to the honeycomb interlayer 23, so that the skin 4 can generate larger stretching deformation and can bear the aerodynamic load vertical to the skin 4, then the load is transmitted to the trailing edge framework, and the trailing edge load of the wing is transmitted to the wing 1 by the trailing edge framework;

the control circuit 6 comprises a first upper driving rope 13, a first lower driving rope 14, a second upper driving rope 15, a second lower driving rope 16, a third upper driving rope 17, a third lower driving rope 18, a fourth upper driving rope 19, a fourth lower driving rope 20, a power supply 24, a control switch 25, a first upper connection point 29, a first lower connection point 30, a second upper connection point 31, a second lower connection point 32, a third upper connection point 33, a third lower connection point 34, a fourth upper connection point 35, a fourth lower connection point 36, a fifth upper connection point 37, a fifth lower connection point 38, a sixth upper connection point 39, a sixth lower connection point 40, a seventh upper connection point 41, a seventh lower connection point 42, an eighth upper connection point 43 and an eighth lower connection point 44, wherein the middle of a first rib section 9 is connected with the beam 2 through a bolt; the upper part of the first rib section 9 is connected with a first upper driving rope 13 through a second upper connecting point 31, the first upper driving rope 13 is connected with the beam 2 through a first upper connecting point 29, the lower part of the first rib section 9 is connected with a first lower driving rope 14 through a second lower connecting point 32, and the first lower driving rope 14 is connected with the beam 2 through a first lower connecting point 30; the middle of the second rib section 10 is connected with the first rib section 9 through a bolt, the upper part of the second rib section 10 is connected with the second upper driving rope 15 through a fourth upper connecting point 35, the second upper driving rope 15 is connected with the first rib section 9 through a third upper connecting point 33, the lower part of the second rib section 10 is connected with the second lower driving rope 16 through a fourth lower connecting point 36, and the second lower driving rope 16 is connected with the first rib section 9 through a third lower connecting point 34; the middle of the third rib section 11 is connected with the second rib section 10 through a bolt, the upper part of the third rib section 11 is connected with a third upper driving rope 17 through a sixth upper connecting point 39, and the third upper driving rope 17 is connected with the second rib section 10 through a fifth upper connecting point 37; the lower part of the third rib section 11 is connected with a lower third driving rope 18 through a sixth lower connecting point 40, and the third lower driving rope 18 is connected with the second rib section 10 through a fourth lower connecting point 36; the middle of a fourth rib section 12 is connected with a third rib section 11 through a bolt, the upper part of the fourth rib section 12 is connected with a fourth upper driving rope 19 through an eighth upper connecting point 43, the fourth upper driving rope 19 is connected with the third rib section 11 through a seventh upper connecting point 41, the lower part of the fourth rib section 12 is connected with a fourth lower driving rope 20 through an eighth lower connecting point 44, the fourth lower driving rope 20 is connected with the third rib section 11 through a seventh lower connecting point 42, the first rib section 9, the second rib section 10, the third rib section 11 and the fourth rib section 12 are combined into a complete rib 3 through the connection, and the ribs 3 are arranged in parallel and connected with the stringer 5 through rivets; and the first upper driving rope 13, the second upper driving rope 15, the third upper driving rope 17 and the fourth upper driving rope 19 are connected in series and connected in parallel with the upper driving ropes of the other parallel ribs 3; the first lower connection point 30, the second lower connection point 32, the third lower connection point 34, the fourth lower connection point 36, the fifth lower connection point 38, the sixth lower connection point 40, the seventh lower connection point 42 and the eighth lower connection point 44 are connected in series and connected in parallel with the lower connection points of the other parallel ribs 3; the upper driving rope after series connection is connected with the lower connecting point after series connection in parallel and then is connected to a power supply 24 through a control switch 25; the next lower drive rope 14, the second lower drive rope 16, the third lower drive rope 18 and the fourth lower drive rope 20 are connected in series and connected in parallel with the lower drive ropes of the other parallel ribs 3; the first upper connecting point 29, the second upper connecting point 31, the third upper connecting point 33, the fourth upper connecting point 35, the fifth upper connecting point 37, the sixth upper connecting point 39, the seventh upper connecting point 41 and the eighth upper connecting point 43 are connected in series and are connected in parallel with the upper connecting points of other parallel ribs 3, and the lower driving ropes after being connected in series are connected in parallel with the upper connecting points after being connected in series and then are connected to the power supply 24 through the control switch 25; starting the control switch 25 to electrify the connection point to heat the driving rope connected with the connection point, and the driving rope contracts to generate driving tension to enable the rib section to deflect;

the first upper driving rope 13, the first lower driving rope 14, the second upper driving rope 15, the second lower driving rope 16, the third upper driving rope 17, the third lower driving rope 18, the fourth upper driving rope 19 and the fourth lower driving rope 20 are identical in structure, length and diameter, so that the driving ropes are identical in resistance, identical in heat generated by electrifying in the same time after series connection, identical in heated temperature and identical in contracted deformation amount in unit length;

each driving assembly comprises a driving rope 26, a connecting point 27 and a cable 28, wherein the driving rope 26 passes through a round hole in the connecting point 27 and is wound on the connecting point 27, the cable 28 is welded at two ends of the driving rope 26, and the driving assembly comprises a first upper connecting point 29, a second upper connecting point 31 and a first upper driving rope 13 by taking the first upper driving rope 13 as an example;

each connecting point 27 comprises a connecting base body 48, a cable 45, a rib section 46 and a nut 47, wherein the connecting base body 48 is made of NiTi shape memory alloy, the connecting base body 48 penetrates through the oval hole of the rib section 46 and is fixed on the rib section 46 through the nut 47, the cable 48 is welded at two ends of the connecting base body 45, and a round hole is formed in the connecting base body 48 and used for fixing the driving rope 26;

the control switch 25 is provided with an upper control state, a middle control state and a lower control state, and when the control switch 25 is in the upper control state, the upper driving rope and the lower connecting point are driven to be connected with the power supply 24; when the control switch 25 is in the lower state, the lower driving rope and the lower connecting point are driven to be connected with the power supply 24; when the control switch 25 is in the neutral state, the circuit is in the open state;

when the control switch 25 is adjusted to an upper state, all the upper driving ropes and the lower connecting points are communicated with the power supply 24, the upper driving ropes contract and deform to generate driving tension, the section of the lower connecting points is changed into a circle, the lower connecting points rotate to enable the lower driving ropes to be loose and not bear load, and the rear edge of the wing deflects upwards and deforms; when the control switch 25 is adjusted to the lower position, all the lower driving ropes and the upper connecting points are connected with the power supply 24, the lower driving ropes contract and deform to generate driving tension, the section of the upper connecting points is changed into a circle, the upper connecting points rotate to enable the upper driving ropes to be loose and not bear load, and the trailing edge of the wing deflects downwards and deforms; when the control switch 25 is set to the neutral state, the circuit is broken, the upper connection point and the lower connection point cannot rotate, the driving rope can bear the load, and the rear edge is kept in the neutral state; all the upper driving ropes comprise a first upper driving rope 13, a second upper driving rope 15, a third upper driving rope 17 and a fourth upper driving rope 19, all the lower connecting points comprise a first lower connecting point 30, a second lower connecting point 32, a third lower connecting point 34, a fourth lower connecting point 36, a fifth lower connecting point 38, a sixth lower connecting point 40, a seventh lower connecting point 42 and an eighth lower connecting point 44, all the lower driving ropes comprise a first lower driving rope 14, a second lower driving rope 16, a third lower driving rope 18 and a fourth lower driving rope 20, and all the upper connecting points comprise a first upper connecting point 29, a second upper connecting point 31, a third upper connecting point 33, a fourth upper connecting point 35, a fifth upper connecting point 37, a sixth upper connecting point 39, a seventh upper connecting point 41 and an eighth upper connecting point 43;

taking the driving rope 26 shown in fig. 6 and 7 as an example, when the power is not supplied, the section of the connecting base 48 matched with the oval hole is oval, so that the connecting base 48 cannot rotate, the driving rope 26 is tightly wound on the connecting base 48, and the driving rope 26 can bear the tension; after the power is switched on and the heating is carried out, the section returns to be circular, the connecting base 48 can rotate, at the moment, the driving rope 26 wound on the connecting base 48 is loosened, and the driving rope 26 cannot bear the tension; the rib section 46 is a general name of a single connecting point 27, taking the second upper connecting point 31 as an example, the rib section is the first rib section 9, the rib section installed on the fourth upper connecting point 35 is the second rib section 10, and so on.

In this embodiment, the distance between the adjacent connection points is equal to the ratio of the height of the rib section, such as the distance from the first lower connection point 30 to the second lower connection point 32, the ratio of the height of the first rib section 9, and the distance from the third lower connection point 34 to the fourth lower connection point 36, the ratio of the height of the second rib section 10,

because the unit length deformation of the driving ropes is the same, when the distance between adjacent connection points of all the rib sections is equal to the height ratio of the rib sections, the driving ropes are electrified to deform, the deflection angles of all the rib sections are the same, and the deflection angles of the rib sections are only in direct proportion to the electrified heating time, so that the operation is simplified, and a plurality of driving ropes can be controlled to deform in a coordinated manner by a simple circuit to ensure the continuous deformation of the trailing edge of the wing.