CN103326479B - Wireless power supply system between aircrafts based on inductive coupling way and power supply method - Google Patents
Wireless power supply system between aircrafts based on inductive coupling way and power supply method Download PDFInfo
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- CN103326479B CN103326479B CN201310293587.5A CN201310293587A CN103326479B CN 103326479 B CN103326479 B CN 103326479B CN 201310293587 A CN201310293587 A CN 201310293587A CN 103326479 B CN103326479 B CN 103326479B
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- 230000001939 inductive effect Effects 0.000 title abstract 3
- 230000005540 biological transmission Effects 0.000 claims abstract description 76
- 238000012545 processing Methods 0.000 claims abstract description 56
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Classifications
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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
- H02J50/00—Circuit arrangements or systems for wireless supply or distribution of electric power
- H02J50/90—Circuit arrangements or systems for wireless supply or distribution of electric power involving detection or optimisation of position, e.g. alignment
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/30—Supply or distribution of electrical power
- B64U50/34—In-flight charging
- B64U50/35—In-flight charging by wireless transmission, e.g. by induction
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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
- H02J50/00—Circuit arrangements or systems for wireless supply or distribution of electric power
- H02J50/10—Circuit arrangements or systems for wireless supply or distribution of electric power using inductive coupling
- H02J50/12—Circuit arrangements or systems for wireless supply or distribution of electric power using inductive coupling of the resonant type
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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
- H02J50/00—Circuit arrangements or systems for wireless supply or distribution of electric power
- H02J50/80—Circuit arrangements or systems for wireless supply or distribution of electric power involving the exchange of data, concerning supply or distribution of electric power, between transmitting devices and receiving devices
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- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention discloses a wireless power supply system between aircrafts based on an inductive coupling way and a power supply method. The power supply system between aircrafts based on the inductive coupling way comprises an energy transmission module, an automatic positioning module and a core processing module, wherein the energy transmission module comprises an energy output end on a first aircraft and an energy receiving end on a second aircraft; the automatic positioning module is used for receiving flying statuses and spatial position signals of the first aircraft and the second aircraft detected by a sensor and for outputting alignment information to the core processing module; the core processing module outputs an alignment command to the energy output end and the energy receiving end, so that the energy output end and the energy receiving end are aligned; the energy output end is used for outputting energy to the energy receiving end. The wireless power supply system can rapidly acquire information on an accurate distance between the first aircraft and the second aircraft through the automatic positioning module, and can acquire energy in a way of wireless energy transmission, so as to conveniently and effectively supply the energy to a flying object.
Description
Technical field
The present invention relates to IPT (Inductively Power Transfer, induction electric energy transmit) technology, be specifically related to wireless power supply system and method for supplying power between a kind of aircraft based on inductively mode.
Background technology
IPT technology is based on faraday electromagnetic induction principle, utilizes high-frequency alternating magnetic field to realize the power supply technique of electric energy a kind of new type of safe of wireless transmission between the power-supply system and removable load of complete electrical insulation.This technology is widely used in electric automobile, the fields such as power consumption equipment, biologic medical, household electrical appliances and mobile electronic device that rotate.
Along with the fast development of economy and the quick emergence of military power, mobile status charging technique is carried out to flexible object and seems further important, how convenient, efficiently for flyer supply energy be the technical problem needing solution badly.
Summary of the invention
In order to overcome the defect existed in above-mentioned prior art, the object of this invention is to provide wireless power supply system and method for supplying power between a kind of aircraft based on inductively mode, the energy supplement to aircraft can be realized.
In order to realize above-mentioned purpose of the present invention, according to a first aspect of the invention, the invention provides wireless power supply system between a kind of aircraft based on inductively mode, it comprises Energy Transfer module, automatic positioning die block and core processing module, described Energy Transfer module is connected with core processing module, and described Energy Transfer module comprises the Energy transmission end being positioned at the first aircraft and the energy acceptance end being positioned at the second aircraft, described automatic positioning die block is connected with core processing module, described automatic positioning die block is for the first aircraft of receiving navigation system and detecting and the state of flight of the second aircraft, locus signal, described automatic positioning die block is to the state of flight of the first aircraft and the second aircraft, locus controls, and export alignment information to described core processing module, described core processing module exports alignment command to the Energy transmission end of the first aircraft with the energy acceptance end being positioned at the second aircraft, the Energy transmission end making the first aircraft and the energy acceptance end being positioned at the second aircraft are aimed at, and export alignment information to described Energy Transfer module, described Energy Transfer module receives the alignment information of core processing module, and the Energy transmission end of described first aircraft exports energy to the energy acceptance end of the second aircraft.
Between the aircraft based on inductively mode of the present invention, wireless power supply system can obtain the accurate distance information of the first aircraft and the second aircraft rapidly by automatic positioning die block, obtain energy in the mode of wireless energy transfer, can more convenient, efficiently give flyer supply energy.
In one preferred embodiment of the invention, described Energy Transfer module comprises the Energy transmission end being positioned at the first aircraft and the energy acceptance end being positioned at the second aircraft; Described Energy transmission end comprises rectifying and wave-filtering power factor correction module, high-frequency inversion module and former limit winding, the input of described rectifying and wave-filtering power factor correction module is connected with mains supply end, be transferred to high-frequency inversion module after the current processing that electrical network inputs by described rectifying and wave-filtering power factor correction module, the output of high-frequency inversion module is connected with former limit winding; Described energy acceptance end comprises vice-side winding, rectifying and wave-filtering power conditioning module, and described vice-side winding receives the energy that former limit winding exports, after the process of rectifying and wave-filtering power conditioning module, be transferred to power consumption equipment; Described Energy transmission end also comprises the first wireless communication module, described energy acceptance end comprises the second wireless communication module, the electricity that power consumption equipment needs by described second wireless communication module and need time tranfer to the first wireless communication module, described first wireless communication module controls to work in the winding of former limit the quantity of sub-winding and turn-on time, realizes the transmission of corresponding energy.
Energy Transfer module of the present invention can judge the energy of Energy Transfer opportunity and needs, energy savings, effectively achieves the unlimited high efficiency of transmission of energy.
In the preferred embodiment of the present invention, the former limit winding of described Energy transmission end comprise sub-winding L p1, Lp2 ..., Lpk ..., Lpn, described n is the sub-winding quantity of former limit winding, described n be greater than 1 positive integer, described k=1,2 ..., n, described sub-winding L pk is connected with switch S k, and described switch S k is connected with core processing module, controls break-make by described core processing module.
In another kind of preferred implementation of the present invention, the vice-side winding of described energy acceptance end comprise sub-winding L s1, Ls2 ..., Lsp ..., Lsm, described m is the sub-winding quantity of former limit winding, described m be greater than 1 positive integer, described p=1,2 ..., m, described sub-winding L sp is connected with switch S p, and described switch S p is connected with core processing module, controls break-make by described core processing module.
The former limit winding of Energy transmission end of the present invention and the vice-side winding of energy acceptance end include multiple sub-winding, can adjust the output energy of former limit winding and the received energy of vice-side winding, regulate the size of transmitting energy.
In the preferred embodiment of the present invention, described first aircraft and the second aircraft all have energy transmitting terminal and energy acceptance end, when needs export energy, and described energy transmitting terminal place in circuit, when needs received energy, described energy acceptance end place in circuit.First aircraft and the second aircraft can either accept energy also can emitted energy, and system utilization is more various.
In the preferred embodiment of the present invention, described automatic positioning die block comprises transducer group and controller, described transducer group is for detecting the state of flight of the first aircraft and the second aircraft, spatial positional information by described information transmission to described controller, described controller controls the state of flight of the first aircraft and the second aircraft, locus, the Energy transmission end making the first aircraft and the energy acceptance end being positioned at the second aircraft are aimed at, and export alignment information to described core processing module.
Automatic positioning die block of the present invention can control the relative position of the first aircraft and the second aircraft, when the Energy transmission end of the first aircraft and the energy acceptance end that is positioned at the second aircraft are aimed at, the Energy transmission end of the first aircraft exports energy to the energy acceptance end of the second aircraft.
In order to realize above-mentioned purpose of the present invention, according to a first aspect of the invention, the invention provides a kind of wireless power method between aircraft based on inductively mode, it comprises the steps:
S1: build wireless power supply system between the aircraft based on inductively mode of the present invention;
S2: described automatic positioning die block receives the first aircraft of navigation system detection and state of flight, the locus signal of the second aircraft, and give described core processing module by described state of flight, locus Signal transmissions, described core processing module controls the state of flight of the first aircraft and the second aircraft, locus, the Energy transmission end making the first aircraft and the energy acceptance end being positioned at the second aircraft are aimed at, and export alignment information to described Energy Transfer module;
S3: Energy Transfer module receives the alignment information of core processing module, the Energy transmission end of described first aircraft exports energy to the energy acceptance end of the second aircraft.
Between the aircraft based on inductively mode of the present invention, wireless power method obtains the accurate distance information of the first aircraft and the second aircraft rapidly by automatic positioning die block, Energy Transfer module with the mode transmitting energy of wireless energy transfer, can more convenient, efficiently give flyer supply energy.
In one preferred embodiment of the invention, when the first aircraft energy acceptance end from Energy transmission end to the second aircraft export energy time, described second wireless communication module needs to work in the number control vice-side winding of electricity according to power consumption equipment the quantity of sub-winding, simultaneously the charge transport that needed by power consumption equipment of described second wireless communication module is to the first wireless communication module, described first wireless communication module controls to work in the winding of former limit the quantity of sub-winding, realizes the transmission of corresponding energy.The accurate transmission of energy demand can be realized, avoid the generation of wasting.
Additional aspect of the present invention and advantage will part provide in the following description, and part will become obvious from the following description, or be recognized by practice of the present invention.
Accompanying drawing explanation
Above-mentioned and/or additional aspect of the present invention and advantage will become obvious and easy understand from accompanying drawing below combining to the description of embodiment, wherein:
Fig. 1 be the inductively mode that the present invention is based on aircraft between the structural representation of wireless power supply system;
Fig. 2 is the structure chart of Energy Transfer module in a kind of preferred implementation of the present invention;
Fig. 3 is the circuit diagram of Energy transmission end and energy acceptance end in a kind of preferred implementation of the present invention;
Fig. 4 is the schematic diagram that in a kind of preferred implementation of the present invention, Energy transmission end and energy acceptance end carry out Energy Transfer;
Fig. 5 is the ON-OFF control circuit of Energy transmission end and energy acceptance end in a kind of preferred implementation of the present invention;
Fig. 6 is the structural representation of automatic positioning die block in a kind of preferred implementation of the present invention.
Embodiment
Be described below in detail embodiments of the invention, the example of described embodiment is shown in the drawings, and wherein same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Being exemplary below by the embodiment be described with reference to the drawings, only for explaining the present invention, and can not limitation of the present invention being interpreted as.
In describing the invention, unless otherwise prescribed and limit, it should be noted that, term " installation ", " being connected ", " connection " should be interpreted broadly, such as, can be mechanical connection or electrical connection, also can be the connection of two element internals, can be directly be connected, also indirectly can be connected by intermediary, for the ordinary skill in the art, the concrete meaning of above-mentioned term can be understood as the case may be.
The invention provides wireless power supply system between a kind of aircraft based on inductively mode, as shown in Figure 1, it comprises Energy Transfer module, automatic positioning die block and core processing module.Wherein, Energy Transfer module is connected with core processing module, and Energy Transfer module comprises the Energy transmission end being positioned at the first aircraft and the energy acceptance end being positioned at the second aircraft.Automatic positioning die block is connected with core processing module, automatic positioning die block is for the first aircraft of receiving navigation system and detecting and the state of flight of the second aircraft, locus signal, automatic positioning die block is to the state of flight of the first aircraft and the second aircraft, locus controls, and export alignment information to described core processing module, described core processing module exports alignment command to the Energy transmission end of the first aircraft with the energy acceptance end being positioned at the second aircraft, the Energy transmission end making the first aircraft and the energy acceptance end being positioned at the second aircraft are aimed at, and export alignment information to described Energy Transfer module, described Energy Transfer module receives the alignment information of core processing module, and the Energy transmission end of described first aircraft exports energy to the energy acceptance end of the second aircraft.
In the present embodiment, Energy Transfer module comprises the Energy transmission end being positioned at the first aircraft and the energy acceptance end being positioned at the second aircraft.As shown in Figure 2, Energy transmission end comprises rectifying and wave-filtering power factor correction module, high-frequency inversion module and former limit winding, the input of described rectifying and wave-filtering power factor correction module is connected with mains supply end, be transferred to high-frequency inversion module after the current processing that electrical network inputs by described rectifying and wave-filtering power factor correction module, the output of high-frequency inversion module is connected with former limit winding; Described energy acceptance end comprises vice-side winding, rectifying and wave-filtering power conditioning module, and described vice-side winding receives the energy that former limit winding exports, after the process of rectifying and wave-filtering power conditioning module, be transferred to power consumption equipment; Described Energy transmission end also comprises the first wireless communication module, described energy acceptance end comprises the second wireless communication module, the electricity that power consumption equipment needs by described second wireless communication module and need time tranfer to the first wireless communication module, described first wireless communication module controls to work in the winding of former limit the quantity of sub-winding and turn-on time, realizes the transmission of corresponding energy.Energy Transfer module of the present invention can judge the energy of Energy Transfer opportunity and needs, energy savings, effectively achieves the unlimited high efficiency of transmission of energy.
In an execution mode be more preferably of the present invention, as shown in Figure 3, Energy transmission end comprises full-bridge inverter, the power end of full-bridge inverter connects DC power supply EVF, the output of full-bridge inverter and former limit winding L p, former limit building-out capacitor Cp is connected to form a series loop, in the present embodiment, former limit winding L p comprises sub-winding L p1, Lp2, Lpk, Lpn, described n is the sub-winding quantity of former limit winding, described n be greater than 1 positive integer, described k=1, 2, n, described sub-winding L pk is connected with switch S k, described switch S k is connected with core processing module, break-make is controlled by described core processing module.
In the execution mode that another is more preferably of the present invention, as shown in Figure 3, Energy transmission end comprises full-bridge inverter, the power end of full-bridge inverter connects DC power supply EVS, the output of full-bridge inverter and vice-side winding Ls, former limit building-out capacitor Cs is connected to form a series loop, in the present embodiment, vice-side winding comprises sub-winding L s1, Ls2, Lsp, Lsm, described m is the sub-winding quantity of former limit winding, described m be greater than 1 positive integer, described p=1, 2, m, described sub-winding L sp is connected with switch S p, described switch S p is connected with core processing module, break-make is controlled by described core processing module.The former limit winding of Energy transmission end of the present invention and the vice-side winding of energy acceptance end include multiple sub-winding, can adjust the output energy of former limit winding and the received energy of vice-side winding, regulate the size of transmitting energy.
In the present embodiment, former limit circuit (Energy transmission end) and secondary circuit (energy acceptance end) all have one piece of magnetic core, are contacted each other by magnetic Field Coupling.Former limit circuit by input 220v AC rectification, filtering, the direct current of stable output.And then through the driving of control circuit, direct current is converted to the alternating current of high frequency, act on primary coil, magnetic field energy is passed to secondary by air by the magnetic field that primary coil is produced, the direct current obtained after taking rectification, filtering to secondary exports, and realizes the transmission of radio energy.
In the present embodiment, as shown in Figures 3 and 4, the first aircraft and the second aircraft all have energy transmitting terminal and energy acceptance end, when needs export energy, described energy transmitting terminal place in circuit, when needs received energy, described energy acceptance end place in circuit.First aircraft and the second aircraft can either accept energy also can emitted energy, and system utilization is more various.In an execution mode be more preferably of the present invention, energy transmitting terminal and energy acceptance end are arranged in the disk at the top of aircraft, this disk can rotate, as shown in Figure 4, when charging is required, in flight course all the time by the radiating portion of maintenance one aircraft and the receiving unit of another aircraft just right.Grey parts represents Ferrite Material in the drawings, produces the Ferrite Material with low magnetic permeability, then adopt the Ferrite Material of high permeability at receiving unit at radiating portion.
As shown in Fig. 3 (b) He Fig. 3 (c), in the execution mode that another is more preferably of the present invention, energy transmitting terminal and energy acceptance end are arranged in the disk at the top of aircraft, and energy transmitting terminal and energy acceptance end occupy the space of half in disk respectively.
As shown in Fig. 3 (a) He Fig. 3 (b), power to the second aircraft for the first aircraft, at this moment the first aircraft performs energy emission function, and disk interior loop switching is held to A, B.As shown in Fig. 3 (c) He Fig. 3 (d), the second aircraft performs energy acceptance function, and disk interior loop switching is held to C, D.In circuit, S1-S4 is switching tube, form two Switch Controller (S1, S4) with (S2, S3), the complementary conductings of two Switch Controller, the DC input voitage of DC power supply EVS converted in loop that square wave formed to Cs and Ls1-7 and produce resonance, resonance current will produce high-frequency energy and transmit electromagnetic field in Ls1-7.And the receiving unit of nigh aircraft 2 is positioned at this elect magnetic field, under magnetic fields, resonance current will be formed in Lp1-7, and in the loop that Cp and Lp1-7 is formed, form resonance thus, by these four diode rectifications of PD1-PD4, Energy transmission will be given the battery or power supply EVP that will charge.
If the second aircraft is powered to the first aircraft, then conversely, the second aircraft performs energy emission function, and disk interior loop switching is to A, B end, and the first aircraft performs energy acceptance function, and disk interior loop switching is held to C, D.Two Switch Controller (P1 that P1-P4 is formed, P4) with (P2, P3), two complementary conductings of Switch Controller, the DC input voitage of DC power supply EVP converted in loop that square wave formed to Cp and Lp1-7 and produce resonance, resonance current will produce high-frequency energy transmission electromagnetic field in Lp1-7.And the receiving unit of nigh first aircraft is positioned at this elect magnetic field, under magnetic fields, resonance current will be formed in Ls1-7, and in the loop that Cs and Ls1-7 is formed, form resonance thus, by these four diode rectifications of SD1-SD4, Energy transmission will be given the battery or power supply EVS that will charge.
In the present embodiment, A, B end and C, D hold the circuit of mutual switching as shown in Figure 5, and wherein J1 and J2 is relay switch, and for being switched on or switched off the connection of radiating portion or receiving unit, J1 and J2 complementary switch, as J1 conducting, then J2 then turns off, and vice versa.
In the present embodiment, as shown in Figure 6, automatic positioning die block comprises transducer group and controller, described transducer group is for detecting the state of flight of the first aircraft and the second aircraft, spatial positional information by described information transmission to described controller, described controller controls the state of flight of the first aircraft and the second aircraft, locus, the Energy transmission end making the first aircraft and the energy acceptance end being positioned at the second aircraft are aimed at, and export alignment information to described core processing module.Automatic positioning die block of the present invention can control the relative position of the first aircraft and the second aircraft, when the Energy transmission end of the first aircraft and the energy acceptance end that is positioned at the second aircraft are aimed at, the Energy transmission end of the first aircraft exports energy to the energy acceptance end of the second aircraft.
In the present embodiment, controller is responsible for state of flight information that each transducer of sense aircraft detects and spatial positional information, comprising: the locus of flight, height and flight attitude etc.Transducer group comprises: three rotary angle transmitter (not shown in FIG.), compass, gyroscope, laser elevation measuring equipments.Wherein, gyroscope plays the effect of the angular speed measuring quadrotor, extremely important in inertial navigation system.The angular speed (pitch rate, rolling angle rate, yawrate) gathering quadrotor 3 directions is responsible in systems in which by gyroscope.In the present embodiment, the angular rate gyroscope of ADI company is adopted.
Compass can provide aircraft around ground coordinate system x, and the corner absolute value in y direction, can record the heading of aircraft in conjunction with angle rotation sensor.Compass is connected with controller by serial ports.
Angle rotation sensor: in the rectangular coordinate system in aircraft flight space, there is an angle rotation sensor in each direction, three directions.It can obtain the angular acceleration in all directions, and the numerical value of the anglec of rotation.Aircraft there is the angle rotation sensor that three same, the angular acceleration in responsible each reference axis and the measurement of the anglec of rotation.Signal type is A/D data, sampling period 5ms.
Laser elevation measuring equipment completes the measurement of aircraft terrain clearance.Adopt serial ports to be connected with controller, current flight elevation information is provided.
Gyroplane rotate speed measuring instrument, is responsible for the measurement of aircraft rotor rotating speed, stand-by motor speed probe.When main rotor invariablenes turning speed, helicopter is in stable condition, and controllability is good.PFM signal is adopted to be connected with controller.
Motor speed sensor completes the detection to motor speed.Make to go straight up to function and normally carry out wireless charging in a rational range of speeds.
In the present embodiment, automatic positioning die block also comprises temperature sensor and power module, described power module is used for powering to controller and transducer group, and described temperature sensor, for monitoring the temperature of automatic positioning die block, ensures the normal work of automatic positioning die block.
In the present embodiment, automatic locating information can be transferred to core processing module by limited or wireless mode by controller, core processing module exports alignment command to the Energy transmission end of the first aircraft with the energy acceptance end being positioned at the second aircraft, the Energy transmission end making the first aircraft and the energy acceptance end being positioned at the second aircraft are aimed at, and export alignment information to Energy Transfer module, Energy Transfer module receives the alignment information of core processing module, and the Energy transmission end of the first aircraft exports energy to the energy acceptance end of the second aircraft.
Between the aircraft based on inductively mode of the present invention, wireless power supply system can obtain the accurate distance information of the first aircraft and the second aircraft rapidly by automatic positioning die block, obtain energy in the mode of wireless energy transfer, can more convenient, efficiently give flyer supply energy.
Present invention also offers a kind of wireless power method between aircraft based on inductively mode, it comprises the steps:
S1: build wireless power supply system between the aircraft based on inductively mode of the present invention;
S2: described automatic positioning die block receives the first aircraft of navigation system detection and state of flight, the locus signal of the second aircraft, and give described core processing module by described state of flight, locus Signal transmissions, described core processing module controls the state of flight of the first aircraft and the second aircraft, locus, the Energy transmission end making the first aircraft and the energy acceptance end being positioned at the second aircraft are aimed at, and export alignment information to described Energy Transfer module;
S3: Energy Transfer module receives the alignment information of core processing module, the Energy transmission end of described first aircraft exports energy to the energy acceptance end of the second aircraft.
Between the aircraft based on inductively mode of the present invention, wireless power method obtains the accurate distance information of the first aircraft and the second aircraft rapidly by automatic positioning die block, Energy Transfer module with the mode transmitting energy of wireless energy transfer, can more convenient, efficiently give flyer supply energy.
In one preferred embodiment of the invention, when the first aircraft energy acceptance end from Energy transmission end to the second aircraft export energy time, described second wireless communication module needs to work in the number control vice-side winding of electricity according to power consumption equipment the quantity of sub-winding, simultaneously the charge transport that needed by power consumption equipment of described second wireless communication module is to the first wireless communication module, described first wireless communication module controls to work in the winding of former limit the quantity of sub-winding, realizes the transmission of corresponding energy.The accurate transmission of energy demand can be realized, avoid the generation of wasting.
In the description of this specification, specific features, structure, material or feature that the description of reference term " embodiment ", " some embodiments ", " example ", " concrete example " or " some examples " etc. means to describe in conjunction with this embodiment or example are contained at least one embodiment of the present invention or example.In this manual, identical embodiment or example are not necessarily referred to the schematic representation of above-mentioned term.And the specific features of description, structure, material or feature can combine in an appropriate manner in any one or more embodiment or example.
Although illustrate and describe embodiments of the invention, those having ordinary skill in the art will appreciate that: can carry out multiple change, amendment, replacement and modification to these embodiments when not departing from principle of the present invention and aim, scope of the present invention is by claim and equivalents thereof.
Claims (9)
1. based on inductively mode aircraft between a wireless power supply system, it is characterized in that: comprising:
Energy Transfer module, automatic positioning die block and core processing module;
Described Energy Transfer module is connected with core processing module, and described Energy Transfer module comprises the Energy transmission end being positioned at the first aircraft and the energy acceptance end being positioned at the second aircraft;
Described automatic positioning die block is connected with core processing module, described automatic positioning die block is used for the first aircraft of receiving sensor detection and the state of flight of the second aircraft, locus signal, described automatic positioning die block is to the state of flight of the first aircraft and the second aircraft, locus controls, and export alignment information to described core processing module, described core processing module exports alignment command to the Energy transmission end of the first aircraft with the energy acceptance end being positioned at the second aircraft, the Energy transmission end making the first aircraft and the energy acceptance end being positioned at the second aircraft are aimed at, and export alignment information to described Energy Transfer module,
Described Energy Transfer module receives the alignment information of core processing module, and the Energy transmission end of described first aircraft exports energy to the energy acceptance end of the second aircraft;
Described Energy Transfer module comprises the Energy transmission end being positioned at the first aircraft and the energy acceptance end being positioned at the second aircraft;
Described Energy transmission end comprises rectifying and wave-filtering power factor correction module, high-frequency inversion module and former limit winding, the input of described rectifying and wave-filtering power factor correction module is connected with mains supply end, be transferred to high-frequency inversion module after the current processing that electrical network inputs by described rectifying and wave-filtering power factor correction module, the output of high-frequency inversion module is connected with former limit winding;
Described energy acceptance end comprises vice-side winding, rectifying and wave-filtering power conditioning module, and described vice-side winding receives the energy that former limit winding exports, after the process of rectifying and wave-filtering power conditioning module, be transferred to power consumption equipment;
Described Energy transmission end also comprises the first wireless communication module, described energy acceptance end comprises the second wireless communication module, the electricity that power consumption equipment needs by described second wireless communication module and need time tranfer to the first wireless communication module, described first wireless communication module controls to work in the winding of former limit the quantity of sub-winding and turn-on time, realizes the transmission of corresponding energy.
2. as claimed in claim 1 based on inductively mode aircraft between wireless power supply system, it is characterized in that: the former limit winding of described Energy transmission end comprise sub-winding L p1, Lp2 ..., Lpk ..., Lpn, described n is the sub-winding quantity of former limit winding, described n be greater than 1 positive integer, described k=1,2 ..., n, described sub-winding L pk is connected with switch S k, and described switch S k is connected with core processing module, controls break-make by described core processing module.
3. as claimed in claim 1 based on inductively mode aircraft between wireless power supply system, it is characterized in that: the vice-side winding of described energy acceptance end comprise sub-winding L s1, Ls2 ..., Lsp ..., Lsm, described m is the sub-winding quantity of former limit winding, described m be greater than 1 positive integer, described p=1,2 ..., m, described sub-winding L sp is connected with switch S p, and described switch S p is connected with core processing module, controls break-make by described core processing module.
4. as claimed in claim 1 based on inductively mode aircraft between wireless power supply system, it is characterized in that: described first aircraft and the second aircraft all have energy transmitting terminal and energy acceptance end, when needs export energy, described energy transmitting terminal place in circuit, when needs received energy, described energy acceptance end place in circuit.
5. as claimed in claim 1 based on inductively mode aircraft between wireless power supply system, it is characterized in that: described automatic positioning die block comprises transducer group and controller, described transducer group is for detecting the state of flight of the first aircraft and the second aircraft, described information transmission is also given described controller by spatial positional information, described controller is to the state of flight of the first aircraft and the second aircraft, locus controls, the Energy transmission end making the first aircraft and the energy acceptance end being positioned at the second aircraft are aimed at, and export alignment information to described core processing module.
6. based on inductively mode aircraft between a wireless power method, it is characterized in that, comprise the steps:
S1: build one of claim 1-5 described based on inductively mode aircraft between wireless power supply system;
S2: described automatic positioning die block receives the first aircraft of navigation system detection and state of flight, the locus signal of the second aircraft, and give described core processing module by described state of flight, locus Signal transmissions, described core processing module controls the state of flight of the first aircraft and the second aircraft, locus, the Energy transmission end making the first aircraft and the energy acceptance end being positioned at the second aircraft are aimed at, and export alignment information to described Energy Transfer module;
S3: Energy Transfer module receives the alignment information of core processing module, the Energy transmission end of described first aircraft exports energy to the energy acceptance end of the second aircraft.
7. as claimed in claim 6 based on inductively mode aircraft between wireless power method, it is characterized in that: described Energy Transfer module comprises the Energy transmission end being positioned at the first aircraft and the energy acceptance end being positioned at the second aircraft;
Described Energy transmission end comprises rectifying and wave-filtering power factor correction module, high-frequency inversion module and former limit winding, the input of described rectifying and wave-filtering power factor correction module is connected with mains supply end, be transferred to high-frequency inversion module after the current processing that electrical network inputs by described rectifying and wave-filtering power factor correction module, the output of high-frequency inversion module is connected with former limit winding;
Described energy acceptance end comprises vice-side winding, rectifying and wave-filtering power conditioning module, and described vice-side winding receives the energy that former limit winding exports, after the process of rectifying and wave-filtering power conditioning module, be transferred to power consumption equipment;
Described Energy transmission end also comprises the first wireless communication module, described energy acceptance end comprises the second wireless communication module, the electricity that power consumption equipment needs by described second wireless communication module and need time tranfer to the first wireless communication module, described first wireless communication module controls to work in the winding of former limit the quantity of sub-winding and turn-on time, realizes the transmission of corresponding energy.
8. as claimed in claim 6 based on inductively mode aircraft between wireless power method, it is characterized in that: the former limit winding of described Energy transmission end comprise sub-winding L p1, Lp2 ..., Lpk ..., Lpn, described n is the sub-winding quantity of former limit winding, described n be greater than 1 positive integer, described k=1,2 ..., n, described sub-winding L pk is connected with switch S k, and described switch S k is connected with core processing module, controls break-make by described core processing module;
The vice-side winding of described energy acceptance end comprise sub-winding L s1, Ls2 ..., Lsp ..., Lsm, described m is the sub-winding quantity of former limit winding, described m be greater than 1 positive integer, described p=1,2 ..., m, described sub-winding L sp is connected with switch S p, described switch S p is connected with core processing module, controls break-make by described core processing module.
9. as claimed in claim 7 or 8 based on inductively mode aircraft between wireless power method, it is characterized in that: when the first aircraft energy acceptance end from Energy transmission end to the second aircraft export energy time, described second wireless communication module needs to work in the number control vice-side winding of electricity according to power consumption equipment the quantity of sub-winding, simultaneously the charge transport that needed by power consumption equipment of described second wireless communication module is to the first wireless communication module, described first wireless communication module controls to work in the winding of former limit the quantity of sub-winding, realize the transmission of corresponding energy.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310293587.5A CN103326479B (en) | 2013-07-12 | 2013-07-12 | Wireless power supply system between aircrafts based on inductive coupling way and power supply method |
| PCT/CN2013/084663 WO2015003430A1 (en) | 2013-07-12 | 2013-09-30 | Inductive coupling mode-based wireless power supply system between aircraft, and power supply method |
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| CN201310293587.5A CN103326479B (en) | 2013-07-12 | 2013-07-12 | Wireless power supply system between aircrafts based on inductive coupling way and power supply method |
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| CN103326479B (en) * | 2013-07-12 | 2015-01-07 | 重庆大学 | Wireless power supply system between aircrafts based on inductive coupling way and power supply method |
| CN103580301B (en) * | 2013-10-30 | 2016-04-27 | 青岛大学 | A kind of wireless power transmission power control system and method |
| CN103594749B (en) * | 2013-10-30 | 2015-12-30 | 中国运载火箭技术研究院 | Based on the spacecraft charging method of wireless energy transmission |
| CN103780313A (en) * | 2014-01-21 | 2014-05-07 | 桂林航天光比特科技股份公司 | Laser energy supply communication system for air vehicle |
| CN106786956B (en) * | 2017-01-11 | 2019-05-10 | 河北省自动化研究所 | Group's unmanned plane power supply unit |
| CN111049243A (en) * | 2020-01-06 | 2020-04-21 | 北京航天自动控制研究所 | Wireless power supply system and aircraft |
| CN114978438A (en) * | 2022-05-07 | 2022-08-30 | 南京理工大学 | Wireless information binding system and binding method for two-dimensional correction bullet testing assembly |
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| JP3158092U (en) * | 2009-10-23 | 2010-03-18 | 完 森田 | Ecological processing computer vehicle system |
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| CN1996711A (en) * | 2006-12-08 | 2007-07-11 | 广州电器科学研究院 | Inductive coupled wireless power transfer device |
| US20100253156A1 (en) * | 2009-04-07 | 2010-10-07 | Jeffrey Iott | Sensor device powered through rf harvesting |
| CN101902062A (en) * | 2010-08-06 | 2010-12-01 | 武汉中原电子集团有限公司 | Vehicle-mounted wireless charging device |
| CN102195367A (en) * | 2011-04-19 | 2011-09-21 | 南京航空航天大学 | Wireless power supply device |
| CN103326479B (en) * | 2013-07-12 | 2015-01-07 | 重庆大学 | Wireless power supply system between aircrafts based on inductive coupling way and power supply method |
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| JP3158092U (en) * | 2009-10-23 | 2010-03-18 | 完 森田 | Ecological processing computer vehicle system |
| CN102163862A (en) * | 2010-02-12 | 2011-08-24 | 株式会社半导体能源研究所 | Moving object, wireless power feeding system, and wireless power feeding method |
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