CN116331543B - Rotor blade, unmanned aerial vehicle driving device using rotor blade and assembly method of unmanned aerial vehicle driving device - Google Patents
Rotor blade, unmanned aerial vehicle driving device using rotor blade and assembly method of unmanned aerial vehicle driving device Download PDFInfo
- Publication number
- CN116331543B CN116331543B CN202310224484.7A CN202310224484A CN116331543B CN 116331543 B CN116331543 B CN 116331543B CN 202310224484 A CN202310224484 A CN 202310224484A CN 116331543 B CN116331543 B CN 116331543B
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- blade
- reinforcing sheet
- rigid reinforcing
- driving motor
- unmanned aerial
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- 238000000034 method Methods 0.000 title claims description 11
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 35
- 238000002788 crimping Methods 0.000 claims abstract description 5
- 230000000694 effects Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 239000003351 stiffener Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Abstract
The invention discloses a rotor blade and an unmanned aerial vehicle driving device using the same, wherein the rotor blade comprises two blade root parts and two blade tip parts, a plurality of middle parts are connected between each group of blade root parts and the blade tip parts in a tail-to-tail manner, one end of each blade root part is provided with an annular part sleeved with an output shaft, one side of each annular part is provided with a limiting part, the other end of each blade root part is provided with a first protruding part, and a first rigid reinforcing sheet is movably arranged in each blade root part; unmanned aerial vehicle drive arrangement includes the frame, is provided with the mounting groove that is used for installing driving motor in the frame, and the lateral wall of mounting groove is provided with two mounting holes, and the downthehole activity of mounting is pegged graft and is had the push rod, is provided with the stopper on driving motor's the output shaft, and rotor blade is pegged graft after the output shaft crimping on the stopper, and rotor blade top is fixed spacingly through the nut. The invention realizes the normal use of the large-volume paddle rotorcraft in a strong wind environment.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a rotor blade, an unmanned aerial vehicle driving device using the rotor blade and an assembly method of the unmanned aerial vehicle driving device.
Background
Unmanned aerial vehicle is a emerging aircraft that develops fast in recent years, and unmanned aerial vehicle is widely used in fields such as agriculture, remote sensing survey and drawing, forest fire control, video shooting by virtue of a plurality of advantages such as low use threshold, high flexibility, application scope and the like. Among them, rotary-wing unmanned aerial vehicle is one of the most widely used unmanned aerial vehicles. In order to meet the requirements of unmanned aerial vehicle on impact resistance, portability and convenience in transportation, rotor blades of a rotor unmanned aerial vehicle are usually detachably mounted on an unmanned aerial vehicle body, and the blades are usually made of high-toughness flexible materials. However, in order to ensure flight stability in a strong wind environment, the blade volume of such a rotorcraft cannot be excessively large, which results in the influence of the limitation of the blade volume on the power performance of the rotorcraft itself.
Disclosure of Invention
The invention aims to solve the technical problem of providing a rotor blade, an unmanned aerial vehicle driving device using the rotor blade and an assembly method thereof, which can solve the defects of the prior art and realize the normal use of a large-volume paddle rotorcraft in a strong wind environment.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows.
The utility model provides a rotor unmanned aerial vehicle drive arrangement, includes the frame, is provided with the mounting groove that is used for installing driving motor in the frame, hemispherical base is installed to driving motor's bottom, the mounting groove bottom is provided with hemispherical recess, hemispherical base's radius is greater than hemispherical base's radius, hemispherical base and hemispherical recess movable contact, the lateral wall of mounting groove is provided with two mounting holes, the axis contained angle of two mounting holes is 90, the downthehole activity grafting of mounting has the push rod, the one end and the drive end of pneumatic cylinder of push rod are connected, the other end of push rod passes through universal joint and plug connection, be provided with two jacks with plug grafting complex on driving motor's the lateral wall, be provided with the stopper on driving motor's the output shaft, the crimping is on the stopper after rotor blade grafting is on the output shaft, the rotor blade top is fixed spacingly through the nut.
Preferably, the rotor blade comprises two blade root parts and two blade tip parts, and a plurality of middle parts are connected between each group of blade root parts and blade tip parts in sequence in a tail-end mode.
Preferably, one end of the blade root is provided with an annular part sleeved with the output shaft, one side of the annular part is provided with a limiting part, the other end of the blade root is provided with a first protruding part, the blade root is internally and movably provided with a first rigid reinforcing sheet, and one end of the first rigid reinforcing sheet is positioned outside the side wall of the first protruding part.
Preferably, a first concave part is arranged at one end of the middle part, a second convex part is arranged at the other end of the middle part, a second rigid reinforcing sheet is movably arranged in the middle part, one end of the second rigid reinforcing sheet is positioned at the outer side of the side wall of the second convex part, and the other end of the second rigid reinforcing sheet is positioned at the inner side of the side wall of the first concave part.
Preferably, a second concave part is arranged at one end of the blade tip part, a third rigid reinforcing sheet is movably arranged in the blade tip part, and one end of the third rigid reinforcing sheet is positioned at the inner side of the side wall of the second concave part.
Preferably, the blade root and the middle part, the middle part and the middle part, and the middle part and the blade tip part are fixedly connected by using one screw.
Preferably, the top cover is movably mounted at the top of the mounting groove and is in press fit with the driving motor, an annular groove is formed in the top surface of the top cover, a sliding block is slidably clamped in the annular groove, a through hole is formed in the bottom surface of the root of the blade, a connecting rod is movably mounted in the through hole, one end of the connecting rod is hinged to the first rigid reinforcing plate, and the other end of the connecting rod is hinged to the sliding block.
A method of assembling a rotorcraft unmanned drive, comprising the steps of:
A. placing the driving motor in the mounting groove, and using a plug to be in plug-in fit with a jack on the driving motor;
B. assembling rotor blades;
C. the assembled rotor blade is mounted on the output shaft, and the nut is used for fixing and limiting.
According to the invention, by designing the driving motor mounting structure capable of adjusting the direction in two dimensions, real-time fine adjustment of the angle of the rotor blade in the flight process is realized, so that the disturbance of strong wind on the fuselage is effectively counteracted by changing the direction of the driving force of the unmanned aerial vehicle. In order to solve the problem that a large-volume blade is easy to deform in strong wind, the invention combines the blade disassembly function and simultaneously strengthens the crimping force between adjacent rigid stiffeners by utilizing the centrifugal force generated by the blade in the rotating process of the blade by designing the rigid stiffeners in a head-to-tail crimping way, thereby improving the integral torsional rigidity of the blade. Because the torsional rigidity of the rotor blade is improved through the rigid reinforcing piece, the number of screws for fixedly connecting the blade can be reduced, and each connecting position is fixed by only using one screw, so that the assembly operation process of the blade is simplified, and more importantly, torsional stress and dislocation generated to different parts of the blade when a plurality of screws are rotated and fixed successively can be avoided. Meanwhile, a connecting rod is arranged between the first rigid reinforcing sheet and the top cover, and a pair of mutually balanced transverse acting forces are applied to the driving motor through the top cover by utilizing centrifugal force generated in the rotation process of the rotor blade, so that the transverse stability of the driving motor is improved.
Drawings
Fig. 1 is a block diagram of one embodiment of the present invention.
FIG. 2 is a block diagram of a single side of a rotor blade in accordance with one embodiment of the present invention.
FIG. 3 is a block diagram of a leaf root in one embodiment of the invention.
Fig. 4 is a structural view of an intermediate portion in one embodiment of the present invention.
Fig. 5 is a block diagram of the tip portion in one embodiment of the present invention.
Fig. 6 is an enlarged partial view of the end of a second stiffening sheet in an embodiment of the invention.
Detailed Description
Referring to fig. 1-6, a specific embodiment of the invention comprises a frame 1, wherein a mounting groove 3 for mounting a driving motor 2 is arranged on the frame 1, a hemispherical base 4 is mounted at the bottom of the driving motor 2, a hemispherical groove 5 is arranged at the bottom of the mounting groove 3, the radius of the hemispherical groove 5 is larger than that of the hemispherical base 4, the hemispherical base 4 is movably contacted with the hemispherical groove 5, two mounting holes 6 are arranged on the side wall of the mounting groove 3, the included angle of the axes of the two mounting holes 6 is 90 degrees, a push rod 7 is movably inserted in the mounting holes 6, one end of the push rod 7 is connected with the driving end of a hydraulic cylinder 8, the other end of the push rod 7 is connected with a plug 10 through a universal joint 9, two insertion holes 11 which are in insertion fit with the plug 10 are arranged on the side wall of the driving motor 2, a limit block 32 is arranged on an output shaft 12 of the driving motor 2, rotor blades 13 are inserted on the output shaft 12 and then are pressed on the limit block 32 in a compression mode, and the upper part of the rotor blades 13 are fixedly limited through nuts 14. Rotor blade 13 includes two sets of end-to-end blade root portion 15, intermediate portion 17, and tip portion 16 (in other use environments, different shapes of blade root portion 15 and tip portion 16 may be arbitrarily selected, as well as different numbers of intermediate portions 17). One end of the blade root 15 is provided with an annular part 18 sleeved with the output shaft 12, one side of the annular part 18 is provided with a limiting part 19, the other end of the blade root 15 is provided with a first protruding part 20, a first rigid reinforcing sheet 21 is movably arranged in the blade root 15, and one end of the first rigid reinforcing sheet 21 is positioned outside the side wall of the first protruding part 20. One end of the middle part 17 is provided with a first concave part 22, the other end of the middle part 17 is provided with a second convex part 23, a second rigid reinforcing sheet 24 is movably arranged in the middle part 17, one end of the second rigid reinforcing sheet 24 is positioned on the outer side of the side wall of the second convex part 23, and the other end of the second rigid reinforcing sheet 24 is positioned on the inner side of the side wall of the first concave part 22. One end of the blade tip 16 is provided with a second concave portion 25, a third rigidity reinforcing sheet 26 is movably arranged in the blade tip 16, and one end of the third rigidity reinforcing sheet 26 is positioned on the inner side of the side wall of the second concave portion 25. The blade root 15 and the middle part 17, and the middle part 17 and the blade tip 16 are fixedly connected by a screw 33. The top of the mounting groove 3 is movably provided with a top cover 27, the top cover 27 is in press fit with the driving motor 2, the top surface of the top cover 27 is provided with an annular groove 28, a sliding block 29 is slidably clamped in the annular groove 28, the bottom surface of the blade root 15 is provided with a through hole 30, a connecting rod 31 is movably arranged in the through hole 30, one end of the connecting rod 31 is hinged with the first rigid reinforcing sheet 21, and the other end of the connecting rod 31 is hinged with the sliding block 29.
Further, the end portions of the first rigid reinforcing sheet 21, the second rigid reinforcing sheet 24, and the third rigid reinforcing sheet 26 are provided with the non-slip contact portions 34, respectively. The non-slip contact portions 34 on adjacent rigid reinforcing sheets are in contact with each other, so that the stability of the press-fit fixation between the adjacent rigid reinforcing sheets can be improved.
The assembly method of the rotor unmanned aerial vehicle driving device comprises the following steps:
A. placing the driving motor 2 in the mounting groove 3, using the plug 10 to be in plug-in fit with the jack 11 on the driving motor 2, and then mounting the top cover 27;
B. the blade root 15, the middle part 17 and the blade tip 16 are assembled through the cooperation of the first convex part 20 and the first concave part 22 or the cooperation of the second convex part 23 and the first concave part 22 or the cooperation of the second concave part 25 and the second convex part 23, and then are fixedly connected by using a screw 33;
C. the assembled rotor blade 13 is mounted on the output shaft 12, the limit parts 19 on the two blade root parts 15 are mutually inserted, the first rigid reinforcing sheet 21 is connected with the slide block 29 by using the connecting rod 31, and the fixing limit is performed by using the nut 14.
During the flight of the rotor unmanned aerial vehicle, the angle of the driving motor 2 can be accurately adjusted through the telescopic control of the two hydraulic cylinders 8, so that the balance of the helicopter body can be maintained by changing the angle of the rotor blades 13 when encountering strong wind. During rotation of the rotor blade 13, centrifugal force causes a pressing force to be generated between the first stiffening plate 21, the second stiffening plate 24 and the third stiffening plate 26 towards the outer side of the rotor blade 13, so that the compression joint firmness between the stiffening plates is improved, and the overall torsional rigidity of the blade is improved. The centrifugal force is applied to the top cover 27 through the pair of connecting rods 31, so that the driving motor 2 receives a set of horizontal pulling forces in opposite directions, thereby improving the lateral stability of the driving motor.
In the description of the present invention, it should be understood that the terms "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention.
The foregoing has shown and described the basic principles and main features of the present invention and the advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (2)
1. An unmanned aerial vehicle drive using rotor blades, characterized in that: the device comprises a frame, wherein an installing groove for installing a driving motor is formed in the frame, a hemispherical base is installed at the bottom of the driving motor, a hemispherical groove is formed in the bottom of the installing groove, two installing holes are formed in the side wall of the installing groove, the included angle of the axes of the two installing holes is 90 degrees, a push rod is movably inserted in the installing holes, one end of the push rod is connected with the driving end of a hydraulic cylinder, the other end of the push rod is connected with a plug through a universal joint, two jacks matched with the plug in an inserting mode are formed in the side wall of the driving motor, a limiting block is arranged on an output shaft of the driving motor, rotor blades are connected onto the limiting block in a pressing mode after being inserted onto the output shaft, and the upper parts of the rotor blades are fixedly limited through nuts; the rotor blade comprises two blade root parts and two blade tip parts, and a plurality of middle parts are sequentially connected between each group of blade root parts and the blade tip parts in a head-tail manner; the inside of the leaf root part is movably provided with a first rigid reinforcing sheet, the inside of the middle part is movably provided with a second rigid reinforcing sheet, and the inside of the leaf tip part is movably provided with a third rigid reinforcing sheet; one end of the blade root is provided with an annular part sleeved with the output shaft, one side of the annular part is provided with a limiting part, the other end of the blade root is provided with a first protruding part, and one end of the first rigid reinforcing piece is positioned outside the side wall of the first protruding part; one end of the middle part is provided with a first concave part, the other end of the middle part is provided with a second convex part, one end of the second rigid reinforcing sheet is positioned at the outer side of the side wall of the second convex part, and the other end of the second rigid reinforcing sheet is positioned at the inner side of the side wall of the first concave part; one end of the leaf tip is provided with a second concave part, and one end of the third rigid reinforcing sheet is positioned on the inner side of the side wall of the second concave part; the ends of the second rigid reinforcing sheet and the third rigid reinforcing sheet of the first rigid reinforcing sheet are respectively provided with an anti-skid contact part; the blade root and the middle part, the middle part and the blade tip part are fixedly connected by using a screw; the radius of the hemispherical groove is larger than that of the hemispherical base, and the hemispherical base is in movable contact with the hemispherical groove; the mounting groove top movable mounting has the top cap, top cap and driving motor crimping cooperation, and the top cap top surface is provided with the ring channel, and slip joint has the slider in the ring channel, and root bottom surface is provided with the through-hole, and movable mounting has the connecting rod in the through-hole, and the one end and the first rigidity enhancement piece of connecting rod are articulated, and the other end and the slider of connecting rod are articulated.
2. A method of assembling a unmanned aerial vehicle drive of claim 1, comprising the steps of:
A. placing the driving motor in the mounting groove, and using a plug to be in plug-in fit with a jack on the driving motor;
B. assembling rotor blades;
C. the assembled rotor blade is mounted on the output shaft, and the nut is used for fixing and limiting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310224484.7A CN116331543B (en) | 2022-10-31 | 2022-10-31 | Rotor blade, unmanned aerial vehicle driving device using rotor blade and assembly method of unmanned aerial vehicle driving device |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211341783.0A CN115384765B (en) | 2022-10-31 | 2022-10-31 | Rotor unmanned aerial vehicle driving device and assembling method thereof |
| CN202310224484.7A CN116331543B (en) | 2022-10-31 | 2022-10-31 | Rotor blade, unmanned aerial vehicle driving device using rotor blade and assembly method of unmanned aerial vehicle driving device |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202211341783.0A Division CN115384765B (en) | 2022-10-31 | 2022-10-31 | Rotor unmanned aerial vehicle driving device and assembling method thereof |
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| Publication Number | Publication Date |
|---|---|
| CN116331543A CN116331543A (en) | 2023-06-27 |
| CN116331543B true CN116331543B (en) | 2023-12-29 |
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| CN202211341783.0A Active CN115384765B (en) | 2022-10-31 | 2022-10-31 | Rotor unmanned aerial vehicle driving device and assembling method thereof |
| CN202310224484.7A Active CN116331543B (en) | 2022-10-31 | 2022-10-31 | Rotor blade, unmanned aerial vehicle driving device using rotor blade and assembly method of unmanned aerial vehicle driving device |
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| CN115384765B (en) * | 2022-10-31 | 2023-03-24 | 四川蓉远地测科技有限公司 | Rotor unmanned aerial vehicle driving device and assembling method thereof |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2516891A1 (en) * | 1981-11-25 | 1983-05-27 | Aerospatiale | ROTOR FOR GIRAVIONS, WITH ARTICULATIONS INTEGRATED INTO THE BLADE FOOT |
| US4676720A (en) * | 1984-07-10 | 1987-06-30 | Kawasaki Jukogyo Kabushiki Kaisha | Bearingless hub structure for rotary-wing aircrafts |
| SE9800231D0 (en) * | 1998-01-28 | 1998-01-28 | Avia Adviser Hb | Unmanned rotor-carrying aircraft |
| RU2005121719A (en) * | 2005-07-11 | 2007-01-20 | Иван Никифорович Хамин (RU) | SCREW |
| CN103373467A (en) * | 2012-04-18 | 2013-10-30 | 尤洛考普特德国有限公司 | Blade attachment for a bearingless rotor of a helicopter |
| CN103770939A (en) * | 2012-10-18 | 2014-05-07 | 尤洛考普特德国有限公司 | Separable blade attachment for a bearingless rotor of a helicopter |
| CN203740123U (en) * | 2014-03-03 | 2014-07-30 | 天津曙光敬业科技有限公司 | Six-rotor aircraft |
| CN104029197A (en) * | 2014-06-26 | 2014-09-10 | 山东大学（威海） | Vector propulsion mechanism of underwater robot |
| CN105947160A (en) * | 2016-05-05 | 2016-09-21 | 哈尔滨工程大学 | Propeller for reducing stress at positions of blade roots and decreasing tip vortexes |
| CN107571989A (en) * | 2017-09-13 | 2018-01-12 | 武汉蓝天翔航空科技有限公司 | Circular single rotor wing unmanned aerial vehicle |
| CN109305359A (en) * | 2017-07-28 | 2019-02-05 | 中交遥感载荷（安徽）科技有限公司 | A kind of agricultural unmanned plane propeller and preparation method thereof |
| CN208559751U (en) * | 2018-06-06 | 2019-03-01 | 中国船舶重工集团公司第七一九研究所 | A kind of multi-rotor aerocraft folding paddle unfolding mechanism with self-locking function |
| CN216232959U (en) * | 2021-11-24 | 2022-04-08 | 上海伽利略腾飞航空科技有限公司 | Unmanned helicopter rotor blade tip |
| CN115384765B (en) * | 2022-10-31 | 2023-03-24 | 四川蓉远地测科技有限公司 | Rotor unmanned aerial vehicle driving device and assembling method thereof |
Family Cites Families (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2921152C2 (en) * | 1979-05-25 | 1982-04-22 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Rotor blade for wind power plants |
| DE3839467A1 (en) * | 1988-11-23 | 1990-05-31 | F & E Fischer & Entwicklungen | Detachable propellor blade fastening |
| IT1282114B1 (en) * | 1995-06-09 | 1998-03-12 | Augusta S P A | HELICOPTER ROTOR. |
| FR2810013B1 (en) * | 2000-06-08 | 2002-09-27 | Eurocopter France | ROTOR ROTOR WITH FOLDABLE BLADES AND ELECTRIC DEFROSTING CONNECTION INSTALLATION |
| DE10235496B4 (en) * | 2002-08-02 | 2015-07-30 | General Electric Co. | Method for producing a rotor blade, rotor blade and wind energy plant |
| US7341430B2 (en) * | 2004-12-28 | 2008-03-11 | Nissan Motor Co., Ltd. | Vane wheel for torque converter and manufacturing method |
| DE102005014948A1 (en) * | 2005-04-01 | 2006-10-05 | Dolch, Stefan, Dipl.-Ing. (FH) | Four-rotor model helicopter, has detachable plug connection to mechanically connect sub-assemblies, and electrical connections to connect electrical components of sub-assemblies, with electrical connections integrated in plug connection |
| JP2010071440A (en) * | 2008-09-22 | 2010-04-02 | Nissan Motor Co Ltd | Impeller for fluid coupling, and method of manufacturing the same |
| EP2479426B1 (en) * | 2011-01-24 | 2017-06-28 | Siemens Aktiengesellschaft | Method for determining a pitch angle offset signal and for controlling a rotor frequency of a wind turbine for speed avoidance control |
| CN104781600B (en) * | 2014-04-04 | 2017-01-18 | 深圳市大疆创新科技有限公司 | Cloud platform drive device and cloud platform assembly adopting drive device |
| GB2526302B (en) * | 2014-05-20 | 2019-07-03 | Teignbridge Propellers International Ltd | Propeller with detachable blades |
| CN104005911B (en) * | 2014-06-23 | 2016-09-07 | 中国石油大学(华东) | Low speed H type vane of vertical shaft wind-driven generator controlled change angle of attack system in one |
| CN205203370U (en) * | 2015-12-08 | 2016-05-04 | 西安斯凯智能科技有限公司 | Screw for unmanned aerial vehicle |
| CN106347636B (en) * | 2016-08-30 | 2019-03-01 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of push rod stall protection control method |
| CN106347612A (en) * | 2016-09-28 | 2017-01-25 | 广船国际有限公司 | Ship propeller with detachable blades |
| CN109110124A (en) * | 2018-09-03 | 2019-01-01 | 南京航空航天大学 | A kind of new Main Rotor Blade |
| CN209051585U (en) * | 2018-09-18 | 2019-07-02 | 云南寰牧无人机科技有限公司 | A kind of unmanned plane device to work under heavy load conditions |
| CN209634720U (en) * | 2019-01-02 | 2019-11-15 | 深圳市帅泰科技有限公司 | Paddle folder folds paddle and Power Component |
| CN109896009B (en) * | 2019-02-20 | 2024-06-21 | 丰翼科技(深圳)有限公司 | Screw and unmanned aerial vehicle |
| CN210258829U (en) * | 2019-05-31 | 2020-04-07 | 深圳创壹通航科技有限公司 | Four-vector control vertical take-off and landing fixed wing aircraft |
| CA3099971A1 (en) * | 2019-11-28 | 2021-05-28 | W&D Innovations B.V. | Electromotive drive device and a method for operating such an electromotive drive device____________________________________ |
| CN211001827U (en) * | 2019-12-13 | 2020-07-14 | 河南昆豫无人机科技有限公司 | Unmanned aerial vehicle rotor structure compounded by aluminum profiles and plastics |
| US11472545B2 (en) * | 2020-04-21 | 2022-10-18 | Liviu Grigorian Giurca | Propulsion system and aircraft with vertical take-off and landing-VTOL |
| CN212220523U (en) * | 2020-05-27 | 2020-12-25 | 镇江金叶螺旋桨有限公司 | Marine propeller capable of being quickly mounted and dismounted |
| US11738864B2 (en) * | 2020-10-08 | 2023-08-29 | Ierus Technologies | Apparatus with variable pitch and continuous tilt for rotors on an unmanned fixed wing aircraft |
-
2022
- 2022-10-31 CN CN202211341783.0A patent/CN115384765B/en active Active
- 2022-10-31 CN CN202310224484.7A patent/CN116331543B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2516891A1 (en) * | 1981-11-25 | 1983-05-27 | Aerospatiale | ROTOR FOR GIRAVIONS, WITH ARTICULATIONS INTEGRATED INTO THE BLADE FOOT |
| US4676720A (en) * | 1984-07-10 | 1987-06-30 | Kawasaki Jukogyo Kabushiki Kaisha | Bearingless hub structure for rotary-wing aircrafts |
| SE9800231D0 (en) * | 1998-01-28 | 1998-01-28 | Avia Adviser Hb | Unmanned rotor-carrying aircraft |
| RU2005121719A (en) * | 2005-07-11 | 2007-01-20 | Иван Никифорович Хамин (RU) | SCREW |
| CN103373467A (en) * | 2012-04-18 | 2013-10-30 | 尤洛考普特德国有限公司 | Blade attachment for a bearingless rotor of a helicopter |
| CN103770939A (en) * | 2012-10-18 | 2014-05-07 | 尤洛考普特德国有限公司 | Separable blade attachment for a bearingless rotor of a helicopter |
| CN203740123U (en) * | 2014-03-03 | 2014-07-30 | 天津曙光敬业科技有限公司 | Six-rotor aircraft |
| CN104029197A (en) * | 2014-06-26 | 2014-09-10 | 山东大学（威海） | Vector propulsion mechanism of underwater robot |
| CN105947160A (en) * | 2016-05-05 | 2016-09-21 | 哈尔滨工程大学 | Propeller for reducing stress at positions of blade roots and decreasing tip vortexes |
| CN109305359A (en) * | 2017-07-28 | 2019-02-05 | 中交遥感载荷（安徽）科技有限公司 | A kind of agricultural unmanned plane propeller and preparation method thereof |
| CN107571989A (en) * | 2017-09-13 | 2018-01-12 | 武汉蓝天翔航空科技有限公司 | Circular single rotor wing unmanned aerial vehicle |
| CN208559751U (en) * | 2018-06-06 | 2019-03-01 | 中国船舶重工集团公司第七一九研究所 | A kind of multi-rotor aerocraft folding paddle unfolding mechanism with self-locking function |
| CN216232959U (en) * | 2021-11-24 | 2022-04-08 | 上海伽利略腾飞航空科技有限公司 | Unmanned helicopter rotor blade tip |
| CN115384765B (en) * | 2022-10-31 | 2023-03-24 | 四川蓉远地测科技有限公司 | Rotor unmanned aerial vehicle driving device and assembling method thereof |
Non-Patent Citations (4)
| Title |
|---|
| 一种旋翼无人机发射灭火装置设计研发;王伟;高铁柱;张明远;何诚;;林业机械与木工设备(第07期);第52-53+58页 * |
| 反流及径向流动相互作用下刚性旋翼气动特性研究;陈恺;张震宇;王同光;;南京航空航天大学学报(02);第187-193页 * |
| 基于双处理器的四旋翼飞行控制系统研究;吴思颖;李亚楠;王年丰;姚远;;软件导刊(01);第44-46页 * |
| 工业级多旋翼无人机自锁折叠件设计及强度计算;严风硕;刘峰;喻辉;;中国战略新兴产业(第40期);第149-151+154页 * |
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| CN115384765A (en) | 2022-11-25 |
| CN115384765B (en) | 2023-03-24 |
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