CN112793795A - Carry on new forms of energy system's unmanned aerial vehicle - Google Patents
Carry on new forms of energy system's unmanned aerial vehicle Download PDFInfo
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- CN112793795A CN112793795A CN202110298631.6A CN202110298631A CN112793795A CN 112793795 A CN112793795 A CN 112793795A CN 202110298631 A CN202110298631 A CN 202110298631A CN 112793795 A CN112793795 A CN 112793795A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
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- B64D27/353—
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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
- Y02T50/50—On board measures aiming to increase energy efficiency
-
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The application provides a carry on new forms of energy system's unmanned aerial vehicle. This application covers flexible solar cell panel at unmanned aerial vehicle's fuselage and wing surface, utilizes flexible solar cell panel to supply the electric energy for the inside energy memory of unmanned aerial vehicle in real time to take off and climb the in-process and regard as extra energy supply source, reduce the consumption of this in-process to the energy memory energy storage. The flexible solar cell panel in this application passes through circuit film and a plurality of layers printing opacity seals and fixes the crystal silicon battery piece on flexible backplate to utilize the toughness of flexible backplate, circuit film and each printing opacity seal to guarantee that crystal silicon battery piece can laminate fuselage, wing curved surface, reduce flight resistance, and guarantee photoelectric conversion efficiency, guarantee that flexible solar cell panel has sufficient mechanical strength and water-proof effects.
Description
Technical Field
The application relates to the technical field of new forms of energy, particularly relates to a carry on new forms of energy system's unmanned aerial vehicle.
Background
The small unmanned aerial vehicle is driven by a motor to fly or cruise. However, since the size of the small unmanned aerial vehicle is limited, the amount of electricity that can be stored by the energy storage device is limited. And unmanned aerial vehicle takes off, the in-process of climbing, and the torque output demand is showing to be higher than the moment of torsion requirement during cruising, consequently, takes off and the in-process of climbing, and the motor often is hardly maintained under rated operating mode for satisfying the demand of output torque, therefore motor operating efficiency is lower, has great consumption to energy memory electric quantity. The energy consumption in the process of taking off and climbing can obviously influence the cruising distance of the unmanned aerial vehicle.
And power systems such as unmanned aerial vehicle motors are difficult to match the cruise power output requirement and simultaneously consider energy consumption and operating efficiency in dynamic processes such as take-off and climbing due to the limitation of hardware conditions. Therefore, how to improve the power supply system of the small unmanned aerial vehicle to increase the cruising distance becomes the design focus of the small unmanned aerial vehicle.
Disclosure of Invention
This application provides a carry on new forms of energy system's unmanned aerial vehicle to prior art not enough, and this application is through covering flexible solar cell panel in unmanned aerial vehicle's surface with in order to supply the electric energy for energy memory in real time to take off and climb the in-process and regard as extra energy supply source, reduce the consumption of this in-process to the energy memory energy storage. The technical scheme is specifically adopted in the application.
Firstly, in order to achieve the purpose, a small unmanned aerial vehicle carrying a new energy system is provided, wherein flexible solar cell panels cover the surfaces of a body and wings of the unmanned aerial vehicle, the flexible solar cell panels are connected with a photoelectric conversion circuit arranged in the unmanned aerial vehicle, and the charging output end of the photoelectric conversion circuit is connected with an energy storage device; wherein the flexible solar panel comprises: a flexible backsheet disposed at the bottom layer; the surface of the circuit film is provided with a conductive path, and the back surface of the circuit film is fixedly bonded with the back plate; the crystalline silicon battery pieces are electrically connected with the conductive paths on the surface of the circuit film through conductive gel, and are arranged in an array mode and fixedly bonded on the surface of the circuit film; the EVA adhesive film covers the surfaces of the crystalline silicon battery piece and the circuit film; the insulating antireflection film covers the surface of the EVA adhesive film; the edge of the flexible backboard is also provided with a conductive through hole, and the conductive through hole is electrically connected with a conductive path on the circuit film and is used as an interface of the photoelectric conversion circuit.
Optionally, the small unmanned aerial vehicle carrying the new energy system is as described in any one of the above, wherein the flexible back plate is a PVC back plate, and a hot melt adhesive film covers a bottom side of the flexible back plate, and is fixedly attached to a fuselage and a wing of the unmanned aerial vehicle through the hot melt adhesive film; wherein, unmanned aerial vehicle's fuselage and wing surface still are being provided with the circuit connection hole in the position that corresponds electrically conductive through-hole on the PVC backplate, and photoelectric conversion circuit's interface connection line by the inside of circuit connection hole stretches into the inside of electrically conductive through-hole on the PVC backplate, will through filling at the inside electrically conductive gel of electrically conductive through-hole photoelectric conversion circuit's interface connection line is fixed and is corresponded electrically conductive route's position in the circuit film.
Optionally, the small unmanned aerial vehicle carrying the new energy system as described above, wherein ribs are further disposed on the inner side surfaces of the fuselage and the wings, and a wiring through hole is further disposed on the rib close to the circuit connection hole, so that an interface connection line of the photoelectric conversion circuit passes through the wiring hole to fix the connection line; and a bending allowance is reserved between the wiring through hole and the circuit connecting hole on the interface connecting line of the photoelectric conversion circuit.
Optionally, as above arbitrary carry on new energy system's unmanned aerial vehicle, wherein, fuselage and wing are assembled as a whole by a plurality of shell part module concatenations, the outside surface of fuselage and wing still is provided with at the edge of each shell part module and presses the layering, flexible solar cell panel's edge still is provided with the mounting hole, press the strip and withhold at flexible solar cell panel's edge, inwards press and connect gradually by bolt or buckle arch the major structure according to layering, flexible solar cell panel and shell part module.
Optionally, the unmanned aerial vehicle carrying the new energy system is as described in any one of the above, wherein the circuit connection hole is located at an edge of the main body structure of the housing part module and below the pressing bar; the conductive through holes in the PVC back plate are located at the edge of the flexible solar cell panel, and only one conductive through hole is arranged between every two adjacent mounting holes.
Optionally, the small unmanned aerial vehicle carrying the new energy system is further provided with a motor driving circuit and a power control unit, wherein the motor driving circuit and the power control unit are connected between the energy storage device and a motor of the unmanned aerial vehicle; the motor driving circuit is internally provided with a switch component which is used for switching an electric path of the switch component according to a preset period so as to drive the motor to operate; the power control unit is connected between the power supply end of the motor driving circuit and the energy storage device and is provided with an interface connected to the energy supply output end of the photoelectric conversion circuit, and the power control unit is arranged to adjust the output power of the motor driving circuit according to the following steps: when a takeoff signal is received, the energy storage device and the photoelectric conversion circuit are connected through a series connection path at the same time, an output signal of the energy storage device and a first output signal of an energy supply output end of the photoelectric conversion circuit are connected in series and combined into a first power output signal, and the first power output signal is output to the motor driving circuit to drive the motor to operate in a first working state; in the ascending process of the unmanned aerial vehicle, the energy storage device and the photoelectric conversion circuit are connected through a parallel passage at the same time, an output signal of the energy storage device and a second output signal of an energy supply output end of the photoelectric conversion circuit are connected in parallel and combined into a second power output signal, and the second power output signal is output to the motor driving circuit to drive the motor to operate in a second working state; in the cruising process of the unmanned aerial vehicle, the output signal of the energy storage device is directly adjusted to a rated power point matched with the motor, and a third power output signal obtained after adjustment is output to the motor driving circuit to drive the motor to operate in a third working state.
Optionally, as described in any above, the unmanned aerial vehicle equipped with the new energy system, wherein the voltage of the first output signal of the photoelectric conversion circuit is lower than the voltage of the second output signal, and the voltage of the second output signal is not lower than the voltage of the output signal of the energy storage device.
Optionally, as mentioned above, the small unmanned aerial vehicle equipped with the new energy system further includes an energy recovery circuit, which is connected between the motor of the unmanned aerial vehicle and the photoelectric conversion circuit, and is used for recovering kinetic energy of the motor and converting the kinetic energy into charging voltage to charge the energy storage device in the descending process of the unmanned aerial vehicle.
Optionally, the unmanned aerial vehicle equipped with the new energy system as described in any of the above, wherein the motor has a rotor position sensor, and the electrical path states of the energy recovery circuit and the motor driving circuit are matched with the trigger state of the rotor position sensor.
Advantageous effects
This application covers flexible solar cell panel at unmanned aerial vehicle's fuselage and wing surface, utilizes flexible solar cell panel to supply the electric energy for the inside energy memory of unmanned aerial vehicle in real time to take off and climb the in-process and regard as extra energy supply source, reduce the consumption of this in-process to the energy memory energy storage. The flexible solar cell panel in this application passes through circuit film and a plurality of layers printing opacity seals and fixes the crystal silicon battery piece on flexible backplate to utilize the toughness of flexible backplate, circuit film and each printing opacity seal to guarantee that crystal silicon battery piece can laminate fuselage, wing curved surface, reduce flight resistance, and guarantee photoelectric conversion efficiency, guarantee that flexible solar cell panel has sufficient mechanical strength and water-proof effects.
Additional features and advantages of the application will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by the practice of the application.
Drawings
The accompanying drawings are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the principles of the application and not limit the application. In the drawings:
fig. 1 is a schematic cross-sectional view of a flexible solar panel covered by the surface of a drone of the present application;
fig. 2 is a schematic view of one housing part module in the drone of the present application;
FIG. 3 is a schematic illustration of a flexible solar panel manufacturing process in the present application;
fig. 4 is a block diagram of a circuit structure in the drone of the present application.
In the drawings, 1 denotes a flexible backsheet; 2 denotes a circuit thin film; 3 represents a crystalline silicon cell; 4 represents an EVA adhesive film; 5 represents an insulating antireflection film; 10 denotes the inboard surfaces of the fuselage and wings; 11 denotes ribs; 12 denotes a wiring via hole; 13 denotes interface connection lines; and 14, a pressing bar.
Detailed Description
In order to make the purpose and technical solutions of the embodiments of the present application clearer, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the drawings of the embodiments of the present application. It should be apparent that the described embodiments are only some of the embodiments of the present application, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the described embodiments of the application without any inventive step, are within the scope of protection of the application.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The meaning of "and/or" as used herein is intended to include both the individual components or both.
The meaning of "inside and outside" in this application means that, with respect to the drone itself, the direction from its case to its fuselage or wing internal drive circuit is inside, and vice versa; and not as a specific limitation on the mechanism of the device of the present application.
The term "connected" as used herein may mean either a direct connection between components or an indirect connection between components via other components.
The meaning of "upper and lower" in this application refers to the user just when unmanned aerial vehicle advancing direction, is promptly down by pressing the direction of the flexible solar cell panel edge conductive through-hole of strip orientation, otherwise promptly is last, and the device mechanism's that is not to this application specific limit.
Fig. 1 is according to the utility model provides a carry on new forms of energy system's unmanned aerial vehicle, for the discharge cycle of energy memory at the in-process that cruises among the extension unmanned aerial vehicle power module, this application all covers at unmanned aerial vehicle's fuselage and wing surface has flexible solar cell panel, utilize flexible solar cell panel as energy memory's replenishment, charge for energy memory through setting up at the inside photoelectric conversion circuit of unmanned aerial vehicle in real time, and take off and climb the in-process at unmanned aerial vehicle and regard as supplementary power supply, together the moment of torsion output for the power control unit power supply is in order to improve the motor for energy memory in coordination, and reduce unmanned aerial vehicle take off and climb the dissipation of in-process to the inside electric energy of energy memory.
For easy to assemble, guarantee that unmanned aerial vehicle fuselage, the plane smoothness of wing surface accord with the hydrodynamics requirement and compromise panel light energy conversion efficiency simultaneously, the flexible solar cell panel of this application is including following structure:
a flexible backsheet 1, which is arranged at the bottom layer,
the surface of the circuit film 2 is provided with a conductive path, and the back surface of the circuit film 2 is fixedly bonded with the back plate;
the crystalline silicon battery pieces 3 are electrically connected with the conductive paths on the surface of the circuit film through conductive gel, and are arranged in an array mode and fixedly bonded on the surface of the circuit film;
the EVA adhesive film 4 covers the surfaces of the crystalline silicon battery piece 3 and the circuit film;
an insulating antireflection film 5 covering the surface of the EVA adhesive film;
the edge of the flexible back plate 1 is further provided with a conductive through hole, the inner wall of the conductive through hole can be covered with a metal coating or a metal patch to increase the area of electrical contact between the interface connecting line of the photoelectric conversion circuit and the conductive through hole, the top end of the conductive through hole is electrically connected with the conductive path on the circuit film 2, and the interface connecting line of the photoelectric conversion circuit can be electrically connected to the circuit film through the conductive through hole to serve as an interface of the photoelectric conversion circuit.
When the solar cell works, sunlight penetrates through the insulating antireflection film and the EVA adhesive film 4 to reach the surface of the crystalline silicon cell piece 3 for photoelectric conversion. The crystal silicon cell 3 has small structural size and is smoothly attached to the surfaces of wings and a machine body by being coated by the EVA adhesive film 4, the circuit film and the flexible back plate. Current and voltage signals formed by photoelectric conversion are communicated to the conductive through hole through a conductive passage on the surface of the circuit film, and are output to the photoelectric conversion circuit through the conductive through hole and an interface connecting wire of the photoelectric conversion circuit connected inside the conductive through hole, so that the charging of the energy storage device is realized through the charging output end of the photoelectric conversion circuit by voltage conversion and amplification, or the current and voltage signals are used as a supplementary power supply to provide extra electric energy for the climbing or takeoff process of the small unmanned aerial vehicle, and the energy consumption of the energy storage device in the process is reduced.
Among the above-mentioned flexible solar cell panel, flexible backplate 1 is the PVC backplate, and its bottom side covers there is hot melt adhesive membrane to it is fixed with fuselage and the laminating of wing of unmanned aerial vehicle to pass through hot melt adhesive membrane. For further guaranteeing that the flexible solar cell panel is stably attached to the rear surface of the fuselage and the wing, the circuit connection structure is stable, the fuselage and the wing surface of the unmanned aerial vehicle can be further provided with circuit connection holes at positions corresponding to the conductive through holes on the PVC backboard, the interface connection line of the photoelectric conversion circuit is formed by extending the inside of the circuit connection holes into the inside of the conductive through holes on the PVC backboard, and the interface connection line of the photoelectric conversion circuit is fixed at the position corresponding to the conductive path in the circuit film 2 through conductive gel filled in the conductive through holes. And correspondingly, for avoiding the internal structure vibrations of fuselage in-process of the fluctuation of flight to lead to photoelectric conversion circuit's interface connecting wire to rock, this application still can cooperate with the electrically conductive through-hole position, further with the mode of figure 2, be provided with rib 11 at the inboard surface 10 of fuselage and wing, wherein, still be provided with wiring through-hole 12 on the rib that is close to the circuit connection hole, supply photoelectric conversion circuit's interface connecting wire to pass the wiring hole is in order to fix the connecting wire. The interface connection line 13 of the photoelectric conversion circuit generally has a bending margin reserved between the wiring through hole and the circuit connection hole. The bending allowance can be adapted to provide small displacement between the conductive through hole and the circuit connecting hole in the fluctuating vibration process of the airplane body and the airplane wing, and the situation that an interface connecting line of the photoelectric conversion circuit is loosened or the circuit is unstable in contact due to pulling is avoided.
In an unmanned aerial vehicle, a fuselage and wings are generally assembled into a whole by splicing a plurality of shell component modules. In order to ensure that the aerodynamic surfaces of the fuselage and the wing surface meet the hydromechanics requirement, in order to ensure that the surfaces of the fuselage and the wing are smooth and flat as far as possible and avoid the flexible solar cell panel from falling off or tilting in the flying process, the outer side surfaces of the fuselage and the wing can be further provided with pressing strips 14 which are turned outwards from the shell component module main body and are arranged on the edges corresponding to the shell component modules, the thickness of the pressing strips is matched with the thickness of the flexible solar cell panel, and the flexible solar cell panel is clamped and fixed between the pressing strips and the shell component module main body. The fixing is realized by pressing the strip for the cooperation, the mounting hole has still further been seted up at flexible solar cell panel's edge, press the strip and withhold at flexible solar cell panel's edge, inwards press and connect gradually by the shown bolt in the left side of figure 1 or the shown buckle arch in the right side of figure 1 press the major structure of layering, flexible solar cell panel and shell part module.
In order to ensure that the interface connecting wire of the photoelectric conversion circuit is stably and electrically connected with the conductive path in the circuit film as far as possible, the circuit connecting holes on the fuselage and the wings can be further arranged at the edge of the main structure of the shell part module and below the pressing strip; and correspondingly arranging the conductive through holes on the PVC back plate at the edge of the flexible solar cell panel. Therefore, through the fixing effect of the pressing strips, the vibration of the interface connecting line of the photoelectric conversion circuit relative to the shell component module of the unmanned aerial vehicle is limited to the minimum in the flying and landing process. The limit sets up only a conductive through hole between two adjacent mounting holes, can further guarantee that conductive through hole circuit connection position is stable, avoids its electric connection circuit to receive the interference of other photoelectric conversion circuit's interface connecting wire and became invalid or unstable.
The manufacturing process of the flexible solar panel can refer to fig. 3:
firstly, a glycol terephthalate film used for manufacturing a conductive film is flatly covered on the upper surface of a mirror material, and a corresponding conductive path pattern is recorded from the upper side of the mirror material to the upper surface of the glycol terephthalate film by a laser etching mode. The thickness of the glycol terephthalate film can be set to be integral multiple of the laser etching wavelength, so that the laser etching light intensity on the surface of the conductive film is strongest due to the standing wave interference effect of the film, and the etching effect is best. The flexible solar cell panel is arranged on the surface of the body and the wing to form a bending radian, and accordingly, the recording depth of an etched pattern in the bending direction can be increased in the etching process, so that the structural strength of a conductive material in the etched conductive path pattern in the bending state is ensured, and the conductivity of the whole conductive film is ensured. After the recording is finished, the polyethylene glycol gel mixed with the copper powder is evenly covered on the upper surface of the whole polyethylene glycol terephthalate film in a centrifugal mode in a vacuum environment, so that the polyethylene glycol gel is evenly filled in an electric path pattern formed by recording on the surface of the film, a gel coating is formed on the surface of the film, and finally, redundant polyethylene glycol gel is removed through an acyl washing and drying curing process, so that the copper powder evenly mixed in the polyethylene glycol gel is flatly attached and fixed inside the electric path pattern formed by recording on the surface of the film, and a conductive path is provided. Therefore, the array formed by a plurality of groups of photoelectric conversion units can be obtained by directly electrically connecting each crystalline silicon cell piece on the connecting point position of the conductive path through the conductive gel. The mirror surface material can further conveniently detect the actually recorded conductive path pattern in a photoelectric scanning mode while further enhancing the etching effect by utilizing reflected light in the laser etching process, thereby ensuring the completeness and accuracy of a circuit connection structure.
And then, adhering and fixing the conductive film with the conductive path on the surface of the back plate made of the PVC material through a hot melt adhesive film, electrically connecting the conductive path on the surface of the flexible conductive film with each crystalline silicon cell piece through conductive gel to obtain an array formed by a plurality of groups of photoelectric conversion units, covering an EVA adhesive film 4 on the surface of the array of the photoelectric conversion units, further covering a layer of insulating antireflection film 5 on the top of the EVA adhesive film in a state close to vacuum through a centrifugal mode or an electrostatic mode after the EVA adhesive film provides waterproof sealing, wherein the insulating antireflection film 5 can provide a complete and smooth plane so as to improve the sunlight absorption efficiency of the crystalline silicon cell piece 3. In addition, the insulating antireflection film can provide a further waterproof effect for the internal crystalline silicon cell piece, and the interference effect of incident sunlight waves is utilized to reduce reflected light rays so as to increase the light ray intensity absorbed by the photoelectric conversion unit.
The insulating antireflection film can be realized by covering a titanium dioxide coating and a zirconium oxide coating with a polyester film. The titanium dioxide and zirconium oxide coating can be filled with a proper amount of argon under a high vacuum state by utilizing a magnetron sputtering method, and direct current voltage is applied between a cathode cylindrical target or a plane target and the wall of an anode coating chamber to generate magnetic control type abnormal glow power generation in the coating chamber so as to ionize the argon. The target material is accelerated and bombarded under the action of an electric field to sputter a large amount of target material molecules, and the sputtered neutral target molecules are deposited on the polyester film substrate to form a film.
Referring to fig. 4, in order to further reduce the consumption of energy stored in the energy storage device during takeoff and climbing, a motor driving circuit and a power control unit are further connected between the motor of the unmanned aerial vehicle and the energy storage device;
the motor driving circuit is internally provided with a switch component which is used for switching an electric path of the switch component according to a preset period so as to drive the motor to operate;
the power control unit is connected between the power supply end of the motor driving circuit and the energy storage device and is provided with an interface connected to the energy supply output end of the photoelectric conversion circuit, and the power control unit is arranged to adjust the output power of the motor driving circuit according to the following steps:
when a takeoff signal is received, the energy storage device and the photoelectric conversion circuit are connected through a series connection path at the same time, an output signal of the energy storage device and a first output signal of an energy supply output end of the photoelectric conversion circuit are connected in series and combined into a first power output signal, and the first power output signal is output to the motor driving circuit to drive the motor to operate in a first working state;
in the climbing process of the unmanned aerial vehicle, the energy storage device and the photoelectric conversion circuit are connected through a parallel connection path, an output signal of the energy storage device and a second output signal of an energy supply output end of the photoelectric conversion circuit are connected in parallel and combined into a second power output signal, and the second power output signal is output to the motor driving circuit to drive the motor to operate in a second working state;
in the cruising process of the unmanned aerial vehicle, the output signal of the energy storage device is directly adjusted to a rated power point matched with the motor, and then the third power output signal obtained after adjustment is output to the motor driving circuit to drive the motor to operate in a third working state.
The series path and the parallel path can be switched directly by switching the switch states of the IJBT transistor, and can also be switched by switching different ports of the chip by using the circuit. The photoelectric conversion circuit is internally provided with a DC-DC converter corresponding to high and low output voltages respectively, wherein the voltage of a first output signal output by the low-voltage DC-DC converter is lower than that of a second output signal output by the high-voltage DC-DC converter, and the voltage of the second output signal is not lower than that of an output signal of the energy storage device. Therefore, when the motor is driven by the first output signal of the photoelectric conversion circuit in a series connection mode, the power supply voltage of the motor can be slightly increased, so that the rotating speed of the motor is increased, and extra takeoff power is provided in an auxiliary mode; when photoelectric conversion circuit's second output signal passes through parallel mode driving motor, can keep the supply voltage of motor near rated power electricity basically, and the supply current that sets up this moment is higher than the electric current of rated power electricity to increase the energy supply of motor, the supplementary extra output torque that provides, with the assurance unmanned aerial vehicle process of climbing has enough power.
For further retrieving the kinetic energy of unmanned aerial vehicle descending in-process inside motor, this application still can further set up the energy recuperation circuit in unmanned aerial vehicle. This energy recuperation circuit connection is between unmanned aerial vehicle's motor and photoelectric conversion circuit for at unmanned aerial vehicle decline in-process, retrieve the kinetic energy of motor and convert it into charging voltage and charge energy memory. The energy recovery circuit can be connected with interfaces of stator windings of the motor, and the on-off state of each switch element in the switch path is switched according to the position of the rotor detected by a rotor position sensor in the motor through the switch path matched with the position of the rotor of the motor, so that the induced current is converted and recovered to an energy storage system through the energy recovery circuit in a high-efficiency mode in the direction of induced current formed by the fact that the rotor rotates and cuts magnetic lines of force between the stator windings.
For making things convenient for laying of flexible solar cell panel, the unmanned aerial vehicle that this application was used generally is fixed wing unmanned aerial vehicle. In rotor unmanned aerial vehicle, flexible solar cell panel generally can lay the surface at unmanned aerial vehicle's fuselage major structure upside and whole rotor linking arm to provide sufficient light energy absorbing area, improve energy storage and power supply effect.
The above are merely embodiments of the present application, and the description is specific and detailed, but not construed as limiting the scope of the present application. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, which falls within the protection scope of the present application.
Claims (9)
1. A small unmanned aerial vehicle carrying a new energy system is characterized in that the body and the wing surfaces of the unmanned aerial vehicle are covered with flexible solar panels, the flexible solar panels are connected with a photoelectric conversion circuit arranged in the unmanned aerial vehicle, and the charging output end of the photoelectric conversion circuit is connected with an energy storage device; wherein the content of the first and second substances,
the flexible solar cell panel includes:
a flexible backsheet (1) arranged at the bottom layer,
the surface of the circuit film (2) is provided with a conductive path, and the back surface of the circuit film (2) is fixedly bonded with the back plate;
the crystalline silicon cell (3) is electrically connected with the conductive path on the surface of the circuit film through conductive gel, and the crystalline silicon cell is arranged in an array mode and is fixedly bonded on the surface of the circuit film;
the EVA adhesive film (4) covers the surfaces of the crystalline silicon battery piece (3) and the circuit film;
an insulating antireflection film (5) covering the surface of the EVA adhesive film;
the edge of the flexible backboard (1) is also provided with a conductive through hole, and the conductive through hole is electrically connected with a conductive path on the circuit film (2) and is used as an interface of the photoelectric conversion circuit.
2. The small unmanned aerial vehicle with the new energy system as claimed in claim 1, wherein the flexible back plate (1) is a PVC back plate, and the bottom side of the flexible back plate is covered with a hot melt adhesive film and is fixed to the body and the wings of the unmanned aerial vehicle by the hot melt adhesive film;
wherein, unmanned aerial vehicle's fuselage and wing surface still are being provided with the circuit connection hole in the position that corresponds electrically conductive through-hole on the PVC backplate, and photoelectric conversion circuit's interface connection line by the inside of circuit connection hole stretches into the inside of electrically conductive through-hole on the PVC backplate, will through filling at the inside electrically conductive gel of electrically conductive through-hole photoelectric conversion circuit's interface connection line fixes the position that corresponds electrically conductive route in circuit film (2).
3. The small unmanned aerial vehicle equipped with a new energy system of claim 2, wherein the inner side surfaces of the fuselage and the wings are further provided with ribs, wherein the ribs close to the circuit connection holes are further provided with wiring through holes for the interface connection wires of the photoelectric conversion circuit to pass through the wiring holes to fix the connection wires;
and a bending allowance is reserved between the wiring through hole and the circuit connecting hole on the interface connecting line of the photoelectric conversion circuit.
4. The small unmanned aerial vehicle with the new energy system, as claimed in claim 3, wherein the fuselage and the wings are assembled by splicing a plurality of shell component modules into a whole, the outer side surfaces of the fuselage and the wings are further provided with pressing strips at the edges of the shell component modules, the edges of the flexible solar panels are further provided with mounting holes, the pressing strips are fastened at the edges of the flexible solar panels, and bolts or fastening protrusions are used for pressing inwards and connecting the main structures of the pressing strips, the flexible solar panels and the shell component modules in sequence.
5. The small unmanned aerial vehicle with the new energy system mounted in claims 1-4, wherein the circuit connection hole is located at the edge of the main body structure of the housing part module and below the pressing bar;
the conductive through holes in the PVC back plate are located at the edge of the flexible solar cell panel, and only one conductive through hole is arranged between every two adjacent mounting holes.
6. The small unmanned aerial vehicle carrying the new energy system as claimed in claims 1-4, wherein a motor driving circuit and a power control unit are further connected between the energy storage device and the motor of the unmanned aerial vehicle;
the motor driving circuit is internally provided with a switch component which is used for switching an electric path of the switch component according to a preset period so as to drive the motor to operate;
the power control unit is connected between the power supply end of the motor driving circuit and the energy storage device and is provided with an interface connected to the energy supply output end of the photoelectric conversion circuit, and the power control unit is arranged to adjust the output power of the motor driving circuit according to the following steps:
when a takeoff signal is received, the energy storage device and the photoelectric conversion circuit are connected through a series connection path at the same time, an output signal of the energy storage device and a first output signal of an energy supply output end of the photoelectric conversion circuit are connected in series and combined into a first power output signal, and the first power output signal is output to the motor driving circuit to drive the motor to operate in a first working state;
in the ascending process of the unmanned aerial vehicle, the energy storage device and the photoelectric conversion circuit are connected through a parallel passage at the same time, an output signal of the energy storage device and a second output signal of an energy supply output end of the photoelectric conversion circuit are connected in parallel and combined into a second power output signal, and the second power output signal is output to the motor driving circuit to drive the motor to operate in a second working state;
in the cruising process of the unmanned aerial vehicle, the output signal of the energy storage device is directly adjusted to a rated power point matched with the motor, and a third power output signal obtained after adjustment is output to the motor driving circuit to drive the motor to operate in a third working state.
7. The unmanned aerial vehicle with new energy system of claim 6, wherein the voltage of the first output signal of the photoelectric conversion circuit is lower than the voltage of the second output signal, and the voltage of the second output signal is not lower than the voltage of the output signal of the energy storage device.
8. The small unmanned aerial vehicle equipped with a new energy system of claim 7, further comprising an energy recovery circuit connected between the motor of the unmanned aerial vehicle and the photoelectric conversion circuit, for recovering kinetic energy of the motor and converting the kinetic energy into a charging voltage to charge the energy storage device during descent of the unmanned aerial vehicle.
9. The drone with new energy system according to claims 1 to 6, wherein the motor has a rotor position sensor, the electrical path status of the energy recovery circuit and the motor drive circuit matching the trigger status of the rotor position sensor.
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Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102737849A (en) * | 2011-03-31 | 2012-10-17 | 索尼公司 | Method of producing photoelectric conversion element, photoelectric conversion element and electronic device |
| CN102774490A (en) * | 2012-04-10 | 2012-11-14 | 北京航空航天大学 | Novel long-endurance solar unmanned aerial vehicle |
| CN103158875A (en) * | 2011-12-15 | 2013-06-19 | 通用电气公司 | System and method for power distribution |
| CN103840745A (en) * | 2013-09-13 | 2014-06-04 | 武汉美格科技有限公司 | Solar energy system for unmanned plane to use |
| CN105449822A (en) * | 2015-12-11 | 2016-03-30 | 中国电子科技集团公司第四十八研究所 | Energy system for high-altitude airship and power supply control method |
| CN206485579U (en) * | 2016-12-28 | 2017-09-12 | 河南云保遥感科技有限公司 | A kind of use rechargeable battery surveys setting loss SUAV as power source |
| CN107215472A (en) * | 2017-05-31 | 2017-09-29 | 中国电子科技集团公司第四十八研究所 | Solar energy unmanned plane energy management system |
| CN107248761A (en) * | 2017-06-09 | 2017-10-13 | 东北大学 | A kind of solar energy radio charging device and charging coat |
| CN107745819A (en) * | 2017-09-27 | 2018-03-02 | 重庆科创职业学院 | A kind of fixed-wing solar powered aircraft |
| CN108839570A (en) * | 2018-06-17 | 2018-11-20 | 北京蓝色动力科技有限公司 | Using solar panel and lithium battery group as the small-sized solar unmanned plane of power source |
| 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 |
| CN209870712U (en) * | 2018-11-27 | 2019-12-31 | 北京铂阳顶荣光伏科技有限公司 | Aircraft passenger plane |
| US20200149427A1 (en) * | 2018-11-08 | 2020-05-14 | Rolls-Royce North American Technologies, Inc. | Hybrid propulsion systems |
-
2021
- 2021-03-19 CN CN202110298631.6A patent/CN112793795B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102737849A (en) * | 2011-03-31 | 2012-10-17 | 索尼公司 | Method of producing photoelectric conversion element, photoelectric conversion element and electronic device |
| CN103158875A (en) * | 2011-12-15 | 2013-06-19 | 通用电气公司 | System and method for power distribution |
| CN102774490A (en) * | 2012-04-10 | 2012-11-14 | 北京航空航天大学 | Novel long-endurance solar unmanned aerial vehicle |
| CN103840745A (en) * | 2013-09-13 | 2014-06-04 | 武汉美格科技有限公司 | Solar energy system for unmanned plane to use |
| CN105449822A (en) * | 2015-12-11 | 2016-03-30 | 中国电子科技集团公司第四十八研究所 | Energy system for high-altitude airship and power supply control method |
| CN206485579U (en) * | 2016-12-28 | 2017-09-12 | 河南云保遥感科技有限公司 | A kind of use rechargeable battery surveys setting loss SUAV as power source |
| CN107215472A (en) * | 2017-05-31 | 2017-09-29 | 中国电子科技集团公司第四十八研究所 | Solar energy unmanned plane energy management system |
| CN107248761A (en) * | 2017-06-09 | 2017-10-13 | 东北大学 | A kind of solar energy radio charging device and charging coat |
| CN107745819A (en) * | 2017-09-27 | 2018-03-02 | 重庆科创职业学院 | A kind of fixed-wing solar powered aircraft |
| CN108839570A (en) * | 2018-06-17 | 2018-11-20 | 北京蓝色动力科技有限公司 | Using solar panel and lithium battery group as the small-sized solar unmanned plane of power source |
| US20200149427A1 (en) * | 2018-11-08 | 2020-05-14 | Rolls-Royce North American Technologies, Inc. | Hybrid propulsion systems |
| CN209870712U (en) * | 2018-11-27 | 2019-12-31 | 北京铂阳顶荣光伏科技有限公司 | Aircraft passenger plane |
| 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 |
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|---|---|
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