CN114560072A - Deformable wing based on array structure driving - Google Patents
Deformable wing based on array structure driving Download PDFInfo
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- CN114560072A CN114560072A CN202210199144.9A CN202210199144A CN114560072A CN 114560072 A CN114560072 A CN 114560072A CN 202210199144 A CN202210199144 A CN 202210199144A CN 114560072 A CN114560072 A CN 114560072A
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- 239000000919 ceramic Substances 0.000 claims description 8
- 239000000758 substrate Substances 0.000 claims description 7
- 239000000446 fuel Substances 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000006870 function Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 230000003321 amplification Effects 0.000 description 2
- 239000003989 dielectric material Substances 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000005684 electric field Effects 0.000 description 2
- 238000003199 nucleic acid amplification method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010344 co-firing Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 230000010287 polarization Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 229910001285 shape-memory alloy Inorganic materials 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
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Abstract
The invention discloses a deformable wing based on array structure driving, which comprises a deformable main wing and a non-deformable aileron, wherein the main wing and the aileron are connected through bolts; the ailerons are arranged on the upper side and the lower side of the main wing, and a gap is arranged between the main wing and the ailerons; the array type driving device is arranged in the front edge of the main wing, and when the array type driving device is electrified, the array type driving device contracts along the width direction to drive the main wing to contract, and the rear edge of the deformable wing bends downwards. The invention discloses a deformable wing based on array structure driving, which innovatively uses a three-section wing layout design and uses two non-deformable ailerons for rectification, so that airflow flowing through a deformable main wing is more stable, the airflow utilization efficiency of the wing is increased, fuel is saved, and the flight efficiency is improved.
Description
Technical Field
The invention belongs to the technical field of aerospace, and particularly relates to a deformable wing driven by an array structure.
Background
In the process of flying, in order to adapt to different flying environments, save fuel to the maximum extent and improve the flying efficiency, the wings are required to provide different lift forces, and the camber of the wings is required to be adjusted. The traditional wing changes the camber of the wing by mechanically operating the flap and the aileron of the wing, and the mode causes the weight of the wing to be increased and the structure to be complicated. In recent years, researchers hope that the purpose of changing the camber of the wing is achieved through the deformation of the wing body under the condition that an additional structure is not added outside the wing, and the effect of the deformation wing is achieved.
The existing technical scheme is that the wing achieves a deformation effect by heating the memory alloy, but the structural strength of the wing is weak, the deformation process is slow, the wing is driven to deform by a complex mechanical device, the overall weight of the wing is increased by the scheme, the complexity of a system is improved, the maintenance cost is high, the deformation is achieved by attaching a piezoelectric material to the surface of the wing, the overall structure of the wing is simple and reliable, but the deformation process is sudden change, and the shape of the wing is difficult to change linearly.
Disclosure of Invention
The invention provides a deformable wing driven based on an array structure, and aims to solve the existing problems.
The invention is realized in such a way that the deformable wing driven based on the array structure comprises a deformable main wing and a non-deformable aileron, wherein the main wing and the aileron are connected through a bolt;
the ailerons are arranged on the upper side and the lower side of the main wing, and a gap is arranged between the main wing and the ailerons;
the array type driving device is arranged in the front edge of the main wing, and when the array type driving device is electrified, the array type driving device contracts along the width direction to drive the main wing to contract, and the rear edge of the deformable wing bends downwards.
Further, the gap between the main wing and the auxiliary wing is 0.5mm-1.5 mm.
Furthermore, two stringers are arranged on the top surface of the inner portion of the front edge of the main wing, and two ends of the array type driving device are respectively installed on the stringers.
Furthermore, the array type driving device comprises two mounting plates and a plurality of deformation units arranged between the two mounting plates in an array manner, and two ends of each deformation unit are respectively fixed on the mounting plates.
Furthermore, the mounting plate is provided with a mounting sleeve, the stringer is provided with a mounting bolt, and two ends of the array type driving device are respectively mounted on the stringer through the mounting sleeve and the mounting bolt.
Furthermore, the deformation unit comprises two elliptical deformation shells which are arranged in series, and a square-column-shaped piezoelectric stack block is embedded in each elliptical deformation shell.
Further, the piezoelectric stack block comprises a plurality of piezoelectric ceramic substrates which are stacked, and the plurality of piezoelectric ceramic substrates are bonded and co-fired to form the piezoelectric stack block.
Furthermore, when the piezoelectric stack block is electrified, the piezoelectric stack block extends along the long axis direction of the elliptical deformation shell, so that the elliptical deformation shell contracts along the short axis direction, and the array type driving device is driven to contract along the width direction.
Compared with the prior art, the invention has the beneficial effects that: the invention discloses a deformable wing based on array structure drive, innovatively uses a three-section wing layout design, and uses two non-deformable ailerons for rectification, so that airflow flowing through a deformable main wing is more stable, the airflow utilization efficiency of the wing is increased, fuel is saved, and the flight efficiency is improved; complex stringer and rib structures in the main wing are abandoned, the structural strength of the wing is enhanced innovatively by using an array type deformation driving structure, the strength requirement is met, and the weight of the wing is reduced; the array type deformation driving device innovatively uses an oval structural design, so that the deformation displacement can be increased, the wing can realize the deformation function by using a small amount of piezoelectric deformation materials with small volume, the internal space is saved, and the weight of the wing is reduced.
Drawings
FIG. 1 is a schematic view of a main wing according to the present invention;
FIG. 2 is a schematic view of a wing structure according to the present invention;
FIG. 3 is a schematic diagram of an array driving device according to the present invention;
in the figure: the structure comprises a main wing 1, an aileron 2, a stringer 3, an array type driving device 4, an installation bolt 5, an installation plate 6, an installation sleeve 7, a deformation unit 8, an elliptical deformation shell 9 and a piezoelectric stacking block 10.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Further, in the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
Referring to fig. 1-3, the present invention provides a technical solution: a deformable wing driven based on an array structure comprises a deformable main wing 1 and a non-deformable auxiliary wing 2, wherein the main wing 1 and the auxiliary wing 2 are connected through bolts;
the ailerons 2 are arranged on the upper side and the lower side of the main wing 1, and a gap is arranged between the main wing 1 and the ailerons 2;
the array type driving device 4 is installed inside the front edge of the main wing 1, when the array type driving device 4 is powered on, the array type driving device 4 contracts along the width direction to drive the main wing 1 to contract, and the rear edge of the morphing wing bends downwards.
Wherein, the clearance between the main wing 1 and the ailerons 2 is 0.5mm-1.5 mm.
The morphing wing designed by the invention mainly comprises a main morphing wing 1 and an auxiliary morphing wing 2, wherein the main morphing wing 1 and the auxiliary morphing wing 2 are fixedly connected by bolts, a gap of 1mm is reserved between the main morphing wing 1 and the auxiliary morphing wing 2, the auxiliary morphing wing 2 at two sides can provide the function of rectification, the airflow flowing through the surface of the main morphing wing 1 is more stable, and the aerodynamic performance of the wing is improved.
In this embodiment, two stringers 3 are disposed on the top surface of the front edge of the main wing 1, two ends of the array type driving device 4 are respectively mounted on the stringers 3, the array type driving device 4 includes two mounting plates 6, and a plurality of deformation units 8 arranged between the two mounting plates 6 in an array manner, two ends of each deformation unit 8 are respectively fixed on the mounting plates 6, a mounting sleeve 7 is disposed on the mounting plate 6, a mounting pin 5 is disposed on the stringer 3, and two ends of the array type driving device 4 are respectively mounted on the stringers 3 through the mounting sleeve 7 and the mounting pin 5.
The upper surface of the inside of the main wing 1 of the invention is provided with a stringer 3 for reinforcing the structure and conducting the acting force, and a bolt on the stringer 3 is used for installing and fixing an array type driving device 4. Without the complicated beams 3 and ribs, the structure is simple and compact, the weight is lighter, and the array type driving device 4 can provide enough structural strength.
Specifically, the deformation unit 8 includes two elliptical deformation shells 9 connected in series, a square-column piezoelectric stack block 10 is embedded in each elliptical deformation shell 9, the piezoelectric stack block 10 includes a plurality of piezoelectric ceramic substrates stacked in a stacked manner, and the piezoelectric ceramic substrates are co-fired by bonding to form the piezoelectric stack block 10.
When the piezoelectric stack block 10 is powered on, the piezoelectric stack block 10 extends along the long axis direction of the elliptical deformation shell 9, so that the elliptical deformation shell 9 contracts along the short axis direction, and the array type driving device 4 is driven to contract along the width direction.
The array type driving device 4 consists of an array basic deformation unit 8 and mounting plates 6 on two sides, and is fixed inside the main wing 1 through mounting sleeves 7 on the mounting plates 6, and the mounting plates 6 and the mounting sleeves 7 are connected through bolts.
The basic deformation unit 8 is formed by connecting two elliptical deformation shell 9 structures in series, and a square column-shaped piezoelectric stack block 10 is embedded in the middle of each elliptical deformation shell 9 structure. The piezoelectric stack 10 is a square columnar stack formed by stacking a plurality of piezoelectric ceramic substrates and co-firing them by bonding. When direct current is applied to the piezoelectric stack 10, an inverse piezoelectric effect is generated, which causes mechanical deformation of the piezoelectric stack 10. Due to the strong anisotropy of the piezoelectric ceramics, the square-column-shaped piezoelectric stack block 10 can deform along the long axis direction of the elliptical shell, thereby participating in the actuation of the structure of the elliptical deformation shell 9.
The inverse piezoelectric effect means that when an electric field is applied in the polarization direction of dielectrics, the dielectrics generate mechanical deformation or mechanical pressure in a certain direction, and when the applied electric field is removed, the deformation or stress disappears.
Anisotropy refers to a property in which all or part of chemical and physical properties of a substance change with a change in direction, and the substance exhibits a difference in different directions.
The actuation along the major axis direction of the elliptical deformation shell 9 enables the shell structure to extend along the major axis direction and contract along the minor axis direction, so as to drive the array type driving device 4 to contract along the width direction, further drive the main wing 1 to contract, and bend the trailing edge of the wing downwards, thereby achieving the purpose of changing the camber of the wing. The limiting structures on two sides of the elliptical deformation shell 9 can prevent the mechanism from being damaged due to too large deformation.
The basic deformation unit 8 is designed to be elliptical, so that the ellipse has a displacement amplification function, and small deformation in the major axis direction can generate larger deformation in the minor axis direction through the amplification of the ellipse. The deformation effect can be further increased by connecting two ellipses in series, and the acting force can be increased by connecting four deformation units 8 in parallel.
The invention abandons the complex structure in the traditional wing, uses the array structure to strengthen the structural strength of the wing, makes the structure of the wing more compact and lighter under the condition of meeting the strength requirement, saves fuel and improves the flight efficiency.
The piezoelectric material is used for deformation, so that the whole structure is simple and reliable, the deformation process is efficient and controllable, the deformation of the piezoelectric material is usually small, the array-type elliptical structure is used, the deformation can be amplified, the deformation effect meeting the requirement can be achieved by stacking the piezoelectric material with small volume, the inner space of the wing is saved, the weight of the wing is reduced, and the flight efficiency is improved.
The acting force of the array type deformation structure is more uniform, so that the deformation of the wings can be carried out linearly, the lifting force which can be provided in the deformation range is more linear, and the airplane provided with the array type deformation wings can adapt to more complex flight environments.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A deformable wing based on array structure drive comprises a deformable main wing and a non-deformable aileron, wherein the main wing and the aileron are connected through bolts, and the deformable main wing and the aileron are characterized in that:
the ailerons are arranged on the upper side and the lower side of the main wing, and a gap is arranged between the main wing and the ailerons;
the array type driving device is arranged in the front edge of the main wing, and when the array type driving device is electrified, the array type driving device contracts along the width direction to drive the main wing to contract, and the rear edge of the deformable wing bends downwards.
2. The array-based architecture driven morphing wing of claim 1, wherein: the gap between the main wing and the auxiliary wing is 0.5mm-1.5 mm.
3. The array-based actuated morphing wing of claim 1, wherein: two stringers are arranged on the top surface of the inner part of the front edge of the main wing, and two ends of the array type driving device are respectively installed on the stringers.
4. The array-based actuated morphing wing of claim 3, wherein: the array type driving device comprises two mounting plates and a plurality of array type deformation units arranged between the two mounting plates, wherein two ends of each deformation unit are respectively fixed on the mounting plates.
5. The array-based actuated morphing wing of claim 4, wherein: the array type driving device is characterized in that the mounting plate is provided with a mounting sleeve, the stringer is provided with a mounting bolt, and two ends of the array type driving device are mounted on the stringer through the mounting sleeve and the mounting bolt respectively.
6. The array-based actuated morphing wing of claim 4, wherein: the deformation unit comprises two elliptical deformation shells which are connected in series, and a square-column-shaped piezoelectric stack block is embedded in each elliptical deformation shell.
7. The array-based architecture driven morphing wing of claim 6, wherein: the piezoelectric stacking block comprises a plurality of piezoelectric ceramic substrates which are arranged in a laminated mode, and the piezoelectric ceramic substrates are bonded and co-fired to form the piezoelectric stacking block.
8. The array-based actuated morphing wing of claim 6, wherein: when the piezoelectric stacking block is electrified, the piezoelectric stacking block extends along the long axis direction of the elliptical deformation shell, so that the elliptical deformation shell contracts along the short axis direction, and the array type driving device is driven to contract along the width direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210199144.9A CN114560072A (en) | 2022-03-02 | 2022-03-02 | Deformable wing based on array structure driving |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210199144.9A CN114560072A (en) | 2022-03-02 | 2022-03-02 | Deformable wing based on array structure driving |
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| CN114560072A true CN114560072A (en) | 2022-05-31 |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2281268A (en) * | 1993-08-19 | 1995-03-01 | Westland Helicopters | Circulation control aerofoils. |
| KR20050061636A (en) * | 2003-12-18 | 2005-06-23 | 한국항공우주연구원 | Wing apparatus for micro aerial vehicle with elastic wing part |
| US20150251747A1 (en) * | 2014-03-05 | 2015-09-10 | Toyota Motor Engineering & Manufacturing North America, Inc. | Smart material trailing edge variable chord morphing wing |
| CN111717368A (en) * | 2020-07-01 | 2020-09-29 | 电子科技大学 | Flexible wing structure based on shape memory alloy and manufacturing method thereof |
| CN112109877A (en) * | 2020-09-22 | 2020-12-22 | 中国石油大学(华东) | Novel morphing wing based on piezoelectric drive |
| CN112550663A (en) * | 2020-12-08 | 2021-03-26 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Deformable wing based on intelligent driving device |
| CN114084342A (en) * | 2021-12-09 | 2022-02-25 | 重庆邮电大学 | Flexible deformable wing control system based on piezoelectric fiber composite material |
| 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 |
-
2022
- 2022-03-02 CN CN202210199144.9A patent/CN114560072A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2281268A (en) * | 1993-08-19 | 1995-03-01 | Westland Helicopters | Circulation control aerofoils. |
| KR20050061636A (en) * | 2003-12-18 | 2005-06-23 | 한국항공우주연구원 | Wing apparatus for micro aerial vehicle with elastic wing part |
| US20150251747A1 (en) * | 2014-03-05 | 2015-09-10 | Toyota Motor Engineering & Manufacturing North America, Inc. | Smart material trailing edge variable chord morphing wing |
| CN111717368A (en) * | 2020-07-01 | 2020-09-29 | 电子科技大学 | Flexible wing structure based on shape memory alloy and manufacturing method thereof |
| CN112109877A (en) * | 2020-09-22 | 2020-12-22 | 中国石油大学(华东) | Novel morphing wing based on piezoelectric drive |
| CN112550663A (en) * | 2020-12-08 | 2021-03-26 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Deformable wing based on intelligent driving device |
| 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 |
| CN114084342A (en) * | 2021-12-09 | 2022-02-25 | 重庆邮电大学 | Flexible deformable wing control system based on piezoelectric fiber composite material |
Non-Patent Citations (1)
| Title |
|---|
| 周学凡，王 露，刘 媛，王登攀，李 军，薛国梁，罗 行，张 斗: "静电纺丝法制备锆钛酸钡钙纳米线及其压电性能" * |
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Application publication date: 20220531 |