CN106483970A - A kind of protection device of unmanned plane inclination maximum and method - Google Patents
A kind of protection device of unmanned plane inclination maximum and method Download PDFInfo
- Publication number
- CN106483970A CN106483970A CN201611205968.3A CN201611205968A CN106483970A CN 106483970 A CN106483970 A CN 106483970A CN 201611205968 A CN201611205968 A CN 201611205968A CN 106483970 A CN106483970 A CN 106483970A
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- switch pipe
- mos switch
- protection device
- inclination maximum
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
Abstract
The invention discloses a kind of protection device of unmanned plane inclination maximum and method, this device includes supply unit and control device；Described supply unit includes three phase mains and power module；Described control device, including CPU control module, MOS switch pipe, motor and gyro sensor；Described motor, each rotor of unmanned plane is installed one, and each motor connects a MOS switch pipe；When this control method is that angle of inclination when gyroscope detects unmanned plane during flying is more than setting value m, the MOS switch pipe on rotor can disconnect, and servomotor shuts down, when the state of flight of unmanned plane returns to horizontality, MOS switch pipe closes, and servomotor operates, and unmanned plane continues flight.The present invention solves the problems, such as that unmanned plane upset in flight course, drifts off the course and crash out of control, and then reaches accurate flight.
Description
Technical field
The present invention relates to a kind of protection device of unmanned plane inclination maximum and method.
Background technology
With the rapid emergence of model plane industry, especially many rotor wing unmanned aerial vehicles etc. obtain increasingly wider application.Such as exist
The fields such as agricultural plant protection, city are taken photo by plane, meteorologic analysis, electric inspection process play an important role.Existing unmanned plane majority passes through
Remote control control, during unmanned plane during flying, often due to misoperation or physical features such as are unfamiliar with the reason, unmanned plane occurs
Situations such as upset or air crash, cause certain loss.
Content of the invention
The deficiency existing for above-mentioned technology, the invention provides a kind of protection device of unmanned plane inclination maximum and side
Method, solves unmanned plane awing retro-speed is excessive to lead to unmanned plane upset air crash or damage.
For achieving the above object, the technical solution used in the present invention is as follows：
A kind of protection device of unmanned plane inclination maximum is it is characterised in that include supply unit and control device.
Further, described unmanned plane is many rotor wing unmanned aerial vehicles.
Further, described supply unit includes three phase mains and power module.
Further, described control device includes CPU control module, MOS switch pipe, motor and gyro sensors
Device.
Further, described motor, each rotor of unmanned plane is installed one, and each motor connects
Connect a MOS switch pipe.
Further, described three phase mains connection power module and MOS switch pipe.
A kind of protection device of unmanned plane inclination maximum, or include battery；Three phase mains is connected with MOS switch pipe, battery
It is connected with power module.
A kind of guard method of unmanned plane inclination maximum：
Start unmanned plane, the gyro sensor of unmanned plane starts to detect the state of flight of unmanned plane, and by the result detecting
Send CPU control module to, when the inclination angle when unmanned plane during flying is more than setting value m, be inclined upwardly on the rotor at that end
MOS switch pipe can disconnect, and the servomotor being connected with MOS switch pipe is shut down, when the state of flight of many rotor wing unmanned aerial vehicles
When returning to horizontality, MOS switch pipe closes, servomotor energising operating, and many rotor wing unmanned aerial vehicles continue flight.
The invention has the beneficial effects as follows according to inclination angle during unmanned plane during flying, controlling opening and disconnected, change of MOS switch pipe
Heeling condition during unmanned plane during flying, solves unmanned plane and upset in flight course, drifts off the course and crash out of control
Problem, and then reach accurate flight.
Brief description
Fig. 1 is a kind of protection device operation principle Fig. 1 of unmanned plane inclination maximum.
Fig. 2 is a kind of protection device operation principle Fig. 2 of unmanned plane inclination maximum.
Specific embodiment
The present invention will be further described below in conjunction with the accompanying drawings.
As Fig. 1, a kind of protection device of unmanned plane inclination maximum is it is characterised in that include supply unit and control device.
Further, described unmanned plane is many rotor wing unmanned aerial vehicles.
Further, described supply unit includes three phase mains and power module.
Further, described control device includes CPU control module, MOS switch pipe, motor and gyro sensors
Device.
Further, described motor, each rotor of unmanned plane is installed one, and each motor connects
Connect a MOS switch pipe.
Further, described three phase mains connection power module and MOS switch pipe.
As Fig. 2, a kind of protection device of unmanned plane inclination maximum, or inclusion battery；Three phase mains and MOS switch Guan Lian
Connect, battery is connected with power module.
A kind of guard method of unmanned plane inclination maximum：
Start unmanned plane, the gyro sensor of unmanned plane starts to detect the state of flight of unmanned plane, and by the result detecting
Send CPU control module to, when the inclination angle when unmanned plane during flying is more than setting value m, be inclined upwardly on the rotor at that end
MOS switch pipe can disconnect, and the servomotor being connected with MOS switch pipe is shut down, when the state of flight of many rotor wing unmanned aerial vehicles
When returning to horizontality, MOS switch pipe closes, servomotor energising operating, and many rotor wing unmanned aerial vehicles continue flight.
Claims (8)
1. a kind of protection device of unmanned plane inclination maximum is it is characterised in that include supply unit and control device.
2. a kind of protection device of unmanned plane inclination maximum according to claim 1 is it is characterised in that described unmanned plane is
Many rotor wing unmanned aerial vehicles.
3. a kind of protection device of unmanned plane inclination maximum according to claim 1 is it is characterised in that described supply unit
Including three phase mains and power module.
4. a kind of protection device of unmanned plane inclination maximum according to claim 1 is it is characterised in that described control device
Including CPU control module, MOS switch pipe, motor and gyro sensor.
5. a kind of protection device of unmanned plane inclination maximum according to claim 4 is it is characterised in that described driving is electric
Machine, each rotor of unmanned plane is installed one, and each motor connects a MOS switch pipe.
6. a kind of unmanned plane inclination maximum according to claim 3 and claim 4 protection device it is characterised in that
Described three phase mains connection power module and MOS switch pipe.
7. a kind of protection device of unmanned plane inclination maximum is it is characterised in that or include battery；Three phase mains and MOS switch pipe
Connect, battery is connected with power module.
8. a kind of guard method of unmanned plane inclination maximum is it is characterised in that start unmanned plane, the gyro sensor of unmanned plane
Start to detect the state of flight of unmanned plane, and the result detecting is sent to CPU control module, inclining when unmanned plane during flying
When oblique angle is more than setting value m, the MOS switch pipe being inclined upwardly on the rotor at that end can disconnect, with watching that MOS switch pipe is connected
Take motor to shut down, when the state of flight of many rotor wing unmanned aerial vehicles returns to horizontality, MOS switch pipe closes, servo electricity
Machine energising operating, many rotor wing unmanned aerial vehicles continue flight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611205968.3A CN106483970A (en) | 2016-12-23 | 2016-12-23 | A kind of protection device of unmanned plane inclination maximum and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611205968.3A CN106483970A (en) | 2016-12-23 | 2016-12-23 | A kind of protection device of unmanned plane inclination maximum and method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106483970A true CN106483970A (en) | 2017-03-08 |
Family
ID=58285132
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611205968.3A Pending CN106483970A (en) | 2016-12-23 | 2016-12-23 | A kind of protection device of unmanned plane inclination maximum and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106483970A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107450581A (en) * | 2017-08-18 | 2017-12-08 | 上海顺砾智能科技有限公司 | Wind resistance power applied to unmanned plane reminds forced landing method |
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| CN104118564A (en) * | 2014-07-21 | 2014-10-29 | 张行晔 | Safety protection system of aircraft with multiple rotor wings |
| WO2015143684A1 (en) * | 2014-03-27 | 2015-10-01 | SZ DJI Technology Co., Ltd. | Assisted takeoff |
| CN205139711U (en) * | 2015-11-05 | 2016-04-06 | 北京精航科技有限公司 | Unmanned aerial vehicle safety guarantee equipment and have its unmanned aerial vehicle |
| CN105573333A (en) * | 2016-01-22 | 2016-05-11 | 青岛大学 | Modular control method for four-rotor aircraft |
| CN105836140A (en) * | 2016-06-08 | 2016-08-10 | 深圳市翼行者科技开发有限公司 | Slow landing protecting device and unmanned aerial vehicle |
| CN105843241A (en) * | 2016-04-11 | 2016-08-10 | 零度智控（北京）智能科技有限公司 | Unmanned aerial vehicle, unmanned aerial vehicle takeoff control method and apparatus |
| CN105912010A (en) * | 2016-06-24 | 2016-08-31 | 苏州工业职业技术学院 | STM32-based micro four-rotor aircraft and control system thereof |
-
2016
- 2016-12-23 CN CN201611205968.3A patent/CN106483970A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015143684A1 (en) * | 2014-03-27 | 2015-10-01 | SZ DJI Technology Co., Ltd. | Assisted takeoff |
| CN104118564A (en) * | 2014-07-21 | 2014-10-29 | 张行晔 | Safety protection system of aircraft with multiple rotor wings |
| CN205139711U (en) * | 2015-11-05 | 2016-04-06 | 北京精航科技有限公司 | Unmanned aerial vehicle safety guarantee equipment and have its unmanned aerial vehicle |
| CN105573333A (en) * | 2016-01-22 | 2016-05-11 | 青岛大学 | Modular control method for four-rotor aircraft |
| CN105843241A (en) * | 2016-04-11 | 2016-08-10 | 零度智控（北京）智能科技有限公司 | Unmanned aerial vehicle, unmanned aerial vehicle takeoff control method and apparatus |
| CN105836140A (en) * | 2016-06-08 | 2016-08-10 | 深圳市翼行者科技开发有限公司 | Slow landing protecting device and unmanned aerial vehicle |
| CN105912010A (en) * | 2016-06-24 | 2016-08-31 | 苏州工业职业技术学院 | STM32-based micro four-rotor aircraft and control system thereof |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107450581A (en) * | 2017-08-18 | 2017-12-08 | 上海顺砾智能科技有限公司 | Wind resistance power applied to unmanned plane reminds forced landing method |
| CN107450581B (en) * | 2017-08-18 | 2021-03-05 | 上海顺砾智能科技有限公司 | Wind force resistant forced landing reminding method applied to unmanned aerial vehicle |
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| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170308 |
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| WD01 | Invention patent application deemed withdrawn after publication |