CN111003173B - High-mobility rotor-free unmanned aerial vehicle - Google Patents
High-mobility rotor-free unmanned aerial vehicle Download PDFInfo
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- CN111003173B CN111003173B CN201911367837.9A CN201911367837A CN111003173B CN 111003173 B CN111003173 B CN 111003173B CN 201911367837 A CN201911367837 A CN 201911367837A CN 111003173 B CN111003173 B CN 111003173B
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- circular ring
- rotor
- motor
- rubber sleeve
- unmanned aerial
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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
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
- B64C29/04—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded characterised by jet-reaction propulsion
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
- B64C15/12—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets the power plant being tiltable
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
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- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
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Abstract
The invention discloses a high-maneuverability rotor-free unmanned aerial vehicle, which comprises a rack, a battery, a controller and a power system, wherein the rack is provided with a power supply; the power system is provided with a plurality of sets and symmetrically arranged at two opposite sides of the frame; the power system comprises a motor, a wind post, a bearing, a circular ring and a rubber sleeve; the circular ring is of a hollow structure, and the inner wall of the circular ring is provided with a circle of open slots; the rubber sleeve is sleeved on the outer wall of the circular ring, and a plurality of through holes are formed in the rubber sleeve; a motor and blades which are matched with each other are arranged in the wind post; the wind column is communicated with the inside of the circular ring; the wind post is embedded in the bearing and is connected with the motor. Compared with the existing fixed-wing unmanned aerial vehicle, the unmanned aerial vehicle can vertically lift and turn under the hovering state, can rapidly switch forward and backward, is flexible in turning and has stronger maneuverability; compare current many rotor unmanned aerial vehicle, horizontal flight speed is faster, and no rotor impeller, anti striking ability is stronger, can only need two sets of driving system, and weight is lighter behind the no rotor, and endurance promotes.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a high-maneuverability rotor-free unmanned aerial vehicle.
Background
The existing unmanned aerial vehicle generally comprises a fixed-wing unmanned aerial vehicle and a multi-rotor unmanned aerial vehicle, wherein the fixed-wing unmanned aerial vehicle has the advantages of high flying speed and large steering radius and cannot take off and land vertically, and the take-off condition is provided by a relatively flat ground; but many rotor unmanned aerial vehicle's advantage is VTOL, and vertical lift-off is fast, and the shortcoming is that the rotor easily receives the striking when taking off and landing unstability and damages, and horizontal flight speed is slow, and mobility is poor.
Disclosure of Invention
The invention aims to solve the problem that the existing unmanned aerial vehicle cannot simultaneously meet the advantages of high maneuverability, vertical take-off and landing, rapid steering and the like, and provides a high-maneuverability rotor-free unmanned aerial vehicle which can take off and land vertically, has high horizontal flight speed and flexible steering and is not easy to be damaged by collision.
In order to achieve the purpose, the high-maneuverability rotor-free unmanned aerial vehicle comprises a rack, a battery, a controller and a power system;
the battery and the controller are arranged on the rack and electrically connected with the power system;
the power systems are provided with a plurality of sets and are symmetrically arranged on two opposite sides of the rack; the power system comprises a motor, a wind column, a bearing, a circular ring and a rubber sleeve;
the circular ring is of a hollow structure and is positioned outside the rack, the upper end and the lower end of the circular ring respectively protrude back to the opposite direction to form arc surfaces, and the inner wall of the circular ring close to the upper end or the lower end is provided with a circle of open slots which are coaxial with the circular ring; the width of the opening of the open slot is 1-2 mm; the outer wall of the circular ring is provided with a mounting opening communicated with the inside of the circular ring;
the rubber sleeve is sleeved on the outer wall of the circular ring, the thickness of the rubber sleeve is greater than that of the circular ring, and a plurality of through holes parallel to the axis of the circular ring are formed in the rubber sleeve;
a motor and blades which are matched with each other are arranged in the wind post; an air inlet is formed in the side wall or one end of the air column, the other end of the air column penetrates through the rubber sleeve to be connected with the mounting opening in the outer wall of the circular ring, and an air outlet communicated with the inside of the circular ring is formed in the other end of the air column;
the motor and the bearing are coaxially arranged, the motor and the bearing are respectively connected with the rack, the wind post is embedded in the bearing, and the wind post is connected with a rotating shaft of the motor.
Furthermore, the through holes in the rubber sleeve are uniformly distributed along the circumferential direction of the rubber sleeve.
Further, the arc length of the arc surface at the upper end of the circular ring is longer than that of the arc surface at the lower end of the circular arc; the distance between the open slot and the upper end of the circular ring is less than the distance between the open slot and the lower end of the circular ring.
Furthermore, the open slot is positioned at the joint of the inner wall of the circular ring and the circular arc surface at the upper end of the circular ring; one side of the open slot close to the upper end of the circular ring is provided with an outer edge circumscribed with the arc surface of the upper end; one side of the open slot close to the lower end of the circular ring is provided with an inner edge inscribed with the arc surface at the upper end; the clearance between outer border and the interior border is 1 mm.
Further, the power system has two sets; and the controller is independently connected with the motor and the motor in each set of power system.
Further, the height of the rubber sleeve is higher than that of the circular ring.
Furthermore, the wind post is connected with the rotating shaft of the motor through a flange plate.
Further, the lower end of the rack is provided with a holder or a shooting device.
The invention has the beneficial effects that: compared with the existing fixed-wing unmanned aerial vehicle, the unmanned aerial vehicle can vertically lift and turn under the hovering state, can rapidly switch forward and backward, is flexible in turning and has stronger maneuverability; compare current many rotor unmanned aerial vehicle, horizontal flight speed is faster, and no rotor impeller, anti striking ability is stronger, can only need two sets of driving system, and weight is lighter behind the no rotor, and endurance promotes.
Drawings
Fig. 1 is a schematic top view of the high mobility drone without rotor of the present invention.
Fig. 2 is a schematic structural view of fig. 1 with the rubber sleeve removed.
FIG. 3 is a schematic sectional view A-A of FIG. 2.
Fig. 4 is a partially enlarged schematic view of fig. 3.
Fig. 5 is a schematic structural diagram of the power system of fig. 2 after rotating a certain angle.
Fig. 6 is a schematic perspective view of the rubber sleeve in fig. 1.
In the figure, a frame 1, a battery 2, a controller 3, a motor 4, a wind post 5, a bearing 6, a circular ring 7, a rubber sleeve 8, a through hole 9, a motor 10, a blade 11, an air inlet 12, an air outlet 13, a flange 14, an outer edge 15, an inner edge 16 and an open slot 17 are arranged.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
The high-maneuverability rotor-free unmanned aerial vehicle shown in fig. 1-6 comprises a frame 1, a battery 2, a controller 3 and a power system;
the battery 2 and the controller 3 are arranged on the frame 1 and electrically connected with the power system;
the power system is provided with a plurality of sets and symmetrically arranged at two opposite sides of the frame 1; the power system comprises a motor 4, a wind column 5, a bearing 6, a circular ring 7 and a rubber sleeve 8;
the circular ring 7 is of a hollow structure and is positioned outside the rack 1, the upper end and the lower end of the circular ring 7 respectively protrude towards the back opposite direction to form arc surfaces, and a circle of open slots 17 which are coaxial with the circular ring 7 are formed in the inner wall of the circular ring 7 close to the upper end or the lower end; the width of the opening of the open slot 17 is 1-2 mm; the outer wall of the circular ring 7 is provided with a mounting opening communicated with the inside of the circular ring;
the rubber sleeve 8 is sleeved on the outer wall of the circular ring 7, the thickness of the rubber sleeve 8 is larger than that of the circular ring 7, and a plurality of through holes 9 parallel to the axis of the circular ring 7 are formed in the rubber sleeve 8; the through holes 9 are uniformly arranged along the circumferential direction of the rubber sleeve 8;
a motor 10 and blades 11 which are matched with each other are arranged in the wind post 5; an air inlet 12 is formed in the side wall or one end of the air column 5, the other end of the air column 5 penetrates through the rubber sleeve 8 to be connected with an installation opening in the outer wall of the circular ring 7, and an air outlet 13 communicated with the inside of the circular ring 7 is formed in the other end of the air column 5;
As shown in fig. 4, the arc length of the arc surface at the upper end of the circular ring 7 is longer than that of the arc surface at the lower end of the circular arc; the distance between the open slot 17 and the upper end of the circular ring 7 is less than the distance between the open slot 17 and the lower end of the circular ring 7. The open slot 17 is positioned at the joint of the inner wall of the circular ring 7 and the circular arc surface at the upper end of the circular ring 7; one side of the open slot 17 close to the upper end of the circular ring 7 is provided with an outer edge 15 which is circumscribed with the circular arc surface of the upper end; an inner edge 16 inscribed with an upper end arc surface is arranged on one side of the open slot 17 close to the lower end of the circular ring 7; the gap between the outer edge 15 and the inner edge 16 is 1 mm.
In the embodiment, two sets of power systems are provided; the controller 3 is separately connected with the motor 4 and the motor 10 in each set of power system. The rotation speed/power on/off of the motor 4 or the motor 10 in different power systems is controlled through the controller 3, so that the flight control of the whole unmanned aerial vehicle is realized.
In order to better protect the ring 7 from impacts, the rubber sleeve 8 is higher than the ring 7.
In order to realize different functions, the lower end of the frame 1 is provided with a cloud deck or a shooting device, the shooting device can be a video camera or a camera, and of course, the cloud deck can also be provided with other equipment, such as a mechanical claw.
As shown in fig. 4, the direction shown by the arrow in the figure is the air flow direction, the motor 10 of this embodiment rotates, the driving blade 11 rotates, the air enters from the air inlet 12 of the wind post 5, and blow out to the ring 7 from the air outlet 13 of the wind post 5, because the ring 7 is provided with the open slot 17 with the slot opening width of 1-2 mm, under the effect of the bernoulli effect, the air volume blown out from the upper end or the lower end (the lower end shown in fig. 4 in this embodiment) of the ring 7 is 15-18 times of the air suction, great thrust is provided for the unmanned aerial vehicle, and vertical rising and fast flight of the unmanned aerial vehicle are realized. For convenience of description, the direction in which air is blown out from the ring 7 is defined as a direction from the upper end to the lower end of the ring 7 in parallel with the axis of the ring 7.
In addition, the rubber sleeve 8 not only plays a role in protecting the circular ring 7, but also can further increase the air volume and improve the stability by the aid of the through holes 9 arranged on the rubber sleeve. Due to the negative air pressure effect at the position of the circular ring 7, air at the periphery of the circular ring 7 is sucked into the circular ring 7 and blown out from the lower end of the circular ring 7, but the air sucked by the negative pressure is not stable enough, the circulation direction is not smooth enough, and particularly, certain turbulent flow is generated when the air close to the inner wall of the circular ring 7 is blown out from the lower end of the circular ring 7, so that the flight stability is influenced; and a plurality of through holes 9 which are parallel to the axis of the circular ring 7 are arranged on the rubber sleeve 8, under the drainage action of the through holes 9, edge airflow is blown out parallel to the axis of the circular ring 7 after passing through the through holes 9 and towards the lower end of the circular ring 7, turbulent flow in the inner wall area of the circular ring 7 is limited, and the flying stability is improved.
When the flying direction needs to be changed, the controller 3 is only needed to control the motor 4 and the motor 10 in the corresponding power system; the direction of the circular ring 7 can be changed by rotating the motor 4, so that the blowing direction of the airflow is changed; after the ring 7 on the left side changes direction, the flight direction of the drone will change, as shown in fig. 5. In addition, through adjusting motor 10 slew rate, also can realize the change of direction, for example, when unmanned aerial vehicle is flying forward fast, ring 7 should be in the vertical state this moment, if reduce the interior motor 10 rotational speed of right side driving system, then under the pushing effect of left side driving system, unmanned aerial vehicle turns to the right, vice versa, after rotating the required position, makes the motor 10 rotational speed of the driving system of left and right sides the same can fly towards this position. When controller 3 simultaneously control motor 4 and motor 10, unmanned aerial vehicle mobility will be stronger, can accomplish fast and move forward, retreat, lift off, descend, turn, upset etc. and move. This kind of high mobility is that current many rotor unmanned aerial vehicle and fixed wing unmanned aerial vehicle can't realize.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (8)
1. The utility model provides a high mobility does not have rotor formula unmanned aerial vehicle which characterized in that: comprises a frame (1), a battery (2), a controller (3) and a power system;
the battery (2) and the controller (3) are arranged on the rack (1) and are electrically connected with the power system;
the power systems are provided with a plurality of sets and are symmetrically arranged on two opposite sides of the rack (1); the power system comprises a motor (4), a wind post (5), a bearing (6), a circular ring (7) and a rubber sleeve (8);
the circular ring (7) is of a hollow structure and is positioned outside the rack (1), the upper end and the lower end of the circular ring (7) are respectively protruded towards the back to the opposite direction to form circular arc surfaces, and a circle of open slot (17) coaxial with the circular ring (7) is arranged on the inner wall of the circular ring (7) close to the upper end or the lower end; the width of the opening of the open slot (17) is 1-2 mm; the outer wall of the circular ring (7) is provided with a mounting opening communicated with the inside of the circular ring;
the rubber sleeve (8) is sleeved on the outer wall of the circular ring (7), the thickness of the rubber sleeve (8) is larger than that of the circular ring (7), and a plurality of through holes (9) parallel to the axis of the circular ring (7) are formed in the rubber sleeve (8);
a motor (10) and blades (11) which are matched with each other are arranged in the wind post (5); an air inlet (12) is formed in the side wall or one end of the air column (5), the other end of the air column (5) penetrates through the rubber sleeve (8) to be connected with an installation opening in the outer wall of the circular ring (7), and an air outlet (13) communicated with the inside of the circular ring (7) is formed in the other end of the air column (5);
the motor (4) and the bearing (6) are coaxially arranged, the motor (4) and the bearing (6) are respectively connected with the rack (1), the wind post (5) is embedded in the bearing (6), and the wind post (5) is connected with a rotating shaft of the motor (4).
2. The high mobility, rotor-less drone of claim 1, wherein: through holes (9) in the rubber sleeve (8) are uniformly distributed along the circumferential direction of the rubber sleeve (8).
3. The high mobility, rotor-less drone of claim 1, wherein: the arc length of the arc surface at the upper end of the circular ring (7) is longer than that of the arc surface at the lower end of the circular arc; the distance between the open slot (17) and the upper end of the circular ring (7) is less than the distance between the open slot (17) and the lower end of the circular ring (7).
4. The high mobility, rotor-less drone of claim 3, wherein: the open slot (17) is positioned at the joint of the inner wall of the circular ring (7) and the arc surface at the upper end of the circular ring (7); one side of the open slot (17) close to the upper end of the circular ring (7) is provided with an outer edge (15) which is circumscribed with the circular arc surface at the upper end; an inner edge (16) inscribed with an arc surface at the upper end is arranged on one side of the open slot (17) close to the lower end of the circular ring (7); the clearance between outer border (15) and interior border (16) is 1 mm.
5. The high mobility, rotor-less drone of claim 1, wherein: the power systems are provided with two sets; and the controller (3) is independently connected with the motor (4) and the motor (10) in each set of power system.
6. The high mobility, rotor-less drone of claim 1, wherein: the height of the rubber sleeve (8) is higher than that of the circular ring (7).
7. The high mobility, rotor-less drone of claim 1, wherein: the wind post (5) is connected with the rotating shaft of the motor (4) through a flange plate (14).
8. The high mobility, rotor-less drone of claim 1, wherein: the lower end of the frame (1) is provided with a holder or a shooting device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911367837.9A CN111003173B (en) | 2019-12-26 | 2019-12-26 | High-mobility rotor-free unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911367837.9A CN111003173B (en) | 2019-12-26 | 2019-12-26 | High-mobility rotor-free unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN111003173A CN111003173A (en) | 2020-04-14 |
| CN111003173B true CN111003173B (en) | 2021-06-01 |
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| CN201911367837.9A Active CN111003173B (en) | 2019-12-26 | 2019-12-26 | High-mobility rotor-free unmanned aerial vehicle |
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| US20040139710A1 (en) * | 1999-05-21 | 2004-07-22 | Lewis Illingworth | Passive transfer chamber separator |
| KR100404117B1 (en) * | 2001-08-03 | 2003-11-03 | 엘지전자 주식회사 | Structure for generating cooling air flow in refrigerator |
| US20080011899A1 (en) * | 2006-07-14 | 2008-01-17 | Aster Amit | Light weight vertical takeoff and landing aircraft |
| CN204846369U (en) * | 2015-06-19 | 2015-12-09 | 谭国荣 | Rotor unmanned aerial vehicle's rotor safety cover and rotor unmanned aerial vehicle |
| KR101607816B1 (en) * | 2015-10-26 | 2016-03-31 | 이진우 | Drone with air guide part |
| CN205273849U (en) * | 2015-11-30 | 2016-06-01 | 湖北易瓦特科技股份有限公司 | Double -oar rotor unmanned aerial vehicle |
| CN205293095U (en) * | 2015-12-30 | 2016-06-08 | 郑云龙 | Unmanned aerial vehicle |
| KR101804325B1 (en) * | 2016-04-12 | 2017-12-04 | (주)하늘과기술 | Drone |
| WO2017188699A1 (en) * | 2016-04-25 | 2017-11-02 | 탁승호 | Discharge device comprising variable nozzle |
| CN106314777B (en) * | 2016-08-29 | 2019-12-24 | 英华达（上海）科技有限公司 | Unmanned aerial vehicle |
| CN207550500U (en) * | 2017-11-01 | 2018-06-29 | 熊云凯 | A kind of Portable unmanned machine |
| KR20190061994A (en) * | 2017-11-28 | 2019-06-05 | 석문전기 주식회사 | Bldc motor of dron for spraying agricultural pesticide |
| CN208036614U (en) * | 2018-03-27 | 2018-11-02 | 郑州大学 | A kind of omnidirectional's aircraft |
| CN208412157U (en) * | 2018-06-21 | 2019-01-22 | 深圳市瑞云无人机技术有限公司 | A kind of unmanned plane vertically force-lands protective device |
| CN208947599U (en) * | 2018-08-01 | 2019-06-07 | 中铁上海工程局集团有限公司 | Unmanned plane paddle blade structure based on bim technology |
| CN109050888A (en) * | 2018-10-26 | 2018-12-21 | 常州大学怀德学院 | A kind of six rotor wing unmanned aerial vehicles |
| CN110341940B (en) * | 2019-08-06 | 2023-01-10 | 中咨数据有限公司 | Stably-moving wind-resistant rescue unmanned aerial vehicle |
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Effective date of registration: 20210519 Address after: 430000 No.39, 1st floor, building B, central shopping mall, Hanzheng Street, Qiaokou District, Wuhan City, Hubei Province Applicant after: Hubei Guiyuan UAV Environmental Protection Technology Co.,Ltd. Address before: 526000 Guangdong Institute of technology, Qifu Avenue, Gaoyao District, Zhaoqing City, Guangdong Province Applicant before: Li Mingchun |
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