CN112109877A - Novel morphing wing based on piezoelectric drive - Google Patents
Novel morphing wing based on piezoelectric drive Download PDFInfo
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- CN112109877A CN112109877A CN202011001383.6A CN202011001383A CN112109877A CN 112109877 A CN112109877 A CN 112109877A CN 202011001383 A CN202011001383 A CN 202011001383A CN 112109877 A CN112109877 A CN 112109877A
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- B64—AIRCRAFT; AVIATION; COSMONAUTICS
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- B64C3/38—Adjustment of complete wings or parts thereof
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Abstract
The utility model provides a novel morphing wing based on piezoelectricity drive, relates to aviation aircraft morphing wing technical field, is the wing box of D shape and connects in the deformation structure of wing box rear end including the cross-section, the wing box include the frame that the rib and the main wing spar that are the L shape by many cross-sections build through the connecting piece to and fixed connection is in the rigid skin of frame surface, deformation structure be located the rear side of main wing spar, including a plurality of flexible truss bearing unit that set up with the rear end face fixed connection of main wing spar and interval, set up the piezoelectricity drive unit between adjacent flexible truss bearing unit and fixed connection in the flexible skin of flexible truss bearing unit upper end. The invention optimizes the structure and the installation position of the piezoelectric driving system, and leads the wing deformation to be more stable and diversified so as to adapt to different flight environments.
Description
Technical Field
The invention relates to the technical field of aerocraft morphing wings, in particular to a novel morphing wing based on piezoelectric drive.
Background
At present, the morphing wings that have been applied to aircraft are mainly rigid morphing wings driven by hydraulic means, in the form of folding-unfolding deformations. The piezoelectric material is used as a brand new functional material, the inverse piezoelectric effect of the piezoelectric material is utilized, the deformation degree of the piezoelectric material can be controlled under the action of an electric field, and the piezoelectric material is also applied to a certain extent in the aspect of a morphing wing, but the piezoelectric material has some defects in the utilization at present.
1. Common rigid morphing wings control the folding and stretching of the wings by using hydraulic devices to change the shape of the airplane, but the morphing wings of the type often have complicated mechanical structures, greatly increase the volume and the mass of the wings and influence the overall flight performance and the stability of the airplane.
2. The variant wing driven by the shape memory material which is proposed at present can achieve the effects of wing thickness and inclination angle, but the problem of slow response can cause that the wing can not change in time according to the flight environment.
3. The morphing wing driven by piezoelectric materials is mainly characterized in that a piezoelectric system is directly combined with a wing skin to achieve the effect of changing the shape of the wing, but the morphing wing can cause the piezoelectric system to be directly contacted with external loads in the flying process to influence the driving effect and the working environment of the piezoelectric system.
4. In addition, the problem of small deformation amplitude of the morphing wing driven by the piezoelectric material can cause the self-adaptability of the wing to be reduced under various flight environment conditions, and the deformation degree and the deformation form of the morphing wing are limited.
The piezoelectric material is formed by polarization treatment, and has advantages of heat resistance, moisture resistance, easy manufacture, and capability of being made into any shape and polarization direction. When a piezoelectric material is subjected to a force or other load, it will develop an electrical charge on its surface; on the other hand, when an electric field is applied to the surface of the piezoelectric material, the piezoelectric material is deformed, and therefore, the piezoelectric material has a positive and negative piezoelectric effect. Due to the advantages of high measurement precision, high response speed, stable performance and the like, the piezoelectric material is widely applied to the fields of aerospace, precision measurement, intelligent structures and the like.
Regarding the inverse piezoelectric effect: as shown in fig. 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 are relatively displaced by the applied electric field, and the piezoelectric material 03 is mechanically deformed to a certain extent, which is called a reverse piezoelectric effect.
With respect to distributed piezoelectric composite beam drivers: as shown in fig. 2, the piezoelectric composite beam actuator formed by attaching a plurality of piezoelectric sheets 06 to a base beam 07 in an up-down symmetrical manner has advantages of piezoelectric materials, can improve structural stability and load-bearing capacity, and can be flexibly deformed. Under the action of an electric field, the piezoelectric sheet 06 drives the matrix beam 07 to deform, so that corresponding engineering requirements are met.
With regard to the diamond amplifier: the diamond amplifier adopts a triangular amplifying mechanism, and aims to ensure the amplification factor on the premise of reducing the occupied space. Fig. 3 shows a triangular amplification schematic diagram of a diamond amplifier. As shown in fig. 3, the rhombic amplifiers are formed by the rod pieces hinged at the end parts in sequence, and the four rod pieces of the rhombic amplifiers adopt rigid rod pieces, so that the deformation under the action of external force is ignored, namely the lengths of the bevel edges of the corresponding triangles are not changed. Let the long right-angle side be a, the included angle between it and the hypotenuse be theta, and the short right-angle side be b. When the long right-angle side is extended by Δ a and the short right-angle side is correspondingly shortened by Δ b, in the case of constant hypotenuse, there is the equation:
a2+b2＝(a-Δa)2+(b+Δb)2 (2)
neglecting Δ a2And Δ b2Two high order infinitesimal quantities, the magnification can be obtained according to equation (2):
from equation (3), it can be seen that the amplification of the diamond amplifier is related to the size of the acute angle, and the displacement amplification is larger as the acute angle is smaller, regardless of the length of the hypotenuse and the right-angle side. According to the principle, the diamond amplifier is utilized to ensure the amplification deformation, and simultaneously, the transverse displacement can be converted into the longitudinal displacement, and the volume of the whole structure can be effectively reduced.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a novel morphing wing based on piezoelectric drive, and the morphing wing optimizes the structure and the installation position of a piezoelectric drive unit, so that the wing deformation is more stable and diversified to adapt to different flight environments. When the piezoelectric driving unit works, the deformation structure of the driving machine is deformed in a self-adaptive manner, so that the thickness and the inclination angle of the wing are changed.
In order to achieve the purpose, the technical scheme of the invention is as follows:
the utility model provides a novel morphing wing based on piezoelectricity drive, includes that the cross-section is the wing box of D shape and connects in the deformation structure of wing box rear end, the wing box include the frame that is built for the rib of L shape, reaches the main wing spar through the connecting piece by many cross-sections to and fixed connection is in the rigid skin of frame surface, deformation structure be located the rear side of main wing spar, including a plurality of flexible truss that set up with the rear end face fixed connection of main wing spar and interval bear the weight of the unit, set up in the piezoelectricity drive unit between adjacent flexible truss bearing the weight of the unit and fixed connection in the flexible skin of flexible truss bearing the weight of the unit upper end.
Preferably, the piezoelectric driving unit includes a first driving portion and a second driving portion, the first driving portion and the second driving portion are arranged at the rear side of the main wing beam side by side, a rigid bottom beam having one end fixedly connected with the main wing beam is arranged at the bottom of the first driving portion and the bottom of the second driving portion, a base for mounting the first driving portion and the second driving portion is respectively arranged at the upper end of the rigid bottom beam, and a rigid skin is fixedly connected to the lower ends of the rigid bottom beam and the flexible truss bearing unit.
Preferably, the base is arranged along the horizontal direction, the first driving part and the second driving part have the same structure and comprise 2 distributed piezoelectric composite beam drivers, an energy storage spring, a diamond amplifier and a deformation transmission guide rod, wherein the bottom end of each distributed piezoelectric composite beam driver is fixedly connected with the upper surface of the base and is arranged in parallel, the energy storage spring is arranged between the 2 distributed piezoelectric composite beam drivers, one end of each energy storage spring is connected with the upper surface of the base, the diamond amplifier is arranged above the energy storage spring, the deformation transmission guide rod is arranged above the diamond amplifier, the lower end of the diamond amplifier is connected with the upper end of the energy storage spring, the upper end of the diamond amplifier is connected with the lower end of the deformation transmission guide rod, two side ends of the diamond amplifier are respectively connected with the top ends of the distributed piezoelectric composite beam drivers on two sides through connecting rods, and two ends of each connecting, the top ends of the deformation transmission guide rods of the first driving part and the second driving part are fixedly connected with a flexible beam, the front end of the flexible beam is fixedly connected with the rear end face of the main wing beam, and the upper end of the flexible beam abuts against the lower surface of the flexible skin.
Preferably, flexible truss bearing unit include arc pole, lower arc pole and connect the truss main part between last arc pole, lower arc pole, the rear end of truss main part flush with the rear end of arc pole down, the length of arc pole be less than the length of last arc pole down, still be connected with the rigidity longeron between the rear end of each flexible truss bearing unit's lower arc pole, still be connected with the flexible skin of corrugate between the rear end of last arc pole of each flexible truss bearing unit and the rigidity longeron.
Preferably, the rear end of the upper arc-shaped rod of each flexible truss bearing unit is provided with a tail line pulley, and the rear end of the corrugated flexible skin is connected with the flexible skin through the tail line pulley; the rear end of flexible roof beam and the rear end of last arc pole flush, and still be connected with the buckled plate between flexible roof beam rear end and rigidity longeron, buckled plate upper end and flexible roof beam tip pass through the tail wire pulley and be connected, lower extreme and rigidity longeron fixed connection.
Preferably, the rigid longitudinal beam is fixedly connected with the rigid bottom beam, a secondary wing beam is further arranged at the joint, the bottom end of the secondary wing beam is fixedly connected with the upper surface of the rigid longitudinal beam, the top end of the secondary wing beam is slidably connected with the flexible beam, a restraint cross beam is further arranged on the upper portion of the secondary wing beam, the front end of the restraint cross beam is fixedly connected with the rear end face of the main wing beam, the rear end of the restraint cross beam is fixedly connected with the upper portion of the secondary wing beam, a guide hole is further formed in the restraint cross beam, a roller is fixedly mounted in the guide hole, and the deformation transmission guide rod penetrates 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 of a hollow structure.
Preferably, the lower end surface of the rigid bottom beam is arc-shaped, the first driving part is positioned on the front side of the second driving part, and the height of the top end of the deformation transmission guide rod of the first driving part is greater than that of the top end of the deformation transmission guide rod of the second driving part when the diamond amplifier is extended.
Preferably, the restraining beam is of 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.
The novel morphing wing based on piezoelectric drive has the following beneficial effects:
1. according to the invention, through the improvement of the deformation structure, the deformation of the wing is promoted through the piezoelectric driving unit arranged in the deformation structure, the defects of large load and poor driving effect caused by the combination of a piezoelectric system and a flexible skin in the prior art are effectively avoided, the flexible wing has a sensitive deformation function, and the service life of the piezoelectric driving unit is long;
2. the mechanical structure of the invention is simple, the driving effect is good, the shape of the deformation structure can keep the airflow shape of the wing through the rough adjustment of the first driving part and the fine adjustment of the second driving part, and the deformation requirement of the aircraft wing can be fully met;
3. according to the invention, the inverse piezoelectric effect is fully utilized, when the deformation structure is driven to deform, all parts are mutually matched, the response speed is high, the requirement of quickly adjusting the shape of the wing of the aircraft in the flight process can be fully met, and the wing can be timely adaptively changed according to the flight environment;
4. the invention overcomes the defect of small deformation amplitude of the conventional morphing wing driven by piezoelectric materials, and the deformation amplitude of the wing can be adapted to various flight environments by the mutual matching of the diamond amplifier, the distributed piezoelectric composite beam driver and the deformation transmission guide rod, thereby effectively improving the self-adaptive capacity of the morphing wing.
Drawings
FIG. 1 is a schematic diagram of the inverse piezoelectric effect;
FIG. 2 is a diagram of a distributed piezoelectric composite beam driver model;
FIG. 3 is a triangular amplification principle of a diamond amplifier;
FIG. 4 is a three-dimensional model diagram of a novel morphing wing;
FIG. 5 is a structural model diagram of a piezoelectric driving unit;
FIG. 6 is a state diagram of a driving part in an initial state;
FIG. 7 is a state diagram of the drive section after deformation of the underdrive;
FIG. 8 is a state diagram of the drive section after deformation of the upper drive;
FIG. 9 shows the displacement change and stress state of each node during the driving-down process;
FIG. 10 shows the displacement change and stress state of each node during the up-drive process;
FIG. 11 is a schematic diagram of energy conversion during deformation;
01: initial state, 02: deformation state, 03: piezoelectric material, 04: piezoelectric region of action, 05: bare beam region, 06: piezoelectric sheet, 07: base beam, 08: wing box, 09: a deformed configuration; 1: rigid skin, 2: main spar, 3: rib, 4: flexible truss load-bearing unit, 5: piezoelectric driving unit, 6: flexible skin, 7: corrugated flexible skin, 8: a rigid stringer; 41: upper arc-shaped rod, 42: lower arc-shaped rod, 43: truss main body, 501: distributed piezoelectric composite beam driver in first driving section, 502: energy storage spring in first drive portion, 503: diamond amplifier in first driving section, 504: deformation transmission guide in first drive portion, 511: base beam in second drive portion, 512: energy storage spring in second drive portion, 513: diamond amplifier in second drive section, 514: deformation transmission guide in the second driving portion, 531: restraint beam, 532: roller, 533: flexible beam, 534: base, 535: rigid bottom beam, 536: corrugated plate, 537: secondary spar, 538: tail pulley, 539: a connecting rod.
Detailed Description
In the following, embodiments of the present invention are described in detail in a stepwise manner, which is merely a preferred embodiment of the present invention and is not intended to limit the scope of the present invention, and any modifications, equivalents, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.
In the description of the present invention, it should be noted that the terms "upper", "lower", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations and positional relationships based on the orientations and positional relationships shown in the drawings, and are only used for describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation and a specific orientation configuration and operation, and thus, the present invention is not to be construed as being limited thereto.
In one embodiment, a novel morphing wing based on piezoelectric drive, as shown in fig. 4, includes a wing box 08 with a D-shaped cross section, and a morphing structure 09 connected to the rear end of the wing box 08, where the wing box includes a frame built by a plurality of ribs 3 with an L-shaped cross section and a main wing spar 2 through connectors, and a rigid skin 1 fixedly connected to the outer surface of the frame, and the wing box 08 has shear resistance and compression resistance, and plays a role in dividing airflow and ensuring the stability of the overall structure of the wing during the flight of an aircraft; the deformation structure is positioned at the rear side of the main wing beam 2 and comprises a plurality of flexible truss bearing units 4 which are fixedly connected with the rear end face of the main wing beam 2 and are arranged at intervals, piezoelectric driving units 5 arranged between the adjacent flexible truss bearing units 4 and flexible skins 6 fixedly connected to the upper ends of the flexible truss bearing units 4; the flexible truss bearing unit 4 can bear the deformed flexible skin 6, the piezoelectric driving unit 5 can drive the flexible skin 6 to deform, and the deformed flexible skin 6 can drive the flexible truss bearing unit 4 to deform; it should be noted that the flexible truss bearing unit 4 needs a certain load to change its original shape until it stops deforming after adapting to the load, and the shape after each deformation has a certain bearing capacity, and when the load is continuously changed to be greater than its bearing capacity, its structure is continuously changed to seek the stable form adapted to the load.
In a further embodiment, as shown in fig. 4 and 5, the piezoelectric driving unit includes a first driving portion and a second driving portion, the first driving portion and the second driving portion are arranged side by side at the rear side of the main spar 2, a rigid bottom beam 535 with one end fixedly connected with the main spar 2 is arranged at the bottom of the first driving portion and the second driving portion, a base 534 for installing the first driving portion and the second driving portion is respectively arranged at the upper end of the rigid bottom beam 535, and a rigid skin 1 is fixedly connected to the lower ends of the rigid bottom beam 535 and the flexible truss carrying unit 4; through installing first drive division and second drive division in the lower part in the deformation structure, can avoid piezoelectric material direct action to flexible skin 6, make piezoelectric drive unit 5 can break away from external load (promptly the skin warp the back to piezoelectric system's reaction force, prior art is with piezoelectric system direct and wing skin combination reach the effect of changing the wing shape, but this type of deformation body wing can cause piezoelectric system and external load direct contact in flight process, piezoelectric system's operational environment is poor, influences piezoelectric system's drive effect), keep drive sensitivity, extension piezoelectric drive unit 5's life.
In a further embodiment, as shown in fig. 4 and 5, the base 1 is arranged along the horizontal direction, the first driving portion and the second driving portion have the same structure, and include 2 distributed piezoelectric composite beam drivers 501\511 whose bottom ends are fixedly connected with the upper surface of the base 534 and which are arranged in parallel, an energy storage spring 502\512 arranged between the 2 distributed piezoelectric composite beam drivers 501\511 and having one end connected with the upper surface of the base 534, a diamond amplifier 503\513 arranged above the energy storage spring, and a deformation transmission guide rod 504\514 arranged above the diamond amplifier, the lower end of the diamond amplifier is connected with the upper end of the energy storage spring, the upper end of the diamond amplifier is connected with the lower end of the deformation transmission guide rod, the two side ends of the diamond amplifier are respectively connected with the top ends of the distributed piezoelectric composite beam drivers on the two sides through a connecting rod 539, the two ends of the connecting rod 539 are respectively hinged with the diamond amplifier and the distributed piezoelectric composite beam driver, the top ends of the deformation transmission guide rods of the first driving part and the second driving part are fixedly connected with a flexible beam 533, the front end of the flexible beam 533 is fixedly connected with the rear end face of the main wing beam, and the upper end of the flexible beam 533 is abutted 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 can slide relatively in the process of abutting against the flexible skin 6, so that the requirement of the deformed structure is met; as can be seen from fig. 5, although the two structures are the same, the sizes of the first driving part and the second driving part are different greatly, and the sizes are respectively used for large-amplitude deformation and small-amplitude deformation of the deformation structure, which is similar to coarse adjustment and fine adjustment, so that the flexible beam can smoothly transit in an arc shape, and the overall airflow shape of the wing is ensured.
In a further embodiment, as shown in fig. 4, the flexible truss support unit 4 includes an upper arc rod 41, a lower arc rod 42, and a truss main body 43 connected between the upper arc rod 41 and the lower arc rod 42, the rear end of the truss main body is flush with the rear end of the lower arc rod 42, the length of the lower arc rod 42 is smaller than that of the upper arc rod 41, a rigid longitudinal beam 8 is connected between the rear ends of the lower arc rods of the flexible truss support units 4, and a corrugated flexible skin 7 is connected between the rear end of the upper arc rod of each flexible truss support unit 4 and the rigid longitudinal beam.
In a further embodiment, as shown in fig. 4 and 5, the rear end of the upper arc-shaped rod of each flexible truss bearing unit 4 is provided with a tail line pulley 538, and the rear end of the corrugated flexible skin 7 is connected with the flexible skin 6 through the tail line pulley 538; the rear end of the flexible beam 533 is flush with the rear end of the upper arc-shaped rod 41, a corrugated plate 536 is further connected between the rear end of the flexible beam 533 and the rigid longitudinal beam 8, the upper end of the corrugated plate 536 is connected with the end part of the flexible beam through a tail line pulley 538, and the lower end of the corrugated plate 536 is fixedly connected with the rigid longitudinal beam 8; the corrugated plate 536 can be unfolded along with the deformation of the deformation structure and has a bearing effect on the corrugated flexible skin 7; the rear end of the corrugated flexible skin 7 is connected with the flexible skin 6 through the tail line pulley 538, deformation can be transmitted in a sliding mode, the corrugated flexible skin 7 and the flexible skin are in a tight state initially, and the flexible skin 6 can make the corrugated flexible skin 7 deform in a adaptability mode when deforming.
In a further embodiment, as shown in fig. 4 and 5, the rigid longitudinal beam 8 is fixedly connected with the rigid bottom beam 535, a secondary spar 537 is further arranged at the connection position, the bottom end of the secondary spar 537 is fixedly connected with the upper surface of the rigid longitudinal beam 8, the top end of the secondary spar 537 is slidably connected with the flexible beam 533, a restraint beam 531 is further arranged at the upper part of the secondary spar, the front end of the restraint beam 531 is fixedly connected with the rear end surface of the main spar, the rear end of the restraint beam 531 is fixedly connected with the upper part of the secondary spar 537, a guide hole is further formed in the restraint beam 531, a roller 532 is fixedly mounted in the guide hole, and the deformation transfer guide rod 504\514 passes through the guide hole and is slidably connected with the roller 532; as can be seen from fig. 5, the rollers 532 are distributed along the axial direction of the guiding hole and the inner surface of the side wall of the guiding hole, and a plurality of rollers 532 can surround the inner wall surface of the guiding hole, and a plurality of groups of such rollers 532 are provided, so as to ensure that the deformation transmission guide rod 504\514 can slide smoothly while maintaining the stability of the transmission direction.
In a further embodiment, as shown in FIG. 5, the deformation transfer guide 504; 514 is an arc-shaped surface, and the inside of the deformation transmission guide rod is a hollow structure; the arc-shaped surface can be better matched with the flexible beam 533, so that the extrusion force of the deformation transmission guide rod on the flexible skin 6 is transmitted flexibly, and the flexible skin 6 can slide relative to the top end of the deformation transmission guide rod in transmission.
In a further embodiment, as shown in fig. 4 and 5, the lower end of the rigid bottom beam 535 is arc-shaped, the first driving part is located at the front side of the second driving part, and the height of the top end of the deformation transmission guide rod 504 of the first driving part is greater than that of the top end of the deformation transmission guide rod 514 of the second driving part when the diamond-shaped amplifier is extended; as can be seen from fig. 5, the size of the first driving portion is larger than that of the second driving portion, and the length of the distributed piezoelectric composite beam driver is longer, so that more piezoelectric sheets can be distributed to be responsible for driving deformation at a critical position.
In a further embodiment, as shown, the restraining beam 531 is a "Z" shaped structure, and the base of the second driving portion has a height greater than the height of the base of the first driving portion.
In the present invention, the flexible material includes a flexible beam 533, a corrugated plate 536 made of a composite material composed of a reinforcing material and a polymer material, such as a composite material composed of epoxy resin and carbon fiber, a flexible skin 6 and a corrugated flexible skin 7 made of a rubber material, a piezoelectric sheet in the distributed piezoelectric composite beam driver is made of a piezoelectric material with high power conversion efficiency, such as a currently commonly used lead zirconate titanate material, and other components in the distributed piezoelectric composite beam driver are made of a commonly used aviation lightweight material.
The use principle of the invention is as follows:
taking the first driving part as an example, the initial state of the driving structure is shown in fig. 6, at this time, the energy storage spring is in a stretched state, the vertex angle of the diamond displacement amplifier is an acute angle, the distributed piezoelectric composite beam driver is kept in a vertical state under the condition of no external electrical load, and the flexible beam is in a tight state.
When an electric field is applied to two sides of the piezoelectric patches to drive the flexible skin 6 at the top of the wing to move downwards, positive charges are applied to the bare surface of the piezoelectric patches (namely the contact surface of the piezoelectric patches and the air) of the right distributed piezoelectric composite beam driver, negative charges are applied to the contact surface of the piezoelectric patches and the matrix beam, meanwhile, negative charges are applied to the bare surface of the piezoelectric sheet on the left distributed piezoelectric composite beam driver, and positive charges are applied to the contact surfaces of the piezoelectric sheets and the matrix beam, as shown in fig. 7, at the moment, the two distributed piezoelectric composite beam drivers bend outwards, so that the transverse diagonal line of the diamond displacement amplifier is increased, the longitudinal diagonal line of the diamond displacement amplifier is reduced, the deformation transmission guide rod moves downwards, the flexible beam naturally descends after releasing the deformation energy in a tight state, the energy storage spring continues to pull upwards, and the displacement change and the stress state in the whole deformation process are as shown in fig. 9.
When an electric field is applied to two sides of the piezoelectric sheets to drive the flexible skin 6 at the top of the wing to move upwards, negative charges need to be applied to the bare surface of the piezoelectric sheet on the right-side distributed piezoelectric composite beam driver, positive charges need to be applied to the contact surface of the piezoelectric sheet and the base beam, positive charges need to be applied to the bare surface of the piezoelectric sheet on the left-side distributed piezoelectric composite beam driver, and negative charges need to be applied to the contact surface of the piezoelectric sheet and the base beam, as shown in fig. 8, at this time, the two piezoelectric composite beam drivers bend inwards, so that the horizontal diagonal line of the diamond amplifier is reduced, the vertical diagonal line is increased, the guide rod moves upwards, the flexible beam 533 is driven to deform upwards, the energy storage spring moves downwards to release elastic potential energy to assist force to deform, and the displacement change and the stress state of the. It is worth mentioning that when an electric field is applied on both sides of the piezoelectric sheet, the absolute values of the voltages are equal in order to ensure that they can be bent synchronously, avoiding damaging the guide rods, despite the different directions of the voltages due to the different directions of motion.
Fig. 11 shows the energy conversion during the deformation of the wing, except for the energy loss during the deformation, during the downward driving, the positive work performed by the distributed piezoelectric composite beam driver under the action of the voltage and the deformation energy lost when the flexible beam falls are mostly converted into the elastic potential energy of the energy storage spring; in the upward driving process, the distributed piezoelectric composite beam driver performs positive work under voltage and most of elastic potential of the energy storage spring for shortening loss is converted into deformation energy of the wing skin.
The combined action of the first driving part and the second driving 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 whole morphing wing, under the combined action of the piezoelectric driving system, the flexible skin 6 and the corrugated flexible skin 7, the flexible truss bearing system can self-adaptively adjust the structure of the flexible truss bearing system according to load change, and provide a certain bearing effect for the skin after the flexible truss bearing system is stably adjusted. When the top flexible skin 6 changes, the corrugated flexible skin 7 can be stretched, and the deformation of the wing is smoother, more stable and easier to change under the combined action of the top flexible skin and the corrugated flexible skin.
Claims (9)
1. A novel morphing wing based on piezoelectricity drive, characterized by: the wing box comprises a frame and a rigid skin, wherein the frame is built by a plurality of ribs with L-shaped sections, a main wing beam through connecting pieces, and the rigid skin is fixedly connected to the outer surface of the frame, the deformation structure is positioned on the rear side of the main wing beam and comprises a plurality of flexible truss bearing units, piezoelectric driving units and flexible skins, the flexible truss bearing units are fixedly connected with the rear end surface of the main wing beam and are arranged at intervals, the piezoelectric driving units are arranged between the adjacent flexible truss bearing units, and the flexible skins are fixedly connected to the upper ends of the flexible truss bearing units.
2. A novel morphing wing based on piezoelectric actuation as claimed in claim 1, wherein: the piezoelectric driving unit comprises a first driving part and a second driving part, the first driving part and the second driving part are arranged at the rear side of the main wing beam side by side, a rigid bottom beam with one end fixedly connected with the main wing beam is arranged at the bottom of the first driving part and the bottom of the second driving part, a base used for installing the first driving part and the second driving part is respectively arranged at the upper end of the rigid bottom beam, and a rigid skin is fixedly connected with the lower ends of the rigid bottom beam and the flexible truss bearing unit.
3. A novel morphing wing based on piezoelectric actuation as claimed in claim 2, wherein: the base is arranged along the horizontal direction, the first driving part and the second driving part have the same structure and comprise 2 distributed piezoelectric composite beam drivers, an energy storage spring, a diamond amplifier and a deformation transmission guide rod, wherein the bottom end of each distributed piezoelectric composite beam driver is fixedly connected with the upper surface of the base and is arranged in parallel with the upper surface of the base, the energy storage spring is arranged between the 2 distributed piezoelectric composite beam drivers, one end of each energy storage spring is connected with the upper surface of the base, the diamond amplifier is arranged above the energy storage spring, the deformation transmission guide rod is arranged above the diamond amplifier, the lower end of the diamond amplifier is connected with the upper end of the energy storage spring, the upper end of the diamond amplifier is connected with the lower end of the deformation transmission guide rod, two side ends of the diamond amplifier are respectively connected with the top ends of the distributed piezoelectric composite beam drivers at two sides through connecting rods, two ends of each connecting rod are respectively hinged with the diamond amplifier and the distributed piezoelectric composite beam, the front end of the flexible beam is fixedly connected with the rear end face of the main wing beam, and the upper end of the flexible beam is abutted to the lower surface of the flexible skin.
4. A novel morphing wing based on piezoelectric actuation as claimed in claim 3, wherein: the flexible truss bearing unit comprises an upper arc-shaped rod, a lower arc-shaped rod and a truss main body connected between the upper arc-shaped rod and the lower arc-shaped rod, the rear end of the truss main body flushes with the rear end of the lower arc-shaped rod, the length of the lower arc-shaped rod is smaller than that of the upper arc-shaped rod, a rigid longitudinal beam is further connected between the rear ends of the lower arc-shaped rods of the flexible truss bearing units, and a corrugated flexible skin is further connected between the rear end of the upper arc-shaped rod of each flexible truss bearing unit and the rigid longitudinal beam.
5. The novel morphing wing based on piezoelectric actuation of claim 4, wherein: the rear end of the upper arc-shaped rod of each flexible truss bearing unit is provided with a tail line pulley, and the rear end of the corrugated flexible skin is connected with the flexible skin through the tail line pulley; the rear end of flexible roof beam and the rear end of last arc pole flush, and still be connected with the buckled plate between flexible roof beam rear end and rigidity longeron, buckled plate upper end and flexible roof beam tip pass through the tail wire pulley and be connected, lower extreme and rigidity longeron fixed connection.
6. A novel morphing wing based on piezoelectric actuation as claimed in claim 4 or 5, wherein: the rigid longitudinal beam is fixedly connected with the rigid bottom beam, a secondary wing beam is further arranged at the joint, the bottom end of the secondary wing beam is fixedly connected with the upper surface of the rigid longitudinal beam, the top end of the secondary wing beam is connected with the flexible beam in a sliding manner, a restraint cross beam is further arranged on the upper portion of the secondary wing beam, the front end of the restraint cross beam is fixedly connected with the rear end face of the main wing beam, the rear end of the restraint cross beam is fixedly connected with the upper portion of the secondary wing beam, a guide hole is further formed in the restraint cross beam, a roller is fixedly mounted in the guide hole, and the deformation transmission guide rod penetrates through the guide hole and is connected with.
7. A novel morphing wing based on piezoelectric actuation as claimed in claim 3 or 4 or 5, wherein: the top end of the deformation transfer guide rod is an arc-shaped surface, and the inside of the deformation transfer guide rod is of a hollow structure.
8. A novel morphing wing based on piezoelectric actuation as claimed in claim 3 or 4 or 5, wherein: the lower end surface of the rigid bottom beam is arc-shaped, the first driving part is positioned on the front side of the second driving part, and the height of the top end of the deformation transmission guide rod of the first driving part is larger than that of the top end of the deformation transmission guide rod of the second driving part when the diamond amplifier extends.
9. A novel morphing wing based on piezoelectric actuation as claimed in claim 6, wherein: the restraint crossbeam be "Z" shape structure, and the height of the base of second drive division is higher than the height of the base of first drive division.
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| CN114560072A (en) * | 2022-03-02 | 2022-05-31 | 电子科技大学 | Deformable wing based on array structure driving |
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