CN202115701U - Automatic flight controller - Google Patents
Automatic flight controller Download PDFInfo
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- CN202115701U CN202115701U CN2011200905848U CN201120090584U CN202115701U CN 202115701 U CN202115701 U CN 202115701U CN 2011200905848 U CN2011200905848 U CN 2011200905848U CN 201120090584 U CN201120090584 U CN 201120090584U CN 202115701 U CN202115701 U CN 202115701U
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- control center
- flight controller
- magnetic field
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Abstract
The utility model discloses an automatic flight controller, which comprises a programmable logical controller (PLC) control center, an acceleration transducer, a rotation angle transducer, a magnetic field transducer, an atmosphere pressure transducer, a light intensity transducer, a temperature and humidity transducer, a video camera transducer, a global positioning system receiver and a global system for mobile communication (GSM) wireless network transceiver. The acceleration transducer, the rotation angle transducer, the magnetic field transducer, the atmosphere pressure transducer, the light intensity transducer, the temperature and humidity transducer, the video camera transducer, the global positioning system receiver and the GSM wireless network transceiver are respectively in electric connection with the PLC control center and send information to the PLC control center. The PLC control center (1) can perform real-time control on flight states of aircrafts. The flight controller not only is simple in structure and small in volume, but also has more advanced functions.
Description
Technical field
The utility model 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 utility model provides a kind of automatic flight controller, and this automatic flight controller is not only simple in structure, and volume is very little, and has more advanced functions.
The utility model 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 the further improvement of the utility model, said acceleration pick-up is a three dimension acceleration sensor, and said acceleration pick-up is at least one.
As the further improvement of the utility model, said magnetic field sensor is a three-D magnetic field sensor, and said magnetic field sensor is at least one.
As the further improvement of the utility model, rotation angle sensor is the Three dimensional rotation angle transducer, and said rotation angle sensor is at least one.
As the further improvement of the utility model, the image that said video camera sensor receives sends via said gsm wireless network transceivers.
As the further improvement of the utility model, 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.
Further improvement as the utility model; 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 the further improvement of the utility model, 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 beneficial effect of the utility model is: 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 the utility model principle schematic.
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 (7)
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: 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).
7. according to each described automatic flight controller in the claim 1 to 5, it 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 |
|---|---|---|---|
| CN2011200905848U CN202115701U (en) | 2011-03-31 | 2011-03-31 | Automatic flight controller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200905848U CN202115701U (en) | 2011-03-31 | 2011-03-31 | Automatic flight controller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202115701U true CN202115701U (en) | 2012-01-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011200905848U Expired - Fee Related CN202115701U (en) | 2011-03-31 | 2011-03-31 | Automatic flight controller |
Country Status (1)
| Country | Link |
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| CN (1) | CN202115701U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102717893A (en) * | 2011-03-31 | 2012-10-10 | 昆山弧光信息科技有限公司 | Automatic flight controller |
| CN110893907A (en) * | 2018-09-12 | 2020-03-20 | 台山市金桥铝型材厂有限公司 | Unmanned aerial vehicle air bag and aluminium system unmanned aerial vehicle undercarriage |
-
2011
- 2011-03-31 CN CN2011200905848U patent/CN202115701U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102717893A (en) * | 2011-03-31 | 2012-10-10 | 昆山弧光信息科技有限公司 | Automatic flight controller |
| CN110893907A (en) * | 2018-09-12 | 2020-03-20 | 台山市金桥铝型材厂有限公司 | Unmanned aerial vehicle air bag and aluminium system unmanned aerial vehicle undercarriage |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120118 Termination date: 20140331 |