CN113955099A - A flapping wing structure with adjustable length fins on the leading edge surface - Google Patents
A flapping wing structure with adjustable length fins on the leading edge surface Download PDFInfo
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- CN113955099A CN113955099A CN202111277562.7A CN202111277562A CN113955099A CN 113955099 A CN113955099 A CN 113955099A CN 202111277562 A CN202111277562 A CN 202111277562A CN 113955099 A CN113955099 A CN 113955099A
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- 230000033001 locomotion Effects 0.000 claims abstract description 31
- 230000007246 mechanism Effects 0.000 claims abstract description 19
- 238000000034 method Methods 0.000 claims abstract description 11
- 230000008569 process Effects 0.000 claims abstract description 11
- 238000009434 installation Methods 0.000 claims description 5
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 230000005540 biological transmission Effects 0.000 description 9
- 239000012530 fluid Substances 0.000 description 7
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 5
- 241000238631 Hexapoda Species 0.000 description 4
- 241001465754 Metazoa Species 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 238000010248 power generation Methods 0.000 description 3
- 230000009182 swimming Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000000737 periodic effect Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 241000251468 Actinopterygii Species 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000003306 harvesting Methods 0.000 description 1
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- 230000004048 modification Effects 0.000 description 1
- 239000011664 nicotinic acid Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
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Abstract
The invention discloses a flapping wing structure with length-adjustable fins on the surface of the front edge, which comprises a flapping wing body group mechanism and a flapping wing fin movement executing mechanism, wherein the flapping wing body group mechanism is provided with a flapping wing fin; the flapping wing machine body group mechanism comprises a flapping wing blade body and the like; the flapping wing fin movement executing mechanism comprises flapping wing fins and the like; the flapping wing blade comprises a flapping wing blade body, a flapping wing blade bottom plate, a multi-section crankshaft, a flapping wing blade top plate, a flapping wing blade bottom plate, a flapping wing blade top plate, a flapping wing blade bottom plate, a flapping wing blade top plate, a flapping wing blade bottom plate, a flapping wing blade top plate, a flapping wing blade bottom plate and a flapping wing blade bottom plate, wherein the flapping wing blade top plate is connected with the flapping wing blade top plate and the flapping wing blade top plate; each crankshaft is movably connected with a flapping wing fin through a connecting rod. The flapping wing blade changes the process of vortex shedding on the surface of the oscillating flapping wing and the pressure distribution, and is beneficial to improving the overall efficiency of the flapping wing blade.
Description
Technical Field
The invention belongs to the technical field of flapping wing blades, and particularly relates to a flapping wing structure with fins with adjustable lengths on the surface of the front edge.
Background
The oscillating flapping wing is a novel fluid kinetic energy collecting device, and energy is extracted by vortex excitation based on the flutter motion of fluid (air or water) flowing through blades of the immersed flapping wing. The fluid can generate boundary layer separation and form shedding vortexes when flowing through the bluff body, the periodic shedding vortexes can cause periodic aerodynamic force, and by controlling proper flapping-wing motion (combination of heave and pitching), high-efficiency fluid energy collection can be obtained, and oscillating flapping-wing power generation is realized. Numerous studies have shown that oscillating rigid wings in pitch and heave motion can achieve 40% energy extraction, comparable to 45% efficiency achieved by conventional wind turbines.
Compared to conventional water turbines and wind turbines, flapping-wing blade power generation has two main advantages: firstly, the system is multifunctional, can be applied to wind fields with limited space, shallow water systems (such as rivers or streams) and larger water flow systems (such as tidal basins), has strong space and territorial adaptability, and has remarkable advantages in the aspect of low-speed fluid energy collection in particular; second, the large tip speeds of conventional water and wind turbines result in noisy operation and death of fish and birds, while flapping wing blade energy harvesting can substantially eliminate the negative impact of rotating blades on the environment.
The most fundamental and effective measure for greatly reducing the power generation cost of the flapping wing is to obviously improve the fluid energy utilization coefficient of the blades of the flapping wing, the waves and the radian observed on flying insects and swimming animals can be found to improve the propelling performance of the flapping wing, and a large number of research results show that compared with the NACA0012 wing type, the optimized wing type with the waves and the radian can improve the efficiency by about 10 percent. Inspired by this concept, many technical measures have been tried to improve the aerodynamic performance of an ornithopter blade, but basically it is a simple matter to study and modify the shape of the tail of an ornithopter blade, such as Gurney flaps and flaps plus trailing edge serrations. In order to improve the fluid energy utilization coefficient of the flapping wing blade and break through the single conventional research idea of changing the tail wing of the flapping wing blade, the invention provides a bionic flapping wing blade structure for deeply simulating the corrugation and radian of flying insects and swimmers and a flapping wing structure with fins with adjustable lengths on the front edge surface.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a flapping wing structure with fins with adjustable length on the front edge surface, which deeply simulates the structures of the corrugation and radian of flying insects and swimming animals, the structure of the fins on the surface of a flapping wing blade has great influence on the flow field around the flapping wing, the fins change the process of vortex shedding on the surface of the oscillating flapping wing and the pressure distribution, and are beneficial to improving the overall efficiency of the flapping wing blade, meanwhile, the extension length of the fins can be flexibly controlled and adjusted, the application range of the prior flapping wing blade is greatly expanded, and a new technical route is provided for improving the pneumatic performance of the flapping wing blade.
The invention is realized by adopting the following technical scheme:
a flapping wing structure with length-adjustable fins on the surface of the front edge comprises a flapping wing body group mechanism and a flapping wing fin movement executing mechanism;
the flapping wing machine body group mechanism comprises a flapping wing blade body, an internal support platform, an input shaft, a flapping wing blade top plate and a flapping wing blade bottom plate; the flapping wing fin movement executing mechanism comprises flapping wing fins, a crankshaft and a connecting rod;
the flapping wing blade comprises a flapping wing blade body, a flapping wing blade bottom plate, a multi-section crankshaft, a flapping wing blade top plate, a flapping wing blade bottom plate, a flapping wing blade top plate, a flapping wing blade bottom plate, a flapping wing blade top plate, a flapping wing blade bottom plate, a flapping wing blade top plate, a flapping wing blade bottom plate and a flapping wing blade bottom plate, wherein the flapping wing blade top plate is connected with the flapping wing blade top plate and the flapping wing blade top plate;
each crankshaft is movably connected with a flapping wing fin through a connecting rod.
The invention is further improved in that a hole is formed in the top plate of the flapping wing blade for mounting a bearing of the flapping wing blade top.
The invention is further improved in that a hole is formed in the bottom plate of the flapping wing blade and used for mounting a bearing at the bottom of the flapping wing blade.
A further development of the invention is that the input shaft is connected to an external input device for providing torque.
The invention has the further improvement that a plurality of flapping wing fins are vertically arranged between a top plate of the flapping wing blade and a bottom plate of the flapping wing blade, the upper surface and the lower surface of each flapping wing fin are tightly attached to the top plate of the flapping wing blade and the bottom plate of the flapping wing blade, the side surfaces of the flapping wing fins are attached to fin grooves formed in the flapping wing blade body 1 in parallel, and the flapping wing fins can reciprocate in the fin grooves formed in the flapping wing blade body 1 under the drive of a crankshaft connecting rod.
The invention is further improved in that the plurality of flapping wing fins are respectively an upper flapping wing 20% chord length position fin, an upper flapping wing 10% chord length position fin, a flapping wing front edge fin, a lower flapping wing 20% chord length position fin and a lower flapping wing 10% chord length position fin which are arranged between a top plate and a bottom plate of the flapping wing blade.
The invention is further improved in that the integral structure of the internal support platform is a boss structure, four internal support platforms are equidistantly arranged along the axis direction of the crankshaft, and a through hole is formed in the internal support platform and is embedded with a support platform bearing.
The invention is further improved in that the inner support platform is provided with an arc groove to avoid mutual interference and collision in the reciprocating motion of the flapping wing fins.
The invention has the further improvement that each crankshaft comprises an upper main mandrel, a lower main mandrel, a cam and an eccentric shaft, the upper main mandrel and the lower main mandrel are coaxial, the upper main mandrels and the lower main mandrels of different crankshafts are fixedly connected with each other, and different crankshafts always keep fixed installation angles; the eccentric shaft is fixedly connected with one end of the cam up and down, and the eccentric shaft synchronously rotates around the main spindle in the rotation process of the crankshaft.
The invention is further improved in that the cam has an upper layer structure and a lower layer structure, so that the cam is prevented from colliding with the connecting rod in the rotating process.
The invention has at least the following beneficial technical effects:
1. the invention relates to a flapping wing structure with length-adjustable fins on the surface of the front edge, which can be flexibly adjusted according to actual use requirements and comprises a plurality of fins with adjustable extension lengths, wherein each fin comprises an independent fin transmission shaft, the reciprocating linear motion of the flapping wing fins is realized under the transmission control of a crankshaft connecting rod mechanism, different molded lines are formed by changing the flapping wing structure, and the effect of flow control is achieved.
2. The invention deeply simulates the structures of the ripples and the radians on the bodies of flying insects and swimming animals, the structure of the fins on the surface of the flapping wing blade has great influence on the flow field around the flapping wing, the fins change the process of vortex shedding on the surface of the oscillating flapping wing and the pressure distribution, the overall efficiency of the flapping wing blade is improved, meanwhile, the extension length of the fins can be flexibly controlled and adjusted, the application range of the prior flapping wing blade is greatly expanded, and a new technical route is provided for improving the pneumatic performance of the flapping wing blade.
Drawings
FIG. 1 is a schematic view of a flapping wing structure with length-adjustable fins on the leading edge surface.
FIG. 2 is a schematic view of the structure of the flapping wing airframe assembly of the present invention.
FIG. 3 is a schematic view of the internal structure of the flapping wing of the present invention.
FIG. 4 is a schematic view of the internal support platform of the flapping wings of the present invention.
FIG. 5 is a schematic view of a crankshaft configuration of the present invention.
FIG. 6 is a schematic view of a connecting rod structure according to the present invention.
FIG. 7 is a schematic view of the flapping wing rib of the present invention.
Fig. 8 (a) - (c) are schematic diagrams of the length adjustment positions of the flapping wing rib of the present invention.
Description of reference numerals:
1-flapping wing blade body, 2-upper flapping wing 20% chord length position fin, 3-upper flapping wing 10% chord length position fin, 4-flapping wing front edge fin, 5-inner support table, 6-lower flapping wing 20% chord length position fin, 7-crankshaft, 8-connecting rod, 9-lower flapping wing 10% chord length position fin, 10-input shaft, 11-flapping wing blade top bearing, 12-flapping wing blade top plate, 13-flapping wing blade bottom bearing, 14-flapping wing blade bottom plate, 15-support table bearing, 16-upper main spindle, 17-cam, 18-eccentric shaft, 19-lower main spindle, 20-connecting rod crankshaft connecting hole, 21-connecting rod fin connecting hole and 22-fin transmission shaft.
Detailed Description
The invention will be described in further detail with reference to the following drawings and specific embodiments:
referring to fig. 1 and 2, the flapping wing structure with length-adjustable fins on the front edge surface according to the present invention includes a flapping wing body assembly mechanism and a flapping wing fin movement executing mechanism. Wherein, flapping wing organism group mechanism includes: the flapping wing blade comprises a flapping wing blade body 1, an internal support table 5, an input shaft 10, a flapping wing blade top bearing 11, a flapping wing blade top plate 12, a flapping wing blade bottom bearing 13 and a flapping wing blade bottom plate 14; the flapping wing rib movement executing mechanism comprises: the flapping wing comprises flapping wing fins (an upper flapping wing fin 2 at the position of 20% of chord length, an upper flapping wing fin 3 at the position of 10% of chord length, a flapping wing front edge fin 4, a lower flapping wing fin 6 at the position of 20% of chord length, a lower flapping wing fin 9 at the position of 10% of chord length), a crankshaft 7 and a connecting rod 8.
Referring to fig. 2, the flapping wing body assembly according to the present invention is a mounting base for a framework and a rib movement actuator of a whole set of flapping wing structure, and has sufficient strength and rigidity to bear various loads. The flapping wing blade is characterized in that a plurality of rib grooves are formed in positions of the flapping wing blade body 1 with different chord lengths, the rib grooves are arranged in parallel with the surfaces of fins (an upper flapping wing fin 2 at the position of 20% chord length, an upper flapping wing fin 3 at the position of 10% chord length, a flapping wing front edge fin 4, a lower flapping wing fin 6 at the position of 20% chord length and a lower flapping wing fin 9 at the position of 10% chord length) and are tightly attached to each other, a plurality of internal supporting tables 5 are installed in the flapping wing blade body 1, the internal supporting tables 5 are tightly connected with the flapping wing blade body 1, and the supporting strength of a crankshaft 7 is improved. The flapping wing blade body 1 is in seamless tight connection with a flapping wing blade top plate 12, and a hole is formed in the flapping wing blade top plate 12 and used for mounting a flapping wing blade top bearing 11; the flapping wing blade body 1 is in seamless tight connection with a flapping wing blade bottom plate 14, and a hole is formed in the flapping wing blade bottom plate 14 and used for mounting a flapping wing blade bottom bearing 13. A multi-section crankshaft 7 is connected between the flapping wing blade top bearing 11 and the flapping wing blade bottom bearing 13, the joint penetrates through the inner supporting platform 5, the inner supporting platform 5 provides supporting strength, an input shaft 10 is connected below the flapping wing blade bottom bearing 13, the input shaft 10 is connected with an external input device of the flapping wing device, torque is provided, and a power source is provided for controlling the reciprocating motion of the flapping wing blade.
Referring to fig. 3, the flapping wing rib motion actuator according to the present invention is a main structure of flapping wing surface ribs for accomplishing reciprocating motion and realizing working cycle, and includes: the flapping wing comprises flapping wing fins (an upper flapping wing fin 2 at the position of 20% of chord length, an upper flapping wing fin 3 at the position of 10% of chord length, a flapping wing front edge fin 4, a lower flapping wing fin 6 at the position of 20% of chord length, a lower flapping wing fin 9 at the position of 10% of chord length), a crankshaft 7 and a connecting rod 8. The crankshaft 7 is a key component of a motion execution mechanism and has the function of converting the rotation moment of the input shaft 10 into the acting force of reciprocating motion of the flapping wing fins (the upper flapping wing fin 2 at the position of 20% chord length, the upper flapping wing fin 3 at the position of 10% chord length, the flapping wing leading edge fin 4, the lower flapping wing fin 6 at the position of 20% chord length and the lower flapping wing fin 9 at the position of 10% chord length) through the connecting rod 8. The connecting rod 8 is used for converting the rotation motion of the crankshaft 7 into the reciprocating linear motion of the flapping wing fins, and the torque transmitted by the crankshaft 7 is applied to one end of each fin. The flapping wing fins (the upper flapping wing 20% chord length position fin 2, the upper flapping wing 10% chord length position fin 3, the flapping wing front edge fin 4, the lower flapping wing 20% chord length position fin 6 and the lower flapping wing 10% chord length position fin 9) are vertically arranged between a flapping wing blade top plate 12 and a flapping wing blade bottom plate 14, the upper and lower surfaces of the flapping wing fins (the upper flapping wing 20% chord length position fin 2, the upper flapping wing 10% chord length position fin 3, the flapping wing front edge fin 4, the lower flapping wing 20% chord length position fin 6 and the lower flapping wing 10% chord length position fin 9) are tightly attached to the flapping wing blade top plate 12 and the flapping wing blade bottom plate 14, the side surfaces of the flapping wing fins are attached to fin grooves formed in the flapping wing blade body 1 in parallel, and the flapping wing fins can reciprocate in the fin grooves formed in the flapping wing blade body 1 under the driving of a crankshaft connecting rod.
Referring to fig. 4, the inner support platforms 5 of the flapping wing body set mechanism of the present invention are integrally formed as a boss structure, are located inside the flapping wing blade body 1, are tightly combined with the flapping wing blade body 1, and are equidistantly arranged along the axial direction of the crankshaft 7 with four inner support platforms 5. The inner supporting platform 5 is internally provided with a through hole embedded with a supporting platform bearing 15, the crankshafts 7 are fixedly arranged on the same axis through the supporting platform bearing 15, the flapping wing blade top bearing 11 and the flapping wing blade bottom bearing 13, different crankshafts 7 are fixedly connected and synchronously rotated, and the initial installation angle difference is always kept in the rotating process. The inner support platform 5 is provided with an arc groove to avoid mutual interference and collision in the reciprocating motion of the flapping wing fins 2 and the flapping wing fins 6.
Referring to fig. 5, the crankshaft 7 in the flapping wing motion actuator according to the present invention includes an upper main spindle 16, a lower main spindle 19, a cam 17 and an eccentric shaft 18, wherein the upper main spindle 16 and the lower main spindle 19 are coaxial and are mounted in a bearing of the flapping wing body assembly mechanism, the upper main spindle 16 and the lower main spindle 19 of different crankshafts 7 are fixedly connected to each other, the input shaft 10 at the bottom drives all the crankshafts to rotate synchronously, and a fixed mounting angle is always maintained between different crankshafts 7; an eccentric shaft 18 is fixedly connected to one end of the cam 17 up and down, and the eccentric shaft 18 rotates synchronously around the main spindle during rotation of the crankshaft 7. The crankshaft 7 is subjected to dynamic balance verification before assembly, and a cam 17 is added on one side symmetrical to an eccentric shaft 18 so as to meet the balance requirement. The cam 17 is designed into an upper-layer structure and a lower-layer structure, so that the cam is prevented from colliding with the connecting rod 8 in the rotating process.
Referring to fig. 6, the connecting rod 8 of the flapping-wing actuator of the present invention is used to transmit the torque input by the crankshaft to the fins and convert the rotation of the crankshaft 7 into the reciprocating linear motion of the fins. One end of the connecting rod 7 is a connecting rod crankshaft connecting hole 20 for installing an eccentric shaft 18 in a crankshaft, and the connecting rod 8 is provided with a connecting rod fin connecting hole 21 for installing fins and driving the fins to complete reciprocating linear motion in the motion process along with the rotation of the eccentric shaft 18 around a main spindle in the rotation process of the crankshaft.
Referring to fig. 7, the rib of the flapping-wing motion actuator of the present invention is composed of a rib plate with equal thickness and a rib transmission shaft 22. The flapping wing blade comprises a flapping wing blade body 1, connecting rods 8, fin transmission shafts 22, connecting rods 8 and connecting rods 22, wherein the fin transmission shafts 22 penetrate through the connecting rod fin connecting holes 21, fins are driven by the connecting rods 8 to do reciprocating linear motion along fin grooves formed in the flapping wing blade body 1, each fin transmission shaft 22 is independently connected with one connecting rod 8, and the connecting rods 8 are arranged in a staggered mode in the axial depth direction; the thickness of the rib plate is uniform, two side surfaces of the rib plate are attached to rib grooves formed in the flapping wing blade body 1 and can freely slide, the upper top surface and the lower top surface of the rib plate are attached to a flapping wing blade top plate 12 and a flapping wing blade bottom plate 14, the front edge of the rib plate is an arc surface, the line type of the arc line of the rib plate is the same as the line type of the flapping wing at the corresponding position, and when the rib plate moves to the shortest limit position, the front edge of the rib plate is completely attached to the surface of the flapping wing to form the flapping wing type with a complete line type.
Referring to fig. 8, the length adjustment positions of the flapping wing fins according to the present invention include a shortest limit position, a normal position, and a longest limit position. The initial installation angle difference between different crankshafts is determined by the angle of the flapping wing fin at the shortest limit position, and an arc groove is formed on the support platform 5 inside the flapping wing according to the position of the flapping wing fin at the moment, so that the mutual interference and collision formed in the reciprocating motion of the flapping wing fin 2 and the flapping wing fin 6 are avoided. When the flapping wing fin is located at the shortest limit position, the front edge surfaces of the fin at different positions are just attached to the surface of the flapping wing blade to form smooth transition, and the fin transmission shaft 22, the crankshaft main spindle and the crankshaft eccentric shaft are sequentially on the same straight line. When the flapping wing fins are located at the longest limit position, the fins at different positions simultaneously reach the maximum extension length on the surface of the blade, and the fin transmission shaft 22, the crankshaft eccentric shaft and the crankshaft main spindle are sequentially on the same straight line. When the flapping wing fins are at the common position, the initial installation angle difference is always kept between different crankshafts in the rotation process, the connecting rods are driven to rotate synchronously, and the connecting rods drive the flapping wing fins to complete reciprocating circular linear motion and simultaneously reach the shortest limit position and the longest limit position.
The above description is only a preferred embodiment of the present invention, and any improvements, modifications or other embodiments obtained by those skilled in the art without making creative efforts shall be included in the protection scope of the present invention.
Claims (10)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111277562.7A CN113955099A (en) | 2021-10-29 | 2021-10-29 | A flapping wing structure with adjustable length fins on the leading edge surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111277562.7A CN113955099A (en) | 2021-10-29 | 2021-10-29 | A flapping wing structure with adjustable length fins on the leading edge surface |
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| Publication Number | Publication Date |
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| CN113955099A true CN113955099A (en) | 2022-01-21 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111277562.7A Pending CN113955099A (en) | 2021-10-29 | 2021-10-29 | A flapping wing structure with adjustable length fins on the leading edge surface |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116729658A (en) * | 2023-04-20 | 2023-09-12 | 北京科技大学 | A flying device with retractable wings and a method of using the same |
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| KR102186684B1 (en) * | 2019-08-02 | 2020-12-04 | 박준규 | Vertical-axix wing turbine |
| CN112810814A (en) * | 2019-11-18 | 2021-05-18 | 上海海事大学 | Novel slender flexible flapping wing |
| CN113492974A (en) * | 2021-07-26 | 2021-10-12 | 西安交通大学 | Bird-like flapping wing aircraft capable of deforming in unfolding direction and driving method |
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2021
- 2021-10-29 CN CN202111277562.7A patent/CN113955099A/en active Pending
Patent Citations (8)
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| US20190085820A1 (en) * | 2014-09-17 | 2019-03-21 | Robert Reginald Bray | Power Generating Device |
| CN104329219A (en) * | 2014-10-29 | 2015-02-04 | 西北工业大学 | Sistan fan propeller |
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| CN116729658B (en) * | 2023-04-20 | 2024-04-26 | 北京科技大学 | A flying device with retractable wings and a method of using the same |
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