CN210102008U - Hybrid power system for unmanned aerial vehicle - Google Patents
Hybrid power system for unmanned aerial vehicle Download PDFInfo
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- CN210102008U CN210102008U CN201920672733.8U CN201920672733U CN210102008U CN 210102008 U CN210102008 U CN 210102008U CN 201920672733 U CN201920672733 U CN 201920672733U CN 210102008 U CN210102008 U CN 210102008U
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Abstract
A hybrid power system for an unmanned aerial vehicle comprises a stable power output module with high energy density, a peak instantaneous power output module with high power density and a charge-discharge management module. The high-energy-density stable power output module and the charge and discharge management module are arranged in the airplane body, the high-power-density peak instantaneous power output module is arranged in the wing, and the charge and discharge management module is connected with the high-energy-density stable power output module and the high-power-density peak instantaneous power output module through a wire harness. And the charge and discharge management module is responsible for charge and discharge management. The utility model has the advantages that: the cruising ability of the unmanned aerial vehicle can be improved, the energy use efficiency is improved, and the structural layout and the load of the unmanned aerial vehicle cannot be influenced; the super capacitor can be processed into various unmanned aerial vehicle components to match the requirements of a power system; the super capacitor provides unmanned aerial vehicle power demand, can use higher energy density lithium cell, satisfies long duration and reduces battery cost simultaneously.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle, a hybrid power system for unmanned aerial vehicle is related to.
Background
Traditional unmanned aerial vehicle adopts electric drive more, and the electric energy source is airborne power battery. The endurance time of the unmanned aerial vehicle is generally between 30min and 60min and the endurance mileage is generally not more than 30km under the influence of self load limit and power system efficiency. In recent years, unmanned aerial vehicles are widely applied in a plurality of fields such as emergency rescue, environmental monitoring, electric power line patrol, aerial surveying and mapping, agricultural plant protection and logistics distribution, and along with the continuous speed increase of global unmanned aerial vehicle industry development, the application popularization range is still continuously expanding, and the problems of the cruising ability and load of the unmanned aerial vehicle are more and more prominent.
Super capacitors have been used on a considerable scale as power starting devices for unmanned aerial vehicles, and hybrid power storage devices combining the principle of lithium battery and capacitor power storage have also been proposed in succession. These mixed use methods have satisfied the performance demand of unmanned aerial vehicle machine-mounted driving system high energy density, high output characteristic to a certain extent, but additional ultracapacitor system device has also increased driving system's weight to a certain extent, has influenced unmanned aerial vehicle's heavy burden and duration.
SUMMERY OF THE UTILITY MODEL
To the problem that exists among the above-mentioned prior art, the utility model provides a hybrid power system for unmanned aerial vehicle, this hybrid power system furthest's optimization has electric unmanned aerial vehicle's continuation of the journey and load now, under the prerequisite that does not increase unmanned aerial vehicle and bear a burden, has realized that the advantage of driving system high energy density and high power density is complementary.
In order to achieve the purpose, the utility model adopts the following technical scheme:
a hybrid power system for an unmanned aerial vehicle comprises a stable power output module with high energy density, a peak instantaneous power output module with high power density and a charge-discharge management module.
The high-energy-density stable power output module and the charge and discharge management module are arranged in the airplane body, the high-power-density peak instantaneous power output module is arranged in the wing, and the charge and discharge management module is connected with the high-energy-density stable power output module and the high-power-density peak instantaneous power output module through a wire harness. And the charge and discharge management module is responsible for charge and discharge management.
Further, the high-energy-density stable power output module may be one or more of a conventional storage battery, a lithium battery, a fuel cell or a solar cell.
Furthermore, the peak instantaneous power output module with high power density is formed by a plurality of super capacitor single module modules, and the super capacitor module is arranged in the wing or the casing to display the super capacitor in a wing or casing structure mode.
Furthermore, a plurality of single super capacitors can form a corresponding module in a series or parallel connection mode, and the structure of the super capacitor is as follows: carbon nanotube and/or graphene modified carbon fiber cloth with high specific surface area is used as an electrode, and structural filler (such as hollow glass beads, glass fibers and the like) is added into solid electrolyte or polymer gel electrolyte to prepare structural electrolyte. The super capacitor with the sandwich structure is prepared by hot pressing or other processing methods.
Further, a plurality of individual ultracapacitor system preparation modules: the packaging structure is packaged by epoxy resin or other insulating skins, the positive electrode tab and the negative electrode tab are arranged on two sides of the packaging structure and connected according to requirements, the connecting structure is insulated and protected by a push-pull mechanical device, and the mechanical device is preferably made of carbon fiber composite materials.
Further, an energy recovery module is arranged in the wing.
Further, the charge and discharge management module is connected with a super capacitor through a wire, and the super capacitor is connected with a motor through a wire.
Further, the motor is connected with a rotor.
Furthermore, the charging and discharging management module is connected with a charging access module through a lead.
Further, the charge and discharge management module is connected with a motor controller through a wire, and the motor controller is connected with the motor through a wire. The motor controller is a direct current and alternating current conversion unit.
Further, the motor is connected with a brake through a lead, the brake is connected with the energy recovery module through a lead, and the energy recovery module is connected with the super capacitor and the charge and discharge management module through leads.
Further, the fuselage and the wings are both made of carbon fiber composite materials.
Furthermore, a power battery module is arranged in the machine body.
When the unmanned aerial vehicle speed is stable, namely when stable energy is required to be input, the charging and discharging management module can control the power battery module to transmit energy, and the motor is driven to work through the motor controller. When the unmanned aerial vehicle is started or rapidly accelerated, the charging and discharging management module controls the high-power super capacitor to output energy and drives the motor to operate. When the unmanned aerial vehicle suddenly brakes, namely the brake runs, the braking energy is generated, and the energy is automatically recovered to the super capacitor through the energy recovery module and the charge-discharge management module, so that the energy is stored. On one hand, the capacity of a power system of the unmanned aerial vehicle can be improved, and the cruising ability of the unmanned aerial vehicle is improved; on the other hand, the energy loss in the charging and discharging process is reduced through the charging and discharging management system, and the energy use efficiency is improved.
The utility model has the advantages that: (1) the fuselage and the wings are made of carbon fiber composite materials, and a structural super capacitor with structural bearing and energy storage capacities is integrated into the fuselage or the wings of the unmanned aerial vehicle, so that the capacity of a power system of the unmanned aerial vehicle can be improved, and the cruising capacity of the unmanned aerial vehicle can be improved; on the other hand reduces the energy loss of charge-discharge process through charge-discharge management system, improves energy availability factor, and does not increase extra volume or weight, can not influence unmanned aerial vehicle structural layout and load. (2) The easy processing nature of structure ultracapacitor system can be processed into various unmanned aerial vehicle subassemblies with ultracapacitor system with the matching driving system demand. (3) The super capacitor provides unmanned aerial vehicle power demand, can use higher energy density lithium cell, satisfies long duration and reduces battery cost simultaneously.
Drawings
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of a cantilever energy storage device of the unmanned aerial vehicle;
FIG. 3 is a schematic diagram of a supercapacitor structure;
FIG. 4 is a schematic diagram of the hybrid power system for the unmanned aerial vehicle;
FIG. 5 is a schematic structural diagram of a supercapacitor module;
FIG. 6 is a schematic diagram of a parallel connection structure of super capacitors;
FIG. 7 is a schematic diagram of a series arrangement of supercapacitors.
Reference numerals: the system comprises a fuselage 1, a wing 2, a charge-discharge management module 3, a power battery module 4, a super capacitor 5, a motor 6, a rotor 7, an energy recovery module 8, a charge access module 9, a motor controller 10, a brake 11, a stable low load and a transient high load.
Detailed Description
For the sake of understanding, the present invention will be explained in detail below by way of example with reference to the accompanying drawings:
a hybrid power system for an unmanned aerial vehicle comprises a stable power output module with high energy density, a peak instantaneous power output module with high power density and a charge-discharge management module 3.
The stable power output module with high energy density and the charge and discharge management module 3 are arranged in the machine body 1. The peak instantaneous power output module of high power density is located in the wing 2. The fuselage 1 and the wings 2 are both made of carbon fiber composite material. The tail end of the wing is provided with a motor 6. The motor 6 is connected with a rotor 7.
The high-energy-density stable power output module can be one or more of a traditional storage battery, a lithium battery, a fuel cell or a solar cell.
The peak instantaneous power output module with high power density is formed by assembling a plurality of super capacitors 5; the super capacitor 5 is arranged in the wing or the casing, and the super capacitor 5 is represented in the form of structural components such as the wing or the casing.
The individual supercapacitors 5 may constitute respective modules in series or in parallel.
The structure of the super capacitor 5 is as follows: the carbon nanotube or graphene modified carbon fiber cloth with high specific surface area is used as an electrode, and a structural filler (such as hollow glass beads, glass fibers and the like) is added into a solid electrolyte or a polymer gel electrolyte to prepare a structural electrolyte. The super capacitor with the sandwich structure is prepared by hot pressing or other processing methods.
The charge and discharge management module 3 is connected with a stable power output module with high energy density and a peak instantaneous power output module with power density through a wire harness.
The charge and discharge management module 3 is connected with the super capacitor 5 through a lead, and the super capacitor 5 is connected with the motor 6 through a lead.
The body 1 is internally provided with a power battery module 4, a charging access module 9, a motor controller 10 and a brake 11.
The charging and discharging management module 3 is connected with the charging access module 9 and the motor controller 10 through a lead, and the motor controller 10 is a direct current and alternating current conversion unit. The motor controller 10 is connected to the motor 6 by a wire.
An energy recovery module 8 is arranged in the wing 2. The motor 6 is connected with the brake 11 through a lead, the brake 11 is connected with the energy recovery module 8 through a lead, and the energy recovery module 8 is connected with the super capacitor 5 and the charging and discharging management module 3 through leads.
The charge and discharge management module 3 is responsible for charge and discharge management. The unmanned aerial vehicle speed is stable, and that is to say when needing stable energy input, be in stable low-load a promptly, charge and discharge management module 3 can control power battery module 4 and carry energy, drives motor 6 work through motor controller 10.
When the unmanned aerial vehicle is started or rapidly accelerated, namely, when the unmanned aerial vehicle is in an instant high load b, the charging and discharging management module 3 controls the high-power super capacitor 5 to output energy and drives the motor 6 to operate.
When the unmanned aerial vehicle brakes suddenly, namely the brake 11 runs, the braking energy is generated, and the energy is automatically recovered to the super capacitor 5 through the energy recovery module 8 and the charge and discharge management module 3, so that the energy is stored. On one hand, the capacity of a power system of the unmanned aerial vehicle can be improved, and the cruising ability of the unmanned aerial vehicle is improved; on the other hand, the energy loss in the charging and discharging process is reduced through the charging and discharging management system, and the energy use efficiency is improved.
The above embodiments are merely illustrative or explanatory of the technical solution of the present invention, and should not be construed as limiting the technical solution of the present invention, and it is obvious that those skilled in the art can make various modifications and variations to the present invention without departing from the spirit and scope of the present invention. The present invention also includes such modifications and variations provided they come within the scope of the appended claims and their equivalents.
Claims (10)
1. A hybrid power system for an unmanned aerial vehicle is characterized in that: the high-power-density stable power output module and the high-power-density peak instantaneous power output module are arranged in the airplane body, the high-power-density peak instantaneous power output module is arranged in the wing, and the charge and discharge management module is connected with the high-power-density stable power output module and the high-power-density peak instantaneous power output module through wiring harnesses.
2. The hybrid system for an unmanned aerial vehicle according to claim 1, wherein: the high-energy-density stable power output module is one or more of a traditional storage battery, a lithium battery, a fuel cell or a solar cell.
3. The hybrid system for an unmanned aerial vehicle according to claim 1, wherein: the peak instantaneous power output module with high power density is formed by a plurality of super capacitor single body modules, and the super capacitor modules are arranged in the wings or the shell.
4. The hybrid system for an unmanned aerial vehicle according to claim 3, wherein: the charge and discharge management module is connected with the super capacitor through a wire, and the super capacitor is connected with the motor through a wire.
5. The hybrid system for an unmanned aerial vehicle according to claim 1, wherein: the charge and discharge management module is connected with a motor controller through a wire, and the motor controller is connected with the motor through a wire.
6. The hybrid system for an unmanned aerial vehicle according to claim 4, wherein: an energy recovery module is arranged in the wing.
7. The hybrid system for an unmanned aerial vehicle according to claim 6, wherein: the motor is connected with a brake through a lead, the brake is connected with the energy recovery module through a lead, and the energy recovery module is connected with the super capacitor and the charge and discharge management module through leads.
8. The hybrid system for an unmanned aerial vehicle according to claim 3, wherein: several individual supercapacitors may constitute respective modules in series or in parallel.
9. The hybrid system for an unmanned aerial vehicle according to claim 3, wherein: the structure of the super capacitor is as follows: carbon nanotube and/or graphene modified carbon fiber cloth with high specific surface area is used as an electrode, a structural filler is added into a solid electrolyte or a polymer gel electrolyte to prepare a structural electrolyte, and the supercapacitor with a sandwich structure is prepared by hot pressing.
10. A hybrid system for an unmanned aerial vehicle according to any one of claims 1 to 9, wherein: the charging and discharging management module is connected with a charging access module through a lead.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920672733.8U CN210102008U (en) | 2019-05-10 | 2019-05-10 | Hybrid power system for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920672733.8U CN210102008U (en) | 2019-05-10 | 2019-05-10 | Hybrid power system for unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN210102008U true CN210102008U (en) | 2020-02-21 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920672733.8U Expired - Fee Related CN210102008U (en) | 2019-05-10 | 2019-05-10 | Hybrid power system for unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110127064A (en) * | 2019-05-10 | 2019-08-16 | 费曼科技(青岛)有限公司 | A kind of unmanned plane hybrid power system |
-
2019
- 2019-05-10 CN CN201920672733.8U patent/CN210102008U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110127064A (en) * | 2019-05-10 | 2019-08-16 | 费曼科技(青岛)有限公司 | A kind of unmanned plane hybrid power system |
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