CN207311837U - A kind of long endurance solar energy unmanned plane - Google Patents
A kind of long endurance solar energy unmanned plane Download PDFInfo
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- CN207311837U CN207311837U CN201721275533.6U CN201721275533U CN207311837U CN 207311837 U CN207311837 U CN 207311837U CN 201721275533 U CN201721275533 U CN 201721275533U CN 207311837 U CN207311837 U CN 207311837U
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Abstract
It the utility model is related to a kind of long endurance solar energy unmanned plane, including fuselage, horizontal tail, vertical fin and wing, fuselage interior sets energy control system, energy-storage battery and power execution unit, solar panel is covered on the wing, the energy control system is by clock circuit, reset circuit, lighting detecting circuit, microcontroller and the ON-OFF control circuit composition for controlling solar panel to charge to energy-storage battery, the solar panel divides two-way to export, export all the way to power execution unit, another way is exported to energy-storage battery, energy-storage battery is powered to power execution unit.The utility model can be navigated by water for a long time using solar panel and energy-storage battery hybrid power supply at daytime, night；The method shunted using electric energy, is made unmanned function too strong or maintain stable operating voltage in the case that illumination is insufficient in illumination, makes unmanned plane stabilized flight；The housing construction that the utility model redesigns has the characteristics that light-weight, intensity is high, wing aspect ratio is big.
Description
Technical field
Unmanned air vehicle technique field is the utility model is related to, especially a kind of long endurance solar energy unmanned plane.
Background technology
Solar energy unmanned plane cruise time under illumination sufficiency is grown, and flying height is high, wide coverage, can perform more
Kind task, has the irreplaceable advantage of conventional airplane.Solar energy unmanned plane utilizes photovoltaic conversion side by energy control system
Solar radiant energy is converted into electric energy by formula, and long-term power is provided for unmanned plane.Due in flight course, the absorptivity of energy
Can be because of Various Seasonal, great changes have taken place for different time, when mission requirements low-latitude flying or runs into and has solar radiant energy rainy days
When insufficient, solar energy unmanned plane will be unable to realize the function of long endurance.In order to reduce solar energy unmanned plane hours underway by season,
The influence of weather, flying height, improves the hours underway of solar energy unmanned plane, need to design a kind of rational long endurance solar energy without
It is man-machine.
Up to the present, the Solong solar energy unmanned plane of U.S. AC companies exploitation is small in summer non-stop flight 48 in 2005
When, it is that the flight time was most long in the world at that time and solar energy unmanned plane that can uniquely fly round the clock.2007, defence company of Britain
Development solar power light aerocraft " west wind Zephyr " numbers, flown in once taking a flight test 54 it is small when, be unmanned machine
The world record of flight time.But these aircrafts are all the high-altitude flights at 20000 meters, illumination is sufficient, in complicated weather feelings
Condition is to will be unable to realize long endurance, and because flying height is high, can not complete low latitude task.
Utility model content
The purpose of this utility model is to provide one kind take into full account Changes in weather, intensity of illumination change, can low latitude fly
On the premise of row, the long endurance solar energy unmanned plane of solar energy unmanned plane navigation for a long time is realized.
To achieve the above object, the utility model employs following technical scheme：A kind of long endurance solar energy unmanned plane, bag
Fuselage, horizontal tail, vertical fin and wing are included, fuselage interior sets energy control system, energy-storage battery and power execution unit, the machine
Solar panel is covered on the wing, the energy control system is by clock circuit, reset circuit, lighting detecting circuit, microcontroller
With for controlling solar panel to be formed to the ON-OFF control circuit that energy-storage battery charges, the solar panel divides two-way
Output, exports to power execution unit all the way, and another way is exported to energy-storage battery, energy-storage battery and powered to power execution unit.
The output terminal of the clock circuit is connected with the first input end of microcontroller, the output terminal and list of the reset circuit
Second input terminal of piece machine is connected, and the output terminal of the lighting detecting circuit is connected with the 3rd input terminal of microcontroller, the list
The output terminal of piece machine is connected with the input terminal of ON-OFF control circuit, and the microcontroller uses AT89C51 microcontrollers.
The lighting detecting circuit includes silicon photocell BPW34, its cathode is defeated by resistance R4 and the positive of amplifier LM358
Enter end to be connected, its anode is connected by resistance R2 with the inverting input of amplifier LM358；A termination amplifier LM358 of resistance R3
Inverting input, the output terminal of another termination amplifier LM358, the output terminal of amplifier LM358 and 26 foot phases of A/D converter
Even, the A/D converter uses ADC0809 chips, 17,14,15,8,18,19,20, the 21 feet difference of the ADC0809 chips
It is connected with P0.0, P0.1, P0.2, P0.3, P0.4, P0.5, P0.6, P0.7 foot of the AT89C51 microcontrollers.
The ON-OFF control circuit includes driving chip U4A, it inputs the P2.0 feet for terminating the AT89C51 microcontrollers,
Its output terminal is connected by resistance R1 with 2 feet of optocoupler U5, and 4 feet of optocoupler U5 are connected with one end of resistance R5,1 foot of optocoupler U5
+ 5V direct currents are connect with 5 feet, and the base stage of the other end of resistance R5 respectively with resistance R6, triode Q1 is connected, and resistance R6's is another
End ground connection, the emitter ground connection of triode Q1, the collector of triode Q1 one end with the coil of relay K1, diode respectively
The anode of D1 is connected, and the other end of the coil of relay K1, the cathode of diode D1 connect+5V direct currents.
The model 7407 of the driving chip U4A, the model TIL 117 of the optocoupler U5, the relay K1's
Model G2R-14-DC5.
As shown from the above technical solution, the utility model has the advantage of：First, using solar panel and energy storage electricity
Pond hybrid power supply, can navigate by water for a long time at daytime, night；Second, the method shunted using electric energy, makes unmanned function in illumination
Stable operating voltage is maintained in the case of strong or illumination deficiency, makes unmanned plane stabilized flight；3rd, the utility model redesigns
Housing construction have the characteristics that light-weight, intensity is high, wing aspect ratio is big.
Brief description of the drawings
Fig. 1 is the circuit structure block diagram of the utility model；
Fig. 2 is the circuit diagram of lighting detecting circuit in Fig. 1；
Fig. 3 is the circuit diagram of AT89C51 microcontrollers in Fig. 1；
Fig. 4 is the circuit diagram of ON-OFF control circuit in Fig. 1；
Fig. 5 is the structure diagram of the utility model.
Embodiment
As shown in Figure 1,5, a kind of long endurance solar energy unmanned plane, including fuselage 1, horizontal tail 2, vertical fin 3 and wing 4, fuselage 1
Inside sets energy control system 5, energy-storage battery and power execution unit, and solar panel 6, institute are covered on the wing 4
Energy control system 5 is stated by clock circuit, reset circuit, lighting detecting circuit 7, microcontroller and for controlling solar panel
6 ON-OFF control circuits 9 to charge to energy-storage battery form, and the solar panel 6 divides two-way to export, and exports all the way to power
Execution unit, another way are exported to energy-storage battery, energy-storage battery and powered to power execution unit.
As shown in Figure 1,3, the output terminal of the clock circuit is connected with the first input end of microcontroller, the reset circuit
Output terminal be connected with the second input terminal of microcontroller, the 3rd input of the output terminal of the lighting detecting circuit 7 and microcontroller
End is connected, and the output terminal of the microcontroller is connected with the input terminal of ON-OFF control circuit 9, and the microcontroller is mono- using AT89C51
Piece machine 8.
As shown in Figure 2,3, the lighting detecting circuit 7 includes silicon photocell BPW34, its cathode passes through resistance R4 and amplifier
The normal phase input end of LM358 is connected, its anode is connected by resistance R2 with the inverting input of amplifier LM358；The one of resistance R3
The inverting input of amplifier LM358, the output terminal of another termination amplifier LM358 are terminated, output terminal and the A/D of amplifier LM358 turn
26 feet of parallel operation are connected, and the A/D converter uses ADC0809 chips, the ADC0809 chips 17,14,15,8,18,
19th, 20,21 feet P0.0, P0.1, P0.2, P0.3, P0.4, P0.5, P0.6, P0.7 foot with the AT89C51 microcontrollers 8 respectively
It is connected.Illuminance signal is converted into current signal using silicon photocell BPW34, silicon photocell BPW34 has the short circuit produced
The electric current characteristic directly proportional to illuminance.By the way that silicon photocell BPW34 is produced using amplifier LM358 as the amplifying circuit that core is formed
Raw short circuit current flow signal is converted to voltage signal and amplifies.AT89C51 microcontrollers 8 control ADC0809 chips collection amplification electricity
The voltage signal of road output simultaneously calculates actual illuminance value.
As shown in Figure 3,4, the ON-OFF control circuit 9 includes driving chip U4A, and it is mono- that it inputs the termination AT89C51
The P2.0 feet of piece machine 8, its output terminal are connected by resistance R1 with 2 feet of optocoupler U5,4 feet of optocoupler U5 and one end phase of resistance R5
Even, 1 foot and 5 feet of optocoupler U5 connect+5V direct currents, the other end of the resistance R5 base stage phase with resistance R6, triode Q1 respectively
Even, the other end of resistance R6 ground connection, the emitter ground connection of triode Q1, the collector of the triode Q1 line with relay K1 respectively
One end of circle, the anode of diode D1 are connected, and the other end of the coil of relay K1, the cathode of diode D1 connect+5V direct currents
Electricity.The model 7407 of the driving chip U4A, the model TIL 117 of the optocoupler U5, the model of the relay K1
G2R-14-DC5。
Optocoupler U5 plays Phototube Coupling, realizes and isolates AT89C51 microcontrollers 8 with ON-OFF control circuit 9, so as to reduce
Interference of the ON-OFF control circuit 9 to AT89C51 microcontrollers 8, improves the reliability of system, and the effect of wherein driving chip U4A is
Input current is provided for optocoupler U5.Relay K1 realizes directly switch control, and the effect of triode Q1 is carried for relay K1
For driving current, the effect of diode D1 is that the induced voltage for preventing relay K1 damages triode Q1.When AT89C51 microcontrollers
During 8 P2.1 pins output low level, optocoupler U5 produces photoelectric current, turns on triode Q1, so that the coil of relay K1 obtains
Electricity, relay K1 closures, on the contrary then relay K1 are disconnected.Relay K1 connection energy-storage batteries, if at a certain time interval
The illuminance detected twice is both less than the illuminance lower limit set and relay K1 states is open, then closes relay K1, this
When unmanned plane powered by energy-storage battery；If the illuminance detected twice at a certain time interval is both greater than the illuminance set
Upper limit value and relay K1 states are closing, then open relay K1, and unmanned plane is powered by solar panel at this time.
It is further described below in conjunction with Fig. 1 to 5 pairs of the utility model.
The power execution unit includes sequentially connected brushless electricity tune, brushless electric machine and propeller.The energy-storage battery
For lithium battery.The monolithic machine testing ambient light illumination, if the illuminance detected twice at a certain time interval is both less than
The illuminance lower limit and on off state set is then turned off the switch to open, this switch is relay K1；If in the regular hour
The illuminance detected twice in interval is both greater than the illuminance upper limit value set and on off state is closes, then opens switch, this is opened
It is relay K1 to close.
During solar energy unmanned plane flight on daytime, energy control system 5 obtains the output voltage of solar panel, and judges
Whether the voltage is higher than operating voltage needed for power execution unit；If so, electric energy is delivered directly to by electric energy by regulator circuit
Power execution unit；If it is not, energy control system 5 controls relay K1, solar panel is set to connect with energy-storage battery, jointly
Electric energy is provided to power execution unit.
For solar energy unmanned plane in night flying, energy control system 5 controls relay K1, energy-storage battery is held with power
Row unit connects, and makes unmanned plane normal flight.
In addition, the solar energy unmanned plane uses high aspect ratio wing, structure uses skeleton stressed-skin construction, and assistant reinforcement is adopted
With carbon fibre composite, structure surface density is small, and intensity is big.
Horizontal tail 2 and 4 keeping parallelism of wing, and it is fixed on 1 end of fuselage；Vertical fin 3 is mutually perpendicular to wing 4, and is fixed on
1 end of fuselage；Solar panel 6 is laid on 4 surface of wing.Further, power execution unit is fixed on 1 front end of fuselage, storage
Energy battery, energy control system are put at 1 equalization point of fuselage, unmanned plane is integrally reached balance, and reduce 4 load of wing, are protected
Demonstrate,proving unmanned plane can be with stabilized flight.
In conclusion the utility model can be grown using solar panel and energy-storage battery hybrid power supply at daytime, night
Time navigates by water；The method shunted using electric energy, makes unmanned function too strong or maintain work electricity in the case that illumination is insufficient in illumination
Pressure is stablized, and makes unmanned plane stabilized flight；The utility model redesign housing construction have it is light-weight, intensity is high, wing exhibition
String than it is big the characteristics of.
Claims (5)
- A kind of 1. long endurance solar energy unmanned plane, it is characterised in that：Including fuselage（1）, horizontal tail（2）, vertical fin（3）And wing（4）, Fuselage（1）Inside sets energy control system（5）, energy-storage battery and power execution unit, the wing（4）Upper covering solar energy Solar panel（6）, the energy control system（5）By clock circuit, reset circuit, lighting detecting circuit（7）, microcontroller and be used for Control solar panel（6）The ON-OFF control circuit to charge to energy-storage battery（9）Composition, the solar panel（6）Point Two-way exports, and exports all the way to power execution unit, and another way is exported to energy-storage battery, energy-storage battery and supplied to power execution unit Electricity.
- 2. long endurance solar energy unmanned plane according to claim 1, it is characterised in that：The output terminal of the clock circuit with The first input end of microcontroller is connected, and the output terminal of the reset circuit is connected with the second input terminal of microcontroller, the illumination Detection circuit（7）Output terminal be connected with the 3rd input terminal of microcontroller, the output terminal and ON-OFF control circuit of the microcontroller （9）Input terminal be connected, the microcontroller uses AT89C51 microcontrollers（8）.
- 3. long endurance solar energy unmanned plane according to claim 2, it is characterised in that：The lighting detecting circuit（7）Bag Silicon photocell BPW34 is included, its cathode is connected by resistance R4 with the normal phase input end of amplifier LM358, its anode passes through resistance R2 It is connected with the inverting input of amplifier LM358；The inverting input of a termination amplifier LM358 of resistance R3, another termination amplifier The output terminal of LM358, the output terminal of amplifier LM358 are connected with 26 feet of A/D converter, and the A/D converter uses ADC0809 Chip, 17,14,15,8,18,19,20,21 feet of the ADC0809 chips respectively with the AT89C51 microcontrollers（8）'s P0.0, P0.1, P0.2, P0.3, P0.4, P0.5, P0.6, P0.7 foot are connected.
- 4. long endurance solar energy unmanned plane according to claim 2, it is characterised in that：The ON-OFF control circuit（9）Bag Driving chip U4A is included, it, which is inputted, terminates the AT89C51 microcontrollers（8）P2.0 feet, its output terminal passes through resistance R1 and optocoupler 2 feet of U5 are connected, and 4 feet of optocoupler U5 are connected with one end of resistance R5, and 1 foot and 5 feet of optocoupler U5 connect+5V direct currents, resistance Base stage of the other end of R5 respectively with resistance R6, triode Q1 is connected, the other end ground connection of resistance R6, the emitter of triode Q1 Ground connection, one end with the coil of relay K1, the anode of diode D1 are connected the collector of triode Q1 respectively, relay K1's The other end of coil, the cathode of diode D1 connect+5V direct currents.
- 5. long endurance solar energy unmanned plane according to claim 4, it is characterised in that：The model of the driving chip U4A For 7407, the model TIL 117 of the optocoupler U5, the model G2R-14-DC5 of the relay K1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721275533.6U CN207311837U (en) | 2017-09-29 | 2017-09-29 | A kind of long endurance solar energy unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721275533.6U CN207311837U (en) | 2017-09-29 | 2017-09-29 | A kind of long endurance solar energy unmanned plane |
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| Publication Number | Publication Date |
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| CN207311837U true CN207311837U (en) | 2018-05-04 |
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ID=62428996
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721275533.6U Expired - Fee Related CN207311837U (en) | 2017-09-29 | 2017-09-29 | A kind of long endurance solar energy unmanned plane |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110481768A (en) * | 2019-09-01 | 2019-11-22 | 西安长峰机电研究所 | Four axis rotor tilting rotor solar energy unmanned planes |
| CN110858713A (en) * | 2018-08-24 | 2020-03-03 | 深圳光峰科技股份有限公司 | Electric shock prevention protection system, projection equipment and electric shock prevention protection method |
| CN113359867A (en) * | 2021-06-07 | 2021-09-07 | 合肥工业大学 | Unmanned aerial vehicle self-stabilizing cradle head and control method |
-
2017
- 2017-09-29 CN CN201721275533.6U patent/CN207311837U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110858713A (en) * | 2018-08-24 | 2020-03-03 | 深圳光峰科技股份有限公司 | Electric shock prevention protection system, projection equipment and electric shock prevention protection method |
| CN110481768A (en) * | 2019-09-01 | 2019-11-22 | 西安长峰机电研究所 | Four axis rotor tilting rotor solar energy unmanned planes |
| CN113359867A (en) * | 2021-06-07 | 2021-09-07 | 合肥工业大学 | Unmanned aerial vehicle self-stabilizing cradle head and control method |
| CN113359867B (en) * | 2021-06-07 | 2022-01-28 | 合肥工业大学 | Unmanned aerial vehicle self-stabilizing cradle head and control method |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180504 Termination date: 20210929 |
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| CF01 | Termination of patent right due to non-payment of annual fee |