A shape memory alloy driven corrugated core flexible wing trailing edge structure

Abstract

The invention discloses a corrugated core flexible wing trailing edge structure driven by shape memory alloy. The invention comprises a wing spar, a composite corrugated plate, a deformable plate, an upper wing skin, a lower wing skin and a rigid tail; the wing spar and the rigid tail are fixedly connected by the upper wing skin and the lower wing skin, the upper wing skin and the lower wing skin are at an angle and arranged at intervals up and down, the upper wing skin and the lower wing skin are fixedly connected by a composite corrugated plate, one end of the composite corrugated plate close to the wing spar is fixedly connected to the middle of the wing spar, and a plurality of deformable plates are fixedly installed in the composite corrugated plate; the deformation drive of the deformable plate causes the wing trailing edge to deform. The invention has a simple structure and is easy to control. The deformation state of the deformable plate is independently controlled by a circuit, and the deformation state of multiple groups of deformable plates is controlled to realize various curvatures of the flexible trailing edge as a whole, so as to adapt to various different flight conditions.

Description

Technical Field

[0001] The invention relates to a flexible wing trailing edge structure, in particular to a corrugated core flexible wing trailing edge structure driven by a shape memory alloy. Background Art

[0002] Shape memory alloys are key metal smart materials in advanced industrial fields. After the low-temperature martensite phase undergoes plastic deformation, when heated through the phase transition temperature range, the martensite crystal structure undergoes thermoelastic changes and returns to its original shape. Compared with traditional mechanical drives, the use of shape memory alloys in drives can effectively reduce the weight of the structure and has the advantages of low drive voltage and high power-to-weight ratio.

[0003] The flight conditions of an aircraft during flight are very complex. Traditional aircraft usually need to use a hinged flap structure called aileron to achieve the tilt of the aircraft during flight. However, the control surface operation also faces the problem of being difficult to adapt to all flight conditions. The movement of the control surface inevitably leads to an increase in parasitic drag. At the same time, the traditional rigid mechanical deformation structure greatly increases the overall weight of the wing. The application of flexible intelligent structure in the field of drive can effectively solve the above problems, which is the starting point of this invention. Summary of the invention

[0004] The purpose of the present invention is to provide a flexible wing trailing edge structure using shape memory alloy, which can realize various curvature deformation of the wing trailing edge during flight, effectively improve aerodynamic efficiency, and adapt to various flight conditions.

[0005] The technical solution adopted by the present invention is:

[0006] The invention comprises a wing spar, a composite corrugated plate, a deformed plate, an upper wing surface skin, a lower wing surface skin and a rigid tail;

[0007] The wing beam and the rigid tail are fixedly connected by an upper wing surface skin and a lower wing surface skin. The upper wing surface skin and the lower wing surface skin are angled and spaced apart from each other. The upper wing surface skin and the lower wing surface skin are fixedly connected by a composite material corrugated plate. One end of the composite material corrugated plate close to the wing beam is fixedly connected to the middle part of the wing beam. A plurality of deformation plates are fixedly installed in the composite material corrugated plate. The deformation of the deformation plate drives the trailing edge of the wing to deform.

[0008] The composite corrugated plate is a quasi-sine corrugated plate composed of a plurality of half-period sinusoidal corrugated plates connected in sequence, the plurality of sinusoidal corrugated plates have equal wavelengths, and the amplitude increases in sequence along the direction from the rigid tail to the wing beam. In the composite corrugated plate, the amplitude of two adjacent wave peaks increases along the direction from the rigid tail to the wing beam, the amplitude corresponding to the wave valley between two adjacent wave peaks is between the amplitudes corresponding to the current two wave peaks, the amplitude of two adjacent wave valleys increases along the direction from the rigid tail to the wing beam, the amplitude corresponding to the wave peak between two adjacent wave valleys is between the amplitudes corresponding to the current two wave valleys; each wave peak surface in the composite corrugated plate is fixedly connected to the upper wing surface skin, each wave valley surface in the composite corrugated plate is fixedly connected to the lower wing surface skin, the junction of two adjacent sinusoidal corrugated plates is recorded as a connection, a corresponding deformation plate is fixedly installed between two adjacent connections, and a corresponding deformation plate is fixedly installed between the connection closest to the wing beam and the end of the composite corrugated plate.

[0009] The composite corrugated plate is formed by eight layers of composite materials stacked in sequence from top to bottom, wherein the eight layers of composite materials are, from top to bottom, a first composite material layer, a second composite material layer, a third composite material layer, a fourth composite material layer, a fifth composite material layer, a sixth composite material layer, a seventh composite material layer and an eighth composite material layer, wherein the fiber directions of materials of the first composite material layer and the eighth composite material layer are the same, the fiber directions of materials of the second composite material layer and the seventh composite material layer are the same, the fiber directions of materials of the third composite material layer and the sixth composite material layer are the same, the fiber directions of materials of the fourth composite material layer and the fifth composite material layer are the same, and the fiber directions of materials of the first to fourth composite material layers are all different.

[0010] In the composite corrugated plate, the first, second, seventh and eighth composite material layers are all made of carbon fiber composite material T800H / 924C, and the third, fourth, fifth and sixth composite material layers are all made of carbon fiber epoxy resin material HT7 / 5438.

[0011] The deformable plate includes a shape memory alloy, an insulating film, a thermal insulation film and a wire. The outside of the shape memory alloy is covered with an insulating film and a thermal insulation film in sequence, and the two ends of the shape memory alloy are respectively connected to the corresponding wires. The original state of the shape memory alloy is an arc plate or a half-period sinusoidal corrugated plate. After power is applied and heated, the shape memory alloy deforms and eventually becomes a flat rectangular plate.

[0012] The upper wing surface skin and the lower wing surface skin are both made of flexible materials.

[0013] The beneficial effects of the present invention are:

[0014] 1. The corrugated plate structure is used as the internal support structure of the flexible trailing edge. Its anisotropy is used to make the trailing edge structure deformable in the chord direction and have sufficient rigidity in the transverse direction. The fiber laying method of the composite material in the corrugated plate increases the fundamental frequency of the corrugated plate, thereby increasing the rigidity of the corrugated plate, while effectively reducing the weight, meeting the comprehensive requirements for the wing structure performance under different bending deformation states;

[0015] 2. Use shape memory alloy as deformation drive, with simple structure and convenient control, and can be triggered by electric drive;

[0016] 3. The deformable plate is used as a deformation drive in the wing trailing edge mechanism. Each deformable plate is driven separately. The combination of multiple deformable plates can achieve a variety of different trailing edge curvatures to adapt to a variety of complex flight conditions. According to the actual flight conditions and their real-time changes, the deformation of the corresponding deformable plate is controlled by the circuit, so that the wing trailing edge is always in the trailing edge shape with the best aerodynamic efficiency, effectively reducing fuel consumption.

[0017] 4. Compared with mechanical drive, the shape memory alloy drive adopted in the present invention makes the overall structure lightweight and effectively saves energy. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the structure of the present invention;

[0019] Figure 2 It is a schematic diagram of the combined structure of the composite material corrugated plate and the deformed plate of the present invention;

[0020] Figure 3 It is a schematic diagram of laying fibers of a composite material corrugated board of the present invention;

[0021] Figure 4 This is the first bending deformation state of the present invention;

[0022] Figure 5 This is the second bending deformation state of the present invention;

[0023] Figure 6 This is the third bending deformation state of the present invention;

[0024] In the figure: wing beam 1, composite material corrugated plate 2, composite material corrugated plate first corrugation 2-1, composite material corrugated plate second corrugation 2-2, composite material corrugated plate third corrugation 2-3, composite material corrugated plate fourth corrugation 2-4, composite material corrugated plate fifth corrugation 2-5, composite material corrugated plate sixth corrugation 2-6, deformation plate 3, first deformation plate 3-1, second deformation plate 3-2, third deformation plate 3-3, fourth deformation plate 3-4, fifth deformation plate 3-5, upper wing surface skin 4, lower wing surface skin 5, rigid tail 6. DETAILED DESCRIPTION

[0025] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0026] like Figure 1 As shown, the present invention comprises a spar 1, a composite corrugated plate 2, a deformed plate 3, an upper wing skin 4, a lower wing skin 5 and a rigid tail 6;

[0027] The spar 1 and the rigid tail 6 are fixedly connected through the upper wing skin 4 and the lower wing skin 5. One end of the upper wing skin 4 and the lower wing skin 5 is fixedly connected to the upper and lower ends of the spar 1, and the other end of the upper wing skin 4 and the lower wing skin 5 is fixedly connected to the upper and lower ends of the rigid tail 6. The upper wing skin 4 and the lower wing skin 5 are arranged at an angle and spaced up and down. The upper wing skin 4 and the lower wing skin 5 are fixedly connected through a composite corrugated plate 2. One end of the composite corrugated plate 2 close to the spar 1 is fixedly connected to the middle of the spar 1. Multiple deformable plates 3 are fixedly installed in the composite corrugated plate 2. The multiple deformable plates 3 do not contact the upper wing skin 4 and the lower wing skin 5. The upper wing skin 4 and the lower wing skin 5 are both made of flexible materials. The deformation drive of the deformable plate 3 causes the trailing edge of the wing to deform.

[0028] The composite corrugated plate 2 is a quasi-sine corrugated plate composed of multiple half-period sinusoidal corrugated plates connected in sequence. The multiple sinusoidal corrugated plates have equal wavelengths and the amplitude increases successively along the direction from the rigid tail 6 to the spar 1. In the composite corrugated plate 2, the amplitude of two adjacent raised peaks increases along the direction from the rigid tail 6 to the spar 1, the amplitude corresponding to the raised trough between two adjacent raised peaks is between the amplitudes corresponding to the current two peaks, the amplitude of two adjacent troughs increases along the direction from the rigid tail 6 to the spar 1, and the amplitude corresponding to the peak between two adjacent troughs is between the amplitudes corresponding to the current two troughs; each peak surface in the composite corrugated plate 2 is fixedly connected to the upper wing skin 4, and each trough surface in the composite corrugated plate 2 is fixedly connected to the lower wing skin 5. The upper surface where each peak of the composite corrugated plate 2 is located is recorded as a peak surface, and the lower surface where each trough of the composite corrugated plate 2 is located is recorded as a trough surface.

[0029] The junction of two adjacent sinusoidal corrugated plates is recorded as a connection, and a corresponding deformation plate 3 is fixedly installed between the two adjacent connections. A corresponding deformation plate 3 is fixedly installed between the connection closest to the wing beam 1 and the end of the composite material corrugated plate 2, and no corresponding deformation plate 3 is arranged between the connection closest to the rigid tail 6 and the end of the composite material corrugated plate 2.

[0030] like Figure 3As shown, the composite corrugated plate 2 is composed of eight layers of composite materials stacked in sequence from top to bottom, and the eight layers of composite materials are, from top to bottom, a first composite material layer, a second composite material layer, a third composite material layer, a fourth composite material layer, a fifth composite material layer, a sixth composite material layer, a seventh composite material layer and an eighth composite material layer. The fiber directions of the materials of the first composite material layer and the eighth composite material layer are the same, the fiber directions of the materials of the second composite material layer and the seventh composite material layer are the same, the fiber directions of the materials of the third composite material layer and the sixth composite material layer are the same, the fiber directions of the materials of the fourth composite material layer and the fifth composite material layer are the same, and the fiber directions of the materials of the first to fourth composite material layers are all different.

[0031] In a specific implementation, when the fiber direction θ1 of the material of the first composite layer and the eighth composite layer is 0°, the fiber direction θ2 of the material of the second composite layer and the seventh composite layer is 90°, the fiber direction θ3 of the material of the third composite layer and the sixth composite layer is -90°, and the fiber direction θ4 of the material of the fourth composite layer and the fifth composite layer is 45°.

[0032] In the composite corrugated plate 2, the first, second, seventh and eighth composite material layers are all made of carbon fiber composite material T800H / 924C, and the third, fourth, fifth and sixth composite material layers are all made of carbon fiber epoxy resin material HT7 / 5438. The fiber laying method of the composite corrugated plate 2 effectively improves the fundamental frequency of the corrugated plate 2, thereby improving the rigidity of the corrugated plate 2, while effectively reducing the weight, meeting the comprehensive requirements for wing structural performance under different bending deformation states.

[0033] The deformable plate 3 includes a shape memory alloy, an insulating film, a thermal insulation film and a wire. The outside of the shape memory alloy is covered with an insulating film and a thermal insulation film in sequence. The two ends of the shape memory alloy are respectively connected to corresponding wires. The wires pass through the insulating film and the thermal insulation film in sequence and are connected to the control circuit. The wires are controlled by the main control console of the aircraft fuselage where the wing is located, and are used to electrically heat the shape memory alloy. The deformable plates 3 of adjacent flexible trailing edges are connected side by side at both ends, and the wires inside are connected and controlled by the main control console of the aircraft fuselage; the original state of the shape memory alloy is an arc plate or a half-period sinusoidal corrugated plate, that is, the original state of all deformable plates 3 is an arc plate or a half-period sinusoidal corrugated plate, so that the deformable plate 3 between two adjacent wave crests forms a wave crest, and the deformable plate 3 between two adjacent wave troughs forms a wave trough, and the central axis formed by all deformable plates 3 is collinear with the central axis of the composite corrugated plate 2, that is, the connecting line of the end faces of all deformable plates 3 is on a straight line, which is recorded as the first straight line, and the connecting line of the end faces of all sinusoidal corrugated plates is on a straight line, which is recorded as the second straight line, and the first straight line and the second straight line are collinear. For a sine wave, the central axis is the line where the propagation direction of the wave is located. After power-on heating, the shape memory alloy is deformed and eventually becomes a flat rectangular plate, that is, the deformable plate 3 is a flat rectangular plate, and then the shape of the composite corrugated plate 2 is adjusted, and finally the shape of the wing trailing edge is changed. The length of any deformable plate 3 is smaller than the length of the corresponding corrugation of the composite corrugated plate 2 to ensure that the deformable plate 3 will not touch the upper wing skin 4 or the lower wing skin 5 during the deformation process; the length of a single deformable plate 3 is designed according to the deformation curvature required for specific flight conditions; the longer the length of the deformable plate 3, the larger the opening of the corresponding corrugation when it is transformed into a deformed state after deformation, and the larger the deformation curvature of the composite corrugated plate 2; in specific implementation, when the deformable plate 3 is installed on the fuselage of the aircraft, all the deformable plates 3 in the same corrugated section are energized and heated at the same time through the control circuit so that the trailing edge angle of the flexible trailing edge changes.

[0034] The corrugations of the composite corrugated plate 2 are arranged from small to large, conforming to the overall shape of the flexible trailing edge, and the raised portion of each corrugation is connected to the adjacent upper wing skin 4 or lower wing skin 5; in the undeformed state, the connection between each deformed plate 3 and the corrugated plate 2 is on the same line, and the flexible trailing edge structure as a whole is approximately triangular; the support of the composite corrugated plate makes the flexible trailing edge of the wing have better stability and strengthens the structural strength of the flexible trailing edge.

[0035] The deformable plate 3 is a curved rectangular plate-like structure in the undeformed state. When the shape memory alloy inside is energized through the wires arranged at both ends of the deformable plate 3, the shape memory alloy deforms as the temperature rises and transforms into a deformed state. At this time, the shape memory alloy is a straight rectangular plate-like structure. The deformation of the shape memory alloy drives the deformation of the deformable plate 3. The deformable plate 3 transforms into a deformed state and its shape becomes a straight rectangular plate-like structure. When the power is kept on, the shape memory alloy maintains a relatively high temperature under the action of the thermal insulation film and continuously maintains the deformed state.

[0036] The deformable plate 3 is a straight rectangular plate-like structure in a deformed state, the wires at both ends of the deformable plate 3 remain energized, and the shape memory alloy maintains a relatively high temperature; after the energization is stopped, the shape memory alloy deforms as it cools and recovers from the deformed state to the undeformed state, and transforms from a curved rectangular plate-like structure to a straight rectangular plate-like structure; the deformation of the shape memory alloy drives the deformation of the deformable plate 3, and recovers from the deformed state to the undeformed state, and transforms from a curved rectangular plate-like structure to a straight rectangular plate-like structure;

[0037] Each deformed plate 3 is a curved rectangular plate structure in an undeformed state. At this time, the middle of the deformed plate 3 moves away from the composite corrugated plate 2 so that the deformed plate 3 forms an arc bend. At this time, the composite corrugated plate 2 and the deformed plate 3 are both in the original state;

[0038] After the single deformable plate 3 in the undeformed state is electrically heated, the deformable plate 3 is deformed and transformed into a deformed state. At this time, the middle part of the deformable plate 3 approaches the composite material corrugated plate 2 until it becomes a straight rod. The two connection points where the deformable plate 3 connects the composite material corrugated plate 2 push the corresponding corrugation in opposite directions on both sides, so that the corresponding corrugation opening becomes larger, and the opening connection line of the corresponding corrugation is no longer collinear with the opening connection line of the adjacent corrugation on the composite material corrugated plate 2. The opening connection line of the corresponding corrugation is deflected at a certain angle with the connection points on both sides as the axis, so that the trailing edge angle of the flexible trailing edge changes from the original angle to the deformed angle;

[0039] After the power is turned off for the single deformed plate 3 in the deformed state, the deformed plate 3 deforms as it cools and recovers from the deformed state to the undeformed state. At this time, the middle part of the deformed plate 3 moves away from the composite material corrugated plate 2 to form an arc shape, and the two connection points where the deformed plate 3 connects the composite material corrugated plate 2 shrink the corresponding corrugations in opposite directions on both sides, so that the corresponding corrugation opening becomes smaller, and the opening connection line of the corresponding corrugation and the opening connection line of the adjacent corrugations on the composite material corrugated plate 2 are restored to be colinear, and the opening connection lines of the corresponding corrugations are deflected at a certain angle with the two side connections as the axis, thereby changing the trailing edge angle of the flexible trailing edge and recovering from the deformation angle to the original angle.

[0040] The deformation plates 3 in different corrugated sections can be independently controlled to deform through the circuit. The states of the multiple groups of deformation plates 3 in different combinations enable the flexible trailing edge to achieve different curvatures as a whole. By controlling the state of each deformation plate 3, the overall curvature of the flexible trailing edge can be controlled.

[0041] When the deformable plate 3 with the opening upward is transformed from the undeformed state to the deformed state, the flexible rear edge bends downward, and as the number of deformable plates 3 that are deformed increases, the downward bending angle increases;

[0042] When the deformable plate 3 with the opening downward changes from the undeformed state to the deformed state, the flexible rear edge bends upward, and as the number of deformable plates 3 that are deformed increases, the upward bending angle increases.

[0043] The upper wing skin 4 and the lower wing skin 5 are both glass fiber reinforced silicone matrix composite materials, which can deform accordingly to conform to the deformation of the corrugated plate, so that the flexible trailing edge has good deformability and compliance.

[0044] like Figure 2 As shown, the two ends of the first deformed plate 3-1 are respectively connected to the intersection of the first corrugation 2-1 of the composite material corrugated plate and the second corrugation 2-2 of the composite material corrugated plate and the intersection of the second corrugation 2-2 of the composite material corrugated plate and the third corrugation 2-3 of the composite material corrugated plate; the two ends of the second deformed plate 3-2 are respectively connected to the intersection of the second corrugation 2-2 of the composite material corrugated plate and the third corrugation 2-3 of the composite material corrugated plate and the fourth corrugation 2-4 of the composite material corrugated plate; the two ends of the third deformed plate 3-3 are respectively connected to the intersection of the third corrugation 2-3 of the composite material corrugated plate and the fourth corrugation 2-4 of the composite material corrugated plate The intersection of the fourth corrugation 2-4 of the corrugated plate and the intersection of the fourth corrugation 2-4 of the composite material corrugated plate and the fifth corrugation 2-5 of the composite material corrugated plate; the two ends of the fourth deformed plate 3-4 are respectively connected to the intersection of the fourth corrugation 2-4 of the composite material corrugated plate and the fifth corrugation 2-5 of the composite material corrugated plate and the intersection of the fifth corrugation 2-5 of the composite material corrugated plate and the sixth corrugation 2-6 of the composite material corrugated plate; the two ends of the fifth deformed plate 3-5 are respectively connected to the intersection of the fifth corrugation 2-5 of the composite material corrugated plate and the sixth corrugation 2-6 of the composite material corrugated plate and the intersection of the sixth corrugation 2-6 of the composite material corrugated plate and the spar 1;

[0045] Figure 1 The embodiment shown has 5 groups of deformable plates 3 installed, with a total of 32 combinations of deformation states, each of which can achieve a flexible trailing edge curvature. By controlling the state of each deformable plate 3, the overall curvature of the flexible trailing edge can be controlled.

[0046] In the undeformed state, all the deformed plates 3 are bent rectangular plate structures. At this time, the middle of the deformed plate 3 moves away from the composite material corrugated plate 2 so that the deformed plate 3 forms an arc bend. The composite material corrugated plate 2 and the deformed plate 3 are both in the original state. The center line of the composite material corrugated plate 2 remains horizontal, and the overall structure of the flexible trailing edge does not bend.

[0047] When the first deformation state occurs, the deformation plate 3-2 and the deformation plate 3-4 are electrically heated respectively, and the deformation plate 3-2 and the deformation plate 3-4 are deformed and transformed into a deformed state. At this time, the middle parts of the deformation plate 3-2 and the deformation plate 3-4 are close to the corrugated plate until they become straight rods; the deformation plate 3-2 is applied to the two connection points connecting the composite material corrugated plate 2 to push the corrugation 2-3 in opposite directions on both sides, so that the opening of the corresponding corrugation 2-3 becomes larger, and the opening connection line of the corresponding corrugation 2-3 and the opening connection line of the adjacent corrugation 2-2 and corrugation 2-4 on the composite material corrugated plate 2 are no longer in the same line, and the connection points on both sides are used as the axis, and the corresponding corrugation 2-3 and the opening connection line of the adjacent corrugation 2-2 and corrugation 2-4 are respectively A certain angle of deflection is generated, changing from the original angle to the deformation angle; the deformation plate 3-4 is applied to the two connections connecting the composite material corrugated plate 2 to push the corrugation 2-5 in opposite directions on both sides, so that the opening of the corresponding corrugation 2-5 becomes larger, and the opening connection line of the corresponding corrugation 2-5 and the opening connection line of the adjacent corrugation 2-4 and corrugation 2-6 on the composite material corrugated plate 2 are no longer collinear, and a certain angle of deflection is generated between the corresponding corrugation 2-5 and the opening connection line of the adjacent corrugation 2-4 and corrugation 2-6 with the two side connections as the axis, changing from the original angle to the deformation angle; the flexible trailing edge overall structure is bent and deformed under the driving force of the bending deformation of the composite material corrugated plate 2, and bends upward at a certain angle, so as to achieve the following Figure 4 The first bending deformation state is shown;

[0048] When the second deformation state occurs, the deformation plate 3-3 and the deformation plate 3-5 are electrically heated respectively, and the deformation plate 3-3 and the deformation plate 3-5 are deformed and transformed into a deformed state. At this time, the middle parts of the deformation plate 3-3 and the deformation plate 3-5 are close to the corrugated plate until they become straight rods; the deformation plate 3-3 is applied to the two connection points connecting the composite material corrugated plate 2 to push the corrugation 2-4 in opposite directions on both sides, so that the opening of the corresponding corrugation 2-4 becomes larger, and the opening connection line of the corresponding corrugation 2-4 and the opening connection line of the adjacent corrugation 2-3 and corrugation 2-5 on the composite material corrugated plate 2 are no longer in the same line, and the connection points on both sides are used as the axis, and the corresponding corrugation 2-4 and the opening connection line of the adjacent corrugation 2-3 and corrugation 2-5 are respectively A certain angle of deflection is generated, changing from the original angle to the deformation angle; the deformation plate 3-5 is applied to the two connections connecting the composite material corrugated plate 2 to push the corrugation 2-6 in opposite directions on both sides, so that the opening of the corresponding corrugation 2-6 becomes larger, and the opening connection line of the corresponding corrugation 2-6 and the opening connection line of the adjacent corrugation 2-5 on the composite material corrugated plate 2 are no longer collinear, and a certain angle of deflection is generated between the corresponding corrugation 2-6 and the opening connection line of the adjacent corrugation 2-5 and the mid-perpendicular line of the wing beam with the two side connections as the axis, changing from the original angle to the deformation angle; the flexible trailing edge overall structure is bent and deformed under the driving force of the bending deformation of the composite material corrugated plate 2, and bends downward at a certain angle, so as to achieve the following Figure 5 The second bending deformation state is shown;

[0049] When the third deformation state occurs, the deformation plates 3-1, 3-3 and 3-5 are electrically heated respectively, and the deformation plates 3-1, 3-3 and 3-5 are deformed and transformed into the deformed state. At this time, the middle parts of the deformation plates 3-1, 3-3 and 3-5 are close to the corrugated plate until they become straight rods; the deformation plate 3-1 is applied to the two joints connecting the composite material corrugated plate 2 to push the corrugation 2-2 in opposite directions on both sides, so that the corresponding corrugation 2-2 The opening becomes larger, and the opening connection line of the corresponding corrugation 2-2 is no longer in line with the opening connection line of the adjacent corrugations 2-1 and 2-3 on the composite corrugated plate 2. A certain angle of deflection is generated between the corresponding corrugation 2-2 and the opening connection lines of the adjacent corrugations 2-1 and 2-3 with the connection points on both sides as the axis, and the original angle is changed to a deformed angle; the deformed plate 3-13 is applied to the two connection points connecting the composite corrugated plate 2 to push the corrugation 2-4 in opposite directions on both sides, so that the corresponding corrugation 2-4 is pushed open ... The opening of corrugation 2-4 becomes larger, and the opening connection line of the corresponding corrugation 2-4 is no longer in line with the opening connection line of the adjacent corrugations 2-3 and 2-5 on the composite corrugated plate 2. A certain angle of deflection is generated between the opening connection lines of the corresponding corrugation 2-4 and the adjacent corrugations 2-3 and 2-5 with the connection points on both sides as the axis, and the original angle is changed to the deformation angle; the deformation plate 3-5 is applied to the two connection points connecting the composite corrugated plate 2 to push the corrugation 2-6 in opposite directions on both sides, so that the opening of the corresponding corrugation 2-6 becomes larger, and the opening connection line of the corresponding corrugation 2-6 is no longer in line with the opening connection line of the adjacent corrugations 2-5 on the composite corrugated plate 2. A certain angle of deflection is generated between the opening connection lines of the corresponding corrugation 2-6 and the adjacent corrugations 2-5 and the mid-perpendicular line of the wing beam with the connection points on both sides as the axis, and the original angle is changed to the deformation angle; the flexible trailing edge overall structure is bent and deformed under the driving of the bending deformation of the composite corrugated plate 2, and bends downward at a certain angle, so as to achieve the following Figure 6 The third bending deformation state is shown.

Claims

1. A shape memory alloy driven corrugated core flexible wing trailing edge structure, characterized in that: It comprises a wing spar (1), a composite corrugated plate (2), a deformable plate (3), an upper wing surface skin (4), a lower wing surface skin (5) and a rigid tail (6); The wing beam (1) and the rigid tail (6) are fixedly connected via an upper wing surface skin (4) and a lower wing surface skin (5); the upper wing surface skin (4) and the lower wing surface skin (5) form an angle and are arranged with an interval up and down; the upper wing surface skin (4) and the lower wing surface skin (5) are fixedly connected via a composite material corrugated plate (2); one end of the composite material corrugated plate (2) close to the wing beam (1) is fixedly connected to the middle of the wing beam (1); a plurality of deformation plates (3) are fixedly installed in the composite material corrugated plate (2); the deformation of the deformation plate (3) causes the wing trailing edge to deform; The deformable plate (3) comprises a shape memory alloy, an insulating film, a heat-insulating film and a conductor. The shape memory alloy is coated with the insulating film and the heat-insulating film in sequence. The two ends of the shape memory alloy are respectively connected to corresponding conductors. The shape memory alloy is originally in the form of an arc plate or a half-period sinusoidal corrugated plate. After being electrically heated, the shape memory alloy is deformed and eventually becomes a flat rectangular plate.

2. The shape memory alloy driven corrugated core flexible wing trailing edge structure according to claim 1, characterized in that: The composite corrugated plate (2) is a quasi-sine corrugated plate composed of a plurality of half-period sinusoidal corrugated plates connected in sequence. The plurality of sinusoidal corrugated plates have equal wavelengths and their amplitudes increase in sequence along the direction from the rigid tail (6) to the wing beam (1). In the composite corrugated plate (2), the amplitudes of two adjacent wave peaks increase along the direction from the rigid tail (6) to the wing beam (1), the amplitude of the trough between two adjacent wave peaks is between the amplitudes of the current two wave peaks, the amplitudes of two adjacent wave troughs increase along the direction from the rigid tail (6) to the wing beam (1), and the amplitudes of two adjacent wave troughs increase along the direction from the rigid tail (6) to the wing beam (1). The amplitude corresponding to the wave crest between the wave troughs is between the amplitudes corresponding to the current two wave troughs; each wave crest surface in the composite material corrugated plate (2) is fixedly connected to the upper wing surface skin (4), each wave trough surface in the composite material corrugated plate (2) is fixedly connected to the lower wing surface skin (5), the junction of two adjacent sinusoidal corrugated plates is recorded as a connection point, a corresponding deformation plate (3) is fixedly installed between two adjacent connection points, and a corresponding deformation plate (3) is fixedly installed between the connection point closest to the wing beam (1) and the end of the composite material corrugated plate (2).

3. The shape memory alloy driven corrugated core flexible wing trailing edge structure according to claim 1, characterized in that: The composite corrugated plate (2) is formed by stacking eight composite layers in sequence from top to bottom, wherein the eight composite layers are, in sequence from top to bottom, a first composite layer, a second composite layer, a third composite layer, a fourth composite layer, a fifth composite layer, a sixth composite layer, a seventh composite layer and an eighth composite layer, wherein the fiber directions of the materials of the first composite layer and the eighth composite layer are the same, the fiber directions of the materials of the second composite layer and the seventh composite layer are the same, the fiber directions of the materials of the third composite layer and the sixth composite layer are the same, the fiber directions of the materials of the fourth composite layer and the fifth composite layer are the same, and the fiber directions of the materials of the first to fourth composite layers are all different.

4. The shape memory alloy driven corrugated core flexible wing trailing edge structure according to claim 3, characterized in that: In the composite material corrugated plate (2), the first, second, seventh and eighth composite material layers are all made of carbon fiber composite material T800H / 924C, and the third, fourth, fifth and sixth composite material layers are all made of carbon fiber epoxy resin material HT7 / 5438.

5. The shape memory alloy driven corrugated core flexible wing trailing edge structure according to claim 1, characterized in that: The upper wing surface skin (4) and the lower wing surface skin (5) are both made of flexible materials.

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