CN112224384A - Self-adaptive variable camber wing trailing edge based on hierarchical piezoelectric stack driving - Google Patents
Self-adaptive variable camber wing trailing edge based on hierarchical piezoelectric stack driving Download PDFInfo
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- CN112224384A CN112224384A CN202010957740.XA CN202010957740A CN112224384A CN 112224384 A CN112224384 A CN 112224384A CN 202010957740 A CN202010957740 A CN 202010957740A CN 112224384 A CN112224384 A CN 112224384A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
- B64C3/50—Varying camber by leading or trailing edge flaps
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Abstract
The invention discloses a self-adaptive variable camber wing trailing edge based on hierarchical piezoelectric stack driving, which comprises an arc-shaped variable camber upper wing rib, a coordinated deformation straight line lower wing rib and a driving member, wherein the arc-shaped variable camber upper wing rib is arranged on the upper wing rib; the arc-shaped variable-camber upper rib consists of a multi-stage deformation unit and a primary head structural unit; the lower wing rib of the coordinated deformation straight line is connected with the tail deformation unit of the upper wing rib with the arc-shaped variable camber; the driving member is composed of a plurality of stages of driving units; according to the invention, through the graded driving output, the large-amplitude deflection of the trailing edge of the wing is realized by using the piezoelectric driver with micro output, and the trailing edge deflection angle can be changed according to different working conditions while the required load is borne.
Description
Technical Field
The invention relates to the field of aircraft wing design, in particular to a self-adaptive variable camber wing trailing edge based on hierarchical piezoelectric stack driving.
Background
Maneuverability is an important indicator of an aircraft, and is particularly important to the overall performance of the aircraft. Efficient, flexible and safe execution of diverse flight missions relies heavily on good design of aircraft wings. Adjusting the profile of the wing in real time during flight can improve the aerodynamic performance of the wing, including changing the sweep angle, wing span, wing camber, etc.
The development of "morphing wings" has been over 100 years, and control surfaces have evolved from early morphing control surfaces to the commonly used control surfaces of leading and trailing edge flaps, etc. At present, the design of the 'morphing wing' is mainly divided into two types, wherein the first morphing comprises variable chord length, variable sweepback angle and the like, namely in-plane morphing. Another type of deformation includes varying chordwise camber, varying spanwise camber, varying wing twist angle, etc., i.e., out-of-plane deformation. Among them, the change of the camber of the trailing edge of the wing has been widely studied because it has a small influence on the whole and at the same time has a significant effect on the aerodynamic performance enhancement. In the research of the camber of the trailing edge of the wing, a lot of results are available from a rigid structure to a flexible structure of a system, and from a conventional material to a functional novel material. In the existing traditional deflection design, a hinge structure is mostly adopted, and the design not only increases the weight of the airplane, but also is easy to cause fatigue failure. In modern morphing wing design, people inspire from the nature and provide a self-adaptive wing, and a wing trailing edge for controlling morphing in real time is designed by using intelligent materials and derivative products thereof and integrating a multidisciplinary intersection technology. In the existing design based on novel functional materials, the variable rear edge adopts large-range linear output to drive the lower surface of the rear edge to do linear motion, so that the rear edge deflection is realized through elastic coordinated deformation, however, the single-point output of the method in the engineering practice is difficult to realize.
Disclosure of Invention
Aiming at two technical difficulties of realizing large-range deflection and supporting load in the current variable trailing edge design, the invention provides a self-adaptive variable camber wing trailing edge based on hierarchical piezoelectric stack driving on the premise of not increasing the structural weight and complexity, a driving unit provides displacement input, and the output of a deflection angle is realized in an elastic deformation mode of an integral structure. The invention realizes the large-amplitude deflection of the micro-input piezoelectric driver to the rear edge through the hierarchical driving structure, and realizes the required deflection output under the load through the good coordination of the rigidity and the flexibility.
In order to achieve the purpose, the invention adopts the following technical scheme:
the self-adaptive variable camber wing trailing edge based on the hierarchical piezoelectric stack driving comprises an arc variable camber upper wing rib, a coordinated deformation straight line lower wing rib 8 and a driving member; the arc-shaped variable-camber upper rib comprises a head structural unit 1, a middle deformation unit and a tail deformation unit 4, wherein the head structural unit 1 is of a flanged rectangular structure, the middle deformation unit comprises a multi-stage deformation member, each stage of deformation member is a combined structure of an upper arc 3 and a lower flanged rectangular 7, the tail deformation unit 4 is of a bevel edge arc right-angle triangular structure with an arc-shaped replacing bevel edge, and the head structural unit 1, the middle deformation unit and the tail deformation unit 4 are sequentially connected through flexible hinges 2 to form the arc-shaped variable-camber upper rib; the coordinated deformation straight lower wing rib 8 is positioned at the bottom of the arc-shaped variable camber upper wing rib, is horizontally connected with a right-angle side of the tail deformation unit 4, and forms a wing trailing edge structural framework together with the arc-shaped variable camber upper wing rib as a whole; the driving member comprises a plurality of stages of driving units 6, each stage of driving unit is positioned below the flexible hinge 2, and a lower flange of the upper section of deformation unit or the head structure unit and an upper flange of the lower section of deformation unit are used as contact surfaces and are arranged between the stages of deformation units of the arc-shaped variable-camber upper wing rib at a preset angle in the anticlockwise direction of a horizontal line.
The preset angle is 45 °.
The arc bevel edge right-angled triangle structure of the tail deformation unit 4 is internally excavated to remove redundant mass, only a frame with a certain width and a spar 9 are reserved to ensure the sufficient rigidity of the structure, and the tail edge tip 5 of the tail deformation unit 4 can bear sufficient load while realizing elastic deformation; the width of the wing beam 9 is 2mm, and an acute angle formed between the wing beam and the horizontal line in the anticlockwise direction is within 60-80 degrees.
The driving unit 6 consists of a piezoelectric stack and a displacement amplification component, the length of the piezoelectric stack is 95mm, and the maximum displacement of 300um can be output by 100V voltage when no load exists; the displacement amplification component is characterized in that four corners of an original rhombus are connected through straight edges so that a piezoelectric stack is mounted inside and integrally arranged between the hierarchical deformation units, the piezoelectric stack is positioned between long diagonal edges of the displacement amplification component, and the long diagonal edges of the amplification component are in contact with the arc-shaped variable-camber upper rib; among the four connected straight sides of the displacement amplification component, the short opposite side distance is 25mm, the long opposite side distance is 95mm, the frame structure thickness is 2.5mm, and the side width is 5 mm.
The flexible hinge 2 is an arc-shaped flexible hinge formed by arc cutting, the cutting radius is 4mm, the minimum thickness is 9mm, and the hinge width is 2 mm; the flexible hinge 2 enables maximum use of the displacement output of the drive member while ensuring sufficient rigidity of the structure.
The staged driving component pushes the arc-shaped variable-camber upper wing rib to generate bending deformation, and the tail deformation unit 4 pulls the coordinated deformation straight-line lower wing rib 8 to generate coordinated deformation, so that the deflection angle output of the whole wing trailing edge is realized; for the trailing edge of the wing with the three-level deformation unit and the three-level driving unit, when no input exists, the frame structure is 266mm long, 70mm high and 2mm thick, the material is 7050 aluminum, and when 1Kg of vertical downward load is applied to the tip 5 of the trailing edge, only the first-level driving input x is 500um, so that the load part can be vertically displaced upwards by 14.9mm, and the deflection angle of the whole structure is 5.2 degrees; when the first-stage drive input x-y is 500um and the second-stage drive input x-y is 350um, the vertical upward displacement is 19.9mm, and the deflection angle of the whole structure is 6.7 degrees; when the first stage drive input x-y-500 um, the second stage drive input x-y-350 um, and the third stage drive input x-y-350 um, a vertical upward displacement of 22.4mm occurs, and the overall structure is deflected by an angle of 8.3 °.
Has the advantages that:
compared with the similar existing design, the self-adaptive variable camber wing trailing edge based on the hierarchical piezoelectric stack driving has the advantages of simple structure, light weight, low development cost and the like. The technical scheme of the invention can improve the aerodynamic performance of the aircraft, improve the flexibility and maneuverability of the aircraft and reduce the oil consumption. The invention avoids the traditional mechanical hinge structure, has high efficiency and brief introduction of design, and has no negative effects of noise, vibration and the like. On the basis of traditional linear output, the invention innovatively uses hierarchical drive, so that the structure can output large deflection and bear rated load.
Drawings
FIG. 1 is a schematic diagram of a structure of a trailing edge of an adaptive variable camber airfoil based on hierarchical piezoelectric stack driving.
FIG. 2 is a schematic diagram of a structure of a driving unit in an adaptive variable camber wing trailing edge based on hierarchical piezoelectric stack driving.
Fig. 3 is a schematic diagram showing a structural modification of the first stage when the first stage drive input x-y-500 um.
Fig. 4 is a schematic diagram illustrating a structural modification of the first stage drive input x-y-500 um and the second stage drive input x-y-350 um.
Fig. 5 is a schematic structural modification diagram when the first-stage drive input x-y-500 um, the second-stage drive input x-y-350 um, and the third-stage drive input x-y-350 um.
Detailed Description
The invention is described in further detail below with reference to the following figures and specific embodiments.
As shown in fig. 1, the self-adaptive variable camber trailing edge driven by a hierarchical piezoelectric stack according to the present invention includes an arc-shaped variable camber upper rib, a coordinated deformation straight lower rib 8, and a driving member; the arc-shaped variable-camber upper rib comprises a head structural unit 1, a middle deformation unit and a tail deformation unit 4, wherein the head structural unit 1 is of a flanged rectangular structure, the middle deformation unit comprises a multi-stage deformation member, each stage of deformation member is a combined structure of an upper arc 3 and a lower flanged rectangular 7, the tail deformation unit 4 is of a bevel edge arc right-angle triangular structure with an arc-shaped replacing bevel edge, and the head structural unit 1, the middle deformation unit and the tail deformation unit 4 are sequentially connected through flexible hinges 2 to form the arc-shaped variable-camber upper rib; the coordinated deformation straight lower wing rib 8 is positioned at the bottom of the arc-shaped variable camber upper wing rib, is horizontally connected with a right-angle side of the tail deformation unit 4, and forms a wing trailing edge structural framework together with the arc-shaped variable camber upper wing rib as a whole; the driving member comprises a plurality of stages of driving units 6, each stage of driving unit is positioned below the flexible hinge 2, and a lower flange of the upper section of deformation unit or the head structure unit and an upper flange of the lower section of deformation unit are used as contact surfaces and are arranged between the stages of deformation units of the arc-shaped variable-camber upper wing rib at an angle of 45 degrees along the anticlockwise direction of a horizontal line.
As shown in fig. 1, as a preferred embodiment of the present invention, the curved hypotenuse right triangle structure of the tail deforming unit 4 is hollowed out of the excess mass, and only a frame with a certain width and a spar 9 are reserved for ensuring sufficient rigidity of the structure, and the rear edge tip 5 of the tail deforming unit 4 can bear sufficient load while achieving the overall elastic deformation. The width of the wing beam 9 is 2mm, and an acute angle formed between the wing beam and the horizontal line in the anticlockwise direction is within 60-80 degrees.
As shown in fig. 2, the driving unit 6 is made of a piezoelectric stack and a displacement amplifying member as a preferred embodiment of the present invention. Piezoelectric stack is long 95mm, 100V voltage outputable maximum displacement 300um when no load. The displacement amplification component is characterized in that four corners of an original rhombus are connected through straight edges, so that a piezoelectric stack is mounted inside and integrally arranged between the hierarchical deformation units, the piezoelectric stack is located between long diagonal edges of the displacement amplification component, and the long diagonal edges of the amplification component are in contact with the arc-shaped variable-camber upper rib. Among the four connected straight sides of the displacement amplification component, the short opposite side distance is 25mm, the long opposite side distance is 95mm, the frame structure thickness is 2.5mm, and the side width is 5 mm.
As a preferred embodiment of the invention, the flexible hinge 2 is a circular arc flexible hinge formed by circular arc cutting, the cutting radius is 4mm, the minimum thickness is 9mm, and the hinge width is 2 mm. The flexible hinge 2 enables maximum use of the displacement output of the drive member while ensuring sufficient rigidity of the structure.
As shown in fig. 1, 3, 4 and 5, the stepped driving member pushes the arc-shaped variable camber upper rib to generate bending deformation, and the tail deformation unit 4 pulls the coordinative deformation straight lower rib 8 to generate coordinative deformation, so that the deflection angle output of the whole wing trailing edge is realized. For the trailing edge of the wing with the three-stage deformation unit and the three-stage driving unit, when no input exists, the frame structure is 266mm long, 70mm high and 2mm thick, the material is 7050 aluminum, when the tip 5 of the trailing edge of the wing is loaded vertically downwards by 1Kg, only the first-stage driving input x is equal to y and is equal to 500um, the load part can be vertically upwards displaced by 14.9mm, and the deflection angle of the whole structure is 5.2 degrees; when the first-stage drive input x-y is 500um and the second-stage drive input x-y is 350um, the vertical upward displacement is 19.9mm, and the deflection angle of the whole structure is 6.7 degrees; when the first stage drive input x-y-500 um, the second stage drive input x-y-350 um, and the third stage drive input x-y-350 um, a vertical upward displacement of 22.4mm occurs, and the overall structure is deflected by an angle of 8.3 °.
Claims (6)
1. Self-adaptation variable camber wing trailing edge based on hierarchical piezoelectric stack drive its characterized in that: comprises an arc-shaped variable-camber upper rib, a coordinated deformation straight lower rib (8) and a driving member; the arc-shaped variable-camber upper wing rib comprises a head structural unit (1), a middle deformation unit and a tail deformation unit (4), wherein the head structural unit (1) is of a flanged rectangular structure, the middle deformation unit comprises a multi-stage deformation member, each stage of deformation member is of a combined structure of an upper arc (3) and a lower flanged rectangular (7), the tail deformation unit (4) is of an arc-shaped hypotenuse right-angled triangle structure with an arc-shaped substituted hypotenuse, and the head structural unit (1), the middle deformation unit and the tail deformation unit (4) are sequentially connected through flexible hinges (2) to form the arc-shaped variable-camber upper wing rib; the lower wing rib (8) of the coordinated deformation straight line is positioned at the bottom of the upper wing rib with the variable camber and is horizontally connected with a right-angle side of the tail deformation unit (4), and the lower wing rib and the upper wing rib with the variable camber form a wing trailing edge structural frame as a whole; the driving member comprises a plurality of stages of driving units (6), each stage of driving unit is positioned below the flexible hinge (2), and a lower flange of the upper section of deformation unit or the head structure unit and an upper flange of the lower section of deformation unit are used as contact surfaces and are arranged between the stages of deformation units of the arc-shaped variable-camber upper wing ribs at preset angles in the anticlockwise direction of a horizontal line.
2. The adaptive variable camber trailing edge based on hierarchical piezoelectric stack driving according to claim 1, wherein: the arc bevel edge right-angled triangle structure of the tail deformation unit (4) is internally dug to remove redundant mass, only a frame with a certain width and a wing beam (9) are reserved for ensuring enough rigidity of the structure, and the tail edge tip (5) of the tail deformation unit (4) can bear enough load while elastic deformation is realized; the width of the wing beam (9) is 2mm, and an acute angle formed by the wing beam and the horizontal line in the anticlockwise direction is within 60-80 degrees.
3. The adaptive variable camber trailing edge based on hierarchical piezoelectric stack driving according to claim 1, wherein: the driving unit (6) consists of a piezoelectric stack and a displacement amplification component, the length of the piezoelectric stack is 95mm, and the maximum displacement of 300um can be output by 100V voltage when no load exists; the displacement amplification component is characterized in that four corners of an original rhombus are connected through straight edges so that a piezoelectric stack is mounted inside and integrally arranged between the hierarchical deformation units, the piezoelectric stack is positioned between long diagonal edges of the displacement amplification component, and the long diagonal edges of the amplification component are in contact with the arc-shaped variable-camber upper rib; among the four connected straight sides of the displacement amplification component, the short opposite side distance is 25mm, the long opposite side distance is 95mm, the frame structure thickness is 2.5mm, and the side width is 5 mm.
4. The adaptive variable camber trailing edge based on hierarchical piezoelectric stack driving according to claim 1, wherein: the flexible hinge (2) is an arc-shaped flexible hinge formed by arc cutting, the cutting radius is 4mm, the minimum thickness is 9mm, and the hinge width is 2 mm; the flexible hinge (2) enables maximum use of the displacement output of the drive member while ensuring sufficient rigidity of the structure.
5. The adaptive variable camber trailing edge based on hierarchical piezoelectric stack driving according to claim 1, wherein: the staged driving component pushes the arc-shaped variable-camber upper wing rib to generate bending deformation, and the tail deformation unit (4) pulls the coordinated deformation straight line lower wing rib (8) to generate coordinated deformation, so that the deflection angle output of the whole wing trailing edge is realized; for the trailing edge of the wing with the three-stage deformation unit and the three-stage driving unit, when no input exists, the frame structure is 266mm long, 70mm high and 2mm thick, the material is 7050 aluminum, and when the tip (5) of the trailing edge is loaded vertically downwards by 1Kg, only the first-stage driving input x is equal to y and is equal to 500um, so that the load part can be vertically upwards displaced by 14.9mm, and the deflection angle of the whole structure is 5.2 degrees; when the first-stage drive input x-y is 500um and the second-stage drive input x-y is 350um, the vertical upward displacement is 19.9mm, and the deflection angle of the whole structure is 6.7 degrees; when the first stage drive input x-y-500 um, the second stage drive input x-y-350 um, and the third stage drive input x-y-350 um, a vertical upward displacement of 22.4mm occurs, and the overall structure is deflected by an angle of 8.3 °.
6. The adaptive variable camber trailing edge based on hierarchical piezoelectric stack driving according to claim 1, wherein: the preset angle is 45 °.
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Cited By (2)
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| CN114104262A (en) * | 2021-11-29 | 2022-03-01 | 中电科技集团重庆声光电有限公司 | Deformable wing assembly |
| CN114261507A (en) * | 2021-12-23 | 2022-04-01 | 北京理工大学 | Self-adaptive deformation driving unit and deformation driving mechanism |
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