CN207148653U - A kind of wind proof unmanned plane during flying system - Google Patents
A kind of wind proof unmanned plane during flying system Download PDFInfo
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- CN207148653U CN207148653U CN201721223216.XU CN201721223216U CN207148653U CN 207148653 U CN207148653 U CN 207148653U CN 201721223216 U CN201721223216 U CN 201721223216U CN 207148653 U CN207148653 U CN 207148653U
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- unmanned plane
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Abstract
The utility model provides a kind of wind proof unmanned plane during flying system, including unmanned plane, base station, terminal；The terminal is by wireless connection base station, and control base station distributes task；Base station receives the carrying out self terminal of the task, and carries out wireless connection with unmanned plane, and control unmanned plane performs task；Provided with GPS module, MCU, Attitude Controller, the motor for driving unmanned plane change of flight posture, gyro module in unmanned plane；The GPS module, gyro module are electrically connected with MCU；The MCU is electrically connected with Attitude Controller；The Attitude Controller is electrically connected with motor；Four sides of the unmanned plane are respectively equipped with air velocity transducer, and air velocity transducer is electrically connected with MCU.MCU calculates flight angle and the speed that unmanned plane adjusts according to wind direction and wind speed needs by internal processes, then by controlling Attitude Controller to drive unmanned plane change of flight posture, so that unmanned plane can adjust flight attitude in real time according to environment, wind loading rating is improved.
Description
Technical field
It the utility model is related to unmanned air vehicle technique field, and in particular to a kind of wind proof unmanned plane during flying system.
Background technology
Multi-rotor unmanned aerial vehicle has that volume and quality are small, disguised and security is good, can flexibly VTOL, flying height
The advantages that low, mobility strong, simple in construction, operation are flexibly and cost is relatively low.The common task such as be used to take photo by plane, detect, scout
Multi-rotor unmanned aerial vehicle be mostly use some rotors are evenly distributed in same circumferential plane, in the central core area of unmanned plane
Hanging head under the use of domain, by battery, flight control, shoot with video-corder or the equipment such as detect and be installed on platform.This unmanned plane is set
Meter with installation method although it is simple in construction, be easily installed, but there is also wind loading rating it is poor, damage fault rate it is high the defects of.Specifically
Show as：More rotors of unmanned plane deploy in a plane, and distribution is larger, cause wind loading rating poor, are happened suddenly when running into
Crosswind or high wind when, frequently can lead to unmanned plane and tumble；Unmanned plane descent is the key link that unmanned plane manipulates, once
High wind is run into when operational error or landing, easily causes unmanned plane to tumble, causes unmanned plane to damage.
Therefore, the wind loading rating for improving unmanned plane is one of the research direction in unmanned air vehicle technique field.
Utility model content
In view of the shortcomings of the prior art, the utility model provides a kind of wind proof unmanned plane during flying system, it is possible to increase nothing
Man-machine wind loading rating.
To achieve the above object, the utility model adopts the following technical scheme that：
A kind of wind proof unmanned plane during flying system, including unmanned plane, base station, terminal；The terminal passes through wireless connection base
Stand, and control base station distribution task；The base station receives the carrying out self terminal of the task, and carries out wireless connection, control with unmanned plane
Unmanned plane performs task；GPS module, MCU, Attitude Controller, driving unmanned plane change of flight are provided with the unmanned plane
The motor of posture, gyro module；The GPS module, gyro module are electrically connected with MCU；The MCU and flight attitude
Controller is electrically connected with；The Attitude Controller is electrically connected with motor；Four sides of the unmanned plane are respectively equipped with
Air velocity transducer, the air velocity transducer are electrically connected with MCU；
The gyro module measurement unmanned plane current 3-axis acceleration and three axis angular rates, are carried out by gyro module
DMP is resolved and is obtained the unmanned aerial vehicle body attitude angle relative to earth coordinates, and unmanned aerial vehicle body attitude angle information is transmitted
To MCU；
The air velocity transducer measures the relative velocity of wind direction and unmanned plane and air in real time, and by wind direction and relatively fast
Information transmission is spent to MCU；
The MCU according to unmanned aerial vehicle body attitude angle information and the relative velocity of wind direction and unmanned plane and air,
Flight angle and the speed that unmanned plane need to adjust are calculated, and flight angle and velocity information that unmanned plane need to be adjusted pass to
Data message is converted into the output of electric signal controlled motor by Attitude Controller, Attitude Controller, so as to control nothing
Man-machine flight attitude.
Further, the unmanned plane is four rotor wing unmanned aerial vehicles, and air velocity transducer is installed between two adjacent rotors.
Further, the air velocity transducer is arranged on the rotor of unmanned plane.
Further, the unmanned aerial vehicle body attitude angle includes roll angle φ ', pitching angle theta ' and yaw angle ψ '.
Beneficial effect：The utility model is respectively equipped with air velocity transducer in four sides of unmanned plane, to measure wind direction
And the relative velocity of unmanned plane and air, while gyro module measures the current 3-axis acceleration of unmanned plane and three shaft angles speed
Degree, and is resolved by DMP and obtains unmanned aerial vehicle body attitude angle, MCU by internal processes calculate unmanned plane according to wind direction with
Wind speed needs flight angle and the speed adjusted, then by controlling Attitude Controller to drive unmanned plane change of flight appearance
State, so that unmanned plane can adjust flight attitude in real time according to environment, improve wind loading rating.
Brief description of the drawings
Fig. 1 is system block diagram of the present utility model；
Fig. 2 is the structure diagram of unmanned plane；
Label in figure：1st, unmanned plane；2nd, air velocity transducer；3rd, GPS module；4th, gyro module；5th, flight attitude controls
Device；6、MCU；7th, motor；8th, rotor.
Embodiment
For detailed description technology contents of the present utility model, the objects and the effects, below in conjunction with embodiment and match somebody with somebody
Accompanying drawing is closed to be explained.
As shown in figure 1, wind proof unmanned plane during flying system provided by the utility model includes GPS module 3, air velocity transducer
2nd, MCU (microprocessor), Attitude Controller 5, motor 7, gyro module 4.GPS module 3, gyro module 4, wind speed pass
Sensor 2 is electrically connected with respectively at MCU 6, and MCU 6 is electrically connected with Attitude Controller 5；Attitude Controller 5 and motor
7 are electrically connected with.Air velocity transducer 2 is arranged on four sides of unmanned plane 1.
Such as the structure diagram that Fig. 2 is the rotor wing unmanned aerial vehicle of one embodiment four of the present utility model, between two neighboring rotor 8
Air velocity transducer 2 is installed.
Gyro module measurement unmanned plane current 3-axis acceleration and three axis angular rates, DMP is carried out by gyro module
Resolve and obtain the unmanned aerial vehicle body attitude angle relative to earth coordinates, and unmanned aerial vehicle body attitude angle information is passed to
MCU；Air velocity transducer measures the relative velocity of wind direction and unmanned plane and air in real time, and wind direction and relative velocity are passed
Pass MCU；MCU calculates according to unmanned aerial vehicle body attitude angle information and the relative velocity of wind direction and unmanned plane and air
Go out flight angle and the speed that unmanned plane need to adjust, and flight angle and velocity information that unmanned plane need to be adjusted pass to flight
Data message is converted into the output of electric signal controlled motor by attitude controller, Attitude Controller, so as to control unmanned plane
Flight attitude.
Above-described embodiment, the purpose of this utility model, technical scheme and beneficial effect are entered
One step describes in detail, should be understood that and the foregoing is only specific embodiment of the present utility model, is not used to limit
The utility model processed, all within the spirit and principles of the utility model, any modification, equivalent substitution and improvements done etc.,
It should be included within the scope of protection of the utility model.
Claims (4)
1. a kind of wind proof unmanned plane during flying system, including unmanned plane, base station, terminal；The terminal by wireless connection base station,
And control base station distribution task；The base station receives the carrying out self terminal of the task, and carries out wireless connection with unmanned plane, controls nobody
Machine performs task；Change characterized in that, being provided with GPS module, MCU, Attitude Controller, driving unmanned plane in the unmanned plane
Become motor, the gyro module of flight attitude；The GPS module, gyro module are electrically connected with MCU；The MCU is with flying
Row attitude controller is electrically connected with；The Attitude Controller is electrically connected with motor；Four sides of the unmanned plane point
She You not air velocity transducer, the air velocity transducer and MCU electric connections；
The gyro module measurement unmanned plane current 3-axis acceleration and three axis angular rates, DMP is carried out by gyro module
Resolve and obtain the unmanned aerial vehicle body attitude angle relative to earth coordinates, and unmanned aerial vehicle body attitude angle information is passed to
MCU；
The air velocity transducer measures the relative velocity of wind direction and unmanned plane and air in real time, and wind direction and relative velocity are believed
Breath passes to MCU；
The MCU calculates according to unmanned aerial vehicle body attitude angle information and the relative velocity of wind direction and unmanned plane and air
Go out flight angle and the speed that unmanned plane need to adjust, and flight angle and velocity information that unmanned plane need to be adjusted pass to flight
Data message is converted into the output of electric signal controlled motor by attitude controller, Attitude Controller, so as to control unmanned plane
Flight attitude.
2. a kind of wind proof unmanned plane during flying system according to claim 1, it is characterised in that the unmanned plane is four rotations
Wing unmanned plane, air velocity transducer are installed between two adjacent rotors.
A kind of 3. wind proof unmanned plane during flying system according to claim 1, it is characterised in that the air velocity transducer peace
On the rotor of unmanned plane.
A kind of 4. wind proof unmanned plane during flying system according to claim 1, it is characterised in that the unmanned aerial vehicle body appearance
State angle includes roll angle φ ', pitching angle theta ' and yaw angle ψ '.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721223216.XU CN207148653U (en) | 2017-09-22 | 2017-09-22 | A kind of wind proof unmanned plane during flying system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721223216.XU CN207148653U (en) | 2017-09-22 | 2017-09-22 | A kind of wind proof unmanned plane during flying system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207148653U true CN207148653U (en) | 2018-03-27 |
Family
ID=61668561
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721223216.XU Expired - Fee Related CN207148653U (en) | 2017-09-22 | 2017-09-22 | A kind of wind proof unmanned plane during flying system |
Country Status (1)
| Country | Link |
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| CN (1) | CN207148653U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109949657A (en) * | 2019-04-19 | 2019-06-28 | 北方天途航空技术发展（北京）有限公司 | Unmanned plane on-line operation learning platform and learning method |
| CN110554703A (en) * | 2018-06-04 | 2019-12-10 | 百度在线网络技术（北京）有限公司 | Unmanned aerial vehicle flight attitude adjusting method and device and storage medium |
| CN111413997A (en) * | 2020-04-14 | 2020-07-14 | 中国人民解放军32180部队 | High-wind-resistance tilting rotor mooring unmanned aerial vehicle and flight control method thereof |
| CN111708373A (en) * | 2019-11-19 | 2020-09-25 | 南京海逸测控技术有限公司 | Automatic flight control system and method of atmosphere detection unmanned aerial vehicle |
-
2017
- 2017-09-22 CN CN201721223216.XU patent/CN207148653U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110554703A (en) * | 2018-06-04 | 2019-12-10 | 百度在线网络技术（北京）有限公司 | Unmanned aerial vehicle flight attitude adjusting method and device and storage medium |
| CN109949657A (en) * | 2019-04-19 | 2019-06-28 | 北方天途航空技术发展（北京）有限公司 | Unmanned plane on-line operation learning platform and learning method |
| CN111708373A (en) * | 2019-11-19 | 2020-09-25 | 南京海逸测控技术有限公司 | Automatic flight control system and method of atmosphere detection unmanned aerial vehicle |
| CN111413997A (en) * | 2020-04-14 | 2020-07-14 | 中国人民解放军32180部队 | High-wind-resistance tilting rotor mooring unmanned aerial vehicle and flight control method thereof |
| CN111413997B (en) * | 2020-04-14 | 2023-08-22 | 中国人民解放军32180部队 | High-wind-resistance tilting rotor wing mooring unmanned aerial vehicle and flight control method thereof |
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Legal Events
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180327 Termination date: 20180922 |