CN106986016B - It is a kind of quickly to disconnect adaptive cruise vertical take-off and landing drone - Google Patents
It is a kind of quickly to disconnect adaptive cruise vertical take-off and landing drone Download PDFInfo
- Publication number
- CN106986016B CN106986016B CN201710221234.2A CN201710221234A CN106986016B CN 106986016 B CN106986016 B CN 106986016B CN 201710221234 A CN201710221234 A CN 201710221234A CN 106986016 B CN106986016 B CN 106986016B
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- Prior art keywords
- wing
- fixed
- controller
- column
- motor
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The present invention provides one kind and quickly disconnects adaptive cruise vertical take-off and landing drone, more particularly to air vehicle technique field, including controller, the surrounding of controller is uniformly set there are four strut, one end of strut connects with the periphery of controller, the other end of strut is equipped with motor, screw wing is equipped with above motor, motor is connected with controller, unmanned plane is additionally provided with fixed-wing, fixed-wing is set to the two sides of controller, and stress sensing module is equipped in fixed-wing, unmanned plane is additionally provided with servo motor, AD conversion module and single-chip microcontroller, stress sensing module connects with AD conversion module, AD conversion module connects with single-chip microcontroller, single-chip microcontroller connects with servo motor, servo motor connects with fixed-wing.The present invention not only has biggish loading, and endurance is long, and adapts to complicated flight environment of vehicle.
Description
Technical field
The invention belongs to air vehicle technique fields, and in particular to a kind of quickly to disconnect adaptive cruise vertical take-off and landing drone
Background technique
Traditional vertical take-off and landing drone is mostly quadrotor drone, turn of the screw wing by the way that controller surrounding is arranged in
The dynamic lifting for realizing unmanned plane, but the unmanned plane of this type, not only loading is smaller, endurance is short, and under the adverse circumstances such as strong wind
Stable type is poor.
A kind of quadrotor drone of patent (application No. is 201410694250.X), discloses a kind of quadrotor drone,
It connects firmly including four propellers, rigid right-angled intersection bracket and master control system, four propellers in rigid right-angled intersection
By four independent motor drivens on bracket institution, the master control system mechanism setting rigid right-angled intersection bracket just under
End can effectively long-time object observing dynamic, the power of four propellers of invention have though invention hovering precision is high
Limit, loading is smaller, and endurance needs to be further increased, it is difficult to be applicable in severe flight environment of vehicle.
In view of the above, one kind is now needed quickly to disconnect adaptive cruise vertical take-off and landing drone, not only had larger
Loading, and endurance is long, and adapts to complicated flight environment of vehicle.
Summary of the invention
For the above situation, it is an object of the invention to provide one kind quickly to disconnect adaptive cruise vertical take-off and landing drone, no
Only there is biggish loading, and endurance is long, and adapts to complicated flight environment of vehicle.
The present invention provides the following technical solutions:
One kind quickly disconnecting adaptive cruise vertical take-off and landing drone, including controller, and the surrounding of the controller is uniform
Set there are four strut, one end of the strut connects with the periphery of the controller, the other end of the strut equipped with motor,
Screw wing is equipped with above the motor, the motor is connected with the controller, it is characterised in that: the unmanned plane is additionally provided with solid
Determine the wing, the fixed-wing is set to the two sides of the controller, and stress sensing module, the unmanned plane are equipped in the fixed-wing
It is additionally provided with servo motor, AD conversion module and single-chip microcontroller, the stress sensing module connects with the AD conversion module, the AD
Conversion module connects with the single-chip microcontroller, and the single-chip microcontroller connects with the servo motor, the servo motor and the fixation
The wing connects.
Preferably, it is equipped with fixed column below the controller, the controller and the fixed column pass through threaded engagement；Institute
The two sides for stating fixed column are equipped with fixed-wing, and the fixed-wing and the fixed column are flexibly connected, the servo motor and the list
Piece machine is set in the fixed column.
Preferably, the one end side of the fixed-wing is equipped with rotation axis, and the surface of the fixed column is equipped with axis hole, and described turn
Moving axis passes through the axis hole and connects with the servo motor.
Preferably, functional component is additionally provided with below the fixed column, the functional component is screw hole, bracket or camera
It is one or more.
Preferably, the screw wing includes rotation column and wing plate, and the wing plate is set to the two sides of the rotation column, and the rotation column is
Hollow form；The motor is equipped with buckle, and the buckle is U-shaped, and the rotation column sleeve is set on the buckle, and the buckle
Surface is equipped with protrusion, and the inner cavity of the rotation column is equipped with the groove to match with the protrusion of the buckle.
Preferably, the end of the buckle is exposed to the inner cavity of the rotation column.
The beneficial effects of the present invention are:
(1) present invention can quickly separate fixed column and controller, screw wing and buckle, realize quickly tearing open for unmanned plane
Solution is not only convenient for the replacement of component, and is convenient for the carrying and transport of unmanned plane；
(2) lift that the present invention is generated by fixed-wing can reduce motor burden, not only reduce energy consumption, increase nothing
Man-machine endurance, and the loading of unmanned plane can be improved；
(3) present invention can automatically adjust the angle of fixed-wing by stress induction device, keep flight more stable, can fit
With severe flight environment of vehicle；
(4) functional component of the invention can be widely applied to goods and materials dispensing, aeroplane photography, agriculture, forestry, water conservancy monitoring, pipeline electricity
The fields such as power maintenance, land resources monitoring, public safety monitoring, it is applied widely.
Detailed description of the invention
Attached drawing is used to provide further understanding of the present invention, and constitutes part of specification, with reality of the invention
It applies example to be used to explain the present invention together, not be construed as limiting the invention.In the accompanying drawings:
Fig. 1 is main view of the present invention；
Fig. 2 is structure of the invention explosive view；
Fig. 3 is fixed-wing structural schematic diagram；
Fig. 4 is screw wing structural schematic diagram；
Fig. 5 is fixed-wing control system figure.
In the figure, it is marked as 1, controller；2, fixed-wing；21, rotation axis；3, screw wing；31, column is revolved；32 wing plates, 4, branch
Bar；5, fixed column；6, functional component；7, servo motor；8, motor；9, it buckles.
Specific embodiment
As shown in Figure 1, Figure 2 and shown in Fig. 5, one kind quickly disconnecting adaptive cruise vertical take-off and landing drone, including controller 1,
The surrounding of controller 1 is uniformly equipped with strut 4, and one end of strut 4 connects with the periphery of controller 1, and the other end of strut 4 is equipped with
Motor 8 is equipped with screw wing 3 above motor 8, and motor 8 is connected with controller 1, and unmanned plane is additionally provided with fixed-wing 2, and fixed-wing 2 is set to
The two sides of fixed column 5, and fixed-wing 2 be equipped with stress sensing module, unmanned plane be additionally provided with servo motor 7, AD conversion module and
Single-chip microcontroller, stress sensing module connect with AD conversion module, and AD conversion module connects with single-chip microcontroller, single-chip microcontroller and servo motor 7
Connect, servo motor 7 connects with fixed-wing 2；By controller 1 control screw wing 3 rotation, can make unmanned plane rise or under
Drop, unmanned plane is during cruise, the lift that fixed-wing 3 generates, and can reduce motor burden, greatly reduces flight power, increases
The endurance of unmanned plane is added, and the loading of unmanned plane can be improved, has been answered further through the surface that stress sensing module can incude fixed-wing 3
Power, and signal is passed into AD conversion module, signal is transmitted to single-chip microcontroller again by AD conversion module, and single-chip microcontroller passes through operation signal
Order-driven servo motor 7 automatically adjusts the deflection angle of fixed-wing 3, keeps unmanned plane during flying more stable, severe to be applicable in
Flight environment of vehicle.
As depicted in figs. 1 and 2, it is equipped with fixed column 5, controller 1 and fixed column 5 below controller 1 and passes through threaded engagement, control
5 threaded engagement of device 1 processed and fixed column can easily realize the Quick Release of unmanned plane convenient for the separation of controller 1 and fixed column 5；；
Functional component 6 is additionally provided with below fixed column 5, functional component 6 is one or more, the functional component 6 of screw hole, bracket or camera
It can be widely applied to goods and materials dispensing, aeroplane photography, agriculture, forestry, water conservancy monitoring, the monitoring of pipeline electric power overhaul, land resources, public safety
The fields such as monitoring, it is applied widely.
As shown in figures 1 and 3, the two sides of fixed column 5 are equipped with fixed-wing 2, and fixed-wing 2 and fixed column 5 are flexibly connected, servo
Motor 7 and single-chip microcontroller are set in fixed column 5；The one end side of fixed-wing 2 is equipped with rotation axis 21, and the peripheral surface of fixed column 5 is set
There is axis hole, the axis hole that rotation axis 21 passes through fixed column 5 connects with servo motor 7；This structure can make servo motor 7 drive fixed-wing
2 along rotation axis 21 longitudinal center line rotate, it can be ensured that the stability of 2 turn of fixed-wing.
As shown in Figure 1 and Figure 4, screw wing 3 includes rotation column 31 and wing plate 32, and wing plate 32 is set to the two sides of rotation column 31, revolves column
31 be hollow form；Motor 8, which is equipped with, buckles 9, and buckle 9 is U-shaped, and rotation column 31 is sheathed on buckle 9, and the surface of buckle 9 is equipped with
Protrusion, the inner cavity of rotation column 31 is equipped with the groove to match with the protrusion of buckle 9, and the end of buckle 9 is exposed to the interior of rotation column 31
Chamber；Buckle 9 can be fixed by screw wing 3, and by closing up the end of U-shaped buckle 9, can be detached from rotation column 31 and buckle 9, not only
The Quick Release of unmanned plane is realized, and is conveniently replaced different types of screw wing 3 and is improved with being applicable in different flight environment of vehicle
The stability of flight.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, although referring to aforementioned reality
Applying example, invention is explained in detail, for those skilled in the art, still can be to aforementioned each implementation
Technical solution documented by example is modified or equivalent replacement of some of the technical features.It is all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (3)
1. one kind quickly disconnects adaptive cruise vertical take-off and landing drone, including controller, the surrounding of the controller is uniform
If one end of the strut connects with the periphery of the controller there are four strut, the other end of the strut is equipped with motor, institute
It states and is equipped with screw wing above motor, the motor is connected with the controller, it is characterised in that: the unmanned plane is additionally provided with fixation
The wing, the fixed-wing is set to the two sides of the controller, and stress sensing module is equipped in the fixed-wing, and the unmanned plane is also
Equipped with servo motor, AD conversion module and single-chip microcontroller, the stress sensing module connects with the AD conversion module, and the AD turns
Mold changing block connects with the single-chip microcontroller, and the single-chip microcontroller connects with the servo motor, the servo motor and the fixed-wing
Connect；The one end side of the fixed-wing is equipped with rotation axis, and the surface of the fixed column is equipped with axis hole, and the rotation axis passes through institute
Axis hole is stated to connect with the servo motor；The screw wing includes rotation column and wing plate, and the wing plate is set to the two sides of the rotation column,
The rotation column is hollow form；The motor is equipped with buckle, and the buckle is U-shaped, and the rotation column sleeve is set on the buckle, and
The surface of the buckle is equipped with protrusion, and the inner cavity of the rotation column is equipped with the groove to match with the protrusion of the buckle；The card
The end of button is exposed to the inner cavity of the rotation column.
2. one kind according to claim 1 quickly disconnects adaptive cruise vertical take-off and landing drone, it is characterised in that: described
Fixed column is equipped with below controller, the controller and the fixed column pass through threaded engagement；The two sides of the fixed column are equipped with
Fixed-wing, the fixed-wing and the fixed column are flexibly connected, and the servo motor and the single-chip microcontroller are set to the fixed column
It is interior.
3. one kind according to claim 2 quickly disconnects adaptive cruise vertical take-off and landing drone, it is characterised in that: described
Functional component is additionally provided with below fixed column, the functional component is the one or more of screw hole, bracket or camera.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710221234.2A CN106986016B (en) | 2017-04-06 | 2017-04-06 | It is a kind of quickly to disconnect adaptive cruise vertical take-off and landing drone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710221234.2A CN106986016B (en) | 2017-04-06 | 2017-04-06 | It is a kind of quickly to disconnect adaptive cruise vertical take-off and landing drone |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106986016A CN106986016A (en) | 2017-07-28 |
| CN106986016B true CN106986016B (en) | 2019-09-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710221234.2A Active CN106986016B (en) | 2017-04-06 | 2017-04-06 | It is a kind of quickly to disconnect adaptive cruise vertical take-off and landing drone |
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| Country | Link |
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| CN (1) | CN106986016B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114802734B (en) * | 2022-06-23 | 2022-10-11 | 江苏云端智能科技有限公司 | Cruise unmanned aerial vehicle and system thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015124556A1 (en) * | 2014-02-18 | 2015-08-27 | Iat 21 Innovative Aeronautics Technologies Gmbh | Aircraft |
| CN205034338U (en) * | 2015-09-06 | 2016-02-17 | 湖北航天飞行器研究所 | Tilted four -rotor aircraft |
| CN205076045U (en) * | 2015-10-29 | 2016-03-09 | 安徽理工大学 | Combined type aircraft of varistructure |
| CN106114848A (en) * | 2016-08-26 | 2016-11-16 | 西安融智航空科技有限公司 | A kind of mooring cruise multi-mode VUAV |
| CN205770149U (en) * | 2016-05-24 | 2016-12-07 | 中电科（德阳广汉）特种飞机系统工程有限公司 | A kind of fixed-wing rotor mixing unmanned plane of multi-configuration |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2688800A2 (en) * | 2011-03-24 | 2014-01-29 | Page, Mark, Allan | Long endurance vertical takeoff and landing aircraft |
| US20160031554A1 (en) * | 2014-07-30 | 2016-02-04 | Siniger LLC | Control system for an aircraft |
-
2017
- 2017-04-06 CN CN201710221234.2A patent/CN106986016B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015124556A1 (en) * | 2014-02-18 | 2015-08-27 | Iat 21 Innovative Aeronautics Technologies Gmbh | Aircraft |
| CN205034338U (en) * | 2015-09-06 | 2016-02-17 | 湖北航天飞行器研究所 | Tilted four -rotor aircraft |
| CN205076045U (en) * | 2015-10-29 | 2016-03-09 | 安徽理工大学 | Combined type aircraft of varistructure |
| CN205770149U (en) * | 2016-05-24 | 2016-12-07 | 中电科（德阳广汉）特种飞机系统工程有限公司 | A kind of fixed-wing rotor mixing unmanned plane of multi-configuration |
| CN106114848A (en) * | 2016-08-26 | 2016-11-16 | 西安融智航空科技有限公司 | A kind of mooring cruise multi-mode VUAV |
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| Publication number | Publication date |
|---|---|
| CN106986016A (en) | 2017-07-28 |
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Effective date of registration: 20190823 Address after: 316000 Zhoushan High-tech Industrial Park, Dinghai District, Zhoushan City, Zhejiang Province Patentee after: ZHEJIANG FREE TRADE ZONE XIETONG TECHNOLOGY Co.,Ltd. Address before: 215000 Changan Road, Wujiang economic and Technological Development Zone, Jiangsu, China Patentee before: SUZHOU ENJI INTELLIGENT TECHNOLOGY CO.,LTD. |
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Effective date of registration: 20230629 Address after: 710000, 4th Floor, Guangde Garden, West Gate, Xigong University, No.127 Youyi West Road, Beilin District, Xi'an City, Shaanxi Province Patentee after: Xi'an Hangke Intelligent Information Technology Co.,Ltd. Address before: 316000 East side of the first floor of standard plant 9, Small and Micro Enterprise Park, No. 220, Xinma Avenue, Xingang Industrial Park, Dinghai District, Zhoushan, Zhejiang Province Patentee before: ZHEJIANG FREE TRADE ZONE XIETONG TECHNOLOGY Co.,Ltd. |