CN204302722U - A kind of telechiric device of four-axle aircraft - Google Patents
A kind of telechiric device of four-axle aircraft Download PDFInfo
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- CN204302722U CN204302722U CN201420790469.5U CN201420790469U CN204302722U CN 204302722 U CN204302722 U CN 204302722U CN 201420790469 U CN201420790469 U CN 201420790469U CN 204302722 U CN204302722 U CN 204302722U
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Abstract
The utility model discloses a kind of telechiric device of four-axle aircraft, mainly comprise: actuation means and flight instruments, described actuation means mainly comprises MCU micro-control unit and the 2nd RF group module, wireless transmitter module, remote control module, image module, hummer, LED, flight instruments mainly comprises gyro module and taking module, one RF group module, control processor, driver module, GPS module, wireless receiving module, altitude location module, when four-axle aircraft loses remote control signal, can by can be accurately homeward by GPS device, be applied to low latitude to take photo by plane, aerial mission activity under the MODEL OVER COMPLEX TOPOGRAPHY such as disaster area exploration.
Description
Technical field
The utility model relates to a kind of four-axle aircraft field, particularly relates to a kind of telechiric device of four-axle aircraft.
Background technology
Now along with the fast development of science and technology, people are increasingly deep for the research of aircraft, and all kinds of aircraft is applied in increasing occasion.Four rotor unmanned aircrafts are compared with other aircraft, and its physical construction is simply compact, and take action more flexible, landing environmental requirement is lower, has good operating performance, can realize among a small circle taking off, hover, landing.Due to these features, quadrotor has been widely used in taking photo by plane, monitor, investigate, search and rescue, control of agricultural pest etc.
Numerous areas.
Four-axle aircraft is a kind of common pattern of Multi-axis aircraft in small aircraft, because of the feature that it is dexterous, motor-driven, is widely used in low latitude and takes photo by plane, the aerial mission activity under the MODEL OVER COMPLEX TOPOGRAPHY such as disaster area exploration.And four-axle aircraft performs the ability of aerial mission under MODEL OVER COMPLEX TOPOGRAPHY, demarcated by flare maneuver executable in its flight course, the airflight attitude of conventional four-axle aircraft needs to keep fuselage overall close to level mostly, and degree of freedom is low, and operability is little.
Summary of the invention
The purpose of this utility model is the telechiric device providing a kind of four-axle aircraft.
For achieving the above object, the utility model adopts following technical scheme: a kind of telechiric device of four-axle aircraft, mainly comprise: actuation means and flight instruments, described actuation means mainly comprises MCU micro-control unit and the 2nd RF group module, wireless transmitter module, remote control module, image module, hummer, LED; Flight instruments mainly comprises gyro module and taking module, a RF group module, control processor, driver module, GPS module, wireless receiving module, altitude location module;
Described remote control module is connected to MCU micro-control unit, and MCU micro-control unit determines the data of each passage by detecting remote control module; Described MCU micro-control unit is connected to the 2nd RF group module, and the mode that MCU micro-control unit communicates with SPI the transmitter register of data write the 2nd RF group module, and writes transmission instruction to the 2nd RF group module; MCU micro-control unit is connected to image module, hummer and LED, MCU micro-control unit transmission instruction and controls image module, hummer and LED work; The 2nd described RF group model calling is in scrambler, and the 2nd RF group module receives the transmission instruction of MCU micro-control unit, and it is radiofrequency signal that transmission instruction sends instruction transformation by scrambler handle; Described scrambler is connected to wireless transmitter module, communication signal is transmitted into the wireless receiving module of flight instruments;
The wireless receiving module of described flight instruments is connected with demoder, and the radiofrequency signal that actuation means sends is sent to demoder by wireless receiving module; Described demoder is connected with a RF group module, and radiofrequency signal is converted to steering order by demoder, and steering order is sent to the receiving register in a RF group module; A described RF group module is connected with control processor, and control processor is read by the corresponding receiving register of reading the one RF group module the signal received; Described control processor is connected to driver module and photographing module, GPS module, altitude location module, gyro module, wireless receiving module, control processor from register read corresponding signal, and exports corresponding control signal to driver module and photographing module, GPS module, altitude location module.
Described driver module is primarily of electric mode transfer block and brushless electric machine two parts composition, and electric mode transfer block is connected between brushless electric machine and control processor, and barometric information is sent to control processor by baroceptor by described altitude location module.
Described gyro module mainly comprises three-axis gyroscope and 3-axis acceleration, and data are sent to control processor by gyro module, and control processor transfers data to electric mode transfer block, is controlled the brushless electric machine of driver module by electric mode transfer block.
Described GPS module is made up of two parts GPS locating device and GPS warning light, GPS locating device and GPS warning light are connected to control processor, locating information is sent to control processor by GPS locating device, and the instruction that several GPS warning lights are sent by reception control processor runs.
Described wireless receiving module is made up of the first wave filter, low noise amplifier and receiving antenna, the radiofrequency signal that the wireless transmitter module of actuation means is launched, first through receiving antenna match circuit, to be amplified by low noise amplifier and the first filter filtering obtains radiofrequency signal accurately.
The wireless transmitter module of described actuation means is provided with carrier module, the second wave filter and emitting antenna, by carrier module the Frequency point of rf-signal modulation in setting, obtained the radiofrequency signal needed by the second filter filtering be connected between carrier module and emitting antenna.
As the further preferred version of the utility model, it is characterized in that:
1, four-axle aircraft installs GPS module, can to aircraft precise positioning and navigation, its GPS module passes through the cooperating of GPS locating device and GPS warning light, the longitude and latitude of user position is carried out record, be convenient to manipulation and the shooting of user, use common remote controlled model airplane not possess navigation feature compared to traditional unmanned aerial photography;
2, four-axle aircraft installs gyro module, gyro module is put by three-axis gyroscope and 3-axis acceleration, meet the operation requirements of user, can allow the flight of aircraft held stationary, compare and conventional aircraft, not only simply easy to operate, be applicable to various age level, and shooting effect is strengthened very well, barometric information is sent to control processor by baroceptor by altitude location module, realizes the function of location, high-altitude.
accompanying drawing illustrates:
Accompanying drawing 1 is flight instruments schematic diagram of the present utility model;
Accompanying drawing 2 is actuation means schematic diagram of the present utility model;
Accompanying drawing 3 is control processor circuit diagram of the present utility model;
Accompanying drawing 4 is flight instruments way circuit figure of the present utility model.
embodiment:
Below in conjunction with accompanying drawing 1-4, the utility model is further illustrated.
A kind of telechiric device of four-axle aircraft, mainly comprise: actuation means 1 and flight instruments 2, described actuation means 1 mainly comprises MCU micro-control unit 11 and the 2nd RF group module 12, wireless transmitter module 13, remote control module 14, image module 15, hummer 3, LED 4; Flight instruments 2 mainly comprises gyro module 23 and taking module 25, a RF group module 22, control processor 21, driver module 24, GPS module 5, wireless receiving module 26, altitude location module 6; Remote control module 14 is connected to MCU micro-control unit 11, MCU micro-control unit 11 determines each passage data by detecting remote control module 14; Described MCU micro-control unit 11 is connected to mode that the 2nd RF group module 12, MCU micro-control unit 11 communicates with SPI the transmitter register 121 of data write the 2nd RF group module 12, and writes transmission instruction to the 2nd RF group module 12; MCU micro-control unit 11 is connected to image module 15, hummer 3 and LED 4, MCU micro-control unit 11 and sends instruction and work to control image module 15, hummer 3 and LED 4; The 2nd described RF group module 12 is connected to scrambler 7, and the 2nd RF group module 12 receives the transmission instruction of MCU micro-control unit 11, and it is radiofrequency signal that transmission instruction sends instruction transformation by scrambler 7 handle; Described scrambler 7 is connected to wireless transmitter module 13, communication signal is transmitted into the wireless receiving module 26 of flight instruments 2; The wireless receiving module 26 of flight instruments 2 is connected with demoder 8, and the radiofrequency signal that actuation means 1 sends is sent to demoder 8 by wireless receiving module 26; Described demoder 8 is connected with a RF group module 22, and radiofrequency signal is converted to steering order by demoder 8, and steering order is sent to the receiving register 221 in a RF group module 22; A described RF group module 22 is connected with control processor 21, and control processor 21 is read by the corresponding receiving register 221 of reading the one RF group module 22 signal received; Described control processor 21 is connected to driver module 24 and taking module 25, GPS module 5, altitude location module 6, gyro module 23, wireless receiving module 26, control processor 21 reads corresponding signal from receiving register 221, and exports corresponding control signal to driver module 24 and taking module 25, GPS module 5, altitude location module 6.
Described driver module 24 is primarily of electric mode transfer block 241 and brushless electric machine 242 two parts composition, electricity mode transfer block 241 is connected between brushless electric machine 242 and control processor 21, control processor 21 passes through mode transfer block 241 sending controling instruction to brushless electric machine 242, thus control the track of flight instruments 2 flight, barometric information is sent to control processor 21 by baroceptor by described altitude location module 6, control the height that flight instruments 2 flies, certain altitude flight can be remained on; Gyro module 23 mainly comprises three-axis gyroscope 231 and 3-axis acceleration 232, data are sent to control processor 21 by gyro module 23, control processor 21 transfers data to electric mode transfer block 241, the brushless electric machine 242 of driver module 24 is controlled by electric mode transfer block 241, engagement height locating module 6, can fix a point in high-altitude floating; GPS module 5 is made up of two parts GPS locating device 51 and GPS warning light 52, GPS locating device 51 and GPS warning light 52 are connected to control processor 21, locating information is sent to control processor 21 by GPS locating device 51, the instruction that several GPS warning lights 52 are sent by reception control processor 21 runs, the position of GPS locating device 51 actuation means 1 positions, be recorded in control processor 21 li, coordinate driver module 24 to complete a key and return function.
Described wireless receiving module 26 is made up of the first wave filter 261, low noise amplifier 262 and receiving antenna 263, the radiofrequency signal that the wireless transmitter module 13 of actuation means 1 is launched, first through receiving antenna 263 match circuit, to be amplified by low noise amplifier 262 and the first wave filter 261 filtering obtains radiofrequency signal accurately; The wireless transmitter module 13 of actuation means 1 is provided with carrier module 131, second wave filter 132 and emitting antenna 133, by carrier module 131 the Frequency point of rf-signal modulation in setting, obtained the radiofrequency signal needed by the second wave filter 132 filtering be connected between carrier module 131 and emitting antenna 133, its radiofrequency signal avoids the interference of unnecessary radiofrequency signal by the first wave filter 261 and the second wave filter 132.
During use, operator by actuation means 1 by sending signal empty flight instruments 2, the MCU micro-control unit 11 of actuation means 1 determines the data of each passage by detecting remote control module 14, instruction is sent to control flight instruments 2 by MCU micro-control unit 11, its instruction writes the transmitter register 121 of the 2nd RF group module 12 in the mode that SPI communicates, the instruction of the 2nd RF group module 12 is converted to radiofrequency signal by scrambler 7, the Frequency point that its radiofrequency signal is being set rf-signal modulation by carrier module 131, the radiofrequency signal needed is obtained by the second wave filter 132, finally by emitting antenna 133, radiofrequency signal is sent to flight instruments 2, its radiofrequency signal is first through receiving antenna 263 match circuit, radiofrequency signal is accurately obtained by low noise amplifier 262 amplification and the first wave filter 261 filtering, radiofrequency signal is converted to steering order by demoder 8, and the receiving register 221 steering order is sent in a RF group module 22, by a RF group module 22, steering order is sent to the control processor 21 of flight instruments 2 again, finally control by control processor 21 flight that driver module 24 completes aircraft, GPS module 5 completes GPS location and a key returns function, altitude location module 6 completes flies on the height of setting, the picture of shooting is sent to the image module 15 of actuation means 1 by the taking module 25 of flight instruments 2 by wireless telecommunications, user can see the picture of shooting by image module 1.
Certainly, above diagram is only the utility model better embodiment, not limits usable range of the present utility model with this, therefore, every make in the utility model principle equivalence change all should be included in protection domain of the present utility model.
Claims (6)
1. the telechiric device of a four-axle aircraft, mainly comprise: actuation means and flight instruments, is characterized in that: described actuation means mainly comprises MCU micro-control unit and the 2nd RF group module, wireless transmitter module, remote control module, image module, hummer, LED; Flight instruments mainly comprises gyro module and taking module, a RF group module, control processor, driver module, GPS module, wireless receiving module, altitude location module;
Described remote control module is connected to MCU micro-control unit, and MCU micro-control unit determines the data of each passage by detecting remote control module;
Described MCU micro-control unit is connected to the 2nd RF group module, and the mode that MCU micro-control unit communicates with SPI the transmitter register of data write the 2nd RF group module, and writes transmission instruction to the 2nd RF group module; MCU micro-control unit is connected to image module, hummer and LED, MCU micro-control unit transmission instruction and controls image module, hummer and LED work;
The 2nd described RF group model calling is in scrambler, and the 2nd RF group module receives the transmission instruction of MCU micro-control unit, and it is radiofrequency signal that transmission instruction sends instruction transformation by scrambler handle;
Described scrambler is connected to wireless transmitter module, communication signal is transmitted into the wireless receiving module of flight instruments;
The wireless receiving module of described flight instruments is connected with demoder, and the radiofrequency signal that actuation means sends is sent to demoder by wireless receiving module;
Described demoder is connected with a RF group module, and radiofrequency signal is converted to steering order by demoder, and steering order is sent to the receiving register in a RF group module;
A described RF group module is connected with control processor, and control processor is read by the corresponding receiving register of reading the one RF group module the signal received;
Described control processor is connected to driver module and photographing module, GPS module, altitude location module, gyro module, wireless receiving module, control processor reads corresponding signal from receiving register, and exports corresponding control signal to driver module and photographing module, GPS module, altitude location module.
2. the telechiric device of a kind of four-axle aircraft according to claim 1, it is characterized in that: described driver module is primarily of electric mode transfer block and brushless electric machine two parts composition, electricity mode transfer block is connected between brushless electric machine and control processor, and barometric information is sent to control processor by baroceptor by described altitude location module.
3. the telechiric device of a kind of four-axle aircraft according to claim 2, it is characterized in that: described gyro module mainly comprises three-axis gyroscope and 3-axis acceleration, data are sent to control processor by gyro module, control processor transfers data to electric mode transfer block, is controlled the brushless electric machine of driver module by electric mode transfer block.
4. the telechiric device of a kind of four-axle aircraft according to claim 1, it is characterized in that: described GPS module is made up of two parts GPS locating device and GPS warning light, GPS locating device and GPS warning light are connected to control processor, locating information is sent to control processor by GPS locating device, and the instruction that several GPS warning lights are sent by reception control processor runs.
5. the telechiric device of a kind of four-axle aircraft according to claim 2,3 or 4, it is characterized in that: described wireless receiving module is made up of the first wave filter, low noise amplifier and receiving antenna, the radiofrequency signal that the wireless transmitter module of actuation means is launched, first through receiving antenna match circuit, to be amplified by low noise amplifier and the first filter filtering obtains radiofrequency signal accurately.
6. the telechiric device of a kind of four-axle aircraft according to claim 5, it is characterized in that: the wireless transmitter module of described actuation means is provided with carrier module, the second wave filter and emitting antenna, by carrier module the Frequency point of rf-signal modulation in setting, obtained the radiofrequency signal needed by the second filter filtering be connected between carrier module and emitting antenna.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420790469.5U CN204302722U (en) | 2014-12-15 | 2014-12-15 | A kind of telechiric device of four-axle aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420790469.5U CN204302722U (en) | 2014-12-15 | 2014-12-15 | A kind of telechiric device of four-axle aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204302722U true CN204302722U (en) | 2015-04-29 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420790469.5U Expired - Fee Related CN204302722U (en) | 2014-12-15 | 2014-12-15 | A kind of telechiric device of four-axle aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204302722U (en) |
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2014
- 2014-12-15 CN CN201420790469.5U patent/CN204302722U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 515000 Shantou new industrial zone, Chenghai, Guangdong Patentee after: GUANGDONG CHENGXING UNMANNED AERIAL VEHICLE COMPANY LIMITED Address before: 515000 Shantou new industrial zone, Chenghai, Guangdong Patentee before: Guangdong Chengxing Modelairplane Science Company Limted |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150429 Termination date: 20181215 |
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| CF01 | Termination of patent right due to non-payment of annual fee |