CN111232186A - Variable camber wing of trailing edge of piezoelectricity fiber material driven - Google Patents
Variable camber wing of trailing edge of piezoelectricity fiber material driven Download PDFInfo
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- CN111232186A CN111232186A CN202010121861.0A CN202010121861A CN111232186A CN 111232186 A CN111232186 A CN 111232186A CN 202010121861 A CN202010121861 A CN 202010121861A CN 111232186 A CN111232186 A CN 111232186A
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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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Abstract
The invention provides a trailing edge variable camber wing driven by piezoelectric fiber materials. The invention comprises a front edge fixed section with invariable camber, a rear edge flexible deformation section with variable camber and a piezoelectric fiber composite material driver for adjusting the change degree of the rear edge flexible deformation section. The trailing edge flexible deformation section comprises a flexible wing rib, a stringer, a deformation skin, a segmented deformation skin and a segmented deformation skin fixing device. The piezoelectric fiber composite material driver is excited by applying voltage, and the generated torque is transmitted to the flexible wing rib structure through the skin, so that the shape of the trailing edge of the wing is continuously and smoothly changed. The invention can greatly reduce the structural quality of the wing, reduce noise and improve stealth characteristics, and can realize accurate control of the camber change of the wing in the flight process by combining a corresponding deformation control system, improve the maneuvering and stalling characteristics of the airplane and greatly enhance the task adaptability of the airplane.
Description
Technical Field
The invention relates to the technical field of aviation products, in particular to a trailing edge variable camber wing driven by piezoelectric fiber materials.
Background
With the continuous improvement of the military and civil field on the performance requirements of the aircraft, the traditional wing has bottlenecks in the aspects of improving the task adaptability of the aircraft, improving the aerodynamic efficiency of the aircraft and the like, and an effective and feasible solution needs to be discussed urgently. The wing deformation technology provides a new method and a new idea for improving the task adaptability of the aircraft.
Morphing wing design concepts have long been known. In 1903, the first airplane of the laite brother realized the control of the flight state in a way of torsional deformation of the wings. 1920, Parker proposed a camber wing design concept that combines mechanical motion with compliant structure. Since the 20 th century and the 80 th century, active deformation technology of wings draws wide attention, research organizations such as the American air force laboratory (AFRL), the defense advanced research program office (DARPL) and the American aerospace administration (NASA) develop research on a series of projects such as a task adaptive Wing (MAW), an Active Flexible Wing (AFW), an intelligent Wing (Smart Wing) and an Active Aeroelastic Wing (AAW) in sequence; the european related countries have also been continuously researching active deformation technology of wing, most of which are developed in european union framework program, and the related projects which have been developed or are in progress are mainly CHANGE, sarristu, SMS and 3AS projects, etc. The research on the deformable wing starts late in China, but relatively rich research results are obtained, and the relevant research results are mainly concentrated on Beijing aerospace university, Nanjing aerospace university, northwest industrial university, Harbin industrial university and the like.
Morphing wings have numerous advantages over conventional wings. Firstly, the shape of the aircraft can be actively changed according to the change of the flight environment and the mission so as to improve the pneumatic performance and meet the requirement of completing multiple missions under the condition of changing flight; in addition, the deformable wing mostly adopts a continuous and smooth deformable structure to replace the traditional discrete control surface, so that the adhesion flow can be maintained to the maximum extent, the pressure distribution is optimized, the stealth performance is improved, and the noise pollution is reduced.
As mentioned above, the design and development of the morphing wing have important scientific research value and higher research heat. At the present stage, although researchers at home and abroad carry out a great deal of research on the wing deformation technology, a plurality of problems still exist to limit the application and development of the technology. For example, in a task adaptive wing project in the united states, an adaptive variable camber structure with multiple hinges is designed for an F-111 aircraft, and a traditional hydraulic actuator is adopted to drive a wing to generate camber change, but finally, further research on the project is stopped due to the reasons of complex deformation structure, high weight loss and the like. Relevant researchers of Nanjing aerospace university and northwest industry university also successively design multi-hinged variable camber self-adaptive wings driven by a plurality of stepping motors, and the wings also have the defects of complex structure, easy blocking and the like, and the pneumatic benefit brought by wing deformation even cannot offset the weight loss brought by additionally arranging a deformation structure. Besides traditional driving mechanisms such as motors and hydraulic motors, intelligent material drivers such as pneumatic muscles, shape memory alloys and ultrasonic motors are widely applied to the design of the deformed wings, but the drivers have corresponding limitations, for example, the shape memory alloys have low driving speed, and the rapid and accurate tracking of the deformation instructions of the wings is difficult to realize. The control precision of pneumatic muscles is general, and a hysteresis effect exists. Whether the service life and the fatigue resistance degree of the ultrasonic motor can meet the performance requirement of long-time service of the wing is still examined.
The main difficulties of the prior variable camber wing design scheme are focused on the following two aspects: (1) the design of the lightweight flexible supporting structure with pneumatic bearing capacity and flexible deformation capacity; (2) a lightweight high output driver design.
Disclosure of Invention
According to the technical problems, the variable trailing edge camber wing driven by the piezoelectric fiber composite material is provided, the composite material MFC with high energy density is used as a wing deformation driver, a corrugated structure is adopted in a wing rib structure of the wing, and the wing has extreme anisotropy performance, so that the contradiction between the compliance deformation capacity and the pneumatic bearing capacity is solved, and the defects that structural gaps exist in the traditional multi-hinged deformation wing rib design and the wing skin is difficult to adapt are overcome. The technical means adopted by the invention are as follows:
a piezoelectric fiber material driven trailing edge variable camber wing is composed of a leading edge fixing section with invariable camber, a trailing edge flexible deformation section with variable camber and a piezoelectric fiber composite material driver for adjusting the change degree of the trailing edge flexible deformation section; the flexible wing rib is used as a framework of the wing, the deformable skin and the stringer are arranged at the top end of the flexible deformation section of the trailing edge, the segmented deformable skin is arranged at the bottom end of the flexible deformation section of the trailing edge, and the segmented deformable skins are connected through the segmented deformable skin fixing devices; the flexible wing ribs are multiple and arranged in parallel along the spanwise direction; the piezoelectric fiber composite driver is adhered to the deformation skin, and the rear end of the front edge fixing section is fixedly connected with the front end of the rear edge flexible deformation section.
Further, the flexible rib upper end in the trailing edge flexible deformation section comprises a trapezoidal corrugated structure; the groove at the upper end of the trapezoidal corrugated structure is fixedly connected with the bottom end of the stringer, and the upper end of the stringer is fixedly connected with the deformation skin; the lower end of the flexible wing rib is provided with at least two groups of double-arm corrugated structure units; the segmented deformation skin is fixedly connected to the lower surface of the lower end of the flexible wing rib; the segmented deformation skin fixing device is arranged between two adjacent double-arm corrugated structures or between the double-arm corrugated structure and the tail end of the flexible deformation section of the rear edge, and penetrates through the flexible wing rib along the unfolding direction.
Furthermore, the trapezoidal corrugated structure is formed by connecting at least two groups of trapezoidal structure units.
Furthermore, the double-arm corrugated structure unit comprises a front rectangular structure and a rear rectangular structure which are the same in shape and size, and the upper right end point of the front rectangular structure is connected with the upper left end point of the rear rectangular structure through a flange strip.
Furthermore, the segmented deformation skins are arranged on the lower surfaces of the double-arm corrugated structures in a scalelike manner, and magnetic substances are arranged on the segmented deformation skins positioned on the outer sides of the joints of the two adjacent segments of the segmented deformation skins.
Furthermore, magnetic substances are arranged in the segmented deformation skin fixing device; and the outer sectional deformation skin at the joint of the sectional deformation skins is tightly attached to the flexible wing rib through magnetic force.
The invention can realize continuous smooth deformation of the camber of the trailing edge of the wing. The method has the advantages that the rapid adjustment among different wing profiles is approximately realized, the aerodynamic efficiency of the aircraft is improved, the task adaptability of the aircraft is greatly improved, the lift characteristic is improved, the airflow separation is delayed, the pressure distribution on the surface of the wing is optimized, and the stall characteristic of the aircraft is improved; in addition, the invention replaces the traditional control surface of the wing to realize the control function on the flight attitude, thereby greatly reducing the weight of the wing structure; because the camber of the wing can be continuously and smoothly changed, the wing has no gap at the hinge joint of the traditional control surface, thereby being beneficial to reducing noise pollution and improving stealth characteristics.
Based on the reason, the invention can be widely popularized in the technical field of aviation products.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic view of a wing of an embodiment of the present invention in a pre-deformed shape;
FIG. 2 is a schematic view of a deformed airfoil according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a leading edge securing segment according to an embodiment of the present invention;
FIG. 4 is a schematic structural diagram of a flexible deformation section of the trailing edge according to an embodiment of the present invention.
In the figure: 1. a leading edge fixing section 1; 101. a rigid wing rib; 102. a structural skin and a front end stringer; 2. a trailing edge flexible deformation section; 201. a flexible rib; 201a, a trapezoidal corrugated structure; 201b, double-arm corrugated structure unit; 202. a stringer; 203. deforming the skin; 204. carrying out sectional deformation on the skin; 205. a segmented deformable skin fixing device; 3. a piezoelectric fiber composite driver.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1, the embodiment of the invention discloses a trailing edge variable camber wing driven by piezoelectric fiber materials, which comprises three parts, namely a leading edge fixed section 1 with invariable camber, a trailing edge flexible deformation section 2 with variable camber and a piezoelectric fiber composite driver 3 for adjusting the change degree of the trailing edge flexible deformation section 2; the trailing edge flexible deformation section 2 comprises a flexible wing rib 201, a stringer 202, a deformation skin 203, a segmented deformation skin 204 and a segmented deformation skin fixing device 205, the flexible wing rib 201 is used as a framework of a wing, the deformation skin 203 and the stringer 202 are arranged at the top end of the trailing edge flexible deformation section 2, the segmented deformation skin is arranged at the bottom end of the trailing edge flexible deformation section 2, and the segmented deformation skins are connected through the segmented deformation skin fixing device 205; the flexible ribs 201 are multiple and arranged in parallel along the span direction. The piezoelectric fiber composite driver 3 is adhered to the deformation skin. The rear end of the front edge fixing section 1 is fixedly connected with the front end of the rear edge flexible deformation section 2, in the practical application process, the shape of the front edge fixing end is kept unchanged, and the curvature change of the rear edge flexible deformation section 2 can be realized under the driving action of a driver.
As shown in fig. 3, the leading edge fixed section 1 is composed 102 of a rigid rib 101, a structural skin and a nose stringer. Grooves are distributed on the rigid wing ribs 101, front-end stringers are fixedly connected among the rigid wing ribs 101 in a riveting mode, and structural skins are distributed on the front-end stringers and used for bearing and transmitting pneumatic loads.
As shown in fig. 4, the upper end of the flexible rib 201 in the trailing edge flexible deformation section 2 comprises a trapezoidal corrugated structure 201 a; the groove at the upper end of the trapezoidal corrugated structure 201a is fixedly connected with the bottom end of the stringer, and the upper end of the stringer is fixedly connected with the deformable skin and is used for bearing and transmitting pneumatic load and driving force of a driver; at least two groups of double-arm corrugated structure units 201b are distributed at the lower end of the flexible wing rib 201; the segmented deformation skin is fixedly connected to the lower surface of the lower end of the flexible rib 201; the segmented deforming skin fixing device 205 is arranged between two adjacent double-arm corrugated structures or between the double-arm corrugated structure and the tail end of the trailing edge flexible deforming section 2, and penetrates through the flexible wing rib 201 along the spanwise direction. The tail end of the flexible deformation section 2 at the rear edge is also provided with a reinforcing structure to prevent the rear edge from generating unexpected warping, and meanwhile, stringers can be inserted into the circular hole of the rear edge structure to ensure that the deformation of each part is the same along the span direction of the wing.
In order to facilitate coordination of wing camber deformation, as a preferred embodiment, the trapezoidal corrugated structure 201a is formed by connecting at least two groups of trapezoidal structure units, and has extreme anisotropic performance, which can coordinate contradictions between aerodynamic bearing capacity and flexible deformation capacity. The piezoelectric composite material driver is a piezoelectric fiber driver-MFC, and when voltage excitation is applied to the MFC, the length of the MFC can be changed. MFC adopts epoxy glue to paste on flexible wing deformation covering, ensures that the connection surface is clean and bubble-free, and the edge of piezoelectric fiber material has been through smooth processing, has guaranteed the continuous level and smooth of wing covering surface. The number of the MFCs is 1 or more selected according to the actual situation, bending moment can be generated by controlling the voltage loaded on the MFCs, the wing is driven to generate bending change, the length of the piezoelectric fiber composite driver 3 is changed to drive the skin and the flexible wing rib 201 to deform, and accordingly the wing is driven to generate bending change. Specifically, the connection of the oblique sides of the trapezoidal corrugations can generate structural deformation under the action of the piezoelectric actuator, so as to realize the change of the camber of the wing as shown in fig. 2.
In a preferred embodiment, the dual-arm corrugated structure unit 201b includes two front and rear rectangular structures with the same shape and size, and the upper right end of the front rectangular structure is connected to the upper left end of the rear rectangular structure through a strip.
The segmented deformation skin is arranged on the lower surface of the double-arm corrugated structure in a scalelike manner and is used for adapting to wing bending deformation, and magnetic substances are arranged on the segmented deformation skin on the outer side of the joint of the two adjacent segments of the segmented deformation skin. Magnetic substances are distributed in the segmented deformation skin fixing device 205; the outer sectional deformation skin at the joint of the sectional deformation skins is tightly attached to the flexible wing rib 201 through magnetic force. The magnetic substance is a magnet, can adsorb a deformation skin (containing metal), prevents the deformation process from warping the sectional skin, and is used for ensuring the air tightness of the wing structure.
The invention adopts a corrugated structure to replace a hinge structure in the structural design of the conventional deformable wing, reduces gaps among connecting structures, reduces the structural weight and complexity, adopts the composite material driver MFC through the skin driver arranged on the surface of the wing, and has a series of advantages of high energy density, high energy conversion rate, high control bandwidth and the like. The method can realize the rapid and accurate control of the change of the camber shape of the wing.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (6)
1. A piezoelectric fiber material driven trailing edge variable camber wing is characterized by comprising a leading edge fixed section with invariable camber, a trailing edge flexible deformation section with variable camber and a piezoelectric fiber composite material driver for adjusting the change degree of the trailing edge flexible deformation section; the flexible wing rib is used as a framework of the wing, the deformable skin and the stringer are arranged at the top end of the flexible deformation section of the trailing edge, the segmented deformable skin is arranged at the bottom end of the flexible deformation section of the trailing edge, and the segmented deformable skins are connected through the segmented deformable skin fixing devices; the flexible wing ribs are multiple and arranged in parallel along the spanwise direction; the piezoelectric fiber composite driver is adhered to the deformation skin, and the rear end of the front edge fixing section is fixedly connected with the front end of the rear edge flexible deformation section.
2. The trailing edge variable camber wing of claim 1, wherein the flexible rib upper end in the trailing edge compliant section comprises a trapezoidal wave structure; the groove at the upper end of the trapezoidal corrugated structure is fixedly connected with the bottom end of the stringer, and the upper end of the stringer is fixedly connected with the deformation skin; the lower end of the flexible wing rib is provided with at least two groups of double-arm corrugated structure units; the segmented deformation skin is fixedly connected to the lower surface of the lower end of the flexible wing rib; the segmented deformation skin fixing device is arranged between two adjacent double-arm corrugated structures or between the double-arm corrugated structure and the tail end of the flexible deformation section of the rear edge, and penetrates through the flexible wing rib along the unfolding direction.
3. The trailing edge variable camber wing according to claim 2, wherein the trapezoidal wave structure is formed by connecting at least two groups of trapezoidal structure units.
4. The trailing edge variable camber wing according to claim 2, wherein the double-armed corrugated structure unit comprises a front rectangular structure and a rear rectangular structure which are identical in shape and size, and the upper right end of the front rectangular structure is connected with the upper left end of the rear rectangular structure through the edge strip.
5. The trailing edge variable camber wing according to claim 2 or 4, wherein the segmented deformation skin is arranged on the lower surface of the double-arm corrugated structure in a fish scale shape, and the segmented deformation skin on the outer side of the joint of two adjacent segments of the segmented deformation skin is arranged with a magnetic substance.
6. The trailing edge variable camber wing according to claim 3, wherein a magnetic substance is disposed in the segmented morphing skin securement; and the outer sectional deformation skin at the joint of the sectional deformation skins is tightly attached to the flexible wing rib through magnetic force.
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112109877A (en) * | 2020-09-22 | 2020-12-22 | 中国石油大学(华东) | Novel morphing wing based on piezoelectric drive |
| CN112224384A (en) * | 2020-09-12 | 2021-01-15 | 西安交通大学 | Self-adaptive variable camber wing trailing edge based on hierarchical piezoelectric stack driving |
| CN112224388A (en) * | 2020-09-25 | 2021-01-15 | 南京航空航天大学 | Trailing edge flap driving device based on ultrasonic motor drive |
| CN112319771A (en) * | 2020-11-05 | 2021-02-05 | 西北工业大学 | Variable trailing edge camber rib based on flexible driver |
| 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 |
| CN113044204A (en) * | 2021-04-29 | 2021-06-29 | 吉林大学 | Carbon fiber wing skeleton structure |
| CN113158337A (en) * | 2021-04-12 | 2021-07-23 | 北京航空航天大学 | Variable camber flexible trailing edge-based wing and gust response slowing method thereof |
| CN113415409A (en) * | 2021-07-27 | 2021-09-21 | 北京理工大学 | Non-control surface aircraft wing with variable camber |
| CN113428345A (en) * | 2021-07-30 | 2021-09-24 | 中国计量大学 | Piezoelectric large-displacement deformation wing based on shape memory polymer skin and method thereof |
| CN113551891A (en) * | 2021-06-17 | 2021-10-26 | 北京航空航天大学 | Design and loading mode of variable-camber flexible skin test platform |
| 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 |
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| CN115320829A (en) * | 2022-06-06 | 2022-11-11 | 北京航空航天大学 | Combined skin of bending variable sweepback wing |
| CN117141692A (en) * | 2023-10-31 | 2023-12-01 | 山东省海洋科学研究院(青岛国家海洋科学研究中心) | Self-adaptive variable-wing underwater glider |
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| CN112224384A (en) * | 2020-09-12 | 2021-01-15 | 西安交通大学 | Self-adaptive variable camber wing trailing edge based on hierarchical piezoelectric stack driving |
| CN112109877A (en) * | 2020-09-22 | 2020-12-22 | 中国石油大学(华东) | Novel morphing wing based on piezoelectric drive |
| CN112224388A (en) * | 2020-09-25 | 2021-01-15 | 南京航空航天大学 | Trailing edge flap driving device based on ultrasonic motor drive |
| CN112319771A (en) * | 2020-11-05 | 2021-02-05 | 西北工业大学 | Variable trailing edge camber rib based on flexible driver |
| CN112319771B (en) * | 2020-11-05 | 2024-04-26 | 西北工业大学 | Flexible driver-based variable trailing edge camber rib |
| 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 |
| CN113158337A (en) * | 2021-04-12 | 2021-07-23 | 北京航空航天大学 | Variable camber flexible trailing edge-based wing and gust response slowing method thereof |
| CN113158337B (en) * | 2021-04-12 | 2022-06-14 | 北京航空航天大学 | Variable camber flexible trailing edge-based wing and gust response slowing method thereof |
| CN113044204A (en) * | 2021-04-29 | 2021-06-29 | 吉林大学 | Carbon fiber wing skeleton structure |
| CN113551891A (en) * | 2021-06-17 | 2021-10-26 | 北京航空航天大学 | Design and loading mode of variable-camber flexible skin test platform |
| CN113551891B (en) * | 2021-06-17 | 2022-04-26 | 北京航空航天大学 | Design and loading mode of variable-camber flexible skin test platform |
| CN113415409A (en) * | 2021-07-27 | 2021-09-21 | 北京理工大学 | Non-control surface aircraft wing with variable camber |
| CN113428345A (en) * | 2021-07-30 | 2021-09-24 | 中国计量大学 | Piezoelectric large-displacement deformation wing based on shape memory polymer skin and method thereof |
| 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 |
| CN114084342B (en) * | 2021-12-09 | 2023-12-12 | 重庆邮电大学 | Flexible deformation wing control system based on piezoelectric fiber composite material |
| CN114537642A (en) * | 2022-03-11 | 2022-05-27 | 西北工业大学 | Continuous deformation mixed scaling airfoil structure for wind tunnel test |
| CN114537642B (en) * | 2022-03-11 | 2024-04-26 | 西北工业大学 | Continuous deformation mixed scaling wing structure for wind tunnel test |
| CN115320829A (en) * | 2022-06-06 | 2022-11-11 | 北京航空航天大学 | Combined skin of bending variable sweepback wing |
| CN117141692A (en) * | 2023-10-31 | 2023-12-01 | 山东省海洋科学研究院(青岛国家海洋科学研究中心) | Self-adaptive variable-wing underwater glider |
| CN117141692B (en) * | 2023-10-31 | 2024-03-12 | 山东省海洋科学研究院(青岛国家海洋科学研究中心) | Self-adaptive variable-wing underwater glider |
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