CN112109877B - Variant wing based on piezoelectric driving - Google Patents

Abstract

A variant wing based on piezoelectric drive, which relates to the technical field of aviation aircraft variant wing, includes a wing box with a D-shaped cross section and a deformation structure connected to the rear end of the wing box, and the wing box includes A frame constructed of a plurality of ribs with L-shaped cross-sections and main spars through connectors, and a rigid skin fixedly connected to the outer surface of the frame. The rear end surface of the beam is fixedly connected to the flexible truss bearing units arranged at intervals, the piezoelectric drive unit is arranged between adjacent flexible truss bearing units, and the flexible skin is fixedly connected to the upper end of the flexible truss bearing unit. The invention optimizes the structure and installation position of the piezoelectric drive unit, makes the wing deformation more stable and diversified, and can adapt to various different flying environments.

Description

A variant wing based on piezoelectric drive

technical field

The invention relates to the technical field of variant wings of aviation aircraft, in particular to a variant wing based on piezoelectric drive.

Background technique

At present, the variant wings that have been applied to aircraft are mainly rigid variant wings that are driven by hydraulic devices and deformed by folding and stretching. As a brand-new functional material, piezoelectric material can control its deformation degree under the action of an electric field by using its inverse piezoelectric effect. There are some deficiencies.

1. The common rigid variant wing uses a hydraulic device to control the folding and stretching of the wing to change the shape of the aircraft, but this type of variant wing often has a complex mechanical structure, which greatly increases the wing volume and Mass, which affects the overall flight performance and stability of the aircraft.

2. Although the modified wings driven by shape memory materials that have been proposed so far can achieve the effect of wing thickness and inclination angle, the problem of slow response will make the wings unable to make timely changes according to the flying environment.

3. The modified wings driven by piezoelectric materials that have been proposed so far mainly combine the piezoelectric system directly with the wing skin to achieve the effect of changing the shape of the wing, but this type of deformed wing will cause piezoelectric The system is in direct contact with external loads during flight, which affects the driving effect and working environment of the piezoelectric system.

4. In addition, the small deformation range of the morphed wing driven by piezoelectric materials will lead to a decrease in the adaptability of the wing in various flight environments, which limits the degree and form of deformation of the morphed wing.

Piezoelectric materials are formed by polarization treatment, and have the advantages of heat resistance, moisture resistance, easy manufacture, and can be made into arbitrary shapes and polarization directions. When the piezoelectric material is subjected to force or other loads, charges will be generated on its surface; and when an electric field is applied to the surface of the piezoelectric material, it will be deformed, so the piezoelectric material has positive and negative piezoelectric effects. Due to the advantages of high measurement accuracy, fast response, and stable performance, piezoelectric materials have been widely used in aerospace, precision measurement, and smart structures.

Regarding the inverse piezoelectric effect: as shown in Figure 1, when an electric field force is applied to the upper and lower surfaces of the crystal of the piezoelectric material 03, the positive and negative charges inside the piezoelectric material 03 will undergo relative displacement under the action of the applied electric field. When the piezoelectric material 03 will produce a certain mechanical deformation, this phenomenon is called the inverse piezoelectric effect.

Regarding the distributed piezoelectric composite beam driver: as shown in Figure 2, the piezoelectric composite beam driver formed by pasting a plurality of piezoelectric sheets 06 symmetrically up and down on the base beam 07 not only has the advantages of piezoelectric materials, but also can improve The stability and bearing capacity of the structure, and the deformation is flexible and diverse. Under the action of the electric field, the piezoelectric sheet 06 drives the base beam 07 to deform, so as to meet the corresponding engineering requirements.

About the rhombus amplifier: currently commonly used amplification mechanisms mainly include bridge-type amplification mechanisms, lever-type amplification mechanisms and triangular amplification mechanisms. The diamond-shaped amplifiers involved in the present invention use triangular amplification mechanisms to ensure the magnification factor while reducing the occupied space. Figure 3 shows the schematic diagram of the triangular amplification of the rhombus amplifier. As shown in Figure 3, the rods hinged at the ends constitute a diamond-shaped amplifier in turn. The four rods of the diamond-shaped amplifier are rigid rods, and the deformation under the action of external force is ignored, that is, the length of the corresponding triangle hypotenuse remains unchanged. . Let the long side be a, the angle between it and the hypotenuse be θ, and the length of the short side be b. When the long right-angled side is extended by Δa, the short right-angled side is correspondingly shortened by Δb. When the hypotenuse is constant, there is an equation:

a ² +b ² =(a-Δa) ² +(b+Δb) ² (2)

Ignoring the two high-order infinitesimal quantities of Δa ² and Δb ² , the magnification can be obtained according to formula (2):

It can be seen from formula (3) that the magnification of the rhombus amplifier is related to the size of its acute angle, and has nothing to do with the length of the hypotenuse and the right-angled side. The smaller the acute angle, the greater the displacement magnification. According to this principle, the use of diamond-shaped amplifiers can not only convert lateral displacement into longitudinal displacement, but also effectively reduce the volume of the overall structure while ensuring the amplification of deformation.

Contents of the invention

In order to overcome the defects of the prior art, the present invention provides a modified wing based on piezoelectric drive. The modified wing involved in the present invention optimizes the structure of the piezoelectric drive unit and its installation position, so that the wing deforms More stable and diversified to adapt to different flight environments. When the piezoelectric drive unit is working, the deformation structure of the drive machine undergoes adaptive deformation, thereby achieving the effect of changing the thickness of the wing and its inclination angle.

For realizing the above object, technical scheme of the present invention is:

A modified wing based on piezoelectric drive, including a wing box with a D-shaped cross section and a deformation structure connected to the rear end of the wing box. The wing box includes a plurality of ribs with an L-shaped cross section, and the frame constructed by the main spar through connectors, and the rigid skin fixedly connected to the outer surface of the frame. The flexible truss bearing units, the piezoelectric drive unit arranged between adjacent flexible truss bearing units, and the flexible skin fixedly connected to the upper end of the flexible truss bearing units.

Preferably, the piezoelectric driving unit includes a first driving part and a second driving part, and the first driving part and the second driving part are arranged side by side on the rear side of the main spar, and the first driving part and the second driving part The bottom of the driving part is provided with a rigid bottom beam fixedly connected to the main wing beam at one end, and a base for installing the first driving part and the second driving part is respectively provided at the upper end of the rigid bottom beam, and the rigid bottom beam and the flexible truss The lower end of the bearing unit is fixedly connected with a rigid skin.

Preferably, the base is arranged along the horizontal direction, and the first driving part and the second driving part have the same structure, including two distributed piezoelectric piezoelectric devices whose bottom ends are fixedly connected to the upper surface of the base and arranged parallel to each other. A composite beam driver, an energy storage spring arranged between two distributed piezoelectric composite beam drivers and one end connected to the upper surface of the base, a rhombus amplifier arranged above the energy storage spring, a deformation transmission guide rod arranged above the rhombus amplifier, The lower end of the diamond-shaped amplifier is connected to the upper end of the energy storage spring, the upper end of the diamond-shaped amplifier is connected to the lower end of the deformation transmission guide rod, and the two ends of the rhomboid amplifier are respectively connected to the distributed piezoelectric composites on both sides through the connecting rod. The top of the beam driver is connected, the two ends of the connecting rod are respectively hinged with the diamond-shaped amplifier and the distributed piezoelectric composite beam driver, and the top ends of the deformation transmission guide rods of the first drive part and the second drive part are fixedly connected with A flexible beam, the front end of the flexible beam is fixedly connected to the rear end surface of the main spar, and the upper end of the flexible beam is against the lower surface of the flexible skin.

Preferably, the flexible truss bearing unit includes an upper arc bar, a lower arc bar, and a truss body connected between the upper arc bar and the lower arc bar, the rear end of the truss body is connected to the lower arc The rear ends of the shaped rods are flush, the length of the lower curved rods is less than the length of the upper curved rods, and rigid longitudinal beams are also connected between the rear ends of the lower curved rods of each flexible truss load-bearing unit. A corrugated flexible skin is also connected between the rear end of the upper arc-shaped rod of the flexible truss bearing unit and the rigid longitudinal beam.

Preferably, the rear end of the upper arc-shaped rod of each flexible truss bearing unit is provided with a tail wire pulley, and the rear end of the corrugated flexible skin is connected with the flexible skin through the tail wire pulley; the flexible The rear end of the beam is flush with the rear end of the upper arc rod, and a corrugated plate is also connected between the flexible beam rear end and the rigid longitudinal beam. Rigid stringers are fixedly connected.

Preferably, the rigid longitudinal beam is fixedly connected to the rigid bottom beam, and an auxiliary wing spar is arranged at the joint, the bottom end of the auxiliary wing beam is fixedly connected to the upper surface of the rigid longitudinal beam, and the top end is slidingly connected to the flexible beam , the upper part of the aileron spar is also provided with a restraint beam, the front end of the restraint beam is fixedly connected with the rear end face of the main spar, the rear end of the restraint beam is fixedly connected with the upper part of the aileron beam, and a A guide hole, a roller is fixedly installed in the guide hole, and the deformation transmission guide rod passes through the guide hole and is slidably connected with the roller.

Preferably, the top end of the deformation transmission guide rod is an arc-shaped surface, and the inside of the deformation transmission guide rod is a hollow structure.

Preferably, the lower end surface of the rigid bottom beam is arc-shaped, the first driving part is located on the front side of the second driving part, and when the diamond-shaped amplifier is stretched, the top end of the deformation transmission guide rod of the first driving part The height is greater than the height of the top end of the deformation transmission guide rod of the second driving part.

Preferably, the constraint beam is a "Z"-shaped structure, and the height of the base of the second driving part is higher than that of the base of the first driving part.

A modified wing based on piezoelectric drive of the present invention has the following beneficial effects:

1. Through the improvement of the deformation structure, the present invention promotes the deformation of the wing through the piezoelectric drive unit arranged inside the deformation structure, effectively avoiding the large load and the large load caused by the combination of the piezoelectric system and the flexible skin in the prior art. The defect of poor driving effect has a sensitive deformation function, and the service life of the piezoelectric drive unit is long;

2. The mechanical structure of the present invention is simple and the driving effect is good. Through the coarse adjustment of the first driving part and the fine adjustment of the second driving part, the shape of the deformed structure can maintain the airflow shape of the wing, which can fully meet the deformation needs of the aircraft wing ;

3. The invention makes full use of the inverse piezoelectric effect. When the deformation of the driving deformation structure is carried out, the various parts cooperate with each other, and the response speed is fast, which can fully meet the needs of the aircraft to quickly adjust the shape of the wing during flight, and can make the wing adapt to the flight environment. Make adaptive changes in a timely manner;

4. The present invention overcomes the defect that the deformation range of the variant wing driven by piezoelectric materials is small, and through the mutual cooperation of the diamond-shaped amplifier, the distributed piezoelectric composite beam driver, and the deformation transmission guide rod, the deformation of the wing The range can be adapted to various flight environments, effectively improving the adaptive ability of the variant wing.

Description of drawings

Figure 1 is a schematic diagram of the inverse piezoelectric effect;

Fig. 2 is a model diagram of a distributed piezoelectric composite beam driver;

Fig. 3 is the triangular amplification principle of rhombus amplifier;

Fig. 4 is a three-dimensional model diagram of a variant wing;

Fig. 5 is a structural model diagram of a piezoelectric drive unit;

Fig. 6 is a state diagram of the drive unit in the initial state;

Fig. 7 is a state diagram of the driving part after the deformation of the lower drive;

Fig. 8 is a state diagram of the driving part after the deformation of the upper drive;

Fig. 9 shows the displacement changes and stress states of each node during the drive down process;

Figure 10 shows the displacement changes and stress states of each node during the updrive process;

Figure 11 is a schematic diagram of energy conversion during deformation;

01: Initial state, 02: Deformed state, 03: Piezoelectric material, 04: Piezoelectric action area, 05: Bare beam area, 06: Piezoelectric sheet, 07: Substrate beam, 08: Wing box, 09: Deformed structure ;1: rigid skin, 2: main spar, 3: rib, 4: flexible truss bearing unit, 5: piezoelectric drive unit, 6: flexible skin, 7: corrugated flexible skin, 8: rigid stringer; 41: upper arc rod, 42: lower arc rod, 43: truss body, 501: distributed piezoelectric composite beam driver in the first driving part, 502: energy storage spring in the first driving part, 503: the first Diamond-shaped amplifier in the first driving part, 504: deformation transmission guide rod in the first driving part, 511: base beam in the second driving part, 512: energy storage spring in the second driving part, 513: second driving part Diamond-shaped amplifier in, 514: deformation transfer guide rod in the second driving part, 531: constraining beam, 532: roller, 533: flexible beam, 534: base, 535: rigid bottom beam, 536: corrugated plate, 537: vice Spar, 538: tail wire pulley, 539: connecting rod.

Detailed ways

The following is a detailed description of the implementation of the present invention in a step-by-step manner. This description is only a preferred embodiment of the present invention, and is not used to limit the scope of protection of the present invention. Where the spirit and principles of the present invention Any amendments, equivalent replacements and improvements made within shall be included within the protection scope of the present invention.

In the description of the present invention, it should be noted that the orientations or positional relationships indicated by the terms "upper", "lower", "left", "right", "top", "bottom", "inner" and "outer" are based on those shown in the accompanying drawings. Orientation or positional relationship is only for describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, as well as a specific orientation configuration and operation, so it should not be construed as a limitation of the present invention.

In one embodiment, a modified wing based on piezoelectric drive, as shown in FIG. The wing box includes a frame constructed of multiple ribs 3 with L-shaped cross-sections and main spars 2 through connectors, and a rigid skin 1 fixedly connected to the outer surface of the frame. The wing box 08 has shear and compression resistance. performance, which plays the role of dividing the airflow and ensuring the stability of the overall structure of the wing during the flight of the aircraft; the deformed structure is located on the rear side of the main spar 2, and includes a plurality of fixedly connected and spaced rear end faces of the main spar 2 The flexible truss bearing unit 4, the piezoelectric drive unit 5 arranged between adjacent flexible truss bearing units 4, and the flexible skin 6 fixedly connected to the upper end of the flexible truss bearing unit 4; the flexible truss bearing unit 4 can be deformed The flexible skin 6 plays a bearing role, and the piezoelectric driving unit 5 can drive the flexible skin 6 to deform, and the deformed flexible skin 6 can drive the deformation of the flexible truss bearing unit 4; it should be noted that the flexible truss bearing unit 4 It takes a certain amount of load to change the original shape until the deformation stops after adapting to the load. The shape after each deformation has a certain bearing capacity. When the load continues to change beyond its bearing capacity, its structure continues to change. Seek a stable configuration that accommodates the load.

In a further embodiment, as shown in Figures 4 and 5, the piezoelectric drive unit includes a first drive part and a second drive part, and the first drive part and the second drive part are arranged side by side on the main spar 2, at the bottom of the first driving part and the second driving part, a rigid bottom beam 535 with one end fixedly connected to the main spar 2 is provided, and the upper end of the rigid bottom beam 535 is respectively provided with the first driving part and the second driving part. The base 534 of the two driving parts, the rigid bottom beam 535, and the lower end of the flexible truss bearing unit 4 are fixedly connected with the rigid skin 1; by installing the first driving part and the second driving part in the lower part of the deformation structure, It can avoid the direct action of the piezoelectric material on the flexible skin 6, so that the piezoelectric drive unit 5 can be separated from the external load (that is, the reaction force of the piezoelectric system after the deformation of the skin, the prior art is to directly connect the piezoelectric system with the wing cover skin combination to achieve the effect of changing the shape of the wing, but this type of deformed wing will cause the piezoelectric system to be in direct contact with the external load during flight, and the working environment of the piezoelectric system is poor, which will affect the driving effect of the piezoelectric system) , maintain the driving sensitivity, and prolong the service life of the piezoelectric driving unit 5 .

In a further embodiment, as shown in Figures 4 and 5, the base 1 is arranged along the horizontal direction, and the first driving part and the second driving part have the same structure, including the bottom end and the upper surface of the base 534 Two distributed piezoelectric composite beam drivers 501\511 fixedly connected and arranged parallel to each other, and an energy storage spring 502 arranged between the two distributed piezoelectric composite beam drivers 501\511 and connected to the upper surface of the base 534 at one end \512, the rhombus amplifier 503\513 that is arranged on the top of the energy storage spring, the deformation transmission guide rod 504\514 that is arranged on the top of the rhombus amplifier, the lower end of the rhombus amplifier is connected with the upper end of the energy storage spring, and the upper end of the rhombus amplifier is connected with the upper end of the energy storage spring The lower end of the deformation transfer guide rod is connected, and the two ends of the diamond amplifier are respectively connected to the top ends of the distributed piezoelectric composite beam drivers on both sides through the connecting rod 539, and the two ends of the connecting rod 539 are respectively connected to the diamond amplifier. , and the distributed piezoelectric composite beam driver is hinged, and the top of the deformation transmission guide rod of the first driving part and the second driving part is fixedly connected with a flexible beam 533, and the front end of the flexible beam 533 is connected to the rear end surface of the main spar Fixed connection, the upper end of the flexible beam 533 is against the lower surface of the flexible skin 6; in the deformation process, the flexible skin 6 is supported by the flexible beam 533 to deform, and the flexible beam 533 is in the process of abutting against the flexible skin 6 It can be slid relative to meet the needs of the deformed structure; as can be seen from Figure 5, although the two structures are the same, there is a large difference in the size of the first driving part and the second driving part, which are used for the large-scale deformation of the deformed structure. Deformation and small deformation, similar to coarse adjustment and fine adjustment, can make the flexible beam transition smoothly in an arc shape, thereby ensuring the overall airflow shape of the wing.

In a further embodiment, as shown in FIG. 4 , the flexible truss bearing unit 4 includes an upper arc-shaped rod 41, a lower arc-shaped rod 42, and The truss main body 43, the rear end of the truss main body is flush with the rear end of the lower arc bar 42, the length of the lower arc bar 42 is less than the length of the upper arc bar 41, and each flexible truss bearing unit Rigid longitudinal beams 8 are also connected between the rear ends of the lower arc-shaped bars of 4, and corrugated flexible skins 7 are also connected between the rear ends of the upper arc-shaped bars of each flexible truss bearing unit 4 and the rigid longitudinal beams.

In a further embodiment, as shown in Figures 4 and 5, the rear ends of the upper arc-shaped rods of each of the flexible truss bearing units 4 are provided with tail wire pulleys 538, and the rear ends of the corrugated flexible skins 7 are The end is connected with the flexible skin 6 through the tail wire pulley 538; the rear end of the flexible beam 533 is flush with the rear end of the upper arc bar 41, and is also connected between the flexible beam 533 rear end and the rigid longitudinal beam 8 There is a corrugated plate 536, the upper end of the corrugated plate 536 is connected with the end of the flexible beam through the tail wire pulley 538, and the lower end is fixedly connected with the rigid longitudinal beam 8; 7 plays a load-bearing role; and the rear end of the corrugated flexible skin 7 is connected with the flexible skin 6 through the tail wire pulley 538, and the deformation can be transmitted by sliding. Both are in a tight state initially, and the flexible skin 6 During deformation, the corrugated flexible skin 7 will undergo adaptive deformation.

In a further embodiment, as shown in Figures 4 and 5, the rigid longitudinal beam 8 is fixedly connected to the rigid bottom beam 535, and an auxiliary wing beam 537 is also provided at the connection, and the bottom end of the auxiliary wing beam 537 It is fixedly connected with the upper surface of the rigid longitudinal beam 8, and the top end is slidably connected with the flexible beam 533. A constraining beam 531 is also provided on the upper part of the auxiliary spar. The front end of the constraining beam 531 is fixedly connected with the rear end surface of the main spar. The rear end of the beam 531 is fixedly connected to the upper part of the auxiliary wing beam 537, and a guide hole is opened on the constraint beam 531, and a roller 532 is fixedly installed in the guide hole, and the deformation transmission guide rod 504\514 passes through The guide hole is also slidingly connected with the roller 532; as can be seen from Figure 5, the roller 532 is distributed along the axial direction of the guide hole and the inner surface of the side wall of the guide hole can be surrounded by a plurality of rollers 532 on the inner wall surface of the guide hole, and set Multiple sets of such rollers 532 ensure the smooth sliding of the deformation transmission guide rods 504\514 while maintaining the stability of the transmission direction.

In a further embodiment, as shown in FIG. 5, the top end of the deformation transmission guide rod 504; 514 is an arc surface, and the inside of the deformation transmission guide rod is a hollow structure; Good cooperation enables the gentle transmission of the extrusion force of the deformation transmission guide rod to the flexible skin 6, and facilitates the sliding of the flexible skin 6 relative to the top end of the deformation transmission guide rod during transmission.

In a further embodiment, as shown in FIGS. 4 and 5 , the lower end surface of the rigid bottom beam 535 is arc-shaped, and the first driving part is located on the front side of the second driving part, and the diamond-shaped amplifier extends , the height of the top end of the deformation transmission guide rod 504 of the first drive part is greater than the height of the top end of the deformation transmission guide rod 514 of the second drive part; as can be seen from Figure 5, the size of the first drive part is larger than that of the second drive part, and its The distributed piezoelectric composite beam driver has a longer length and can distribute more piezoelectric sheets, which are responsible for driving deformation at key locations.

In a further embodiment, as shown in the figure, the constraining beam 531 is in a "Z" shape, and the height of the base of the second driving part is higher than that of the base of the first driving part.

In the present invention, the flexible materials involved include the flexible beam 533 and the corrugated plate 536. The composite material composed of reinforcing material and polymer material, such as the composite material composed of epoxy resin and carbon fiber, the flexible skin 6 and the corrugated flexible skin 7 Rubber materials are used. The piezoelectric sheet in the distributed piezoelectric composite beam driver uses piezoelectric materials with high power conversion efficiency, such as the commonly used lead zirconate titanate material, while other components in the distributed piezoelectric composite beam driver You can choose commonly used aviation lightweight materials.

Principle of use of the present invention:

Taking the first driving part as an example, the initial state of the driving structure is shown in Figure 6. At this time, the energy storage spring is in a stretched state, and the vertex angle of the diamond-shaped displacement amplifier is an acute angle. The distributed piezoelectric composite beam driver has no external electric load In the case of keeping the vertical state, the flexible beam is in a tight state.

When an electric field is applied on both sides of the piezoelectric sheet to drive the flexible skin 6 on the top of the wing to move downward, positive charges need to be applied to the bare surface of the piezoelectric sheet of the distributed piezoelectric composite beam driver on the right side (that is, the piezoelectric sheet and the air on the contact surface of the piezoelectric composite beam), and apply the negative charge to the contact surface of the piezoelectric sheet and the substrate beam, and at the same time, apply the negative charge to the bare surface of the piezoelectric sheet on the left distributed piezoelectric composite beam driver, and put the A positive charge is applied to the contact surface between the piezoelectric sheet and the substrate beam, as shown in Figure 7. At this time, the two distributed piezoelectric composite beam drivers bend outwards, causing the transverse diagonal of the diamond-shaped displacement amplifier to increase, and the longitudinal direction of the beam to increase. The angle line decreases, the deformation transfer guide rod moves downward, the flexible beam releases the deformation energy in the tight state and then falls naturally, and the energy storage spring continues to pull upward. The displacement change and stress state of the entire deformation process are shown in Figure 9.

When an electric field is applied on both sides of the piezoelectric sheet to drive the flexible skin 6 on the top of the wing to move upward, it is necessary to apply negative charges to the bare surface of the piezoelectric sheet on the right distributed piezoelectric composite beam driver, and apply positive charges To the contact surface of the piezoelectric sheet and the substrate beam, at the same time, apply positive charges to the bare surface of the piezoelectric sheet on the left distributed piezoelectric composite beam driver, and apply negative charges to the piezoelectric sheet and the substrate beam , as shown in Figure 8, at this time, the two piezoelectric composite beam drivers bend inwards, causing the rhombus amplifier’s horizontal diagonal to decrease and the vertical diagonal to increase, and the guide rod moves upward, driving the flexible The beam 533 is deformed upwards, and the energy storage spring moves downwards to release the elastic potential energy to facilitate the deformation. The displacement changes and stress states during the entire deformation process are shown in FIG. 10 . It is worth noting that when an electric field is applied on both sides of the piezoelectric sheet, although the direction of the voltage is different due to the different direction of motion, the absolute value of the voltage is equal to ensure that they can bend synchronously and avoid damage to the guide rod.

Figure 11 shows the energy conversion during wing deformation, in addition to the energy loss during the deformation process, the positive work done by the distributed piezoelectric composite beam driver under the voltage and the flexible beam falling during the downward driving process Most of the deformation energy lost at the time is converted into the elastic potential energy of the energy storage spring; in the upward driving process, the positive work done by the distributed piezoelectric composite beam driver at the voltage and the elastic potential lost by the shortening of the energy storage spring are mostly converted into the wing The deformation energy of the skin.

For the piezoelectric drive system as a whole, the joint action of the first drive part and the second drive part can promote the smoothness, stability and diversification of the deformation of the flexible structure, so as to adapt to different flight environments. On the other hand, for the modified wing as a whole, under the joint action of the piezoelectric drive system, flexible skin 6 and corrugated flexible skin 7, the flexible truss bearing system can adaptively adjust its own structure according to the load change, and After adjusting and stabilizing, it provides a certain load-bearing effect for the skin. When the top flexible skin 6 changes, the corrugated flexible skin 7 can be expanded and contracted, and the two work together to make the deformation of the wing more smooth, stable and easy to change.

Claims (7)

1. A variant wing based on piezoelectric drive, characterized in that: it comprises a D-shaped wing box and a deformation structure connected to the rear end of the wing box, and the wing box includes a plurality of sections It is a frame constructed of L-shaped ribs and main spars through connectors, and a rigid skin fixedly connected to the outer surface of the frame. The deformation structure is located on the rear side of the main spar, including multiple The flexible truss bearing units fixedly connected and arranged at intervals, the piezoelectric drive unit arranged between adjacent flexible truss bearing units, and the flexible skin fixedly connected to the upper end of the flexible truss bearing units; The piezoelectric driving unit includes a first driving part and a second driving part, and the first driving part and the second driving part are arranged side by side on the rear side of the main spar, and between the first driving part and the second driving part The bottom is provided with a rigid bottom beam fixedly connected to the main wing beam at one end, and bases for installing the first driving part and the second driving part are respectively provided at the upper end of the rigid bottom beam, and the rigid bottom beam and the flexible truss bearing unit The lower end is fixedly connected with a rigid skin; The base is arranged along the horizontal direction, and the first driving part and the second driving part have the same structure, including two distributed piezoelectric composite beam drivers whose bottom ends are fixedly connected to the upper surface of the base and arranged parallel to each other. , an energy storage spring arranged between two distributed piezoelectric composite beam drivers and one end connected to the upper surface of the base, a rhombus amplifier arranged above the energy storage spring, and a deformation transmission guide rod arranged above the rhombus amplifier, said The lower end of the diamond-shaped amplifier is connected to the upper end of the energy storage spring, and the upper end of the diamond-shaped amplifier is connected to the lower end of the deformation transmission guide rod. The top end is connected, the two ends of the connecting rod are respectively hinged with the diamond-shaped amplifier and the distributed piezoelectric composite beam driver, and the top ends of the deformation transmission guide rods of the first driving part and the second driving part are fixedly connected with flexible beams, The front end of the flexible beam is fixedly connected to the rear end surface of the main spar, and the upper end of the flexible beam is against the lower surface of the flexible skin. 2. A modified wing based on piezoelectric drive according to claim 1, characterized in that: said flexible truss bearing unit includes an upper arc-shaped rod, a lower arc-shaped rod, and a , the truss main body between the lower arc bars, the rear end of the truss main body is flush with the rear end of the lower arc bars, the length of the lower arc bars is less than the length of the upper arc bars, and each flexible A rigid longitudinal beam is also connected between the rear ends of the lower arc-shaped rods of the truss bearing units, and a corrugated flexible skin is also connected between the rear ends of the upper arc-shaped rods of each flexible truss bearing unit and the rigid longitudinal beams. 3. A modified wing based on piezoelectric drive as claimed in claim 2, characterized in that: the rear ends of the upper arc-shaped rods of each of the flexible truss bearing units are provided with tail pulleys, and the The rear end of the corrugated flexible skin is connected to the flexible skin through a tail wire pulley; the rear end of the flexible beam is flush with the rear end of the upper arc rod, and a The corrugated plate, the upper end of the corrugated plate is connected to the end of the flexible beam through a tail wire pulley, and the lower end is fixedly connected to the rigid longitudinal beam. 4. A modified wing based on piezoelectric drive as claimed in claim 2 or 3, characterized in that: the rigid longitudinal beam is fixedly connected to the rigid bottom beam, and an aileron spar is also provided at the joint, The bottom end of the aileron spar is fixedly connected to the upper surface of the rigid longitudinal beam, and the top end is slidably connected to the flexible beam. A constraining beam is also arranged on the upper part of the aileron spar. The front end of the constraining beam is connected to the rear end surface of the main spar. Fixed connection, the rear end of the constraining beam is fixedly connected with the upper part of the aileron beam, and a guide hole is opened on the constraining beam, and a roller is fixedly installed in the guide hole, and the deformation transmission guide rod passes through the guide hole and Sliding connection with rollers. 5. A modified wing based on piezoelectric drive according to claim 1, 2 or 3, characterized in that: the top end of the deformation transmission guide rod is an arc-shaped surface, and the inside of the deformation transmission guide rod It is a hollow structure. 6. A modified wing based on piezoelectric drive according to claim 1, 2 or 3, characterized in that: the lower end surface of the rigid bottom beam is arc-shaped, and the first driving part is located at The front side of the second driving part, and when the diamond-shaped amplifier is stretched, the height of the top end of the deformation transmission guide rod of the first driving part is greater than the height of the top end of the deformation transmission guide rod of the second drive part. 7. A modified wing based on piezoelectric drive according to claim 4, characterized in that: the restraining beam is a "Z" shape structure, and the height of the base of the second driving part is higher than that of the first The height of the base of the drive unit.

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