CN105083563A - Double-battery-powered aircraft and power supply control method thereof - Google Patents
Double-battery-powered aircraft and power supply control method thereof Download PDFInfo
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- CN105083563A CN105083563A CN201510462443.7A CN201510462443A CN105083563A CN 105083563 A CN105083563 A CN 105083563A CN 201510462443 A CN201510462443 A CN 201510462443A CN 105083563 A CN105083563 A CN 105083563A
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- aircraft
- electric energy
- control chip
- drive motor
- rom drive
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
A double-battery-powered aircraft comprises a frame, four rotor wings, a lithium battery, a control chip and four driving motors, wherein the rotor wings, the lithium battery and the control chip are all installed on the frame. The aircraft further comprises a solar battery arranged on the surface of the frame, wherein the solar battery is used for absorbing sunlight, converting the absorbed sunlight into electric energy, and then outputting the electric energy to the driving motors and the lithium battery. The invention further provides a power supply control method of the aircraft.
Description
Technical field
The present invention relates to aircraft, particularly relate to a kind of aircraft of Double-battery powered and the method for controlling power supply of this aircraft.
Background technology
At present, the small aircraft on market has a lot.Quadrotor as wherein a kind of important aircraft because the preceence of its controller performance is subject to widespread use.Quadrotor is also referred to as four-rotor helicopter, quadrotor adopts four rotors as the direct driving force source of flight, four rotors are symmetrically distributed in all around four direction of frame, one group of rotor rotates clockwise, another group rotor rotates counterclockwise, thus makes quadrotor can realize the actions such as hovering, acceleration, upset.
Such quadrotor generally only adopts high-capacity lithium battery (capacity of cell is at more than 2000mA) to carry out energy supply, can make this quadrotor can long-distance flight.But the safety of high-capacity lithium battery is usually poor, the flying distance of quadrotor and flight safety cannot be taken into account.
Summary of the invention
In view of this, be necessary to provide a kind of endurance strong and can the aircraft of safe flight, can overcome the above problems.
In addition, there is a need to the method for controlling power supply that this aircraft a kind of is provided.
The invention provides a kind of aircraft of Double-battery powered, it comprises a frame, multiple rotor, one lithium cell, one control chip and multiple CD-ROM drive motor, described rotor, lithium cell and control chip are all installed on this frame, described aircraft also comprises the solar cell that is arranged at this frame top, this solar cell is for absorbing sunshine and absorbed sunshine being converted to electric energy, then the Part I electric energy in described electric energy and Part II electric energy is exported to described CD-ROM drive motor and lithium cell respectively, described CD-ROM drive motor after reception Part I electric energy for driving described rotor rotational, described lithium cell after reception Part II electric energy for powering to control chip, make described control chip control this aircraft and perform corresponding action.
Preferably, the proportion that described Part I electric energy accounts for described electric energy is greater than 90%, and the proportion that described Part II electric energy accounts for described electric energy is less than 10%.
Preferably, described solar cell is a thin-film solar cell panel being covered in this frame top, and it has flexibility, flexible.
Preferably, this solar cell is electrically connected through a buck circuit and described CD-ROM drive motor and lithium cell, and this buck circuit is used for the rated voltage loss in voltage that this solar cell exports being low to moderate described CD-ROM drive motor and lithium cell.
Preferably, this control chip is provided with an opto-electronic pickup, described opto-electronic pickup is used for the Illumination intensity of this aircraft surrounding environment of detecting real-time, described control chip is used for the Illumination intensity that detected by described opto-electronic pickup and a predetermined strength compares, and reduced the rotating speed of described rotor by described CD-ROM drive motor when described Illumination intensity is less than this predetermined strength, this aircraft security is landed.
Preferably, described control chip also for when described Illumination intensity is greater than this predetermined strength, regulates the maximum speed of described rotor according to described Illumination intensity, thus regulates the maximum flying speed of described aircraft.
Preferably, described solar cell also connects a detecting voltage unit, for the output voltage of this solar cell of detecting real-time, described control chip is used for the output voltage that detected by described detecting voltage unit and a predetermined voltage compares, and reduced the rotating speed of described rotor by described CD-ROM drive motor when described output voltage is less than this predetermined voltage, this aircraft security is landed.
Preferably, described control chip also for when described output voltage is greater than this predetermined voltage, according to described go out the maximum speed of rotor described in voltage-regulation, thus regulate the maximum flying speed of described aircraft.
Preferably, this frame comprises one for the central machine box of accommodating described control chip and multiple support being fixed on described central machine box, this central machine box comprises a shell, and the sidewall of this shell offers the through hole of the corresponding described support of multiple difference, one end of each support to be inserted in corresponding through hole and is fixed on this central machine box, each support is also fixed with a motor mount away from the other end of described central machine box, for an accommodating wherein CD-ROM drive motor, each motor mount offers the through hole of a corresponding described support, each support to insert in described through hole and is fixed on this motor mount.
The present invention also provides a kind of method for controlling power supply of aircraft, described aircraft comprises a frame, multiple rotor, one lithium cell, one control chip and multiple CD-ROM drive motor, described rotor, lithium cell and control chip are all installed on this frame, described aircraft also comprises the solar cell that is covered in this frame top, described method for controlling power supply comprises: under described aircraft is positioned over sunshine, described solar cell is absorbed solar energy, absorbed sunshine is converted to electric energy, then described electric energy is exported to described lithium cell with to described lithium cell charging, make described lithium cell can be control chip to power, described solar cell constant absorption solar energy is to produce electric energy, it exports the Part I electric energy in described electric energy and Part II electric energy to described CD-ROM drive motor and described lithium cell respectively when described control chip starts, enable described CD-ROM drive motor drive described rotor rotational to make this aircraft start to fly and to perform corresponding action, and make described lithium cell continue to power to control chip, and described solar cell constant absorption solar energy in the flight course of described aircraft, to produce electric energy, thus constantly gives described CD-ROM drive motor and described lithium battery power supply.
Aircraft of the present invention comprises solar cell and lithium cell simultaneously, by solar cell for absorbing sunshine and absorbed sunshine being converted to electric energy, thus constantly can charge to lithium cell to CD-ROM drive motor energy supply in flight course, thus extend the flight time of this aircraft and be conducive to improving the safety performance of lithium cell.
Accompanying drawing explanation
Fig. 1 is the schematic top plan view of the aircraft in the present invention one better embodiment.
Fig. 2 is the partial exploded view of the aircraft shown in Fig. 1.
The principle of work schematic diagram that Fig. 3 is the aircraft shown in Fig. 1.
Fig. 4 is the method for controlling power supply of the aircraft in the present invention one better embodiment.
Main element nomenclature
| Aircraft | 1 |
| Frame | 10 |
| Central machine box | 11 |
| Support | 12 |
| Rotor | 20 |
| Storage battery | 30 |
| Control chip | 40 |
| CD-ROM drive motor | 50 |
| Solar cell | 60 |
| Shell | 110 |
| Through hole | 111，121 |
| Motor mount | 120 |
| Step | S41；S42；S43 |
Following detailed description of the invention will further illustrate the present invention in conjunction with above-mentioned accompanying drawing.
Detailed description of the invention
Fig. 1 and Fig. 2 illustrates the aircraft 1 of the Double-battery powered in the present invention one better embodiment, and it comprises a frame 10, storage battery 30(is shown in Figure 2 for multiple rotor 20), a control chip 40 and multiple CD-ROM drive motor 50.Described rotor 20, storage battery 30 and control chip 40 are all installed in this frame 10.
Described aircraft 1 also comprises the solar cell 60 that is arranged at this frame 10 top.Please with reference to Fig. 3, this solar cell 60, for absorbing sunshine and absorbed sunshine being converted to electric energy, then exports described electric energy to described CD-ROM drive motor 50 and storage battery 30 respectively.Described CD-ROM drive motor 50 comprises the axle drive shaft (not shown) be connected with rotor 20.Described CD-ROM drive motor 50 reception electric energy after for being rotated by rotor 20 described in described drive shaft.Described storage battery 30 for powering to control chip 40, being made described control chip 40 control this aircraft 1 and starts to fly and perform corresponding action, such as, being regulated the rotating speed of rotor 20 by described CD-ROM drive motor 50 after reception electric energy.In the present embodiment, described solar cell 60 exports the Part I electric energy E1 in described electric energy to described CD-ROM drive motor 50, export remaining Part II electric energy E2 to described storage battery 30, because described CD-ROM drive motor 50 energy consumption is comparatively large, control chip 40 energy consumption is less, and Part I electric energy E1 is greater than Part II electric energy E2.More specifically, the proportion that described Part I electric energy E1 accounts for described electric energy is greater than 90%, states the proportion that Part II electric energy E2 accounts for described electric energy and is less than 10%.
In the present embodiment, described solar cell 60 is a thin-film solar cell panel being covered in this frame 10 top, and it is roughly equilateral polygon (as square), has flexibility, flexible.This solar cell 60 is electrically connected through a buck circuit and described CD-ROM drive motor 50 and storage battery 30.This buck circuit is used for the rated voltage loss in voltage that this solar cell 60 exports being low to moderate described CD-ROM drive motor 50 and storage battery 30, thus the voltage avoiding solar cell 60 to export is excessive and burn out described CD-ROM drive motor 50 and storage battery 30.
Described control chip 40, when receiving the control command that a remote controller (not shown) sends, controls this aircraft 1 according to this control command and performs corresponding action.Wherein, described remote controller can be a model plane 6 passage remote controller or a model plane 9 passage remote controller, and its remote control distance is greater than 100 meters.This control chip 40 is provided with an opto-electronic pickup (not shown).Described opto-electronic pickup is used for the Illumination intensity (being generally the Illumination intensity of sunshine) of this aircraft 1 surrounding environment of detecting real-time.The Illumination intensity that described opto-electronic pickup detects by described control chip 40 and a predetermined strength compare, and reduced the rotating speed of described rotor 20 by described CD-ROM drive motor 50 when described Illumination intensity is less than this predetermined strength, make this aircraft 1 safe falling.Wherein, described predetermined strength can be arranged as required, and it is make this aircraft 1 can the minimum Illumination intensity of low-speed operations safely.Described control chip 40 also for when described Illumination intensity is greater than this predetermined strength, regulates the maximum speed of described rotor 20 according to described Illumination intensity, thus regulates the maximum flying speed of described aircraft 1.Certainly, in other embodiments, described opto-electronic pickup can omit, and described control chip 40 regulates the rotating speed of described rotor 20 according to the output voltage of this solar cell 60.Now, described solar cell 60 also connects a detecting voltage unit (figure does not show, as volt meter), for the output voltage of this solar cell 60 of detecting real-time.Understandable, the output voltage of this solar cell 60 is directly proportional to the Illumination intensity of this aircraft 1 surrounding environment.The output voltage that described detecting voltage unit detects by described control chip 40 and a predetermined voltage compare, and reduce the rotating speed of described rotor 20 according to comparative result or regulate the maximum speed of described rotor 20.
In the present embodiment, described storage battery 30 is less than the lithium cell of 10g for quality, and its capacity of cell is greater than 200mAh.Concrete, described storage battery 30 is low capacity poly-lithium battery.Described storage battery 30 also can connect one and overcharge/over-discharge protection circuit (not shown); it for automatically disconnecting charge circuit when described storage battery 30 charging reaches maximum voltage and automatically disconnecting discharge circuit when electric discharge reaches minimum voltage, thus plays a protective role to described storage battery 30.Describedly to overcharge/over-discharge protection circuit also can be provided with an indicator lamp (as LED light), light, thus the current storage battery of reminding user 30 charge complete after charging at described storage battery 30.
In the present embodiment, described CD-ROM drive motor 50 is hollow cup DC motor, and it has higher rotating speed, and quality is less, thus is conducive to the total mass alleviating described aircraft 1.
In the present embodiment, this frame 10 comprises one for the central machine box 11 of accommodating described control chip 40 and multiple support 12 being fixed on described central machine box 11.This central machine box 11 comprises the shell 110 that an employing rigid plastic is made, and the sidewall of this shell 110 offers the through hole 111 of the corresponding described support 12 of multiple difference.Be appreciated that the quantity of described through hole 111 is identical with the quantity of rotor 20 and support 12.One end of each support 12 is inserted in corresponding through hole 111 and is also fixed on this central machine box 11 by fastener (as screw).This solar cell 60 is fixed on described central machine box 11 and support 12 by the mode of pasting.Described storage battery 30 is fixed on the surface of central machine box 11 away from solar cell 60 by the mode of pasting.
Each support 12 is also fixed with a motor mount 120 away from the other end of described central machine box 11, for an accommodating wherein CD-ROM drive motor 50.Concrete, each motor mount 120 offers the through hole 121 of a corresponding described support 12, and each support 12 to insert in described through hole 121 and is fixed on this motor mount 120 by fastener.In the present embodiment, each support 12 all adopts aluminum alloy to make, and is hollow structure, and its wall thickness is roughly 0.2mm, thus is conducive to the total mass alleviating this aircraft 1.The wire (not shown) connecting described solar cell 60 and each CD-ROM drive motor 50 can be passed through this support 12 inside and be connected to described CD-ROM drive motor 50.
In the present embodiment, described aircraft 1 is quadrotor, namely comprises the CD-ROM drive motor 50 that four rotors 20 and four are respectively used to drive described rotor 20 to rotate.Described rotor 20 is symmetrically distributed in all around four direction of frame 10, and one group of rotor 20 rotates clockwise, and another group rotor 20 rotates counterclockwise, thus makes described quadrotor can realize the actions such as hovering, acceleration, upset.
During use, under described aircraft 1 is positioned over sunshine, the electric energy that conversion sunshine obtains is exported to described storage battery 30 after described solar cell 60 is fully absorbed solar energy, until described indicator lamp lights (showing that current described storage battery 30 charges complete), make described storage battery 30 can be control chip 40 and power.Then, described solar cell 60 constant absorption solar energy is to produce electric energy, it is when described control chip 40 starts and carries out channel adaptation with remote controller and connect, export the Part I electric energy E1 in described electric energy and Part II electric energy E2 to described CD-ROM drive motor 50 and described storage battery 30 respectively, thus make described CD-ROM drive motor 50 that described rotor 20 can be driven to rotate to make this aircraft 1 start to fly and perform corresponding action, and described storage battery 30 is made to continue to power to control chip 40.In addition, described solar cell 60 constant absorption solar energy in the flight course of described aircraft 1, to produce electric energy, thus charges constantly to described CD-ROM drive motor 50 and described storage battery 30.
Fig. 4 illustrates the method for controlling power supply of the aircraft 1 in the present invention one better embodiment, and it comprises the steps:
Step S41: under described aircraft 1 is positioned over sunshine, described solar cell 60 is absorbed solar energy, absorbed sunshine is converted to electric energy, then described electric energy is exported to described storage battery 30 to charge to described storage battery 30, until described indicator lamp lights, make described storage battery 30 can be control chip 40 and power.Wherein, the charging duration of described solar cell 60 can set as required, only need ensure that described storage battery 30 starts to make described control chip 40 for described control chip 40 metapedes of powering.
Step S42: described solar cell 60 constant absorption solar energy is to produce electric energy, it exports the Part I electric energy E1 in described electric energy and Part II electric energy E2 to described CD-ROM drive motor 50 and described storage battery 30 respectively when described control chip 40 starts, thus make described CD-ROM drive motor 50 that described rotor 20 can be driven to rotate to make this aircraft 1 start to fly and perform corresponding action, and described storage battery 30 is made to continue to power to control chip 40.
Step S43: described solar cell 60 constant absorption solar energy in the flight course of described aircraft 1, to produce electric energy, thus charges constantly to described CD-ROM drive motor 50 and described storage battery 30.
Those skilled in the art will be appreciated that; above embodiment is only used to the present invention is described; and be not used as limitation of the invention; as long as within spirit of the present invention, the appropriate change do above embodiment and change all drop within the scope of protection of present invention.
Claims (10)
1. the aircraft of a Double-battery powered, it comprises a frame, multiple rotor, one lithium cell, one control chip and multiple CD-ROM drive motor, described rotor, lithium cell and control chip are all installed on this frame, it is characterized in that: described aircraft also comprises the solar cell that is arranged at this frame top, this solar cell is for absorbing sunshine and absorbed sunshine being converted to electric energy, then the Part I electric energy in described electric energy and Part II electric energy is exported to described CD-ROM drive motor and lithium cell respectively, described CD-ROM drive motor after reception Part I electric energy for driving described rotor rotational, described lithium cell after reception Part II electric energy for powering to control chip, make described control chip control this aircraft and perform corresponding action.
2. aircraft as claimed in claim 1, it is characterized in that: the proportion that described Part I electric energy accounts for described electric energy is greater than 90%, the proportion that described Part II electric energy accounts for described electric energy is less than 10%.
3. aircraft as claimed in claim 1, is characterized in that: described solar cell is a thin-film solar cell panel being covered in this frame top, and it has flexibility, flexible.
4. aircraft as claimed in claim 1, it is characterized in that: this solar cell is electrically connected through a buck circuit and described CD-ROM drive motor and lithium cell, this buck circuit is used for the rated voltage loss in voltage that this solar cell exports being low to moderate described CD-ROM drive motor and lithium cell.
5. aircraft as claimed in claim 1, it is characterized in that: this control chip is provided with an opto-electronic pickup, described opto-electronic pickup is used for the Illumination intensity of this aircraft surrounding environment of detecting real-time, described control chip is used for the Illumination intensity that detected by described opto-electronic pickup and a predetermined strength compares, and reduced the rotating speed of described rotor by described CD-ROM drive motor when described Illumination intensity is less than this predetermined strength, this aircraft security is landed.
6. aircraft as claimed in claim 5, it is characterized in that: described control chip is also for when described Illumination intensity is greater than this predetermined strength, regulate the maximum speed of described rotor according to described Illumination intensity, thus regulate the maximum flying speed of described aircraft.
7. aircraft as claimed in claim 1, it is characterized in that: described solar cell also connects a detecting voltage unit, for the output voltage of this solar cell of detecting real-time, described control chip is used for the output voltage that detected by described detecting voltage unit and a predetermined voltage compares, and reduced the rotating speed of described rotor by described CD-ROM drive motor when described output voltage is less than this predetermined voltage, this aircraft security is landed.
8. aircraft as claimed in claim 7, is characterized in that: described control chip also for when described output voltage is greater than this predetermined voltage, according to described go out the maximum speed of rotor described in voltage-regulation, thus regulate the maximum flying speed of described aircraft.
9. aircraft as claimed in claim 1, it is characterized in that: this frame comprises one for the central machine box of accommodating described control chip and multiple support being fixed on described central machine box, this central machine box comprises a shell, and the sidewall of this shell offers the through hole of the corresponding described support of multiple difference, one end of each support to be inserted in corresponding through hole and is fixed on this central machine box, each support is also fixed with a motor mount away from the other end of described central machine box, for an accommodating wherein CD-ROM drive motor, each motor mount offers the through hole of a corresponding described support, each support to insert in described through hole and is fixed on this motor mount.
10. the method for controlling power supply of an aircraft, described aircraft comprises a frame, multiple rotor, a lithium cell, a control chip and multiple CD-ROM drive motor, described rotor, lithium cell and control chip are all installed on this frame, described aircraft also comprises the solar cell that is covered in this frame top, it is characterized in that: described method for controlling power supply comprises:
Under described aircraft is positioned over sunshine, described solar cell is absorbed solar energy, absorbed sunshine is converted to electric energy, then described electric energy is exported to described lithium cell with to described lithium cell charging, make described lithium cell can be control chip and power;
Described solar cell constant absorption solar energy is to produce electric energy, it exports the Part I electric energy in described electric energy and Part II electric energy to described CD-ROM drive motor and described lithium cell respectively when described control chip starts, enable described CD-ROM drive motor drive described rotor rotational to make this aircraft start to fly and to perform corresponding action, and make described lithium cell continue to power to control chip; And
Described solar cell constant absorption solar energy in the flight course of described aircraft, to produce electric energy, thus constantly gives described CD-ROM drive motor and described lithium battery power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510462443.7A CN105083563A (en) | 2015-07-31 | 2015-07-31 | Double-battery-powered aircraft and power supply control method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510462443.7A CN105083563A (en) | 2015-07-31 | 2015-07-31 | Double-battery-powered aircraft and power supply control method thereof |
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| CN105083563A true CN105083563A (en) | 2015-11-25 |
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| CN201510462443.7A Pending CN105083563A (en) | 2015-07-31 | 2015-07-31 | Double-battery-powered aircraft and power supply control method thereof |
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| CN109823547A (en) * | 2019-01-26 | 2019-05-31 | 东北农业大学 | Twin-engined unmanned autogyros |
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