CN110550208A - Blade opening and closing mechanism based on rotary flapping wing vertical take-off and landing power device - Google Patents
Blade opening and closing mechanism based on rotary flapping wing vertical take-off and landing power device Download PDFInfo
- Publication number
- CN110550208A CN110550208A CN201910976164.0A CN201910976164A CN110550208A CN 110550208 A CN110550208 A CN 110550208A CN 201910976164 A CN201910976164 A CN 201910976164A CN 110550208 A CN110550208 A CN 110550208A
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- blade
- head
- steering
- power device
- tail
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- 230000007246 mechanism Effects 0.000 title claims abstract description 17
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 9
- 229910052744 lithium Inorganic materials 0.000 claims description 9
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 9
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- 229910000838 Al alloy Inorganic materials 0.000 claims description 5
- 230000000087 stabilizing effect Effects 0.000 claims description 5
- 239000007787 solid Substances 0.000 claims description 3
- 238000005265 energy consumption Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 5
- 238000009434 installation Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 239000004411 aluminium Substances 0.000 description 1
- 230000001174 ascending effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000003278 mimic effect Effects 0.000 description 1
- 239000011664 nicotinic acid Substances 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
Abstract
The invention relates to a blade opening and closing mechanism based on a rotary flapping wing vertical take-off and landing power device, belongs to the field of aerospace, and particularly relates to take-off and landing control of a novel rotary flapping wing vertical take-off and landing power device. The invention has the advantages of small overall mass, low energy consumption, simple structure, high reliability and the like.
Description
Technical Field
The invention belongs to the field of aerospace, and particularly relates to take-off and landing control of a novel rotary flapping wing vertical take-off and landing power device, which is suitable for solving the problem of inconvenient take-off and landing control of the novel rotary flapping wing vertical take-off and landing power device.
Background
The vertical take-off and landing power device is rapidly developed in recent years, scientific research institutions and enterprise companies of many countries strive for research, development and experiments, and the aircraft with the vertical take-off and landing power device can be free of special airports and runways, so that the use cost is reduced, the limitation of the field is avoided, and the application range is enriched. The rotary flapping wing flight is a flight mode simulating the wing motion rule of birds in the flying process, is a low-energy-consumption and high-efficiency flight method, and can move forward while taking off and landing vertically. Flapping-wing flight is continuously explored from ancient times to present, but the bionic motion becomes complex multidimensional motion after thousands of years of change. A mechanical mechanism which can simplify the movement and is easy to realize is an important breakthrough for realizing the vertical take-off and landing aircraft. Many conventional ornithopters achieve flapping, but still do not closely mimic the motion of birds' wings, which is inefficient and costly. The vertical take-off and landing power device based on the rotary flapping wings is blank in the market, and a method for simply and effectively controlling the vertical take-off and landing power device based on the rotary flapping wings to realize ascending, descending and hovering is not available.
Disclosure of Invention
In order to realize the function of the vertical take-off and landing power device based on the rotary flapping wings, the invention decomposes the power generated by the rotary flapping wings into a constant lift power source and a power source for adjusting the lift output, and provides a blade opening and closing mechanism based on the vertical take-off and landing power device of the rotary flapping wings. The constant output power is regulated and controlled according to the artificial requirement, the control method of the vertical take-off and landing power device is simplified, and the vertical take-off and landing of the whole device are controlled simply, reliably and low in cost.
the aim of the invention is realized by the following technical scheme:
a blade opening and closing mechanism based on a rotary flapping wing vertical take-off and landing power device comprises blades, a large bearing, a connecting shaft, a control system, a steering engine, a steering head, a linkage rod and a small bearing, wherein the blades are elongated light aluminum strips formed by stretching the cross section formed by a water drop-shaped head and a circular tail, the circular tail is axially connected with the head of the connecting shaft, the connecting shaft is formed by a head-like convex cylinder and a tail cylinder, the tail end of the tail cylinder of the connecting shaft is provided with a key groove matched with a concave hole at the level of the thick end of the steering head, the steering head is an arrow-like part, the head-like flush end is provided with a concave hole, the head-like flush end is fixed with a rotating shaft of the steering engine, the tail-like flush end is provided with a stepped hole matched with the outer ring of the small bearing, the inner ring of the small bearing is coaxially matched with the stepped shaft at the flush end of the linkage rod, the linkage rod, the steering engine is used for synchronizing the rotating speeds of all steering heads and blades, and the motion of a rotating shaft of the steering engine is controlled by a control system.
The control system comprises an STM-32 single chip microcomputer, a lithium battery and 3 voltage stabilizing modules, wherein the STM-32 single chip microcomputer integrates a Bluetooth module and a Wi-Fi module, the Bluetooth module and the Wi-Fi module are used for receiving signals of motion speed and motion angle of a steering engine sent by people, the STM-32 single chip microcomputer sends motion signals to the steering engine after processing the signals of Bluetooth and Wi-Fi, the lithium battery is an energy source of the whole control system and the steering engine, and the voltage stabilizing module is a battery voltage control panel and used for adjusting output voltage of the lithium battery to each module.
The water drop-shaped head of the cross section of each blade is hollow in the middle, the overall mass is reduced, the rigidity is improved, the axial middle of the cylindrical tail of the cross section of each blade is solid, concave holes are formed in the two sides of the cylindrical tail of the cross section of each blade and are used for being connected with a connecting shaft, the water drop-shaped head of any blade and the circular tail of the adjacent blade cannot be in complete contact, and a gap of at least 1 cm is reserved.
The coaxial cooperation of big bearing inner circle is on the connecting axle, and the outer lane of big bearing is fixed in the top bearing hole of casing, and the casing is a cuboid cavity aluminum alloy frame, and there are two rows of coaxial symmetrical bearing shoulder holes of equidistance at the top, and there are two sides in the casing middle part to have 8 dead eye respectively for the rotatory flapping wing power device of installation, there is a boss support casing top steering wheel machine side, the boss support is "L" shape angle aluminium, has two steering wheel mounting holes and the coaxial cooperation of the mounting hole on the steering wheel on the support, and uses the bolt-up.
The invention has the advantages and positive effects that:
1. The invention is arranged on the top of the vertical take-off and landing device, and simply and effectively realizes the adjustment of the lifting force of the whole mechanism while not influencing the internal power work of the vertical take-off and landing device, thereby adjusting the actions of the vertical take-off and landing device such as rising, falling, hovering and the like.
2. The invention has low requirement on the shell of the vertical take-off and landing device, low manufacturing cost and wide applicability.
3. The invention realizes the simultaneous and constant-speed motion of the blades by utilizing the connecting rod mechanism, and has simple structure and reliable work.
4. The control system is independent of the control of the power mechanical structure in the vertical take-off and landing mechanism, is easy to realize, is not easy to couple interference, and is easy to realize the motion control of the mechanism from the control point of view.
Drawings
FIG. 1 is a side view of the present invention after installation;
FIG. 2 is an exploded view of the present invention;
FIG. 3 is a cross-sectional view of the present invention;
FIG. 4 is an isometric working view of the present invention;
Wherein: the vertical take-off and landing power device comprises a blade 1, a large bearing 2, a connecting shaft 3, a control system 4, a steering engine 5, a steering head 6, a linkage rod 7, a small bearing 8 and a vertical take-off and landing power device shell 9.
Detailed Description
the present invention will be described in further detail with reference to the accompanying drawings.
The invention comprises a blade 1, a large bearing 2, a connecting shaft 3, a control system 4, a steering engine 5, a steering head 6, a linkage rod 7 and a small bearing 8, wherein the blade 1 is a long-strip light aluminum strip formed by stretching the section consisting of a water drop-shaped head and a circular tail, the middle of the water drop-shaped head of the cross section of the blade 1 is hollowed out so as to reduce the overall mass and improve the rigidity, and the water drop-shaped head of the blade 1 and the circular tail of the adjacent blade can not be in complete contact and have a gap of at least 1 cm. The axial middle of the tail of the cylinder of the cross section of the blade 1 is solid, concave holes are formed in two sides of the tail of the cylinder and used for being connected with the connecting shaft 3, the connecting shaft 3 is composed of a head-like convex-shaped column and a tail cylinder, a key groove is formed in the tail end of the cylinder of the tail of the connecting shaft 3 and matched with a concave hole in the position where the thick end of the steering head 6 is flush, the steering head 6 is an arrow-like part, the flush end of the head is provided with a concave hole, the projecting end of the head is fixed with a rotating shaft of the steering engine 5, the flush end of the tail is provided with a stepped hole, the stepped hole is matched with the outer ring of the small bearing 8, the inner ring of the small bearing 8 is coaxially matched with the stepped shaft of the projecting end of the linkage rod 7, the linkage rod 7 is a long-strip-shaped aluminum alloy strip and used for synchronizing the rotating speeds of. Control system 4 contains an STM-32 singlechip and a lithium cell and 3 steady voltage module that have integrateed the bluetooth module, Wi-Fi module, bluetooth module and Wi-Fi module are used for receiving 5 movement velocity of steering wheel and the signal of motion angle that people sent, STM-32 singlechip sends the motion signal to steering wheel 5 through handling bluetooth and Wi-Fi's signal afterwards, and the lithium cell is whole control system and steering wheel 5's energy source, and steady voltage module is a battery voltage control panel for adjust the output voltage of lithium cell and give every module. The inner ring of the big bearing 2 is coaxially matched on the connecting shaft 3, the outer ring of the big bearing 2 is fixed in a bearing hole at the top of the casing 9, the casing 9 is a cuboid hollow aluminum alloy frame, two rows of bearing stepped holes with equal distance and coaxial symmetry are arranged at the top of the casing, 8 bearing holes are respectively arranged at two sides of the middle of the casing 9 and used for installing a rotary flapping wing power device, a boss support is arranged at the 5 side of a steering engine at the top of the casing 9 and is L-shaped angle aluminum, and two steering engine mounting holes are coaxially matched with mounting holes in the steering engine 5 and fastened by bolts.
After the voltage output of a voltage stabilizing module in the rear adjusting control system 4 is installed, after power supply begins, a mobile phone downloads FeasyBlue software, a Bluetooth module of an STM-32 single chip microcomputer is connected, and then an instruction is sent, the steering engine 5 starts to rotate clockwise by 30 degrees, the steering block 6 connected with the steering engine 5 also rotates clockwise by 30 degrees around the rotating shaft of the steering engine 5, the rotating shaft 3 fixedly connected with the steering block 6 rotates clockwise by 30 degrees, the blade 1 fixedly connected with the rotating shaft 3 also rotates clockwise by 30 degrees, meanwhile, the linkage rod 7 rotates clockwise by 30 degrees around the rotating shaft of the steering engine 5 and keeps the level of the linkage rod 7 under the driving of the steering block 6 and the small bearing 8, and the linkage rod 7 also drives other blades 1 to rotate clockwise by 30 degrees through other small bearings 8 and other steering blocks 6.
In conclusion, the invention provides a blade opening and closing mechanism based on a rotary flapping wing vertical take-off and landing power device, and the mode solves the problem of inconvenient take-off and landing control of the novel rotary flapping wing vertical take-off and landing power device. The function of the vertical take-off and landing power device based on the rotary flapping wings is realized, the constant power generated by the power mechanism of the rotary flapping wings is output and regulated according to the artificial requirement, the control method of the vertical take-off and landing power device is simplified, and the vertical take-off and landing of the whole device is simply, reliably and inexpensively controlled.
Claims (4)
1. The utility model provides a blade mechanism that opens and shuts based on rotatory flapping wing VTOL power device which characterized in that: the steering mechanism comprises a blade (1), a large bearing (2), a connecting shaft (3), a control system (4), a steering engine (5), a steering head (6), a linkage rod (7) and a small bearing (8), wherein the blade (1) is a long-strip-shaped light aluminum strip formed by stretching a cross section formed by a water drop-shaped head and a circular tail, the circular tail is axially connected with the head of the connecting shaft (3), the connecting shaft (3) is formed by a head convex-like column and a tail cylinder, a key groove is arranged at the tail cylinder end of the connecting shaft (3) and matched with a concave-shaped hole at the level of the thick end of the steering head (6), the steering head (6) is an arrow-like part, the head convex-shaped end is provided with a concave-shaped hole, the head convex end is fixed with a rotating shaft of the steering engine (5), the tail convex end is provided with a stepped hole, and the stepped hole is matched with an outer ring of the small bearing (8), the inner ring of the small bearing (8) is coaxially matched with a stepped shaft at the protruding end of the linkage rod (7), the linkage rod (7) is an elongated aluminum alloy strip and used for synchronizing the rotating speeds of all steering heads (6) and the blades (1), and the movement of a rotating shaft of the steering engine (5) is controlled by the control system (4).
2. The blade opening and closing mechanism based on the rotary flapping wing vertical take-off and landing power device as claimed in claim 1, wherein: control system (4) contain one and have integrateed bluetooth module, the STM-32 singlechip and a lithium cell and 3 voltage stabilizing module of Wi-Fi module, bluetooth module and Wi-Fi module are used for receiving steering wheel (5) velocity of motion and the signal of motion angle that people sent, STM-32 singlechip sends the motion signal to steering wheel (5) through handling bluetooth and Wi-Fi's signal afterwards, and the lithium cell is the energy source of whole control system and steering wheel (5), and voltage stabilizing module is a battery voltage control panel for adjust the output voltage of lithium cell and give every module.
3. The blade opening and closing mechanism based on the rotary flapping wing vertical take-off and landing power device as claimed in claim 1, wherein: the blade is characterized in that the head of the cross section of the blade (1) is hollow in the middle of the water drop-shaped head, so that the overall mass is reduced, the rigidity is improved, the axial middle of the cylindrical tail of the cross section of the blade (1) is solid, concave holes are formed in two sides of the cylindrical tail of the cross section of the blade (1) and are used for being connected with the connecting shaft (3), the water drop-shaped head of the blade (1) and the circular tail of the adjacent blade cannot be in complete contact, and at least 1 cm of gap.
4. The blade opening and closing mechanism based on the rotary flapping wing vertical take-off and landing power device as claimed in claim 1, wherein: the large bearing (2) is coaxially matched with the inner ring of the connecting shaft (3), the outer ring of the large bearing (2) is fixed in a bearing hole in the top of the casing (9), the casing (9) is a cuboid hollow aluminum alloy frame, two rows of bearing stepped holes which are coaxially symmetrical at equal intervals are formed in the top of the casing, 8 bearing holes are formed in the middle of the casing (9) and used for installing a rotary flapping wing power device, a boss support is arranged on the side of a steering engine (5) in the top of the casing (9) and is L-shaped angle aluminum, and two steering engine mounting holes are coaxially matched with mounting holes in the steering engine (5) on the support and fastened by bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910976164.0A CN110550208A (en) | 2019-10-15 | 2019-10-15 | Blade opening and closing mechanism based on rotary flapping wing vertical take-off and landing power device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910976164.0A CN110550208A (en) | 2019-10-15 | 2019-10-15 | Blade opening and closing mechanism based on rotary flapping wing vertical take-off and landing power device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110550208A true CN110550208A (en) | 2019-12-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910976164.0A Pending CN110550208A (en) | 2019-10-15 | 2019-10-15 | Blade opening and closing mechanism based on rotary flapping wing vertical take-off and landing power device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110550208A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022012827A1 (en) | 2020-07-14 | 2022-01-20 | Volkswagen Aktiengesellschaft | Wing locking system for vertical power plants in evtol aircraft |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0576800A1 (en) * | 1992-06-30 | 1994-01-05 | Aviatika Joint-Stock Company | Acrobatic airplane |
| DE10208595A1 (en) * | 2002-02-27 | 2003-09-11 | Alfred Dudszus | Active rudder arrangement with integral thrust or rotary device, has propeller drive integrated into rudder reinforcing unit beneath rudder support |
| CN102556335A (en) * | 2012-01-30 | 2012-07-11 | 西北工业大学 | Flying-wing layout aircraft provided with cycloidal propellers |
| EP2669195A1 (en) * | 2012-06-01 | 2013-12-04 | EMT Ingenieurgesellschaft Dipl.-Ing. Hartmut Euer mbH | Airplane |
| RU2627965C1 (en) * | 2016-06-28 | 2017-08-14 | Дмитрий Сергеевич Дуров | High-speed amphibious rotorcraft |
| US20180029699A1 (en) * | 2016-07-27 | 2018-02-01 | Bell Helicopter Textron Inc. | Rotor Blade Erosion Protection Systems |
| CN107697281A (en) * | 2017-09-20 | 2018-02-16 | 大连民族大学 | A kind of culvert vertical take-off and landing unmanned aerial vehicle |
| CN108454843A (en) * | 2018-01-26 | 2018-08-28 | 易瓦特科技股份公司 | Power fuselage device for fixed-wing unmanned plane |
| CN210852912U (en) * | 2019-10-15 | 2020-06-26 | 中国计量大学 | Blade opening and closing mechanism based on rotary flapping wing vertical take-off and landing power device |
-
2019
- 2019-10-15 CN CN201910976164.0A patent/CN110550208A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0576800A1 (en) * | 1992-06-30 | 1994-01-05 | Aviatika Joint-Stock Company | Acrobatic airplane |
| DE10208595A1 (en) * | 2002-02-27 | 2003-09-11 | Alfred Dudszus | Active rudder arrangement with integral thrust or rotary device, has propeller drive integrated into rudder reinforcing unit beneath rudder support |
| CN102556335A (en) * | 2012-01-30 | 2012-07-11 | 西北工业大学 | Flying-wing layout aircraft provided with cycloidal propellers |
| EP2669195A1 (en) * | 2012-06-01 | 2013-12-04 | EMT Ingenieurgesellschaft Dipl.-Ing. Hartmut Euer mbH | Airplane |
| RU2627965C1 (en) * | 2016-06-28 | 2017-08-14 | Дмитрий Сергеевич Дуров | High-speed amphibious rotorcraft |
| US20180029699A1 (en) * | 2016-07-27 | 2018-02-01 | Bell Helicopter Textron Inc. | Rotor Blade Erosion Protection Systems |
| CN107697281A (en) * | 2017-09-20 | 2018-02-16 | 大连民族大学 | A kind of culvert vertical take-off and landing unmanned aerial vehicle |
| CN108454843A (en) * | 2018-01-26 | 2018-08-28 | 易瓦特科技股份公司 | Power fuselage device for fixed-wing unmanned plane |
| CN210852912U (en) * | 2019-10-15 | 2020-06-26 | 中国计量大学 | Blade opening and closing mechanism based on rotary flapping wing vertical take-off and landing power device |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022012827A1 (en) | 2020-07-14 | 2022-01-20 | Volkswagen Aktiengesellschaft | Wing locking system for vertical power plants in evtol aircraft |
| DE102020208780A1 (en) | 2020-07-14 | 2022-01-20 | Volkswagen Aktiengesellschaft | Wing locking system for vertical drives in EVTOL vehicles |
| DE102020208780B4 (en) | 2020-07-14 | 2022-03-31 | Volkswagen Aktiengesellschaft | Wing locking system for vertical drives in EVTOL vehicles |
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