CN106647789A - UAV maximum inclination control method - Google Patents
UAV maximum inclination control method Download PDFInfo
- Publication number
- CN106647789A CN106647789A CN201611207289.XA CN201611207289A CN106647789A CN 106647789 A CN106647789 A CN 106647789A CN 201611207289 A CN201611207289 A CN 201611207289A CN 106647789 A CN106647789 A CN 106647789A
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- servomotor
- control
- flight
- speed regulator
- 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.)
- Withdrawn
Links
- 238000000034 method Methods 0.000 title claims abstract description 15
- 238000001514 detection method Methods 0.000 claims description 6
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- 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, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Toys (AREA)
Abstract
The invention discloses a UAV maximum inclination control method The method includes that when the UAV flight inclination angle is greater than the set value m, the control signal is transmitted to an electronic governor through a receiver, the electronic governor controls a servomotor, and the operating speed of the servomotor is reduced, and when the flight state of the UVA recovers to the horizontal state, the electronic governor control the servomotor to accelerate the operation, and the UAV continues to fly. According to the method, the problems of overturn, course deviation, and out-of-control crash of the UVA in the flight process are solved, and accurate flight can be achieved.
Description
Technical field
The present invention relates to a kind of control method of unmanned plane inclination maximum.
Background technology
As the rapid emergence of model plane industry, especially multi-rotor unmanned aerial vehicle 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.
The content of the invention
For the deficiency that above-mentioned technology is present, the invention provides a kind of control method of unmanned plane inclination maximum, solves
Awing retro-speed is excessive causes unmanned plane upset air crash or damage for unmanned plane.
A kind of control method of unmanned plane inclination maximum, starts unmanned plane, and nothing is worked as in the attitude detection module work of unmanned plane
When inclination angle during man-machine flight is more than setting value m, ground controller sends control signals to receiver, and receiver receives control
After signal, and transmit a signal to produce the electron speed regulator on the larger rotor of moment of torsion, electron speed regulator controls servomotor,
The running speed of servomotor is reduced, when the state of flight of unmanned plane returns to horizontality, electron speed regulator control servo
Motor accelerated service, unmanned plane continues to fly.
A kind of control method of unmanned plane inclination maximum, starts unmanned plane, and nothing is worked as in the attitude detection module work of unmanned plane
When inclination angle during man-machine flight is more than setting value m, the winged control module of autopilot sends instruction, produces on the larger rotor of moment of torsion
Electron speed regulator works, and the running speed of servomotor is reduced, when the state of flight of unmanned plane returns to horizontality, electronics
Governor control servomotor accelerated service, unmanned plane continues to fly.
The invention has the beneficial effects as follows controlling the speed of servomotor operating by electron speed regulator, change unmanned plane during flying
When heeling condition, solve the problems, such as that unmanned plane occurs overturning in flight course, drifts off the course and crash out of control, and then
Reach accurate flight.
Description of the drawings
Fig. 1 is a kind of operation principle Fig. 1 of the protection device of unmanned plane inclination maximum.
Fig. 2 is a kind of operation principle Fig. 2 of the protection device of unmanned plane inclination maximum.
Fig. 3 is the schematic diagram of four rotor wing unmanned aerial vehicles.
Specific embodiment
Below in conjunction with the accompanying drawings the present invention will be further described.
Such as Fig. 3, by taking four rotor wing unmanned aerial vehicles as an example, the invention will be further described.
A kind of protection device of unmanned plane inclination maximum, it is characterised in that including supply unit and control device.
Further, the unmanned plane is multi-rotor unmanned aerial vehicle.
Further, it is battery to state supply unit.
Further, the control device includes electron speed regulator, receiver and motor.
Further, the electron speed regulator is brushless electronic speed regulator.
Further, the electron speed regulator and motor, install one on each rotor of unmanned plane, electronics is adjusted
Fast device is arranged on below motor.
The control device includes electron speed regulator, autopilot and motor.
Such as Fig. 1, a kind of guard method of unmanned plane inclination maximum, start unmanned plane, the attitude detection module work of unmanned plane
Make, when the inclination angle when unmanned plane during flying is more than setting value m, ground controller sends control signals to receiver, receiver
After receiving control signal, and transmit a signal to produce the electron speed regulator on the larger rotor of moment of torsion, electron speed regulator control
Servomotor, the running speed of servomotor is reduced, when the state of flight of unmanned plane returns to horizontality, electron speed regulator
Control servomotor accelerated service, unmanned plane continues to fly.
Such as Fig. 2, a kind of guard method of unmanned plane inclination maximum, start unmanned plane, the attitude detection module work of unmanned plane
Make, when the inclination angle when unmanned plane during flying is more than setting value m, the winged control module of autopilot sends instruction, produces moment of torsion larger
Electron speed regulator work on rotor, the running speed of servomotor is reduced, when the state of flight of unmanned plane return to it is horizontal
During state, electron speed regulator control servomotor accelerated service, unmanned plane continues to fly.
Claims (2)
1. a kind of control method of unmanned plane inclination maximum, it is characterised in that start unmanned plane, the attitude detection module of unmanned plane
Work, when the inclination angle when unmanned plane during flying is more than setting value m, ground controller sends control signals to receiver, receives
Machine is received after control signal, and transmits a signal to produce the electron speed regulator on the larger rotor of moment of torsion, electron speed regulator control
Servomotor processed, the running speed of servomotor is reduced, when the state of flight of unmanned plane returns to horizontality, electronic speed regulation
Device controls servomotor accelerated service, and unmanned plane continues to fly.
2. a kind of control method of unmanned plane inclination maximum, it is characterised in that start unmanned plane, the attitude detection module of unmanned plane
Work, when the inclination angle when unmanned plane during flying is more than setting value m, the winged control module of autopilot sends instruction, produces moment of torsion larger
Rotor on electron speed regulator work, the running speed of servomotor is reduced, when the state of flight of unmanned plane returns to level
During state, electron speed regulator control servomotor accelerated service, unmanned plane continues to fly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611207289.XA CN106647789A (en) | 2016-12-23 | 2016-12-23 | UAV maximum inclination control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611207289.XA CN106647789A (en) | 2016-12-23 | 2016-12-23 | UAV maximum inclination control method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106647789A true CN106647789A (en) | 2017-05-10 |
Family
ID=58828323
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611207289.XA Withdrawn CN106647789A (en) | 2016-12-23 | 2016-12-23 | UAV maximum inclination control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106647789A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203038112U (en) * | 2012-09-19 | 2013-07-03 | 苏州工业园区职业技术学院 | Unmanned aerial vehicle (UAV) automatic control system |
| CN203780797U (en) * | 2014-03-24 | 2014-08-20 | 田屋科技有限公司 | Double-motor variable-pitch multi-rotor aircraft |
| CN104407586A (en) * | 2014-11-14 | 2015-03-11 | 山东农业大学 | Drive decoupled plant protection unmanned aerial vehicle control system and control method |
| CN105151290A (en) * | 2015-10-22 | 2015-12-16 | 朱丽芬 | High-altitude posture stable quadrotor unmanned plane |
| US9412278B1 (en) * | 2015-03-31 | 2016-08-09 | SZ DJI Technology Co., Ltd | Authentication systems and methods for generating flight regulations |
-
2016
- 2016-12-23 CN CN201611207289.XA patent/CN106647789A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203038112U (en) * | 2012-09-19 | 2013-07-03 | 苏州工业园区职业技术学院 | Unmanned aerial vehicle (UAV) automatic control system |
| CN203780797U (en) * | 2014-03-24 | 2014-08-20 | 田屋科技有限公司 | Double-motor variable-pitch multi-rotor aircraft |
| CN104407586A (en) * | 2014-11-14 | 2015-03-11 | 山东农业大学 | Drive decoupled plant protection unmanned aerial vehicle control system and control method |
| US9412278B1 (en) * | 2015-03-31 | 2016-08-09 | SZ DJI Technology Co., Ltd | Authentication systems and methods for generating flight regulations |
| CN105151290A (en) * | 2015-10-22 | 2015-12-16 | 朱丽芬 | High-altitude posture stable quadrotor unmanned plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20170510 |