CN102717893A - Automatic flight controller - Google Patents
Automatic flight controller Download PDFInfo
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- CN102717893A CN102717893A CN2011100795081A CN201110079508A CN102717893A CN 102717893 A CN102717893 A CN 102717893A CN 2011100795081 A CN2011100795081 A CN 2011100795081A CN 201110079508 A CN201110079508 A CN 201110079508A CN 102717893 A CN102717893 A CN 102717893A
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Abstract
The invention discloses an automatic flight controller comprising an PLC (Programmable Logic Controller) control center, an acceleration sensor, a rotation angle sensor, a magnetic field sensor, an atmospheric pressure sensor, a light intensity sensor, a temperature and humidity sensor, a video frequency camera sensor, a global positioning system receiver and a GSM (Global System of Mobile Communications) wireless network transceiver, wherein the acceleration sensor, the rotation angle sensor, the magnetic field sensor, the atmospheric pressure sensor, the light intensity sensor, the temperature and humidity sensor, the video frequency camera sensor, the global positioning system receiver and the GSM wireless network transceiver are respectively and electrically connected with the PLC control center and used for transmitting information to the PLC control center; and the PLC control center can be used for controlling the flight state of an aircraft in real time. The automatic flight controller not only is simple in structure and small in size, but also has more advanced functions.
Description
Technical field
The present invention relates to a kind of automatic flight controller.
Background technology
Unmanned vehicle (Unmanned Aerial Vehicle is called for short UAV) is meant the aircraft (aircraft) that does not have chaufeur and can fly for long-distance.This aircraft can be by predetermined route flight.They militarily with civilianly go up, prevent and reduce natural disasters like atmospheric surveillance, aquatic monitoring, fields such as law enforcement, fire-fighting, search and rescue, railway, pipeline/electric wireline monitoring, forestry, agricultural, mapping have the potentiality of widespread use.Concrete application examples as: detect weather such as temperature, humidity, wind direction; Monitor large-area environmental problem such as desertification, forest; Militarily, scout to dangerous enemy like anti-terrorism.
These aircraft can carry different instrument and equipments according to the needs of different task.For example the forest thermal monitoring just carries camera or infrared temperature imaging system.Because UAV can use militarily, and often be to be purpose with military affairs at the very start, all there is strict outlet restriction various countries to the UAV technology.In addition, generally all volume is bigger for present employed aircraft, and is very heavy.
Summary of the invention
In order to overcome above-mentioned defective, the invention provides a kind of automatic flight controller, this automatic flight controller is not only simple in structure, and volume is very little, and has more advanced functions.
The present invention for the technical scheme that solves its technical matters and adopt is: a kind of automatic flight controller; It comprises PLC control center, acceleration pick-up, rotation angle sensor, magnetic field sensor, atmospheric pressure sensor, light intensity sensor, temperature and humidity sensor, video camera sensor, GPS receiver and gsm wireless network transceivers; Said acceleration pick-up, rotation angle sensor, magnetic field sensor, atmospheric pressure sensor, light intensity sensor, temperature and humidity sensor, video camera sensor, GPS receiver and gsm wireless network transceivers are electrically connected and are messaging in said PLC control center with said PLC control center respectively, and said PLC control center can control the state of flight of said aircraft in real time.
As further improvement of the present invention, said acceleration pick-up is a three dimension acceleration sensor, and said acceleration pick-up is at least one.
As further improvement of the present invention, said magnetic field sensor is a three-D magnetic field sensor, and said magnetic field sensor is at least one.
As further improvement of the present invention, rotation angle sensor is the Three dimensional rotation angle transducer, and said rotation angle sensor is at least one.
As further improvement of the present invention, the image that said video camera sensor receives sends via said gsm wireless network transceivers.
As further improvement of the present invention, the altitude reading of the aircraft that the flying height of said automatic flight controller is received by said GPS receiver and the altitude reading of said BARO sensor obtain through weighted calculation.
As further improvement of the present invention; Also be provided with nine dimension K character filters in said PCL control center, said nine dimension K character filters receive the signal of said acceleration pick-up, rotation angle sensor and magnetic field sensor and confirm the state of flight of aircraft.
As further improvement of the present invention, also be provided with the driven by servomotor circuit in said PCL control center, this driven by servomotor circuit can be controlled the angle of the flank and the empennage of said flight controller.
The invention has the beneficial effects as follows: through integrated acceleration pick-up, rotation angle sensor, magnetic field sensor, atmospheric pressure sensor, light intensity sensor, temperature and humidity sensor, video camera sensor, GPS receiver and gsm wireless network transceivers at the center of flight controller; And they are messaging in PCL control center; So better controlling aircraft; Simultaneously; According to the true altitude that the signal of GPS receiver and atmospheric pressure sensor comes the weighted calculation aircraft, can greatly improve the accuracy of highly measuring, in addition; Integrated driven by servomotor circuit can be controlled the angle of flank and empennage in controller the Caspian Sea, thereby keeps aircraft smooth flight more.
Description of drawings
Fig. 1 is a principle of the invention scheme drawing.
In conjunction with accompanying drawing, explanation below doing:
1---PLC control center 2---acceleration pick-up
3---rotation angle sensor 4---magnetic field sensor
5---atmospheric pressure sensor 6---light intensity sensor
7---temperature and humidity sensor 8---video camera sensor
9---GPS receiver
10---the gsm wireless network transceivers
The specific embodiment
A kind of automatic flight controller; It comprises PLC control center 1, acceleration pick-up 2, rotation angle sensor 3, magnetic field sensor 4, atmospheric pressure sensor 5, light intensity sensor 6, temperature and humidity sensor 7, video camera sensor 8, GPS receiver 9 and gsm wireless network transceivers 10; Said acceleration pick-up 2, rotation angle sensor 3, magnetic field sensor 4, atmospheric pressure sensor 5, light intensity sensor 6, temperature and humidity sensor 7, video camera sensor 8, GPS receiver 9 and gsm wireless network transceivers 10 are electrically connected and are messaging in said PLC control center 1 with said PLC control center 1 respectively, and said PLC control center 1 can control the state of flight of said aircraft in real time.
Above-mentioned acceleration pick-up is a three dimension acceleration sensor, and said acceleration pick-up is at least one.
Above-mentioned magnetic field sensor is a three-D magnetic field sensor, and said magnetic field sensor is at least one.
Above-mentioned rotation angle sensor is the Three dimensional rotation angle transducer, and said rotation angle sensor is at least one.
The image that above-mentioned video camera sensor receives sends via said gsm wireless network transceivers.
The altitude reading of the aircraft that the flying height of above-mentioned automatic flight controller is received by said GPS receiver and the altitude reading of said BARO sensor obtain through weighted calculation.
Also be provided with nine dimension K character filters in above-mentioned PCL control center, said nine dimension K character filters receive the signal of said acceleration pick-up 2, rotation angle sensor 3 and magnetic field sensor 4 and confirm the state of flight of aircraft.
Also be provided with the driven by servomotor circuit in above-mentioned PCL control center, this driven by servomotor circuit can be controlled the angle of the flank and the empennage of said flight controller.
Claims (8)
1. automatic flight controller; It is characterized in that: it comprises PLC control center (1), acceleration pick-up (2), rotation angle sensor (3), magnetic field sensor (4), atmospheric pressure sensor (5), light intensity sensor (6), temperature and humidity sensor (7), video camera sensor (8), GPS receiver (9) and gsm wireless network transceivers (10); Said acceleration pick-up (2), rotation angle sensor (3), magnetic field sensor (4), atmospheric pressure sensor (5), light intensity sensor (6), temperature and humidity sensor (7), video camera sensor (8), GPS receiver (9) and gsm wireless network transceivers (10) are electrically connected and are messaging in said PLC control center (1) with said PLC control center (1) respectively, and said PLC control center (1) can control the state of flight of said aircraft in real time.
2. automatic flight controller according to claim 1 is characterized in that: said acceleration pick-up is a three dimension acceleration sensor, and said acceleration pick-up is at least one.
3. automatic flight controller according to claim 1 is characterized in that: said magnetic field sensor is a three-D magnetic field sensor, and said magnetic field sensor is at least one.
4. automatic flight controller according to claim 1 is characterized in that: rotation angle sensor is the Three dimensional rotation angle transducer, and said rotation angle sensor is at least one.
5. automatic flight controller according to claim 1 is characterized in that: the image that said video camera sensor receives sends via said gsm wireless network transceivers.
6. according to each described automatic flight controller in the claim 1 to 5, it is characterized in that: the altitude reading of the aircraft that the flying height of said automatic flight controller is received by said GPS receiver and the altitude reading of said BARO sensor obtain through weighted calculation.
7. automatic flight controller according to claim 6; It is characterized in that: also be provided with nine dimension K character filters in said PCL control center, said nine dimension K character filters receive the state of flight of signal and definite aircraft of said acceleration pick-up (2), rotation angle sensor (3) and magnetic field sensor (4).
8. automatic flight controller according to claim 6 is characterized in that: also be provided with the driven by servomotor circuit in said PCL control center, this driven by servomotor circuit can be controlled the angle of the flank and the empennage of said flight controller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100795081A CN102717893A (en) | 2011-03-31 | 2011-03-31 | Automatic flight controller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100795081A CN102717893A (en) | 2011-03-31 | 2011-03-31 | Automatic flight controller |
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| CN102717893A true CN102717893A (en) | 2012-10-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2011100795081A Pending CN102717893A (en) | 2011-03-31 | 2011-03-31 | Automatic flight controller |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103034229A (en) * | 2012-11-26 | 2013-04-10 | 中国商用飞机有限责任公司 | Integrated type testing device for flying control |
| CN103057712A (en) * | 2012-12-31 | 2013-04-24 | 北京航空航天大学 | Integration flight control system for miniature flying robot |
| CN104066250A (en) * | 2014-07-02 | 2014-09-24 | 西南科技大学 | Intelligent navigation light controller for aircraft, and control method |
| CN106054737A (en) * | 2016-07-19 | 2016-10-26 | 陈昊 | Photosensitive sensor-based unmanned aerial vehicle visual recognition device and using method thereof |
| CN106377903A (en) * | 2016-10-12 | 2017-02-08 | 徐付超 | Brain sensing unmanned aerial vehicle |
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2011
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| CN201429796Y (en) * | 2009-04-23 | 2010-03-24 | 深圳市大疆创新科技有限公司 | Unmanned helicopter automatic flight control system circuit |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103034229A (en) * | 2012-11-26 | 2013-04-10 | 中国商用飞机有限责任公司 | Integrated type testing device for flying control |
| CN103057712A (en) * | 2012-12-31 | 2013-04-24 | 北京航空航天大学 | Integration flight control system for miniature flying robot |
| CN103057712B (en) * | 2012-12-31 | 2015-06-17 | 北京航空航天大学 | Integration flight control system for miniature flying robot |
| CN104066250A (en) * | 2014-07-02 | 2014-09-24 | 西南科技大学 | Intelligent navigation light controller for aircraft, and control method |
| CN104066250B (en) * | 2014-07-02 | 2016-04-06 | 西南科技大学 | A kind of control method of aircraft intelligence boat lamp |
| CN106054737A (en) * | 2016-07-19 | 2016-10-26 | 陈昊 | Photosensitive sensor-based unmanned aerial vehicle visual recognition device and using method thereof |
| CN106377903A (en) * | 2016-10-12 | 2017-02-08 | 徐付超 | Brain sensing unmanned aerial vehicle |
| CN106377903B (en) * | 2016-10-12 | 2018-12-21 | 徐州惠博机电科技有限公司 | A kind of brain sensing unmanned aerial vehicle |
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Application publication date: 20121010 |