CN112109877B - Variant wing based on piezoelectric driving - Google Patents
Variant wing based on piezoelectric driving Download PDFInfo
- Publication number
- CN112109877B CN112109877B CN202011001383.6A CN202011001383A CN112109877B CN 112109877 B CN112109877 B CN 112109877B CN 202011001383 A CN202011001383 A CN 202011001383A CN 112109877 B CN112109877 B CN 112109877B
- Authority
- CN
- China
- Prior art keywords
- flexible
- wing
- piezoelectric
- driving part
- deformation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Piezo-Electric Transducers For Audible Bands (AREA)
- General Electrical Machinery Utilizing Piezoelectricity, Electrostriction Or Magnetostriction (AREA)
Abstract
The utility model provides a variant wing based on piezoelectricity drive, relates to aircraft variant wing technical field, including the cross-section for the wing box of D shape, and connect in the deformation structure of wing box rear end, the wing box include by many cross-sections for the rib of L shape, and the main wing roof beam passes through the frame that the connecting piece was built to and fixed connection is in the rigidity covering of frame surface, deformation structure be located the rear side of main wing spar, including a plurality of flexible truss bearing units that are connected with the rear end face fixed connection of main wing roof beam and interval setting, set up the piezoelectricity drive unit between adjacent flexible truss bearing unit, and fixed connection is in the flexible covering of flexible truss bearing unit upper end. The structure and the installation position of the piezoelectric driving unit are optimized, so that the wing deformation is more stable and diversified, and the device can adapt to various different flight environments.
Description
Technical Field
The invention relates to the technical field of aerocraft variant wings, in particular to a variant wing based on piezoelectric driving.
Background
Currently, morphing wings that have been applied to aircraft are mainly rigid morphing wings that are actuated by hydraulic means to fold-extend into a deformed form. The piezoelectric material is used as a brand new functional material, the deformation degree of the piezoelectric material can be controlled under the action of an electric field by utilizing the inverse piezoelectric effect of the piezoelectric material, and the piezoelectric material is also applied to the aspect of a variant wing to a certain extent, but the utilization of the piezoelectric material still has some defects at present.
1. The common rigid variant wing is to control the folding and stretching of the wing by utilizing a hydraulic device to change the shape of the airplane, but the variant wing of the type often has a complex mechanical structure, greatly increases the volume and the mass of the wing and influences the overall flight performance and the stability of the airplane.
2. The shape memory material-driven variant wing which is proposed at present can achieve the effects of the thickness and the inclination angle of the wing, but the problem of slow response can cause the wing to be incapable of timely changing according to the flight environment.
3. The prior variant wing driven by piezoelectric materials mainly combines a piezoelectric system with a wing skin directly to achieve the effect of changing the shape of the wing, but the variant wing can lead the piezoelectric system to be in direct contact with external load in the flying process, so that the driving effect and the working environment of the piezoelectric system are affected.
4. In addition, the problem of small deformation amplitude of the variant wing driven by the piezoelectric material can cause the self-adaptability of the wing under various flight environment conditions to be reduced, and the deformation degree and deformation form of the variant wing are limited.
The piezoelectric material is formed by polarization treatment, and has advantages of heat resistance, moisture resistance, easy manufacturing, and capability of being made into any shape and polarization direction. When the piezoelectric material is subjected to a force or other load, an electrical charge will be generated on its surface; when an electric field is applied to the surface of the piezoelectric material, the piezoelectric material deforms, so that the piezoelectric material has a positive and negative piezoelectric effect. Because of the advantages of high measurement accuracy, high response speed, stable performance and the like, the piezoelectric material is widely applied to the fields of aerospace, precise measurement, intelligent structure 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 in 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 an inverse piezoelectric effect.
Regarding distributed piezoelectric composites Liang Qudong: as shown in fig. 2, the piezoelectric composite Liang Qudong device formed by vertically and symmetrically attaching the plurality of piezoelectric sheets 06 to the base beam 07 has the advantages of a piezoelectric material, and can improve the stability and the bearing capacity of the structure and flexibly and variously deform. Under the action of the electric field, the piezoelectric sheet 06 drives the matrix beam 07 to deform, thereby meeting the corresponding engineering requirements.
Regarding diamond amplifiers: the invention relates to a diamond amplifier which mainly comprises a bridge type amplifying mechanism, a lever type amplifying mechanism and a triangular amplifying mechanism, wherein the triangular amplifying mechanism is adopted by the diamond amplifier, and the purpose of ensuring the amplification factor is achieved on the premise of reducing the occupied space. Fig. 3 shows a triangle enlargement principle of a diamond amplifier. As shown in fig. 3, the rods hinged at the ends sequentially form a diamond-shaped amplifier, four rods of the diamond-shaped amplifier adopt rigid rods, and deformation under the action of external force is ignored, namely the length of the corresponding hypotenuse of the triangle is unchanged. Let the long right-angle side be a, its included angle with the hypotenuse be θ, the short right-angle side be b. When the long right-angle side is extended by deltaa, the short right-angle side is correspondingly shortened by deltab, and under the condition that the hypotenuse is constant, the equation is as follows:
a 2 +b 2 ＝(a-Δa) 2 +(b+Δb) 2 (2)
ignoring deltaa 2 And Deltab 2 Two higher order infinitely small amounts, the magnification can be obtained according to equation (2):
from equation (3), it can be seen that the magnification of the diamond amplifier is related to the magnitude of its acute angle, and the smaller its acute angle, the larger the displacement magnification, irrespective of the length of the hypotenuse and the right-angle side. According to the principle, the diamond amplifier can convert transverse displacement into longitudinal displacement while ensuring amplification deformation, and the whole structure volume can be effectively reduced.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a variant wing based on piezoelectric driving, and the variant wing optimizes the structure and the installation position of a piezoelectric driving 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 adaptively deformed, so that the effect of changing the thickness of the wing and the inclination angle of the wing is achieved.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
the utility model provides a variant wing based on piezoelectricity drive, includes the wing box that the cross-section is D shape and connects in the deformation structure of wing box rear end, the wing box include by many cross-sections for the rib of L shape, and the main wing roof beam is built through the connecting piece frame to and fixed connection is in the rigidity covering of frame surface, deformation structure be located the rear side of main wing spar, including a plurality of flexible truss bearing units that are connected with the rear end face fixed of main wing spar and the interval sets up, set up the piezoelectricity drive unit between adjacent flexible truss bearing unit, and fixed connection is in the flexible covering of flexible truss bearing unit upper end.
Preferably, 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 on the rear side of the main spar side by side, a rigid bottom beam with one end fixedly connected with the main spar is arranged at the bottoms of the first driving part and the second driving part, bases for installing the first driving part and the second driving part are respectively arranged at the upper ends of the rigid bottom beams, and rigid skins are fixedly connected with the lower ends of the rigid bottom beam and the flexible truss bearing unit.
Preferably, the base set up along the horizontal direction, first drive portion and second drive portion have the same structure, including bottom and base upper surface fixed connection, and 2 distributed piezoelectricity composite Liang Qudong ware of mutual parallel arrangement, set up between 2 distributed piezoelectricity composite beam driver and the energy storage spring of one end and base upper surface connection, set up the rhombus amplifier in energy storage spring top, set up the deformation transmission guide arm in the rhombus amplifier top, the lower extreme of rhombus amplifier be connected with the upper end of energy storage spring, the upper end of rhombus amplifier is connected with the lower extreme of deformation transmission guide arm, the both sides end of rhombus amplifier be connected with the top of the distributed piezoelectricity composite beam driver of both sides through the connecting rod respectively, the both ends of connecting rod articulated with rhombus amplifier and distributed piezoelectricity composite Liang Qudong ware respectively, the deformation transmission guide arm top fixed connection of first drive portion and second drive portion have the flexible roof beam, the front end of flexible roof beam and the rear end fixed connection of main spar, the upper end of flexible roof beam offset with the lower surface of flexible skin.
Preferably, the flexible truss bearing unit comprises an upper arc rod, a lower arc rod and a truss main body connected between the upper arc rod and the lower arc rod, wherein the rear end of the truss main body is flush with the rear end of the lower arc rod, the length of the lower arc rod is smaller than that of the upper arc rod, a rigid longitudinal beam is further connected between the rear ends of the lower arc rods of the flexible truss bearing units, and a corrugated flexible skin is further connected between the rear ends of the upper arc rods of the flexible truss bearing units and the rigid longitudinal beam.
Preferably, a tail wire pulley is arranged at the rear end of the upper arc-shaped rod of each flexible truss bearing unit, and the rear end of the corrugated flexible skin is connected with the flexible skin through the tail wire pulley; the rear end of the flexible beam is flush with the rear end of the upper arc-shaped rod, a corrugated plate is further connected between the rear end of the flexible beam and the rigid longitudinal beam, the upper end of the corrugated plate is connected with the end part of the flexible beam through a tail wire pulley, and the lower end of the corrugated plate is fixedly connected with the rigid longitudinal beam.
Preferably, the rigid longitudinal beam is fixedly connected with the rigid bottom beam, a secondary spar is further arranged at the joint, the bottom end of the secondary spar is fixedly connected with the upper surface of the rigid longitudinal beam, the top end of the secondary spar is slidably connected with the flexible beam, a constraint cross beam is further arranged on the upper portion of the secondary spar, the front end of the constraint cross beam is fixedly connected with the rear end face of the main spar, the rear end of the constraint cross beam is fixedly connected with the upper portion of the secondary spar, a guide hole is further formed in the constraint cross beam, a roller is fixedly installed in the guide hole, and a 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 at the front side of the second driving part, and when the diamond amplifier stretches, the top end of the deformation transmission guide rod of the first driving part is higher than the top end of the deformation transmission guide rod of the second driving part.
Preferably, the restraining beam has 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 variant wing based on piezoelectric driving has the following beneficial effects:
1. according to the invention, through improving the deformation structure and promoting the wing deformation through the piezoelectric driving unit arranged in the deformation structure, the defects of large load and poor driving effect caused by combining the piezoelectric system with the flexible skin in the prior art are effectively avoided, the flexible deformation structure has a sensitive deformation function, and the service life of the piezoelectric driving unit is long;
2. the invention has simple mechanical structure and good driving effect, and the shape of the deformation structure can keep the airflow shape of the wing through coarse adjustment of the first driving part and fine adjustment of the second driving part, so that 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 the aircraft on quick adjustment of the shape of the wing in the flight process can be fully met, and the wing can be adaptively changed in time according to the flight environment;
4. the invention overcomes the defect of small deformation amplitude of the conventional variant wing driven by the piezoelectric material, and the deformation amplitude of the wing can be adapted to various flight environments by the mutual cooperation of the diamond amplifier, the distributed piezoelectric composite Liang Qudong device and the deformation transmission guide rod, so that the self-adaptation capability of the variant wing is effectively improved.
Drawings
FIG. 1 is a schematic diagram of the inverse piezoelectric effect;
FIG. 2 is a schematic diagram of a distributed piezoelectric composite beam driver;
fig. 3 is a triangle amplification principle of a diamond amplifier;
FIG. 4 is a three-dimensional model diagram of a morphing wing;
fig. 5 is a structural model diagram of the piezoelectric driving unit;
fig. 6 is a state diagram of the driving section in the initial state;
FIG. 7 is a state diagram of the driving portion after the downward driving deformation;
FIG. 8 is a state diagram of the driving portion after deformation of the upper drive;
FIG. 9 shows the displacement change and stress state of each node in the driving process;
FIG. 10 shows the displacement change and stress state of each node in the driving process;
FIG. 11 is a schematic representation of energy conversion during deformation;
01: initial state, 02: deformation state, 03: piezoelectric material, 04: piezoelectric action area, 05: bare beam area, 06: piezoelectric sheet, 07: matrix beam, 08: wing box, 09: a deformed structure; 1: rigid skin, 2: main spar, 3: rib, 4: flexible truss load carrying unit, 5: piezoelectric driving unit, 6: flexible skin, 7: corrugated flexible skin, 8: rigid stringers; 41: upper arc bar, 42: lower arc lever, 43: truss body, 501: distributed piezoelectric composite Liang Qudong in first drive portion, 502: energy storage spring in first drive portion, 503: diamond-shaped amplifiers in the first drive section, 504: deformation transmission guide rod in first drive portion, 511: matrix beam in the second drive section, 512: energy storage spring in second drive portion, 513: diamond-shaped amplifiers in the second drive section, 514: deformation transmission guide rods in the second driving part, 531: restraint beam, 532: roller, 533: flexible beam, 534: base, 535: rigid bottom beams, 536: corrugated plate, 537: auxiliary spar, 538: tail pulley, 539: and a connecting rod.
Detailed Description
The following detailed description of the embodiments of the present invention in a stepwise manner is provided merely as a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, but any modifications, equivalents, improvements, etc. within the spirit and principles 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 positional or positional relationship indicated by the terms "upper", "lower", "left", "right", "top", "bottom", "inner", "outer", etc. are based on the positional or positional relationship shown in the drawings, are merely for describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, and specific orientation configuration and operation, and thus should not be construed as limiting the present invention.
In one embodiment, as shown in fig. 4, the variant wing based on piezoelectric driving comprises a wing box 08 with a D-shaped section and a deformation structure 09 connected to the rear end of the wing box 08, wherein the wing box comprises a frame constructed by a plurality of ribs 3 with L-shaped sections and main spars 2 through connecting pieces, and a rigid skin 1 fixedly connected to the outer surface of the frame, and the wing box 08 has shearing and compression resistance, and plays roles in dividing airflow and guaranteeing the stability of the whole structure of the wing in the navigation process 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 fixedly connected with the rear end surface of the main wing beam 2 and arranged at intervals, piezoelectric driving units 5 arranged between adjacent flexible truss bearing units 4 and flexible skins 6 fixedly connected with 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 load-bearing unit 4 needs a load action of a certain size to change the original shape, until the deformation stops after adapting to the load, the shape after each deformation stabilization has a certain bearing capacity, and when the load is continuously changed to be greater than the bearing capacity, the structure is continuously changed to seek a stable form adapting 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 on the rear side of the main spar 2, a rigid bottom beam 535 with one end fixedly connected to the main wing beam 2 is provided 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 provided at the upper end of the rigid bottom beam 535, and a rigid skin 1 is fixedly connected to the lower end of the rigid bottom beam 535 and the flexible truss carrier unit 4; through installing the first drive portion and the second drive portion in the lower part in the deformation structure, can avoid the piezoelectric material to directly act on flexible covering 6, make piezoelectric drive unit 5 can break away from external load (namely the reaction force to the piezoelectric system after the covering warp, prior art is with the piezoelectric system direct with the wing covering combination come the effect of changing the wing shape, but this type of deformation wing can cause piezoelectric system and external load direct contact in the flight, piezoelectric system's operational environment is poor, influence piezoelectric system's driving effect), keep driving sensitivity, extension piezoelectric drive unit 5's life.
In a further embodiment, as shown in fig. 4 and 5, the base 1 is disposed along a horizontal direction, the first driving portion and the second driving portion have the same structure, and include 2 distributed piezoelectric composite Liang Qudong devices 501/511 with bottom ends fixedly connected to an upper surface of the base 534 and disposed parallel to each other, an energy storage spring 502/512 disposed between the 2 distributed piezoelectric composite Liang Qudong devices 501/511 and having one end connected to an upper surface of the base 534, a diamond-shaped amplifier 503/513 disposed above the energy storage spring, a deformation transmission guide rod 504/514 disposed above the diamond-shaped amplifier, the lower end of the diamond-shaped amplifier is connected to an upper end of the energy storage spring, the upper end of the diamond-shaped amplifier is connected to a lower end of the deformation transmission guide rod, two side ends of the diamond-shaped amplifier are respectively connected to top ends of the distributed piezoelectric composite beam drivers on two sides through a connecting rod 539, two ends of the diamond-shaped amplifier and the distributed piezoelectric composite Liang Qudong device are respectively hinged to the diamond-shaped amplifier, the upper end of the first driving portion and the second driving portion are fixedly connected to a flexible beam 533, and the flexible beam 533 is fixedly connected to a flexible beam 533; in the deformation process, the flexible skin 6 is supported by the flexible beams 533 to deform, and the flexible beams 533 and the flexible skin 6 can relatively slide in the process of propping against each other, so that the deformed structure needs are met; as can be seen from fig. 5, although the two structures are the same, the first driving portion and the second driving portion have larger differences in size, and are used for large-amplitude deformation and small-amplitude deformation of the deformation structure respectively, and similar to coarse adjustment and fine adjustment, the flexible beam can be smoothly transited in an arc shape, so that the overall airflow shape of the wing is ensured.
In a further embodiment, as shown in fig. 4, the flexible truss carrying units 4 include 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 further connected between the rear ends of the lower arc rods of the flexible truss carrying units 4, and a corrugated flexible skin 7 is further connected between the rear ends of the upper arc rods of the flexible truss carrying units 4 and the rigid longitudinal beam.
In a further embodiment, as shown in fig. 4 and 5, a tail pulley 538 is arranged at the rear end of the upper arc-shaped rod of each flexible truss carrying unit 4, and the rear end of the corrugated flexible skin 7 is connected with the flexible skin 6 through the tail 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 of the flexible beam through a tail pulley 538, and the lower end of the corrugated plate 536 is fixedly connected with the rigid longitudinal beam 8; the corrugated plates 536 may expand as the deformed structure deforms and act as a load bearing function for the corrugated flexible skin 7; the rear end of the corrugated flexible skin 7 is connected with the flexible skin 6 through a tail pulley 538, deformation can be transmitted in a sliding mode, both the flexible skin 6 and the tail pulley are in a tightening state initially, and the flexible skin 7 can be deformed adaptively during deformation.
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 provided 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 is slidably connected with the flexible beam 533, a constraint beam 531 is further provided at the upper part of the secondary spar, the front end of the constraint beam 531 is fixedly connected with the rear end surface of the main spar, the rear end of the constraint beam 531 is fixedly connected with the upper part of the secondary spar 537, a guide hole is further provided on the constraint beam 531, a roller 532 is fixedly installed in the guide hole, and the deformation transmission 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 guide hole and the inner surface of the side wall of the guide hole, and a plurality of rollers 532 can surround the inner wall surface of the guide hole, and a plurality of groups of such rollers 532 are provided, so that the smooth sliding of the deformation transmission guide rods 504/514 is ensured while the stable transmission direction is maintained.
In a further embodiment, as shown in FIG. 5, the deformation imparting guide 504;514 is an arc-shaped surface, and the inside of the deformation transmission guide rod is of a hollow structure; the arc surface can be better matched with the flexible beam 533, so that the extrusion force of the deformation transmission guide rod to the flexible skin 6 is transmitted softly, and the flexible skin 6 slides 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 surface 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 when the diamond amplifier stretches, the height of the top end of the deformation transmission guide rod 504 of the first driving part is greater than the height of the top end of the deformation transmission guide rod 514 of the second driving part; as can be seen from fig. 5, the first driving portion is larger than the second driving portion, and the length of the distributed piezoelectric composite beam driver is longer, so that more piezoelectric sheets can be distributed and the driving deformation of the key position is responsible.
In a further embodiment, as shown, the constraining beam 531 has a "Z" shape, and the base of the second driving section has a higher height than the base of the first driving section.
In the present invention, the flexible material includes a flexible beam 533, a corrugated plate 536, a flexible skin 6 and a corrugated flexible skin 7, and the flexible skin and corrugated flexible skin are made of a composite material composed of a reinforcing material and a polymer material, such as an epoxy resin and a carbon fiber, the piezoelectric sheet in the distributed piezoelectric composite beam driver is made of a piezoelectric material with high power conversion efficiency, such as a lead zirconate titanate material commonly used at present, and other components in the distributed piezoelectric composite beam driver are made of a commonly used aviation lightweight material.
The application 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, 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 Liang Qudong device is kept in a vertical state under the condition of no external electric load, and the flexible beam is in a tight state.
When an electric field is applied to two sides of the piezoelectric sheet to drive the flexible skin 6 at the top of the wing to move downwards, positive charges are required to be applied to the bare surface of the piezoelectric sheet (namely the contact surface of the piezoelectric sheet and air) of the right-side distributed piezoelectric composite beam driver, negative charges are required to be applied to the contact surface of the piezoelectric sheet and the matrix beam of the piezoelectric composite beam driver, meanwhile, negative charges are required to be applied to the bare surface of the piezoelectric sheet on the left-side distributed piezoelectric composite beam driver, positive charges are required to be applied to the contact surface of the piezoelectric sheet and the matrix beam of the piezoelectric composite beam driver, at the moment, the two distributed piezoelectric composite Liang Qudong devices bend outwards, so that the transverse diagonal of the diamond-shaped displacement amplifier is increased, the longitudinal diagonal is reduced, the deformation transmission guide rod moves downwards, the deformation energy in a flexible Liang Shifang is naturally reduced after the deformation energy in a tightening state, the energy storage spring continues to be pulled upwards, and the displacement change and the stress state of the whole deformation process are shown in fig. 9.
When an electric field is applied to two sides of the piezoelectric sheet to drive the flexible skin 6 at the top of the wing to move upwards, negative charges are required to be applied to the bare surface of the piezoelectric sheet on the right-side distributed piezoelectric composite beam driver and positive charges are required to be applied to the contact surface of the piezoelectric sheet on the left-side distributed piezoelectric composite beam driver and negative charges are required to be applied to the contact surface of the piezoelectric sheet on the left-side distributed piezoelectric composite beam driver and the substrate beam, as shown in fig. 8, at the moment, the two piezoelectric composite beam drivers bend inwards, so that the horizontal diagonal of the diamond amplifier is reduced, the vertical diagonal is increased, the guide rod moves upwards to drive the flexible beam 533 to deform upwards, and the energy storage spring moves downwards to release elastic potential energy to assist deformation, and the displacement change and the stress state of the whole deformation process are shown in fig. 10. It should be noted that when an electric field is applied across the piezoelectric sheet, the absolute values of the voltages are equal, although the directions of the voltages are different due to the different directions of movement, in order to ensure that they can bend synchronously, avoiding damaging the guide rods.
FIG. 11 shows the energy conversion during wing deformation, except for the energy loss during deformation, during downward driving, the deformation energy lost by the distributed piezoelectric composite Liang Qudong device during positive work and the falling of the flexible beam under voltage is mostly converted into the elastic potential energy of the energy storage spring; in the upward driving process, the positive power of the distributed piezoelectric composite Liang Qudong device and the elastic potential of the energy storage spring, which are shortened and lost by the voltage, are mostly converted into deformation energy of the wing skin.
For the whole piezoelectric driving system, 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 variant 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 adaptively adjust the structure according to load change and provide a certain bearing effect for the skin after adjustment and stabilization. When the top flexible skin 6 changes, the corrugated flexible skin 7 can be stretched, and the wing deformation is smoother and more stable and is easier to change under the combined action of the top flexible skin and the corrugated flexible skin.
Claims (7)
1. A variant wing based on piezoelectric actuation, characterized by: the wing box comprises a frame formed by a plurality of ribs with L-shaped cross sections and main wing beams through connecting pieces, and a rigid skin fixedly connected to the outer surface of the frame, wherein the deformation structure is positioned at the rear side of the main wing beam and comprises a plurality of flexible truss bearing units fixedly connected with the rear end surface of the main wing beam and arranged at intervals, piezoelectric driving units arranged between adjacent flexible truss bearing units, and a flexible skin fixedly connected to the upper end of the flexible truss bearing units;
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 on the rear side of the main spar side by side, a rigid bottom beam with one end fixedly connected with the main wing beam is arranged at the bottoms of the first driving part and the second driving part, a base 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 end of the flexible truss bearing unit;
the base set up along the horizontal direction, first drive portion and second drive portion have the same structure, including bottom and base upper surface fixed connection, and 2 distributed piezoelectricity composite Liang Qudong ware of mutual parallel arrangement, set up between 2 distributed piezoelectricity composite beam driver and the energy storage spring of one end and base upper surface connection, set up the rhombus amplifier in energy storage spring top, set up the deformation transmission guide arm in rhombus amplifier top, the lower extreme of rhombus amplifier be connected with the upper end of energy storage spring, the upper end of rhombus amplifier is connected with the lower extreme of deformation transmission guide arm, the both sides end of rhombus amplifier be connected with the top of the distributed piezoelectricity composite beam driver of both sides through the connecting rod respectively, the both ends of connecting rod articulated with rhombus amplifier and distributed piezoelectricity composite Liang Qudong ware respectively, the deformation transmission top fixed connection of first drive portion and second drive portion have the flexible roof beam, the front end of flexible roof beam and the rear end fixed connection of main spar, the upper end of flexible roof beam offset with the lower surface of flexible skin.
2. A piezoelectric-driven morphing wing according to claim 1, wherein: the flexible truss bearing units comprise an upper arc-shaped rod, a lower arc-shaped rod and truss main bodies connected between the upper arc-shaped rod and the lower arc-shaped rod, the rear ends of the truss main bodies are flush with the rear ends of the lower arc-shaped rod, the length of the lower arc-shaped rod is smaller than that of the upper arc-shaped rod, rigid longitudinal beams are further connected between the rear ends of the lower arc-shaped rods of the flexible truss bearing units, and corrugated flexible skins are further connected between the rear ends of the upper arc-shaped rods of the flexible truss bearing units and the rigid longitudinal beams.
3. A piezoelectric-driven morphing wing according to claim 2, wherein: the tail 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 rear end of the flexible beam is flush with the rear end of the upper arc-shaped rod, a corrugated plate is further connected between the rear end of the flexible beam and the rigid longitudinal beam, the upper end of the corrugated plate is connected with the end part of the flexible beam through a tail wire pulley, and the lower end of the corrugated plate is fixedly connected with the rigid longitudinal beam.
4. A variant wing based on piezoelectric actuation according to claim 2 or 3, characterized in that: the rigid longitudinal beam is fixedly connected with the rigid bottom beam, a secondary spar is further arranged at the joint, the bottom end of the secondary spar is fixedly connected with the upper surface of the rigid longitudinal beam, the top end of the secondary spar is slidably connected with the flexible beam, a constraint cross beam is further arranged on the upper portion of the secondary spar, the front end of the constraint cross beam is fixedly connected with the rear end face of the main spar, the rear end of the constraint cross beam is fixedly connected with the upper portion of the secondary spar, guide holes are further formed in the constraint cross beam, rollers are fixedly installed in the guide holes, and a deformation transmission guide rod penetrates through the guide holes and is slidably connected with the rollers.
5. A variant wing based on piezoelectric actuation according to claim 1 or 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 is of a hollow structure.
6. A variant wing based on piezoelectric actuation according to claim 1 or 2 or 3, characterized in that: the lower end face of the rigid bottom beam is arc-shaped, the first driving part is positioned at the front side of the second driving part, and when the diamond-shaped amplifier stretches, 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.
7. A piezoelectric actuation-based morphing wing of claim 4, wherein: the constraint 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011001383.6A CN112109877B (en) | 2020-09-22 | 2020-09-22 | Variant wing based on piezoelectric driving |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011001383.6A CN112109877B (en) | 2020-09-22 | 2020-09-22 | Variant wing based on piezoelectric driving |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112109877A CN112109877A (en) | 2020-12-22 |
| CN112109877B true CN112109877B (en) | 2023-05-26 |
Family
ID=73800391
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011001383.6A Active CN112109877B (en) | 2020-09-22 | 2020-09-22 | Variant wing based on piezoelectric driving |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112109877B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113120219B (en) * | 2021-04-22 | 2022-10-21 | 北京航空航天大学 | Control device, aircraft and control method of flexible wing |
| CN114130611A (en) * | 2021-12-03 | 2022-03-04 | 浙江理工大学 | Dual piezoelectric injection dispensing valve based on four-bar amplification mechanism and adhesive injection method thereof |
| CN114560072A (en) * | 2022-03-02 | 2022-05-31 | 电子科技大学 | Deformable wing based on array structure driving |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9233749B1 (en) * | 2013-12-04 | 2016-01-12 | The United States Of America As Represented By The Secretary Of The Air Force | Variable camber adaptive compliant wing system |
| CN107628229A (en) * | 2017-08-28 | 2018-01-26 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of continuous variable camber structure of the truss-like leading edge of a wing |
| US9896188B1 (en) * | 2013-12-04 | 2018-02-20 | The United States Of America As Represented By The Secretary Of The Air Force | Variable camber adaptive compliant wing system |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5224826A (en) * | 1989-07-26 | 1993-07-06 | Massachusetts Institute Of Technology | Piezoelectric helicopter blade flap actuator |
| US8056865B2 (en) * | 2009-03-05 | 2011-11-15 | The Boeing Company | Mechanism for changing the shape of a control surface |
| CN202345908U (en) * | 2011-09-22 | 2012-07-25 | 西北工业大学 | Wing with movable wing surface |
| US10468545B1 (en) * | 2017-02-28 | 2019-11-05 | Solaero Technologies Corp. | Airfoil body including a moveable section of an outer surface carrying an array of transducer elements |
| CN210258812U (en) * | 2019-04-17 | 2020-04-07 | 陶伟灏 | Morphing wing based on active deformation negative Poisson ratio honeycomb structure |
| CN111162687B (en) * | 2020-01-15 | 2020-12-08 | 中国计量大学 | Large displacement deformation wing based on pre-compression laminated piezoelectric composite double-chip and method thereof |
| CN111232186B (en) * | 2020-02-26 | 2022-12-06 | 大连理工大学 | Variable camber wing of trailing edge of piezoelectricity fiber material driven |
-
2020
- 2020-09-22 CN CN202011001383.6A patent/CN112109877B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9233749B1 (en) * | 2013-12-04 | 2016-01-12 | The United States Of America As Represented By The Secretary Of The Air Force | Variable camber adaptive compliant wing system |
| US9896188B1 (en) * | 2013-12-04 | 2018-02-20 | The United States Of America As Represented By The Secretary Of The Air Force | Variable camber adaptive compliant wing system |
| CN107628229A (en) * | 2017-08-28 | 2018-01-26 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of continuous variable camber structure of the truss-like leading edge of a wing |
Non-Patent Citations (1)
| Title |
|---|
| 变形机翼的关键技术研究现状及其展望;段富海;初雨田;关文卿;来进勇;;空军预警学院学报(第03期);51-57+61 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112109877A (en) | 2020-12-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112109877B (en) | Variant wing based on piezoelectric driving | |
| US7931240B2 (en) | Cellular support structures used for controlled actuation of fluid contact surfaces | |
| CN109515683B (en) | Deformable wing with variable chord length and curvature | |
| Sofla et al. | Shape morphing of aircraft wing: Status and challenges | |
| CN111268092B (en) | Structure for improving torsional rigidity of trailing edge structure of flexible wing | |
| CN108839788B (en) | Variable camber wing trailing edge based on compliant mechanism | |
| Monner et al. | Design aspects of the adaptive wing—the elastic trailing edge and the local spoiler bump | |
| US20080035798A1 (en) | Fluid-driven artificial muscles as mechanisms for controlled actuation | |
| CN109176420B (en) | Middle-mounted movable joint type flexible decoupling precision positioning structure | |
| US20150251747A1 (en) | Smart material trailing edge variable chord morphing wing | |
| Liu et al. | In-plane corrugated cosine honeycomb for 1D morphing skin and its application on variable camber wing | |
| CN103395493A (en) | Piezoelectric ceramic flapping-wing-type robot | |
| Lesieutre et al. | Scaling of performance, weight, and actuation of a 2-D compliant cellular frame structure for a morphing wing | |
| CN111688911B (en) | Deformation wing device based on four-corner star-shaped scissor mechanism and rib plates with variable lengths | |
| CN104900573B (en) | A kind of differential lever micro-displacement amplifying device of symmetrical expression | |
| Wu et al. | A morphing aerofoil with highly controllable aerodynamic performance | |
| Wang et al. | Design and analysis of a configuration-based lengthwise morphing structure | |
| US20240132199A1 (en) | Aircraft wing section assembly | |
| CN113844636B (en) | Omega-shaped flexible skin honeycomb structure | |
| CN109760859B (en) | Active vibration suppression actuating mechanism with flexible structure | |
| CN115806042A (en) | Morphing wing and aircraft | |
| CN116461691A (en) | Airfoil continuous deformation mechanism based on slide bar-flexible truss-skin | |
| CN108050219B (en) | High-bearing truss type high-flexibility mechanism | |
| CN113415409A (en) | Non-control surface aircraft wing with variable camber | |
| CN106655880A (en) | Cross beam bistable device-based piezoelectric steering gear with adjustable angle and control method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |