CN108910029B - Protection mechanism of unmanned aerial vehicle wing - Google Patents
Protection mechanism of unmanned aerial vehicle wing Download PDFInfo
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- CN108910029B CN108910029B CN201810871549.6A CN201810871549A CN108910029B CN 108910029 B CN108910029 B CN 108910029B CN 201810871549 A CN201810871549 A CN 201810871549A CN 108910029 B CN108910029 B CN 108910029B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
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Abstract
The invention provides a protection mechanism for wings of an unmanned aerial vehicle, which comprises a bending support plate, a transverse positioning plate, a square threaded sleeve, a sliding positioning rod, a spring, a top ring and a plum blossom threaded rod, wherein the bending support plate is arranged on the top ring; the rotor wing driving motor is arranged at the head end of the rotor wing supporting plate in a supporting mode, and two positioning slots are symmetrically arranged on the left side and the right side of the front end of the rotor wing supporting plate in a supporting mode; the three sliding positioning rods respectively penetrate through the semicircular top plates of the three vertical supporting sleeves and protrude downwards to be inserted into the three vertical supporting sleeves, and the tail ends of the three sliding positioning rods are respectively provided with a prescription-shaped baffle which can slide downwards along the three vertical supporting sleeves to be pressed against the middle buffer ring.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicle matched protection devices, and particularly relates to a protection mechanism for wings of an unmanned aerial vehicle.
Background
The unmanned aerial vehicle is influenced by sundries such as fallen leaves, branches, flying paper, food bags and the like in the air in the flying process, once the sundries are involved in a rotor wing of the unmanned aerial vehicle, the rotor wing is wound, the unmanned aerial vehicle slowly falls when the sundries are light, and the unmanned aerial vehicle is directly stuck and falls when the sundries are heavy, so that destructive damage is caused; meanwhile, various control problems are easy to occur to an unmanned aerial vehicle operator in the operation process, for example, the unmanned aerial vehicle blades hurt people, the unmanned aerial vehicle blades collide with buildings or trees or aerial cables, and the like, so that the protection device is especially important for ensuring the flight safety.
Combine prior art inventor discovery, current equipment though can carry out conventional use, but it exists in practical application, and buffer structure designs unreasonablely, mostly can only carry out single buffering protection, causes the mechanism body to easily take place the breakage when receiving very big impact, causes the rotor to damage the probability increase, the comparatively inconvenient problem of loading and unloading operation of mechanism body in addition.
Therefore, in view of the above, research and improvement are performed on the existing structure and defects, and a protection mechanism for wings of an unmanned aerial vehicle is provided, so as to achieve the purpose of higher practical value.
Disclosure of Invention
In order to solve the technical problems, the invention provides a protection mechanism for wings of an unmanned aerial vehicle, which aims to solve the problems that the existing wing protection mechanism is not reasonable in buffer structure design and can only carry out single buffer protection, so that a mechanism body is easy to break when being subjected to a great impact force, the damage probability of a rotor wing is increased, and in addition, the assembly and disassembly operation of the mechanism body is inconvenient.
The invention relates to a protection mechanism of an unmanned aerial vehicle wing, which is achieved by the following specific technical means:
a protection mechanism for wings of an unmanned aerial vehicle comprises a rotor wing supporting plate, a positioning slot, a rotor wing driving motor, a bottom ring, a buffer bracket, an arc-shaped supporting plate, a middle buffer ring, a vertical supporting sleeve, a bending supporting plate, a transverse positioning plate, a square threaded sleeve, a sliding positioning rod, a spring, a top ring and a plum-blossom-shaped threaded rod; the rotor wing driving motor is arranged at the head end of the rotor wing supporting plate in a supporting mode, and two positioning slots are symmetrically arranged on the left side and the right side of the front end of the rotor wing supporting plate in a supporting mode; the three vertical supporting sleeves are arranged in a rectangular shape with semicircular transition at two ends, are in an annular array and are sleeved on the middle buffer ring and the bottom ring, and are fixedly connected together; the three sliding positioning rods respectively penetrate through the semicircular top plates of the three vertical supporting sleeves and protrude downwards to be inserted into the three vertical supporting sleeves, and the tail ends of the three sliding positioning rods are provided with a prescription-shaped baffle which can slide downwards along the three vertical supporting sleeves to be pressed against the middle buffer ring; the transverse positioning plate and the two prescription-shaped threaded sleeves are correspondingly inserted and leaned on the front side and the rear side of the two positioning slots, the two plum blossom-shaped threaded rods sequentially penetrate through the two jacks and the two positioning slots on the transverse positioning plate and are locked inside the two prescription-shaped threaded sleeves, and then the protection mechanism body is locked, clamped and positioned on the rotor wing supporting plate.
Furthermore, six buffer supports are arranged between the middle buffer ring and the bottom ring in an annular array support mode and are formed by connecting and combining the left U-shaped bent ribbon board and the right U-shaped bent ribbon board.
Furthermore, three arc supporting plates which are supported downwards are arranged on the top ring in an annular array mode, and the tail ends of the three arc supporting plates are connected with the bottom ring in a locking mode through screws.
Furthermore, the top ends of the three sliding positioning rods are locked and supported by screws to form a top ring, and the three sliding positioning rods are sleeved with springs which are compressed and clamped between the top ring and the three vertical supporting sleeves.
Furthermore, the inner side end faces of the lower half parts of the three vertical support sleeves are respectively hung and supported with a bending support plate, the tail end of the front bending support plate is provided with a transverse positioning plate in an injection molding mode, the left end and the right end of the transverse positioning plate are symmetrically provided with two insertion holes, and the tail ends of the two bending support plates on the left side and the right side are respectively provided with a prescription-shaped threaded sleeve in a forming mode.
Compared with the prior art, the invention has the following beneficial effects:
according to the invention, three springs, six buffer brackets and three arc-shaped support plates are matched with each other for supporting, so that the vertical impact force acting on the top ring can be buffered and diluted for three times, further the impact damage strength is greatly reduced, the probability of rotor wing damage caused by the broken protective cover is reduced, and the protective mechanism body can realize convenient sliding, inserting, disassembling and assembling through the transverse positioning plate and the two-square threaded sleeve.
Drawings
Fig. 1 is a schematic view of the installation position relationship of the present invention.
Fig. 2 is a three-dimensional structure diagram of the installation position relationship of the present invention.
Fig. 3 is a schematic structural diagram of the present invention.
Fig. 4 is a schematic diagram of a three-dimensional structure of the present invention.
In the drawings, the corresponding relationship between the component names and the reference numbers is as follows:
1-rotor wing supporting plate, 101-positioning slot, 2-rotor wing driving motor, 3-bottom ring, 301-buffer bracket, 4-arc supporting plate, 5-middle buffer ring, 6-vertical supporting sleeve, 601-bending supporting plate, 6011-transverse positioning plate, 6012-square thread sleeve, 7-sliding positioning rod, 701-spring, 8-top ring and 9-quincunx threaded rod.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.
In the description of the present invention, "a plurality" means two or more unless otherwise specified; the terms "upper", "lower", "left", "right", "inner", "outer", "front", "rear", "head", "tail", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, should not be construed as limiting the invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "connected" and "connected" are to be interpreted broadly, e.g., as being fixed or detachable or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example (b):
as shown in figures 1 to 4:
the invention provides a protection mechanism of an unmanned aerial vehicle wing, which comprises a rotor wing support plate 1, a positioning slot 101, a rotor wing driving motor 2, a bottom ring 3, a buffer bracket 301, an arc-shaped support plate 4, a middle buffer ring 5, a vertical support sleeve 6, a bent support plate 601, a transverse positioning plate 6011, a square thread sleeve 6012, a sliding positioning rod 7, a spring 701, a top ring 8 and a plum blossom threaded rod 9; the front end of the rotor wing supporting plate 1 is supported and provided with a rotor wing driving motor 2, and the left side and the right side of the front end of the rotor wing supporting plate are symmetrically supported with two positioning slots 101; the three vertical supporting sleeves 6 are arranged in a rectangular shape with semicircular transition at two ends, are in an annular array and are sleeved on the middle buffer ring 5 and the bottom ring 3, and the three vertical supporting sleeves 6 are fixedly connected with the bottom ring 3; the three sliding positioning rods 7 respectively penetrate through semicircular top plates of the three vertical supporting sleeves 6 and protrude downwards to be inserted into the three vertical supporting sleeves 6, and the tail ends of the three sliding positioning rods 7 are respectively provided with a prescription-shaped baffle which can slide downwards along the three vertical supporting sleeves 6 to be pressed against the middle buffer ring 5; the transverse positioning plate 6011 and the two prescription-shaped threaded sleeves 6012 are correspondingly inserted and leaned against the front side and the rear side of the two positioning slots 101, and the two quincunx threaded rods 9 sequentially pass through the two jacks and the two positioning slots 101 on the transverse positioning plate 6011 and are locked inside the two prescription-shaped threaded sleeves 6012, so that the protection mechanism body is locked and clamped on the rotor wing supporting plate 1.
The middle buffer ring 5 is connected with the bottom ring 3 through the U-shaped bent slats, and the middle buffer ring 5 is connected with the three sliding positioning rods 7 through the U-shaped bent slats, so that impact force can be transmitted to the six buffer brackets 301, and the U-shaped bent slats can be elastically bent and deformed to buffer and absorb the impact force.
Wherein, be the arc backup pad 4 that the annular array was provided with three supports downwards on the top ring 8, and the tail end of these three arc backup pads 4 all is in the same place with 3 screw lock of bottom ring locks, and arc backup pad 4 can bear the side striking, carries out the side to the rotor and supports the protection.
Wherein, the top end screws of the three sliding positioning rods 7 are locked and supported with a top ring 8, and the three sliding positioning rods 7 are sleeved with a spring 701, the three springs 701 are compressed and clamped between the top ring 8 and the three vertical supporting sleeves 6, when the unmanned aerial vehicle is turned on one side and lands, the top ring 8 firstly impacts and contacts the ground to support and protect the rotor wing, in the process, the top ring 8 drives the three sliding positioning rods 7 to compress the three springs 701 to slide downwards under the action of impact force, and then three spring 701 can carry out first buffering absorption to the impact force by the elastic rebound, and three spring 701, six buffering support 301 and three arc backup pad 4 cooperate to support and use and can carry out cubic buffering to the perpendicular impact that acts on top ring 8 and dilute, reduce the impact damage that the impact force caused top ring 8, reduce the broken probability of top ring 8, and then make top ring 8 can support the protection to the rotor more effectually.
The protection mechanism can realize convenient sliding, inserting, disassembling and assembling by inserting, locking or loosening and taking out two quincuncial threaded rods 9, and can complete disassembling and assembling operations of the protection mechanism, so that the assembling and disassembling processes of the protection mechanism body are greatly simplified, and the use flexibility of the protection mechanism is improved.
The specific use mode and function of the embodiment are as follows:
according to the assembly process, the transverse positioning plate 6011 and the two prescription-shaped threaded sleeves 6012 are correspondingly inserted and leaned against the front side and the rear side of the two positioning slots 101, and then the two quincunx threaded rods 9 sequentially penetrate through the two jacks and the two positioning slots 101 on the transverse positioning plate 6011 and are locked inside the two prescription-shaped threaded sleeves 6012, so that the protection mechanism body is locked, clamped and supported on the rotor wing supporting plate 1.
The embodiments of the present invention have been presented for purposes of illustration and description, and are not intended to be exhaustive or limited to the invention in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiment was chosen and described in order to best explain the principles of the invention and the practical application, and to enable others of ordinary skill in the art to understand the invention for various embodiments with various modifications as are suited to the particular use contemplated.
Claims (1)
1. The utility model provides a protection machanism of unmanned aerial vehicle wing which characterized in that: the rotor wing type aircraft engine comprises a rotor wing supporting plate (1), a positioning slot (101), a rotor wing driving motor (2), a bottom ring (3), a buffer bracket (301), an arc-shaped supporting plate (4), a middle buffer ring (5), a vertical supporting sleeve (6), a bending supporting plate (601), a transverse positioning plate (6011), a square thread sleeve (6012), a sliding positioning rod (7), a spring (701), a top ring (8) and a plum blossom threaded rod (9); a rotor wing driving motor (2) is supported and installed at the head end position of the rotor wing supporting plate (1), and two positioning slots (101) are symmetrically supported at the left side and the right side of the front end position of the rotor wing supporting plate; the three vertical supporting sleeves (6) are arranged in a rectangular manner with semicircular transition at two ends, are in an annular array and are sleeved on the middle buffer ring (5) and the bottom ring (3), and the three vertical supporting sleeves (6) are fixedly connected with the bottom ring (3); the three sliding positioning rods (7) respectively penetrate through semicircular top plates of the three vertical supporting sleeves (6) and are convexly inserted into the three vertical supporting sleeves (6), the tail ends of the three sliding positioning rods (7) are respectively provided with a prescription-shaped baffle, and the three prescription-shaped baffles can slide downwards along the three vertical supporting sleeves (6) and are pressed against the middle buffer ring (5); the transverse positioning plate (6011) and the two prescription-shaped threaded sleeves (6012) are correspondingly inserted and leaned against the front side and the rear side of the two positioning slots (101), the two plum blossom-shaped threaded rods (9) sequentially penetrate through the two jacks and the two positioning slots (101) on the transverse positioning plate (6011) and are locked inside the two prescription-shaped threaded sleeves (6012), and then the protection mechanism body is locked and clamped on the rotor wing supporting plate (1); six buffer brackets (301) are supported between the middle buffer ring (5) and the bottom ring (3) in an annular array manner, and the six buffer brackets (301) are formed by connecting and combining two left and right U-shaped bent battens; three arc-shaped supporting plates (4) which are supported downwards are arranged on the top ring (8) in an annular array, and the tail ends of the three arc-shaped supporting plates (4) are all in screw locking connection with the bottom ring (3); the top ends of the three sliding positioning rods (7) are in screw locking support with a top ring (8), the three sliding positioning rods (7) are sleeved with springs (701), and the three springs (701) are compressed and clamped between the top ring (8) and the three vertical supporting sleeves (6); the inner side end faces of the lower half parts of the three vertical support sleeves (6) are respectively hung and supported with a bending support plate (601), wherein the tail end of the front bending support plate (601) is provided with a transverse positioning plate (6011) in an injection molding mode, the left end and the right end of the transverse positioning plate (6011) are symmetrically provided with two jacks, and the tail ends of the two bending support plates (601) on the left side and the right side are respectively provided with a prescription-shaped threaded sleeve (6012) in a forming mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810871549.6A CN108910029B (en) | 2018-08-02 | 2018-08-02 | Protection mechanism of unmanned aerial vehicle wing |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810871549.6A CN108910029B (en) | 2018-08-02 | 2018-08-02 | Protection mechanism of unmanned aerial vehicle wing |
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| CN108910029A CN108910029A (en) | 2018-11-30 |
| CN108910029B true CN108910029B (en) | 2021-06-04 |
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| CN201810871549.6A Active CN108910029B (en) | 2018-08-02 | 2018-08-02 | Protection mechanism of unmanned aerial vehicle wing |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110254693A (en) * | 2019-06-27 | 2019-09-20 | 江苏大成航空科技有限公司 | A kind of agricultural plant protection unmanned plane failure protecting device |
| CN111874225A (en) * | 2020-08-02 | 2020-11-03 | 嘉兴勤慎智能技术有限公司 | Unmanned aerial vehicle ground-imitating flying device based on laser radar |
| CN111891371A (en) * | 2020-08-02 | 2020-11-06 | 嘉兴勤慎智能技术有限公司 | Unmanned aerial vehicle topography survey device |
| CN113772083B (en) * | 2021-10-22 | 2023-08-25 | 湖南文理学院 | Unmanned aerial vehicle for personnel tracking |
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| CN208602713U (en) * | 2018-08-02 | 2019-03-15 | 滨州学院 | A kind of protection mechanism of unmanned plane wing |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| ITTO20020667A1 (en) * | 2002-07-26 | 2004-01-26 | Fiat Ricerche | MICRO-AIRCRAFT VTOL |
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105366045A (en) * | 2015-12-17 | 2016-03-02 | 湖南云顶智能科技有限公司 | Multi-rotor-wing unmanned aerial vehicle |
| CN107985615A (en) * | 2017-12-13 | 2018-05-04 | 福州堂影智能科技有限公司 | A kind of unmanned plane active safety feature |
| CN107839877A (en) * | 2017-12-18 | 2018-03-27 | 南京灿华光电设备有限公司 | A kind of unmanned plane for preventing wing from losing wing detachable protector |
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| CN108910029A (en) | 2018-11-30 |
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Effective date of registration: 20230815 Address after: No. 105, Building 8, Yuanmeng Huibu Agricultural Trade Market, Huibu Community, Xingsha Street, Changsha County, Hunan Province, 410100 Patentee after: Changsha Dawoye Drone Technology Co.,Ltd. Address before: 230000 Room 203, building 2, phase I, e-commerce Park, Jinggang Road, Shushan Economic Development Zone, Hefei City, Anhui Province Patentee before: Hefei Jiuzhou Longteng scientific and technological achievement transformation Co.,Ltd. Effective date of registration: 20230815 Address after: 230000 Room 203, building 2, phase I, e-commerce Park, Jinggang Road, Shushan Economic Development Zone, Hefei City, Anhui Province Patentee after: Hefei Jiuzhou Longteng scientific and technological achievement transformation Co.,Ltd. Address before: 256603, No. five, 391 the Yellow River Road, Bincheng District, Shandong, Binzhou Patentee before: BINZHOU University |