CN206476101U - A kind of six rotor flight devices - Google Patents
A kind of six rotor flight devices Download PDFInfo
- Publication number
- CN206476101U CN206476101U CN201621430637.5U CN201621430637U CN206476101U CN 206476101 U CN206476101 U CN 206476101U CN 201621430637 U CN201621430637 U CN 201621430637U CN 206476101 U CN206476101 U CN 206476101U
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- circuit
- power supply
- voltage
- stabilized power
- generator
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Abstract
A kind of six rotor flight devices, are fixed with petrol engine and generator, the rotating shaft of the petrol engine and the rotating shaft of generator are connected by bearing, and Switching Power Supply is fixed with fuselage, and the output end of the generator is connected with Switching Power Supply on undercarriage；Control circuit unit includes governor circuit, charging circuit, the first voltage-stabilized power supply circuit and the second voltage-stabilized power supply circuit, hollow-cup motor drive circuit, more than one sensor module interface circuit.The device reduces the interference of control circuit itself, strengthens the stationarity of six axle aircraft flights, and with longer cruising time, can complete more aerial missions.
Description
Technical field
The utility model is related to a kind of six rotor flight device.
Background technology
Six rotor flight devices are one kind of unmanned plane, are to utilize radio robot and the presetting apparatus provided for oneself
The not manned aircraft manipulated.Unmanned plane press application field, can be divided into it is military with it is civilian.Military aspect, unmanned plane is divided into reconnaissance plane
And target drone.Civilian aspect, unmanned plane adds sector application, is that unmanned plane has really just been needed；At present taking photo by plane, agricultural, plant protection, oneself
Bat, express transportation, disaster relief, observation wild animal, monitoring infectious disease, mapping, news report, electric inspection process, the disaster relief, video display
The application in romance etc. field is shot, manufactured, the purposes of unmanned plane in itself has greatly been expanded.Existing unmanned air vehicle technique development
Rapidly, still there are sufficiently development and room for improvement in terms of hardware and control circuit, especially in continuation of the journey, most of six revolve at present
Wing flight instruments is worked using battery power supply mode, is typically controlled after boat ability at 20 minutes or so, and easily by itself
The interference of component, influences the stability of flight.
The content of the invention
The utility model patent provides a kind of six rotor flight device, can reduce the interference of control circuit itself, enhancing
The stationarity of six axle aircraft flights, and with longer cruising time, more aerial missions can be completed.
Solve above-mentioned technical problem, a kind of six rotor flight device of the present utility model, including battery, control circuit group
Part, 6 groups of oar components, fuselages, undercarriage is had in fuselage, and oar component includes paddle arm, blade and is electrically connected with control circuit unit
The blade motor connect, the control circuit unit is connected with battery, and petrol engine and generating are fixed with the undercarriage
Machine, the rotating shaft of the petrol engine and the rotating shaft of generator are connected by bearing, and Switching Power Supply is fixed with fuselage, described
The output end of generator is connected with Switching Power Supply；Control circuit unit includes governor circuit, charging circuit, the first voltage-stabilized power supply
Circuit and the second voltage-stabilized power supply circuit, hollow-cup motor drive circuit, more than one sensor module interface circuit, the master
Control circuit respectively with the first voltage-stabilized power supply circuit, hollow-cup motor drive circuit, the connection of sensor module interface circuit, described the
Two voltage-stabilized power supply circuits are connected with sensor module interface circuit, and the battery of the charging circuit and six rotor flight devices connects
Connect；The governor circuit is STM32F103T8U6 single-chip microcomputers, 2 and 3 pin single-chip microcomputers of the STM32F103T8U65 single-chip microcomputers
8M crystal oscillator chip X1 are connected with, crystal oscillator chip X1 is connected with 2 22PF ceramic disc capacitor C1, C2 and 10K resistance R5；It is described
STM32F103T8U65 single-chip microcomputers 1,6,19 and 27 pins are also connected with four electric capacity C5, C6, C7, C8 in parallel；The charging electricity
Road includes TP4056 master chips and indicator lamp D1 and D2；First voltage-stabilized power supply circuit include the first ME620233 master chips,
104 ceramic disc capacitor C14 and 100UF electrochemical capacitor C12, the second voltage-stabilized power supply circuit include the 2nd main cores of ME620233
The electrochemical capacitor C9 of piece, 104 ceramic disc capacitor C11 and 100UF；Hollow-cup motor drive circuit is by six SI2302 chipsets
Into the grid of six SI2302 chips concatenates 1K resistance R10, R11, R12, R16, R17, a R18 respectively；Sensor die
Block interface circuit include nRF24L01 wireless modules interface, MPU6050 3-axis accelerations and three-axis gyroscope sensor interface,
ADX345 slant angle sensors module interface, HMC5883 electronic compass sensors interface, GPS geo-location system module interface,
SW download program interfaces；Switching Power Supply connection charging circuit and blade motor, the Switching Power Supply and blade motor it
Between be connected with electric tune.
Further, the petrol engine is two-cycle gasoline engine.
Further, the generator is the generator that 220V is exported.
The beneficial effect of above-mentioned six rotor flight device is, due to the use of single voltage-stabilized power supply circuit being respectively master control electricity
Road and sensor module interface circuit are powered, and the clutter of power-supply system is filtered by filter circuit, it is ensured that monolithic
Machine stable operation, and then the interference of control circuit itself can be reduced, strengthen the stationarity of six axle aircraft flights；And due to
Install petrol engine and generator on six rotor flight devices additional, driven by engine electrical power generators supply electric energy and flown
Device is used, and increase aircraft can complete more aerial missions after ETS estimated time of sailing.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model.
Fig. 2 is system construction drawing of the present utility model.
Fig. 3 is the circuit structure diagram of main control module and charging circuit.
Fig. 4 is the circuit structure of the first voltage-stabilized power supply circuit, the second voltage-stabilized power supply circuit and sensor module interface circuit
Figure.
Fig. 5 is the circuit structure diagram of hollow-cup motor drive circuit.
Embodiment
Come that the utility model is described in more detail with reference to the accompanying drawings and detailed description.
As illustrated in fig. 1 and 2, the present embodiment is a kind of six rotor flight device, including battery 5, control circuit unit, 6 groups
Oar component, fuselage 6, undercarriage 7 is had in fuselage 6, and oar component includes paddle arm 81, blade 82 and is electrically connected with control circuit unit
The blade motor 83 connect, the charging circuit 2 of the control circuit unit is connected with battery 5, and vapour is fixed with the undercarriage 7
Oil turbine 9 and generator 10, the rotating shaft of the petrol engine 9 are connected with the rotating shaft of generator 10 by bearing 11, in machine
Switching Power Supply 12 is fixed with body 6, the output end of the generator 10 is connected with Switching Power Supply 12, and the Switching Power Supply 12 is connected
Control circuit unit.The control circuit unit includes governor circuit 1, charging circuit 2, the first voltage-stabilized power supply circuit 31 and the
Two voltage-stabilized power supply circuits 32, hollow-cup motor drive circuit 4, more than one sensor module interface circuit 5, the master control electricity
Road 1 is connected with the first voltage-stabilized power supply circuit 31, hollow-cup motor drive circuit 4, sensor module interface circuit 5 respectively, described
Second voltage-stabilized power supply circuit 32 is connected with sensor module interface circuit 5, the battery 5 of the axle aircraft of charging circuit 2 and six
Connection, the first voltage-stabilized power supply circuit 31 and the second voltage-stabilized power supply circuit 32 are connected with the battery 5 of six axle aircraft.
During work, shown in Fig. 3 to 4, the governor circuit 1 is STM32F103T8U6 single-chip microcomputers, described
2 and 3 pin single-chip microcomputers of STM32F103T8U65 single-chip microcomputers are connected with 8M crystal oscillator chip X1, and crystal oscillator chip X1 is connected with 2
22PF ceramic disc capacitor C1, C2 and 10K resistance R5；The STM32F103T8U65 single-chip microcomputers 1,6,19 and 27 pins also connect
Four electric capacity C5, C6, C7, C8 in parallel are met, electric capacity C5, C6, C7, C8 are filtered to the clutter of power-supply system in circuit,
Ensure single-chip microcomputer stable operation.The charging circuit 2 includes TP4056 master chips and indicator lamp D1 and D2, indicator lamp D1 chargings
Represent fully charged with indicator lamp D2.First voltage-stabilized power supply circuit 31 includes the first ME620233 master chips, 104 ceramic disc capacitor
C14 and 100UF electrochemical capacitor C12, produces 3.3V voltages, is individually for STM32F103T8U6 single-chip microcomputers and powers.Second voltage stabilizing electricity
Source circuit 32 includes the 2nd ME620233 master chips, 104 ceramic disc capacitor C11 and 100UF electrochemical capacitor C9, C11 and C9
For filtering power supply clutter, the second voltage-stabilized power supply circuit 32 produces 3.3V voltages, is that each road sensor assembly is used.Drag cup electricity
Drive circuit 4 is made up of six SI2302 chips, and six hollow-cup motors, the grid of six SI2302 chips are driven altogether
1K resistance R10, R11, R12, R16, R17, a R18 are concatenated respectively, and STM32F103T8U6 single-chip microcomputers are by PWM ripples to motor
Driving chip output current is controlled, and 6 road pwm control signals is exported altogether 6 motor drive ics are controlled.Sensor
Module interface circuit 5 connects including nRF24L01 wireless modules interface 51, MPU6050 3-axis accelerations and three-axis gyroscope sensor
Mouth 52, ADX345 slant angle sensors module interface 53, HMC5883 electronic compass sensors interface 54, GPS geo-location system
Module interface 55, SW download programs interface 56, for connecting wireless module, gyro sensor, slant angle sensor module, electronics
Compass detector, GPS module and download.The connection charging circuit 2 of Switching Power Supply 12 and blade motor 83, it is described to open
Electricity is connected between powered-down source 12 and blade motor 83 and adjusts 13, both can be battery charging, and can also directly be blade motor 83
Power supply lifting cruising time.
Claims (3)
1. a kind of six rotor flight device, including battery, control circuit unit, 6 groups of oar components, fuselages, have had in fuselage
Fall frame, oar component includes paddle arm, blade and the blade motor electrically connected with control circuit unit, the control circuit unit and electricity
Pond is connected, it is characterised in that：Petrol engine and generator, the rotating shaft of the petrol engine are fixed with the undercarriage
It is connected with the rotating shaft of generator by bearing, Switching Power Supply, output end and the switch electricity of the generator is fixed with fuselage
Source is connected；
Control circuit unit includes governor circuit, charging circuit, the first voltage-stabilized power supply circuit and the second voltage-stabilized power supply circuit, sky
The heart cup motor-drive circuit, more than one sensor module interface circuit, the governor circuit respectively with the first voltage-stabilized power supply
Circuit, hollow-cup motor drive circuit, the connection of sensor module interface circuit, second voltage-stabilized power supply circuit and sensor die
Block interface circuit is connected, and the charging circuit is connected with the battery of six rotor flight devices；
The governor circuit is STM32F103T8U6 single-chip microcomputers, 2 and 3 pin monolithics of the STM32F103T8U65 single-chip microcomputers
Machine is connected with 8M crystal oscillator chip X1, and crystal oscillator chip X1 is connected with 2 22PF ceramic disc capacitor C1, C2 and 10K resistance R5；Institute
State STM32F103T8U65 single-chip microcomputers 1,6,19 and 27 pins are also connected with four electric capacity C5, C6, C7, C8 in parallel；
The charging circuit includes TP4056 master chips and indicator lamp D1 and D2；
First voltage-stabilized power supply circuit includes the first ME620233 master chips, 104 ceramic disc capacitor C14 and 100UF electrolysis electricity
Hold C12, the second voltage-stabilized power supply circuit includes the 2nd ME620233 master chips, 104 ceramic disc capacitor C11 and 100UF electrolysis
Electric capacity C9；
Hollow-cup motor drive circuit is made up of six SI2302 chips, and the grid of six SI2302 chips concatenates one respectively
Individual 1K resistance R10, R11, R12, R16, R17, R18；
Sensor module interface circuit includes nRF24L01 wireless modules interface, MPU6050 3-axis accelerations and three-axis gyroscope
Sensor interface, ADX345 slant angle sensors module interface, HMC5883 electronic compass sensors interface, GPS global positioning systems
System module interface, SW download program interfaces；
The Switching Power Supply connection charging circuit and blade motor, electricity is connected between the Switching Power Supply and blade motor
Adjust.
2. six rotor flight device according to claim 1, it is characterised in that：The petrol engine is two-cycle gasoline
Engine.
3. six rotor flight device according to claim 2, it is characterised in that：The generator is the generating that 220V is exported
Machine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621430637.5U CN206476101U (en) | 2016-12-25 | 2016-12-25 | A kind of six rotor flight devices |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621430637.5U CN206476101U (en) | 2016-12-25 | 2016-12-25 | A kind of six rotor flight devices |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206476101U true CN206476101U (en) | 2017-09-08 |
Family
ID=59749936
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621430637.5U Expired - Fee Related CN206476101U (en) | 2016-12-25 | 2016-12-25 | A kind of six rotor flight devices |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206476101U (en) |
-
2016
- 2016-12-25 CN CN201621430637.5U patent/CN206476101U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170908 Termination date: 20171225 |