CN107104496B - Photovoltaic power module for unmanned aerial vehicle - Google Patents
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/345—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering using capacitors as storage or buffering devices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
- H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
- H01L31/04—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof adapted as photovoltaic [PV] conversion devices
- H01L31/042—PV modules or arrays of single PV cells
- H01L31/05—Electrical interconnection means between PV cells inside the PV module, e.g. series connection of PV cells
- H01L31/0504—Electrical interconnection means between PV cells inside the PV module, e.g. series connection of PV cells specially adapted for series or parallel connection of solar cells in a module
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
- H02S40/00—Components or accessories in combination with PV modules, not provided for in groups H02S10/00 - H02S30/00
- H02S40/30—Electrical components
- H02S40/36—Electrical components characterised by special electrical interconnection means between two or more PV modules, e.g. electrical module-to-module connection
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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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
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- Aviation & Aerospace Engineering (AREA)
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Abstract
A photovoltaic power module for an unmanned aerial vehicle comprises N rows and M columns of photovoltaic cell bridge units, wherein two photovoltaic cell bridge units adjacent to each other in each row are connected in series, and two photovoltaic cell bridge units adjacent to each other in each column are connected in series. The photovoltaic power module for the unmanned aerial vehicle can reduce the utilization efficiency of the photovoltaic power due to the existence of shadows in the flight process of the unmanned aerial vehicle.
Description
Technical Field
The invention relates to a photovoltaic power module for an unmanned aerial vehicle, and belongs to the technical field of aircrafts.
Background
Due to the characteristics of low cost, easy use and the like, the small unmanned aerial vehicle is increasingly widely used in the fields of consumption and industry. At present, three types of unmanned aerial vehicles exist at home and abroad, wherein the first type is a fixed wing unmanned aerial vehicle, the second type is a traditional unmanned helicopter, and the third type is an electric multi-shaft unmanned aerial vehicle. The first type of fixed wing unmanned aerial vehicle has high flight efficiency but cannot take off and land vertically, and the use field is limited; the second type of traditional unmanned helicopter can vertically take off and land, but has complex mechanical and power transmission structure, high cost, low safety and high operation difficulty; the third type of electric multi-axis unmanned aerial vehicle is simple to operate, but most of the unmanned aerial vehicle adopts a storage battery to provide energy, and the flight time of the unmanned aerial vehicle is limited, generally about half an hour, due to limited stored electric energy of the storage battery. In order to overcome the above technical problems, in the prior art, it is proposed to use solar energy to supply power to an unmanned aerial vehicle, for example, chinese patent application publication CN104943860 a discloses a photovoltaic six-rotor aircraft, as shown in fig. 1, a solar power supply of the photovoltaic six-rotor aircraft provided in the prior art includes a plurality of electrically parallel responsive solar sub-power supplies: the first solar energy sub power source A1, the second solar energy sub power sources A2 and … and the nth solar energy sub power source An, n are integers which are more than or equal to 2. Each solar subsidiary power supply comprises a plurality of solar grandcells electrically connected in series, i.e. each solar subsidiary power supply comprises a solar grandcell electrically connected in series from the top surface of the aircraft, a solar grandcell from the front of the aircraft, a solar grandcell from the left of the aircraft, a solar grandcell from the right of the aircraft and a solar grandcell from the back of the aircraft. Each solar sub-power supply comprises a series of solar energy Sun Dianyuan with electric series response, a first DC/DC converter 105, a first controller 107, a diode D4 and a diode D3, wherein the positive output end of solar energy Sun Dianyuan is connected to the power input end of the first DC/DC converter 5, and the common end of the solar grandson power supply is connected to the power input common end of the first DC/DC converter 105; the first DC/DC converter 5 converts a series of solar energy Sun Dianyuan with electric series response to a first direct current voltage into a second direct current voltage, and the power output end of the first DC/DC converter 105 is connected to the positive end of the diode D4; the negative electrode end of the diode D4 is connected with the positive electrode end of the diode D3 and is connected with the first wiring terminal Sc, namely the positive electrode output end of the solar power supply; the negative terminal of the diode D3 is connected to the second connection terminal, i.e. the common terminal of the solar power supply, while the negative terminal of the diode D3 is connected to the output common terminal of the first DC/DC converter 105, and the first controller 7 controls the operating state of the first DC/DC converter according to the first direct current voltage. The first controller 107 is preferably a first comparator. Each solar sub-power supply further comprises a first voltage sensor 106 for sampling a first direct voltage, the first comparator 7 controls the operation state of the first DC/DC converter according to the voltage sampled by the first voltage sensor, and when the sampled voltage is smaller than the reference voltage Vrf0, the first DC/DC converter is stopped. The purpose of setting D3 in the invention is to automatically disconnect the solar sub-power supply of the branch when the performance of the sub-power supply is degraded, and the purpose of setting D4 is to prevent other sub-power supplies working normally from providing energy for the sub-power supplies. Each solar grandson power supply comprises a photovoltaic cell unit 101, a second DC/DC converter 104, a second controller 3, a diode D2 and a diode D1, wherein the photovoltaic cell units 101 are connected in series, in parallel or in a series-parallel manner, a positive output end of the photovoltaic cell unit 101 is connected with a power input end of the second DC/DC converter 4, and a common end of the photovoltaic cell unit 101 is connected with a power input common end of the second DC/DC converter 4; the second DC/DC converter 104 converts the third direct current voltage output by the photovoltaic cell unit 1 into a fourth direct current voltage, and the power output end of the second DC/DC converter 104 is connected to the positive end of the diode D2; the negative electrode end of the diode D2 is connected with the positive electrode end of the diode D1 and is connected with a third wiring terminal; the negative terminal of the diode D1 is connected to the fourth connection terminal and simultaneously connected to the output common terminal of the second DC/DC converter 104, and the second controller 103 controls the operating state of the second DC/DC converter 104 according to the third DC voltage. The second controller 103 is preferably a second comparator. Each solar sub-power supply further comprises a second voltage sensor 102 for sampling a third direct voltage, and a second comparator 103 controls the operation state of the second DC/DC converter 104 according to the voltage sampled by the second voltage sensor 2. When the sampled voltage is less than the reference voltage Vrf1, the second DC/DC converter is stopped. The purpose of setting D1 in the present invention is to automatically disconnect Sun Dianyuan of this branch when the photovoltaic cell performance of this branch is degraded, and setting D2 is to prevent Sun Dianyuan of the other branches working properly from providing energy to them. In order to overcome the degradation of power performance caused by shadows during the flight of the unmanned aerial vehicle, the photovoltaic power supply provided in the prior art CN104943860 a adopts a control circuit in the solar sub-power supply and Sun Dianyuan, wherein the control circuit is a circuit composed of a comparator, a converter, a sampler and two diodes, which necessarily increases the manufacturing cost of the unmanned aerial vehicle and the load of the unmanned aerial vehicle.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention aims to provide a photovoltaic power module for an unmanned aerial vehicle, which can reduce the utilization efficiency of the photovoltaic power due to the existence of shadows in the flight process of the unmanned aerial vehicle and has low cost.
To achieve the above object, the present invention provides a photovoltaic power module for an unmanned aerial vehicle, which is characterized in that it includes N rows and M columns of photovoltaic cell bridge units, two photovoltaic cell bridge units adjacent to each other in each row are connected in series, and two photovoltaic cell bridge units adjacent to each other in each column are connected in series.
Preferably, each photovoltaic cell bridge unit comprises a first photovoltaic cell, a second photovoltaic cell, a third photovoltaic cell and a fourth photovoltaic cell, wherein the positive end of the first photovoltaic cell is connected with the positive end of the second photovoltaic cell, the negative end of the first photovoltaic cell is connected with the positive end of the third photovoltaic cell, the negative end of the second photovoltaic cell is connected with the positive end of the fourth photovoltaic cell, and the negative end of the third photovoltaic cell is connected with the wind end of the fourth photovoltaic cell.
Preferably, the first photovoltaic cell is attached to the front of the unmanned aerial vehicle housing, the second photovoltaic cell is attached to the rear of the unmanned aerial vehicle housing, the third photovoltaic cell is attached to the left of the unmanned aerial vehicle housing, and the fourth photovoltaic cell is attached to the right of the unmanned aerial vehicle housing.
Preferably, the unmanned aerial vehicle at least comprises a converter and a super capacitor, wherein the converter is used for converting the voltage of electric energy output by the photovoltaic power module and charging the super capacitor.
Preferably, the super capacitor is utilized to provide energy for a power driver of the unmanned aerial vehicle.
Preferably, the power driver of the unmanned aerial vehicle is a magneto-motive power driver.
Preferably, the magnetomotive force driver at least comprises a stator and a rotor, the rotor is arranged on the periphery of the rotor, the stator is provided with permanent magnets with N polarity and S polarity in a staggered manner, the stator at least comprises a first stator winding and a second stator winding, a third stator winding is arranged on the stator, alternating current is input through the first stator winding, and alternating electric energy is output through the second stator winding; a part of energy output by the second stator winding is converted and applied to the third stator winding, and the rotating speed of the rotor is changed by controlling the phase angle of electric energy applied to the third stator winding relative to the alternating current applied to the first stator winding.
Preferably, the third stator winding is identical to the coil of the first stator winding and is tightly coupled respectively.
Compared with the prior art, the photovoltaic power module for the unmanned aerial vehicle provided by the invention has the advantages that due to the adoption of the bridge type photovoltaic cell connecting structure, the utilization efficiency of the photovoltaic power can be reduced due to the existence of shadows in the flight process of the unmanned aerial vehicle without an additional control circuit, and the cost is low.
Drawings
FIG. 1 is a schematic diagram of the composition of a photovoltaic power module of a photovoltaic six-rotor aircraft provided in the prior art;
FIG. 2 is a schematic illustration of a magnetomotive rotary-wing drone provided by an embodiment of the present invention;
FIG. 3 is a circuit diagram of a photovoltaic power module for a drone provided by one embodiment of the present invention;
fig. 4 is a schematic diagram of a control system of a rotary-wing unmanned aerial vehicle according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of the composition of a magnetomotive force drive provided by an embodiment of the present invention;
FIG. 6 is a control flow diagram of an engine module provided by one embodiment of the present invention;
fig. 7 is a block diagram of a wireless transmitter of a drone according to one embodiment of the present invention;
fig. 8 is a circuit diagram of a radio transmitter high frequency power amplifier provided by one embodiment of the present invention;
fig. 9 is a circuit diagram of a carrier generator of a wireless transmitter according to an embodiment of the present invention.
Detailed Description
Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. The same or corresponding portions in the drawings are denoted by the same reference numerals, and repetitive description thereof will not be given.
Fig. 2 is a schematic diagram of a magnetomotive rotary-wing drone provided by an embodiment of the present invention. As shown in fig. 2, the unmanned aerial vehicle 20 according to an embodiment of the present invention at least includes a casing 21, six rotors 22, a control system disposed in the casing, and a magnetomotive driver controlled by the control system and used for driving the six rotors to rotate, where solar cell films 23 are adhered to the casing 21, and are mainly disposed near the front, rear, left and right sides of the top surface, so that the resistance of the solar cell films to wind during the flight of the unmanned aerial vehicle can be reduced. The solar cell film mainly comprises a window layer and a photovoltaic cell arranged on the window layer, wherein the photovoltaic cell sequentially comprises an n+ emitter layer, a P-type base layer, a back surface field layer and heavily doped P-type and n-type layers, the n+ emitter layer is composed of InGA (Al), and the P-type base layer is composed of InGa (Al); the back surface field layer is used to reduce recombination losses, the back surface field layer driving minority carriers from regions near the base layer interface surface to minimize the effects of recombination losses; the heavily doped p-type and n-type layers form a tunnel diode. The solar cell film may be formed on a surface conforming to a support having a non-planar configuration, and the support may be attached to an upper surface near the top of the drone with an adhesive.
Fig. 3 is a circuit diagram of a photovoltaic power module for a drone according to one embodiment of the present invention, and as shown in fig. 3, the photovoltaic power module for a drone according to one embodiment of the present invention includes N rows and M columns of photovoltaic cell bridge units; two photovoltaic cell bridge units adjacent to each other in each row are connected in series, and two photovoltaic cell bridge units adjacent to each other in each column are connected in series, and further, the photovoltaic cell bridge unit in the 1 st column of each row is connected with the photovoltaic cell bridge unit in the M th column. Each photovoltaic cell bridge unit includes a first photovoltaic cell (e.g., 11A, 12A, 1MA, 21A, 22A, 2MA, N1A, N a, …, NMA), a second photovoltaic cell (e.g., 11B, 12B, 1MB, 21B, 22B, 2MB, N1A, N B, …, NMB), a third photovoltaic cell (e.g., 11C, 12C, 1MC, 21C, 22C, 2MC, N1C, N2C, …, NMC), and a fourth photovoltaic cell (e.g., 11D, 12D, 1MD, 21D, 22D, 2MD, N1D, N D, …, NMD), the positive terminal of the first photovoltaic cell being connected to the positive terminal of the second photovoltaic cell and functioning as a first lead-out terminal for column connection, the negative terminal of the first photovoltaic cell being connected to the positive terminal of the third photovoltaic cell and functioning as a second lead-out terminal for row connection, the negative terminal of the second photovoltaic cell being connected to the positive terminal of the fourth photovoltaic cell and functioning as a second lead-out terminal for column connection. The second leading-out terminals connected with the columns of the two photovoltaic cell bridge units adjacent to each other are connected end to end with the first leading-out terminals connected with the columns, the first leading-out terminals connected with the columns of the first row are connected and provide positive polarity voltage outwards, and the second leading-out terminals connected with the columns of the N row are connected and provide negative polarity voltage outwards; the second leading-out terminals connected with the rows of the two adjacent photovoltaic cell bridge units are connected end to end with the first leading-out terminals connected with the rows, the first leading-out terminals connected with the rows of the 1 st row are connected with the second leading-out terminals connected with the rows of the M th row, so that a three-dimensional power supply structure is formed, if one or more photovoltaic cells are in shadow, the internal resistance of the photovoltaic cell is increased, the external power supply of other photovoltaic cells is not influenced, and the utilization rate of a photovoltaic power supply is improved. According to one embodiment of the invention, the first photovoltaic cell is adhered to the front of the unmanned aerial vehicle housing, the second photovoltaic cell is adhered to the rear of the unmanned aerial vehicle housing, the third photovoltaic cell is adhered to the left of the unmanned aerial vehicle housing, and the fourth photovoltaic cell is adhered to the right of the unmanned aerial vehicle housing, so configured as to balance the outward power supply performance of the photovoltaic cell bridge unit.
Fig. 4 is a schematic diagram of a control system of a rotary-wing unmanned aerial vehicle according to an embodiment of the present invention; as shown in fig. 4, the driver drives the rotor to rotate by using the electric energy stored in the super capacitor, so that the unmanned aerial vehicle flies. In the present invention, the super-capacitor is preferably a fractal capacitor which can be charged by a converter to store electrical energy therein. In the invention, the driver is preferably a magnetomotive driver, the magnetomotive driver at least comprises a stator 5 and a rotor 4, the stator 4 is arranged on the periphery of the rotor 5, the rotor 5 at least comprises permanent magnets with N polarity and S polarity which are arranged in a staggered manner, and the stator at least comprises first stator windings U1, V1 and W1 which are respectively arranged in three winding posts or three wire slots; the stator further comprises at least second stator windings U2, V2 and W2, wherein the second stator windings U2, V2 and W2 are respectively arranged in the other three winding posts or three wire slots, and at least third stator windings U3, V3 and W3 which are respectively arranged in the same three winding posts or three wire slots as the first stator windings. This is described in detail later with reference to fig. 4.
According to one embodiment of the invention, the control system of the unmanned aerial vehicle comprises a second DC/AC converter 15 which converts the electric energy provided by the supercapacitor C1 into a first three-phase alternating current which is applied to the three coils U1, V1 and W1 of the winding of the first stator, respectively, for generating a rotating magnetic field which drives the rotor in rotation, which rotates the rotor of the unmanned aerial vehicle, thereby flying the unmanned aerial vehicle. According to one embodiment of the present invention, the super capacitor C1 is charged by using a first charging module, where the first charging and discharging module includes a DC/DC converter 1, and two power input terminals of the DC/DC converter 1 are respectively connected to two ends of the super capacitor C1, so as to charge the super capacitor C1. In one embodiment of the invention, the solar cell film is adhered to the shell of the unmanned aerial vehicle, so that the solar cell film converts solar energy into electric energy, and the DC/DC converter stores the electric energy converted by the solar energy in the super capacitor C1 in the flying process of the unmanned aerial vehicle, so that the consumption of the energy of the super capacitor C1 is supplemented, and the endurance time of the unmanned aerial vehicle is prolonged.
The unmanned aerial vehicle control system further comprises an MPPT control module, the MPPT control module adjusts the power of the charger according to sampling values of output voltage and output current of the photovoltaic battery, and when the ambient temperature and the light intensity change, the solar battery is always in a maximum power output state, so that the service efficiency of the solar battery is improved. As shown in fig. 3, the resistors R1 and R2 are connected in series and then connected in parallel to two ends of the photovoltaic cell, and the middle node is used for taking out the sampling voltage of the photovoltaic voltage; the negative pole of photovoltaic cell is grounded through resistance R7, and R7 is current sampling resistance, and MPPT control module provides control signal for DC/DC converter 1 according to the value of sampling voltage and sampling current.
The control system of the drone further comprises a rectifier 10, the rotating magnetic field generated by the rotating rotor generating induced currents in the three coils U2, V2 and W2 of the second stator winding. The rectifier 10 is used for rectifying and filtering the current output by the second stator windings U2, V2 and W2 to generate a direct current voltage. The control system of the unmanned aerial vehicle further comprises a second DC/AC converter 12 for converting the direct voltage output by the rectifier 10 into a second three-phase alternating current and applying it to the three coils U3, V3 and W3 of a third stator winding, which is the same in number as the coils of the first stator winding and is usually arranged in the same winding post or wire slot. So configured, the efficiency of the battery is improved. Preferably, a DC/DC converter 11 and a super capacitor C2 are further disposed between the rectifier 10 and the DC/AC converter 12, the DC power output from the rectifier 10 is stored in the super capacitor C2 through the DC/DC converter 11, and the DC/AC converter 12 converts the power provided by the super capacitor C2 into a second three-phase AC power. Because the stator comprises the second stator winding, the rotor rotates in the flying process of the unmanned aerial vehicle, so that induced voltages are generated in the second stator windings U2, V2 and W2, the induced voltages are rectified and converted into direct current through the rectifier, the direct current electric energy is stored in the super capacitor C2 by the DC/DC converter 11, the electric energy provided by the super capacitor C2 is converted into alternating current with the same frequency as the first three-phase alternating current, and a rotating magnetic field is generated, so that the rotor is further driven to rotate, and the energy sources of the first battery pack and the second battery pack are saved.
The control system of the unmanned aerial vehicle according to an embodiment of the present invention further comprises an engine control module, a first sampling circuit 16 and a second sampling circuit 13, wherein the first sampling circuit is used for sampling the voltage and the current of each phase of the first three-phase alternating current outputted by the DC/AC converter 15, the second sampling circuit is used for sampling the voltage and the current of each phase of the second three-phase alternating current outputted by the DC/AC converter 12, and the engine control module controls the second DC/AC converter 15 and the DC/AC converter 12 according to the sampled values of the voltage and the current respectively. In one embodiment of the present invention, the three-phase alternating currents output from the DC/AC converter 15 and the DC/AC converter 12 may be controlled such that each of them is in phase with the same frequency, thus further saving the electric power of the animal cell. The operation thereof is described in detail later with reference to fig. 6.
In one embodiment provided by the invention, in the case of breeze, the breeze drives the rotor of the unmanned aerial vehicle to rotate, and the rotor drives the rotor to rotate, preferably induction electric energy is generated in the second stator winding, and the electric energy is additionally stored in the super capacitor C2. Under the condition of light, the photovoltaic energy is stored in the super capacitor C1, so that the capacity of the super capacitor carried by the unmanned aerial vehicle is not required to be too large, the load of the unmanned aerial vehicle is reduced, and the endurance time of the unmanned aerial vehicle is further prolonged.
The magnetomotive force driver of the rotor unmanned aerial vehicle further comprises a local controller, wherein the local controller comprises a man-machine interface and a communication control interface, and the man-machine interface is used for connecting keys and a display; the communication control interface is used for connecting with a local personal computer and/or a network.
Fig. 5 is a schematic diagram of the magnetomotive force driver provided by the present invention, as shown in fig. 5, the rotor 5 includes a rotor magnet holder 18 and permanent magnets with N-polarity and S-polarity alternately arranged. The magnet holder is made of a non-magnetic material. The material of the magnet holder is not particularly limited as long as it is a non-magnetic material. In one embodiment, the magnet holder is formed of a non-magnetic metal (e.g., aluminum, titanium alloy, etc.). If the temperature of the permanent magnet is too high, the permanent magnet may be demagnetized. That is, the magnetic force of the permanent magnet may be weakened. By forming the magnet holder using a nonmagnetic metal, the heat generated by the permanent magnet can be efficiently released to the outside, and thus the possibility of such a problem can be reduced. In another embodiment, the magnet holder is formed of a resin material. By forming the magnet holder from a resin material, the weight of the magnet holder can be reduced. Further, the advantage of easy molding of the magnet holder can be obtained.
Rare earth magnets are preferably used as the permanent magnets. Generally, rare earth magnets have stronger magnetic forces than ferrite magnets of the same size. As the rare earth magnet, for example, a samarium cobalt magnet or a neodymium magnet can be used. Neodymium magnets are particularly preferred in embodiments of the present invention. Compared with samarium cobalt magnets, neodymium magnets have stronger magnetic force at the same size. Thus, for example, a small permanent magnet can be used. The use of neodymium magnets can increase the output of the energy conversion device (allow for greater energy extraction) than would be possible if the same size samarium cobalt magnets were used. However, the embodiment of the present invention does not exclude permanent magnets other than rare earth magnets. It is of course also possible to use ferrite magnets for the permanent magnets.
The stator includes at least a coil holder formed in a ring shape, and at least six winding posts or slots are uniformly provided along a radial direction thereof. The stator further comprises at least a first stator winding, wherein three coils U1, V1 and W1 of the first stator winding are respectively arranged in three winding posts or three wire slots; the stator winding is provided with a second stator winding, three coils U2, V2 and W2 of the second stator winding are respectively arranged in another three winding posts or three wire slots, three wire posts or wire slots of the three coils U1, V1 and W1 of the first stator winding are staggered with the three wire posts or wire slots of the three coils U2, V2 and W2 of the second stator winding and are separated by equal intervals, the stator winding is provided with a third stator winding, and the three coils U3, V3 and W3 of the third stator winding are respectively arranged with the three coils U1, V1 and W1 of the first stator winding in the same post or same slot, so that the three coils of the first stator winding and the three coils of the third stator winding are respectively tightly coupled.
FIG. 6 is a control flow diagram of an engine module provided by the present disclosure; as shown in fig. 6, the control process of the wind turbine module is as follows:
step 1: detecting a current signal and a voltage signal of each phase of the first three-phase alternating current outputted from the DC/AC converter 15 sampled by the first sampling circuit; detecting a current signal and a voltage signal of each phase of the second three-phase alternating current outputted from the DC/AC converter 12 sampled by the second sampling circuit;
step 2: judging that if the phases of the current and voltage signals of each phase of the first three-phase alternating current and each phase of the second three-phase alternating current respectively reach the phase angles appointed by the local controller, executing the step 3; otherwise, executing the step 4;
step 3: the three-phase alternating current output by the DC/AC converter 12 is respectively connected to the third stator windings;
step 4: a control signal is sent to the DC/AC converter 15 and the DC/AC converter 12 to adjust the current signal and the voltage signal of each phase of the first three-phase alternating current outputted from the DC/AC converter 15 and the current signal and the voltage signal of each phase of the second three-phase alternating current outputted from the DC/AC converter 12, respectively, and then step 1 is returned.
The engine module of the engine at least comprises a processor and a memory, wherein the control flow of the engine module can be programmed into a computer program and stored in the memory, and the processor can call the stored program of the memory and execute the stored program. The storage program may be stored in other storage media and transmitted over a data network.
The magnetomotive force actuator according to the embodiment of the present invention is configured to be capable of converting one of electric energy (electric power) and mechanical energy (kinetic energy) into the other. In one embodiment, the magnetomotive force drive acts as a generator. At this time, the kinetic energy of the rotor rotation is imparted to the magnetomotive force driver due to the rotation of the rotor of the unmanned aerial vehicle. The second stator coil generates a voltage. Magnetomotive force drives convert mechanical energy into electrical energy.
In another embodiment, a magnetomotive force drive is used as the motor. The first stator coil and the third stator coil are supplied with electric energy and are arranged at a predetermined electric angle. The polarity of the voltage applied to each of the first stator and/or the third stator coil is switched in synchronization with the electrical angle. Thereby, the rotor rotates. That is, the magnetomotive force driver converts electrical energy into mechanical energy.
The present invention has been described with respect to three coils of the first stator winding, the second stator winding, and the third stator winding, but the present invention is not limited to three coils, and one or more coils may be used.
According to one embodiment of the invention, the unmanned aerial vehicle control system further comprises a wireless transmitter, through which the present controller 9 communicates with a ground control station. The wireless transmitter provided by the present invention is described in detail below with reference to fig. 7-9.
Fig. 7 is a block diagram showing a wireless transmitter of a drone according to an embodiment of the present invention, wherein the wireless transmitter includes a modulator 400, a carrier generator 600, a high frequency power amplifier 500 and a power amplification source, the modulator 400 is used for modulating a signal provided by a local controller 9 to a carrier generated by an oscillator to generate a modulated wave, the high frequency power amplification circuit 500 is used for amplifying the power of the modulated wave generated by the modulator, and the wireless transmitter includes a delay 300, and the delay 300 is used for delaying a modulated signal generated by the modulated signal generator and then providing the delayed signal to the modulator 400; the power amplifier source comprises: the amplitude detector 200 is used for extracting the amplitude of the modulation signal generated by the modulation signal generator and providing the amplitude to the processor 700, the processor 700 controls the output voltage of the variable power supply 800 according to the amplitude to supply the high-frequency power amplifier 500, and the processor 700 and the variable power supply 800.
The variable power supply 800 includes n-stage dc voltage units, each of which is cascade-connected, each of which includes a battery pack, such as E1, E2, and En, a flywheel diode, such as D1, D2, and Dn, and an electronic switch, such as T1, T2, and Tn, the positive electrode of the battery pack being connected to the negative electrode of the flywheel diode; the positive pole of freewheel diode is connected to the first end of electronic switch, and the second end of electronic switch is connected to the negative pole of group battery, and electronic switch's control end is connected to the treater, and the break-make of electronic switch is controlled to the signal that the treater provided according to the range detector, n is more than or equal to 2 integer.
More specifically, the first dc voltage unit includes a battery E1, a freewheeling diode D81, and an electronic switch T1, which is a CMOS tube, where the anode of the battery E1 is connected to the cathode of the freewheeling diode D81; the positive electrode of the freewheeling diode D81 is connected to the drain electrode of the CMOS tube T1, the source electrode of the CMOS tube T1 is connected to the negative electrode of the battery pack E1, the grid electrode of the CMOS tube T1 is connected to one output end of the processor 700, and the processor 700 controls the on-off state of the CMOS tube T1. The CMOS transistor T1 is operated in a switching state, and when a high potential is input to the gate of the CMOS transistor T1, the CMOS transistor T1 is turned on, and the negative electrode of the battery E1 is equivalent to the positive electrode of the flywheel diode D81. The voltage across the freewheeling diode D1 is positive at the upper end and negative at the lower end. When a low potential is input to the gate of the CMOS transistor T1, the CMOS transistor T1 is turned off. The voltage across the freewheeling diode D81 is the diode junction voltage.
The second direct-current voltage unit comprises a battery E2, a freewheeling diode D82 and an electronic switch T2, wherein the electronic switch is a CMOS (complementary metal oxide semiconductor) tube, and the anode of the battery E2 is connected with the cathode of the freewheeling diode D2; the positive electrode of the freewheeling diode D82 is connected to the drain electrode of the CMOS tube T2, the source electrode of the CMOS tube T2 is connected to the negative electrode of the battery E2, the gate electrode of the CMOS tube T2 is connected to an output terminal of the processor 700, and the processor 700 controls the on-off state of the CMOS tube T2. The CMOS transistor T2 is operated in a switching state, and when a high potential is input to the gate of the CMOS transistor T2, the CMOS transistor T2 is turned on, and the negative electrode of the battery E2 is equivalent to the positive electrode of the freewheeling diode D2. The voltage across the freewheeling diode D82 is positive at the upper end and negative at the lower end. When the gate of the CMOS transistor T2 inputs a low potential, the CMOS transistor T2 is turned off. The voltage across freewheeling diode D82 is the diode junction voltage.
By analogy, the nth direct-current voltage unit comprises a battery pack En, a freewheeling diode D8n and an electronic switch Tn, wherein the electronic switch is a CMOS tube, and the anode of the battery pack En is connected with the cathode of the freewheeling diode Dn; the positive pole of the freewheel diode Dn is connected to the drain electrode of the CMOS tube Tn, the source electrode of the CMOS tube Tn is connected to the negative pole of the battery pack En, the grid electrode of the CMOS tube Tn is connected to one output end of the processor 700, and the processor 700 controls the on-off state of the CMOS tube Tn. The CMOS tube Tn is operated in a switching state, when a high potential is input to the grid electrode of the CMOS tube Tn, the CMOS tube Tn is conducted, and the cathode of the battery pack En is equivalent to the anode connected to the flywheel diode D8 n. The voltage across the freewheeling diode Dn is positive at the upper end and negative at the lower end. When the gate of the CMOS transistor Tn inputs a low potential, the CMOS transistor Tn is turned off. The voltage across the freewheeling diode D8n is the diode junction voltage.
Thus, if the electronic switches of each dc voltage unit are turned on simultaneously, the total output total voltage of the dc modulated power supply is Vcc 1=e1+e2+ … +en. The output voltage values of the direct-current voltage units are the same.
In the present invention, the processor 700 controls the on-off of each electronic switch according to the signal provided by the amplitude detector, when the amplitude is large, the plurality of electronic switches are turned on, and a high power supply is provided for the power amplifier, and when the amplitude is small, the plurality of electronic switches are turned on, and a small common power supply is provided for the power amplifier. So long as the sum of the output power supplies of the respective ones is made slightly larger than the detected amplitude value, the power amplification source is configured so that the power source is greatly saved, thereby making the stand-by time of the wireless transmitter having such configuration circuit, which may be the transmitting portion of the handset, longer.
Fig. 8 is a circuit diagram of a radio transmitter high frequency power amplifier according to an embodiment of the present invention, and as shown IN fig. 8, the high frequency power amplifier according to the present invention includes a high frequency signal input terminal IN, an input matching network 520, a high frequency amplifier 510, an output matching network 530, a high frequency signal output terminal OUT, and a bias circuit 540, wherein the high frequency amplifier 510 includes: a transistor T501 and a high frequency choke L2, the bias circuit 540 being connected to the base of the transistor T501 and being adapted to provide a bias current to the base of the transistor T501 in accordance with a control voltage Vcon 1; the emitter of the transistor T501 is grounded, and the collector is connected to the power supply Vcc1 via the high-frequency choke coil L2 and also to the output matching network 530. Preferably, power supply Vcc1 is also grounded through filter capacitor C3.
The bias circuit 540 for providing a bias voltage to the transistor T501 according to a reference voltage includes a transistor T11, the collector of the transistor T11 is connected to the power supply Vcc1, and the emitter is connected to the base of the transistor T501 via a resistor R11 and a high frequency choke L11 in sequence. The reference voltage is provided by a power supply circuit 550 for controlling the bias of the transistor T501, the power supply circuit 550 comprises a resistor R14, a transistor T12 and a transistor T13, and the transistor T5012 is connected in a diode structure, i.e. the collector and the base of the transistor T12 are connected in a short circuit; the transistor T13 is connected in a diode configuration, i.e. the collector and base of the transistor T13 are short-circuited. The resistor R14 has a first terminal connected to the control voltage Vcon1, a second terminal connected to the base of the transistor T12, and the transistors T12 and T13 are connected in series and between the resistor R14 and the overshoot control circuit. The control signal Vcon1 is used to control the start and stop of the bias circuit 540. In the power supply circuit 550, the resistor R14 and the transistors T12 and T13 are provided so that the modulation accuracy is reduced due to temperature shift when the temperature is changed, and the above components function as temperature compensation. In the present invention, the node where the resistor R11 and the high-frequency choke coil L11 are connected in series is also grounded via the bypass capacitor C12.
During the rise of the control voltage Vcon1, the acceleration circuit serves to temporarily increase the reference voltage output from the power supply circuit 550, thereby increasing the amount of increase in the transistor T501 by the bias circuit 540. The accelerating circuit comprises a capacitor C11, a time constant control circuit, a discharging circuit and an overshoot control circuit, wherein a first end of the capacitor C11 is connected with the control voltage Vcon1, a second end of the capacitor C11 is connected with the time constant control circuit, and the discharging circuit is connected with the capacitor C11 in parallel. The discharge circuit includes a transistor T16 having a gate connected to ground, a source connected to the base of the transistor T14, and a drain connected to the control voltage Vcon1. The time constant control circuit comprises a transistor T14, a resistor R12 and a transistor T15, wherein the base electrode of the transistor T14 is connected with the second end of the capacitor C11, the collector electrode is connected with the voltage Vcc1, and the emitter electrode is connected with the end of the resistor R12; a second end of the resistor R12 is connected to the base electrode of the transistor T5015; the transistor T15 has a collector connected to the voltage Vcon1 and an emitter connected to ground through the resistor R13. The time constant control circuit is used to determine the time constant for charging and discharging the capacitor C11. The overshoot circuit is used to determine the amount of the reference voltage output from the power supply circuit 550, and the reference voltage is temporarily increased according to the discharge amount of the capacitor C11. For example, the overshoot circuit may be a circuit including only a resistor R13, the resistor R13 having a first terminal connected to ground and a second terminal connected to the power supply circuit 110.
IN the high frequency power amplifier shown IN fig. 8, a high frequency signal is input from an input terminal IN, then impedance-matched via an input matching network 520 to a base of a common-emitter amplifier including a transistor T501, output from a collector of the transistor T501 via power amplification, and then impedance-matched to an antenna (not shown IN fig. 1) via an output matching network 530 to an output terminal OUT.
During the rise of the control voltage Vcon1, the capacitor C11 is charged, and a charging current flows from the base to the emitter of the transistor T14, the resistor R12, and the base to the emitter of the transistor T15, and flows into the resistor R13 in this order. The temporary rise of the base potential of the bias transistor T11 causes the base bias of the amplifying transistor T501 to rise, thereby causing the gain of the transistor T501 to rise temporarily. During the falling of the control voltage Vcon1, the charge on the capacitor C11 is discharged by the transistor T16. In the invention, the accelerating circuit is configured, so that the reduction of the modulation precision caused by the heat generated by the amplifier is further restrained.
Fig. 9 is a circuit diagram of a carrier generator of a wireless transmitter according to an embodiment of the present invention, and as shown in fig. 9, the carrier generator provided in the present invention includes: the source electrode of the field effect transistor T601 is grounded, the drain electrode is connected with the first end of the inductor L601 and the positive electrode end of the varactor diode D601, and the grid electrode is connected with the second end of the inductor L601; the source electrode of the field effect transistor T602 is grounded, the drain electrode is connected with the second end of the inductor L601 and the positive electrode end of the varactor D602, and the grid electrode is connected with the first end of the inductor L601; the negative terminal of the varactor diode D602 is connected to the negative terminal of the varactor diode D601 and to the control voltage ctrl, which is used to control the capacitance of the two varactors and thus the operating frequency. The source electrode of the field effect transistor T603 is grounded, the drain electrode is connected with the first end of the inductor L602 and the positive electrode end of the varactor D603, and the grid electrode is connected with the second end of the inductor L602; the source electrode of the field effect transistor T604 is grounded, the drain electrode is connected with the second end of the inductor L602 and the positive electrode end of the varactor D604, and the grid electrode is connected with the first end of the inductor L602; the negative terminal of the varactor diode D603 is connected to the negative terminal of the varactor diode D604 and to a control voltage ctrl, which is used to control the capacitance of the two varactors and thus the operating frequency. A capacitor C601 is connected between the first end of an inductor L603 coupled with the inductor L601 and the first end of an inductor L604 coupled with the inductor L602, and the capacitor C601 is coupled; a capacitor C602 is connected between the second end of the inductor L603 and the second end of the inductor L604, and the capacitor C602 is coupled; the middle tap of the inductor L601 and the middle tap of the inductor L602 are connected to a current source S601; the center tap N1 of the inductor L603 and the center tap N2 of the inductor L604 are connected to ground. When the current in the current source flows into the inductor L601, an oscillation signal S1 is generated, the inductor L601 is coupled with the inductor L603, so as to generate an oscillation signal S2 with a phase difference of 90 degrees with the oscillation signal S1, the oscillation signal S2 is coupled with the capacitor C601 and the capacitor C602, an oscillation signal S3 with a phase difference of 90 degrees with the oscillation signal S2 is generated on the inductor L604, the inductor L604 is coupled with the inductor L602, and an oscillation signal S4 with a phase difference of 90 degrees with the oscillation signal S3 is generated on the inductor L602. The voltage-controlled oscillator (VCO) provided by the invention can generate I, Q signals which are mutually orthogonal, so that the signals generated by the local controller 9 can be subjected to orthogonal modulation after being delayed.
In the invention, as the three-dimensional structure of the photovoltaic cell bridge unit is adopted, the cost is saved, and the load of the unmanned aerial vehicle is reduced; the use of the magnetomotive force driver improves the utilization efficiency of the power supply. Thus, the flight time of the unmanned aerial vehicle is greatly prolonged.
The foregoing description of the principles of the invention has been presented in detail with reference to the drawings, but the description is only illustrative of the invention. The description is only intended to explain the claims. The scope of the invention is not limited by the description. Any changes or substitutions that would be readily apparent to one skilled in the art within the scope of the present disclosure are intended to be encompassed within the scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.
Claims (7)
1. A photovoltaic power module for an unmanned aerial vehicle, comprising N rows and M columns of photovoltaic cell bridge units; two photovoltaic cell bridge units adjacent to each other in each row are connected in series, and two photovoltaic cell bridge units adjacent to each other in each column are connected in series;
each photovoltaic cell bridge unit comprises a first photovoltaic cell, a second photovoltaic cell, a third photovoltaic cell and a fourth photovoltaic cell, wherein the positive end of the first photovoltaic cell is connected with the positive end of the second photovoltaic cell, the negative end of the first photovoltaic cell is connected with the positive end of the third photovoltaic cell, the negative end of the second photovoltaic cell is connected with the positive end of the fourth photovoltaic cell, and the negative end of the third photovoltaic cell is connected with the negative end of the fourth photovoltaic cell.
2. The photovoltaic power module for an unmanned aerial vehicle of claim 1, wherein the first photovoltaic cell is attached to the front of the unmanned aerial vehicle housing, the second photovoltaic cell is attached to the rear of the unmanned aerial vehicle housing, the third photovoltaic cell is attached to the left of the unmanned aerial vehicle housing, and the fourth photovoltaic cell is attached to the right of the unmanned aerial vehicle housing.
3. The photovoltaic power module for a drone of claim 2, wherein the drone includes at least one super capacitor, and the converter is configured to convert the voltage of the electrical energy output by the photovoltaic power module and charge the super capacitor.
4. A photovoltaic power module for an unmanned aerial vehicle according to claim 3, wherein the power driver of the unmanned aerial vehicle is powered by a super capacitor.
5. The photovoltaic power module for an unmanned aerial vehicle of claim 4, wherein the power driver of the unmanned aerial vehicle is a magneto-dynamic driver.
6. The photovoltaic power module for a unmanned aerial vehicle of claim 5, wherein the magnetomotive force driver comprises at least one stator and one rotor, the rotating stator is arranged on the periphery of the rotor, the stators are alternately provided with permanent magnets with N polarity and S polarity, the stators comprise at least a first stator winding, a second stator winding and a third stator winding, alternating current is input through the first stator winding, and alternating electric energy is output through the second stator winding; a part of energy output by the second stator winding is converted and applied to the third stator winding, and the rotating speed of the rotor is changed by controlling the phase angle of electric energy applied to the third stator winding relative to the alternating current applied to the first stator winding.
7. The photovoltaic power module for a drone of claim 6, wherein the third stator winding is identical to the coils of the first stator winding and are respectively tightly coupled.
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| CN204144967U (en) * | 2014-09-16 | 2015-02-04 | 安徽理工大学 | Based on the large-sized photovoltaic grid-connected system of MMC |
| CN204886933U (en) * | 2015-07-13 | 2015-12-16 | 国鹰航空科技有限公司 | Unmanned aerial vehicle photovoltaic modulation power source transmitter |
| CN105429177A (en) * | 2015-12-16 | 2016-03-23 | 国网青海省电力公司 | Modularized photovoltaic energy storage system |
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