CN103326479A - 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
- Publication number
- CN103326479A CN103326479A CN2013102935875A CN201310293587A CN103326479A CN 103326479 A CN103326479 A CN 103326479A CN 2013102935875 A CN2013102935875 A CN 2013102935875A CN 201310293587 A CN201310293587 A CN 201310293587A CN 103326479 A CN103326479 A CN 103326479A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- energy
- winding
- module
- output
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 15
- 230000008878 coupling Effects 0.000 title abstract description 4
- 238000010168 coupling process Methods 0.000 title abstract description 4
- 238000005859 coupling reaction Methods 0.000 title abstract description 4
- 230000001939 inductive effect Effects 0.000 title abstract 3
- 238000012545 processing Methods 0.000 claims abstract description 60
- 230000005540 biological transmission Effects 0.000 claims abstract description 17
- 238000004804 winding Methods 0.000 claims description 92
- 238000012546 transfer Methods 0.000 claims description 40
- 238000004891 communication Methods 0.000 claims description 35
- 230000006698 induction Effects 0.000 claims description 23
- 238000001914 filtration Methods 0.000 claims description 22
- 238000012937 correction Methods 0.000 claims description 12
- 238000001514 detection method Methods 0.000 claims description 10
- 230000003750 conditioning effect Effects 0.000 claims description 8
- 239000000463 material Substances 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 230000000295 complement effect Effects 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 229910000859 α-Fe Inorganic materials 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 239000003990 capacitor Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000005672 electromagnetic field Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000035699 permeability Effects 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 230000002950 deficient Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010292 electrical insulation Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000004886 process control Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
Images
Classifications
-
- 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
-
- 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
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Power Engineering (AREA)
- 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, the induction electric energy transmission) technology, be specifically related to a kind of based on wireless power supply system and method for supplying power between the aircraft of induction coupled modes.
Background technology
The IPT technology is based on the Faradic electricity magnetic 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 of complete electrical insulation and removable load.This technology is widely used in fields such as electric automobile, rotation power consumption equipment, biologic medical, household electrical appliances and mobile electronic devices.
Along with the fast development of economy and the quick emergence of military power, flexible object is carried out the mobile status charging technique seems further important, how convenient, efficiently for flyer supply energy be the technical problem of needing solution badly.
Summary of the invention
In order to overcome the defective that exists in the above-mentioned prior art, the purpose of this invention is to provide a kind of based on the induction coupled modes aircraft between wireless power supply system and method for supplying power to, can realize the energy supplement to aircraft.
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 responding to coupled modes, it comprises Energy Transfer module, automatic positioning die piece and core processing module; Described Energy Transfer module links to each other with core processing module, and described Energy Transfer module comprises the energy output that is positioned at the first aircraft and is positioned at the energy receiving terminal of the second aircraft; Described automatic positioning die piece links to each other with core processing module, described automatic positioning die piece is used for receiving the first aircraft of navigation system detection and the state of flight of the second aircraft, the locus signal, described automatic positioning die piece is to the state of flight of the first aircraft and the second aircraft, the locus is controlled, and to described core processing module output alignment information, described core processing module is to the energy output and the energy receiving terminal output alignment command that is positioned at the second aircraft of the first aircraft, the energy output of the first aircraft is aimed at the energy receiving terminal that is positioned at the second aircraft, and exported alignment information to described Energy Transfer module; Described Energy Transfer module receives the alignment information of core processing module, and the energy output of described the first aircraft is to the energy receiving terminal output energy of the second aircraft.
The accurate distance information that can obtain rapidly by the automatic positioning die piece the first aircraft and the second aircraft based on wireless power supply system between the aircraft of induction coupled modes of the present invention, mode with wireless energy transfer is obtained energy, can give more convenient, efficiently flyer supply energy.
In a preferred embodiment of the present invention, described Energy Transfer module comprises the energy output that is positioned at the first aircraft and is positioned at the energy receiving terminal of the second aircraft; Described energy output 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 links to each other with the mains supply end, be transferred to the high-frequency inversion module after the current processing of described rectifying and wave-filtering power factor correction module with the electrical network input, the output of high-frequency inversion module links to each other with former limit winding; Described energy receiving terminal comprises secondary winding, rectifying and wave-filtering power conditioning module, and described secondary winding receives the energy of former limit winding output, is transferred to power consumption equipment after processing through the rectifying and wave-filtering power conditioning module; Described energy output also comprises the first wireless communication module, described energy receiving terminal comprises the second wireless communication module, the electric weight that described the second wireless communication module needs power consumption equipment and need time tranfer to the first wireless communication module, described the first wireless communication module is controlled quantity and the turn-on time of the sub-winding of working in the winding of former limit, realizes the transmission of corresponding energy.
Energy Transfer module of the present invention can be judged Energy Transfer opportunity and the energy that needs, and energy savings has effectively realized the unlimited high efficiency of transmission of energy.
In a kind of preferred implementation of the present invention, the former limit winding of described energy output comprise sub-winding L p1, Lp2 ..., Lpk ..., Lpn, described n is the sub-winding quantity of former limit winding, described n is the positive integer greater than 1, described k=1,2 ..., n, described sub-winding L pk links to each other with switch S k, and described switch S k links to each other with core processing module, by described core processing module control break-make.
In another kind of preferred implementation of the present invention, the secondary winding of described energy receiving terminal comprise sub-winding L s1, Ls2 ..., Lsp ..., Lsm, described m is the sub-winding quantity of former limit winding, described m is the positive integer greater than 1, described p=1,2 ..., m, described sub-winding L sp links to each other with switch S p, and described switch S p links to each other with core processing module, by described core processing module control break-make.
The former limit winding of energy output of the present invention and the secondary winding of energy receiving terminal include a plurality of sub-windings, can adjust the received energy of output energy and the secondary winding of former limit winding, regulate the size of transmitting energy.
In a kind of preferred implementation of the present invention, described the first aircraft and the second aircraft all have energy transmitting terminal and energy receiving terminal, when needs output energy, and described energy transmitting terminal place in circuit, when the needs received energy, described energy transmitting terminal place in circuit.The first aircraft and the second aircraft can either be accepted energy also can emitted energy, and system's purposes is more various.
In a kind of preferred implementation of the present invention, described automatic positioning die piece comprises transducer group and controller, described transducer group is given described controller for detection of the state of flight of the first aircraft and the second aircraft, spatial positional information and with described communication, described controller is controlled state of flight, the locus of the first aircraft and the second aircraft, the energy output of the first aircraft is aimed at the energy receiving terminal that is positioned at the second aircraft, and to described core processing module output alignment information.
Automatic positioning die piece of the present invention can be controlled the relative position of the first aircraft and the second aircraft, aim at the energy receiving terminal that is positioned at the second aircraft when the energy output of the first aircraft, the energy output of the first aircraft is exported energy to the energy receiving terminal 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 wireless power method between a kind of aircraft based on responding to coupled modes, it comprises the steps:
S1: build of the present invention based on wireless power supply system between the aircraft of induction coupled modes;
S2: described automatic positioning die piece receives the first aircraft of navigation system detection and state of flight, the locus signal of the second aircraft, and described state of flight, locus signal be transferred to described core processing module, described core processing module is controlled state of flight, the locus of the first aircraft and the second aircraft, the energy output of the first aircraft is aimed at the energy receiving terminal that is positioned at the second aircraft, and to described Energy Transfer module output alignment information;
S3: the Energy Transfer module receives the alignment information of core processing module, and the energy output of described the first aircraft is to the energy receiving terminal output energy of the second aircraft.
The accurate distance information of obtaining rapidly the first aircraft and the second aircraft based on wireless power method between the aircraft of induction coupled modes by the automatic positioning die piece of the present invention, the Energy Transfer module can be given flyer supply energy more convenient, efficiently with the mode transmitting energy of wireless energy transfer.
In a preferred embodiment of the present invention, when the energy output of the first aircraft is exported energy to the energy receiving terminal of the second aircraft, described the second wireless communication module is according to work in the secondary winding quantity of sub-winding of how much controlling of power consumption equipment needs electric weight, described the second wireless communication module is transferred to the first wireless communication module with the electric weight that power consumption equipment needs simultaneously, the quantity that described the first wireless communication module is controlled the sub-winding of working in the winding of former limit realizes the transmission of corresponding energy.Can realize the accurate transmission of energy demand, the generation that avoids waste.
Additional aspect of the present invention and advantage in the following description part provide, and part will become obviously from the following description, or recognize by practice of the present invention.
Description of drawings
Above-mentioned and/or additional aspect of the present invention and advantage are from obviously and easily understanding becoming the description of embodiment in conjunction with following accompanying drawing, wherein:
Fig. 1 is the structural representation that the present invention is based on wireless power supply system between the aircraft of responding to coupled modes;
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 output and energy receiving terminal in a kind of preferred implementation of the present invention;
Fig. 4 is the schematic diagram that energy output and energy receiving terminal carry out Energy Transfer in a kind of preferred implementation of the present invention;
Fig. 5 is the ON-OFF control circuit of energy output and energy receiving terminal in a kind of preferred implementation of the present invention;
Fig. 6 is the structural representation of automatic positioning die piece in a kind of preferred implementation of the present invention.
Embodiment
The below describes embodiments of the invention in detail, and the example of described embodiment is shown in the drawings, and wherein same or similar label represents same or similar element or the element with identical or similar functions from start to finish.Be exemplary below by the embodiment that is described with reference to the drawings, only be used for explaining the present invention, and can not be interpreted as limitation of the present invention.
In description of the invention, unless otherwise prescribed and limit, need to prove, term " installation ", " linking to each other ", " connection " should be done broad understanding, for example, can be mechanical connection or electrical connection, also can be the connection of two element internals, can be directly to link to each other, and also can indirectly link to each other by intermediary, for the ordinary skill in the art, can understand as the case may be the concrete meaning of above-mentioned term.
The invention provides wireless power supply system between a kind of aircraft based on responding to coupled modes, as shown in Figure 1, it comprises Energy Transfer module, automatic positioning die piece and core processing module.Wherein, the Energy Transfer module links to each other with core processing module, and the Energy Transfer module comprises the energy output that is positioned at the first aircraft and is positioned at the energy receiving terminal of the second aircraft.The automatic positioning die piece links to each other with core processing module, the automatic positioning die piece is used for receiving the first aircraft of navigation system detection and the state of flight of the second aircraft, the locus signal, the automatic positioning die piece is to the state of flight of the first aircraft and the second aircraft, the locus is controlled, and to described core processing module output alignment information, described core processing module is to the energy output and the energy receiving terminal output alignment command that is positioned at the second aircraft of the first aircraft, the energy output of the first aircraft is aimed at the energy receiving terminal that is positioned at the second aircraft, and exported alignment information to described Energy Transfer module; Described Energy Transfer module receives the alignment information of core processing module, and the energy output of described the first aircraft is to the energy receiving terminal output energy of the second aircraft.
In the present embodiment, the Energy Transfer module comprises the energy output that is positioned at the first aircraft and the energy receiving terminal that is positioned at the second aircraft.As shown in Figure 2, the energy output 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 links to each other with the mains supply end, be transferred to the high-frequency inversion module after the current processing of described rectifying and wave-filtering power factor correction module with the electrical network input, the output of high-frequency inversion module links to each other with former limit winding; Described energy receiving terminal comprises secondary winding, rectifying and wave-filtering power conditioning module, and described secondary winding receives the energy of former limit winding output, is transferred to power consumption equipment after processing through the rectifying and wave-filtering power conditioning module; Described energy output also comprises the first wireless communication module, described energy receiving terminal comprises the second wireless communication module, the electric weight that described the second wireless communication module needs power consumption equipment and need time tranfer to the first wireless communication module, described the first wireless communication module is controlled quantity and the turn-on time of the sub-winding of working in the winding of former limit, realizes the transmission of corresponding energy.Energy Transfer module of the present invention can be judged Energy Transfer opportunity and the energy that needs, and energy savings has effectively realized the unlimited high efficiency of transmission of energy.
In an execution mode that is more preferably of the present invention, as shown in Figure 3, the energy output 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 is the positive integer greater than 1, described k=1,2, n, described sub-winding L pk links to each other with switch S k, described switch S k links to each other with core processing module, by described core processing module control break-make.
In the execution mode that another is more preferably of the present invention, as shown in Figure 3, the energy output comprises full-bridge inverter, the power end of full-bridge inverter connects DC power supply EVS, the output of full-bridge inverter and secondary winding L s, former limit building-out capacitor Cs is connected to form a series loop, in the present embodiment, the secondary winding comprises sub-winding L s1, Ls2, Lsp, Lsm, described m is the sub-winding quantity of former limit winding, described m is the positive integer greater than 1, described p=1,2, m, described sub-winding L sp links to each other with switch S p, described switch S p links to each other with core processing module, by described core processing module control break-make.The former limit winding of energy output of the present invention and the secondary winding of energy receiving terminal include a plurality of sub-windings, can adjust the received energy of output energy and the secondary winding of former limit winding, regulate the size of transmitting energy.
In the present embodiment, former limit circuit (energy output) all has a magnetic core with secondary circuit (energy receiving terminal), contacts by magnetic Field Coupling each other.Former limit circuit is with 220v AC rectification, the filtering of input, the direct current of stable output.And then the driving of process control circuit, direct current is converted to the alternating current of high frequency, act on primary coil, the magnetic field that primary coil is produced is passed to secondary by air with magnetic field energy, the direct current that secondary is taked to obtain after rectification, the filtering is exported, realized the transmission of radio energy.
In the present embodiment, shown in Fig. 3 and 4, the first aircraft and the second aircraft all have energy transmitting terminal and energy receiving terminal, when needs output energy, described energy transmitting terminal place in circuit, when the needs received energy, described energy transmitting terminal place in circuit.The first aircraft and the second aircraft can either be accepted energy also can emitted energy, and system's purposes is more various.In an execution mode that is more preferably of the present invention, energy transmitting terminal and energy receiving terminal are arranged in the disk at the top of aircraft, this disk can rotate, as shown in Figure 4, when needs charge, the receiving unit that in flight course, will keep all the time the radiating portion of an aircraft and another aircraft over against.Grey in the drawings color part represents Ferrite Material, produces the Ferrite Material with low magnetic permeability at radiating portion, then adopts the Ferrite Material of high permeability at receiving unit.
Shown in Fig. 3 (b) and Fig. 3 (c), in the execution mode that another is more preferably of the present invention, energy transmitting terminal and energy receiving terminal are arranged in the disk at the top of aircraft, and energy transmitting terminal and energy receiving terminal occupy respectively in the disk space of half.
Shown in Fig. 3 (a) and Fig. 3 (b), power supply is as example take the first aircraft to the second aircraft, and at this moment the first aircraft is carried out the energy emission function, and disk interior loop switching is to A, and B holds.Shown in Fig. 3 (c) and Fig. 3 (d), the second aircraft is carried out the energy receiving function, and disk interior loop switching is to C, and D holds.In circuit, S1-S4 is switching tube, form two switches to (S1, S4) with (S2, S3), two switches are to complementary conducting, the DC input voitage of DC power supply EVS is converted in the loop that square wave forms to Cs and Ls1-7 produce resonance, and 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, to in Lp1-7, form resonance current, and in the loop of Cp and Lp1-7 formation, form resonance thus, to by these four diode rectifications of PD1-PD4, energy be exported to battery or the power supply EVP that will charge.
If the second aircraft is powered to the first aircraft, then conversely, the second aircraft is carried out the energy emission function, and disk interior loop switching is to A, and B holds, and the first aircraft is carried out the energy receiving function, and disk interior loop switching is to C, and D holds.Two switches that P1-P4 forms are to (P1, P4) with (P2, P3), two switches are to complementary conducting, the DC input voitage of DC power supply EVP converted in the loop that square wave forms to Cp and Lp1-7 produce resonance, resonance current will produce high-frequency energy and transmit electromagnetic field in Lp1-7.And the receiving unit of nigh the first aircraft is positioned at this elect magnetic field, under magnetic fields, to in Ls1-7, form resonance current, and in the loop of Cs and Ls1-7 formation, form resonance thus, to by these four diode rectifications of SD1-SD4, energy be exported to battery or the power supply EVS that will charge.
In the present embodiment, the circuit that A, B end and C, D hold mutual switching as shown in Figure 5, wherein J1 and J2 are relay switch, are used for being switched on or switched off the connection of radiating portion or receiving unit, J1 and J2 complementary switch, such as the J1 conducting, then J2 then turn-offs, vice versa.
In the present embodiment, as shown in Figure 6, the automatic positioning die piece comprises transducer group and controller, described transducer group is given described controller for detection of the state of flight of the first aircraft and the second aircraft, spatial positional information and with described communication, described controller is controlled state of flight, the locus of the first aircraft and the second aircraft, the energy output of the first aircraft is aimed at the energy receiving terminal that is positioned at the second aircraft, and to described core processing module output alignment information.Automatic positioning die piece of the present invention can be controlled the relative position of the first aircraft and the second aircraft, aim at the energy receiving terminal that is positioned at the second aircraft when the energy output of the first aircraft, the energy output of the first aircraft is exported energy to the energy receiving terminal of the second aircraft.
In the present embodiment, controller is responsible for state of flight information and the spatial positional information that each transducer of sense aircraft detects, and comprising: the locus of flight, height and flight attitude etc.The transducer group comprises: three rotary angle transmitter (not shown in FIG.), compass, gyroscope, laser elevation measuring equipment.Wherein, gyroscope plays the effect of the angular speed of measuring quadrotor, and is extremely important in inertial navigation system.Gyroscope is responsible for gathering the angular speed (pitch rate, rolling angle rate, yawrate) of 3 directions of quadrotor in system.In the present embodiment, adopt the angular rate gyroscope of ADI company.
Compass can provide aircraft around ground coordinate system x, and the corner absolute value of y direction can record the heading of aircraft in conjunction with the angle rotation sensor.Compass links to each other with controller by serial ports.
The angle rotation sensor: in the rectangular coordinate system in aircraft flight space, three each directions of direction have an angle rotation sensor.It can obtain the angular acceleration on all directions, and the numerical value of the anglec of rotation.Three same angle rotation sensors are arranged, the angular acceleration on responsible each reference axis and the measurement of the anglec of rotation on the aircraft.Signal type is the A/D data, sampling period 5ms.
The laser elevation measuring equipment is finished the measurement of aircraft terrain clearance.Adopt serial ports to link to each other with controller, the current flight elevation information is provided.
The gyroplane rotate speed measuring instrument is responsible for the measurement of aircraft rotor rotating speed, the stand-by motor speed probe.When the main rotor invariablenes turning speed, helicopter is in stable condition, and controllability is good.Adopt the PFM signal to link to each other with controller.
Motor speed sensor is finished the detection to motor speed.In a rational range of speeds, normally carry out wireless charging so that go straight up to function.
In the present embodiment, the automatic positioning die piece also comprises temperature sensor and power module, described power module is used for to controller and the power supply of transducer group, and described temperature sensor is used for the temperature of monitoring automatic positioning die piece, guarantees the normal operation of automatic positioning die piece.
In the present embodiment, controller can be transferred to core processing module with automatic locating information by limited or wireless mode, core processing module is to the energy output and the energy receiving terminal output alignment command that is positioned at the second aircraft of the first aircraft, the energy output of the first aircraft is aimed at the energy receiving terminal that is positioned at the second aircraft, and export alignment information to the Energy Transfer module, the Energy Transfer module receives the alignment information of core processing module, and the energy output of the first aircraft is to the energy receiving terminal output energy of the second aircraft.
The accurate distance information that can obtain rapidly by the automatic positioning die piece the first aircraft and the second aircraft based on wireless power supply system between the aircraft of induction coupled modes of the present invention, mode with wireless energy transfer is obtained energy, can give more convenient, efficiently flyer supply energy.
It is a kind of based on wireless power method between the aircraft of induction coupled modes that the present invention also provides, and it comprises the steps:
S1: build of the present invention based on wireless power supply system between the aircraft of induction coupled modes;
S2: described automatic positioning die piece receives the first aircraft of navigation system detection and state of flight, the locus signal of the second aircraft, and described state of flight, locus signal be transferred to described core processing module, described core processing module is controlled state of flight, the locus of the first aircraft and the second aircraft, the energy output of the first aircraft is aimed at the energy receiving terminal that is positioned at the second aircraft, and to described Energy Transfer module output alignment information;
S3: the Energy Transfer module receives the alignment information of core processing module, and the energy output of described the first aircraft is to the energy receiving terminal output energy of the second aircraft.
The accurate distance information of obtaining rapidly the first aircraft and the second aircraft based on wireless power method between the aircraft of induction coupled modes by the automatic positioning die piece of the present invention, the Energy Transfer module can be given flyer supply energy more convenient, efficiently with the mode transmitting energy of wireless energy transfer.
In a preferred embodiment of the present invention, when the energy output of the first aircraft is exported energy to the energy receiving terminal of the second aircraft, described the second wireless communication module is according to work in the secondary winding quantity of sub-winding of how much controlling of power consumption equipment needs electric weight, described the second wireless communication module is transferred to the first wireless communication module with the electric weight that power consumption equipment needs simultaneously, the quantity that described the first wireless communication module is controlled the sub-winding of working in the winding of former limit realizes the transmission of corresponding energy.Can realize the accurate transmission of energy demand, the generation that avoids waste.
In the description of this specification, the description of reference term " embodiment ", " some embodiment ", " example ", " concrete example " or " some examples " etc. means to be contained at least one embodiment of the present invention or the example in conjunction with specific features, structure, material or the characteristics of this embodiment or example description.In this manual, the schematic statement of above-mentioned term not necessarily referred to identical embodiment or example.And the specific features of description, structure, material or characteristics can be with suitable mode combinations in any one or more embodiment or example.
Although illustrated and described embodiments of the invention, those having ordinary skill in the art will appreciate that: in the situation that do not break away from principle of the present invention and aim can be carried out multiple variation, modification, replacement and modification to these embodiment, scope of the present invention is limited by claim and equivalent thereof.
Claims (10)
- One kind based on the induction coupled modes aircraft between wireless power supply system, it is characterized in that: comprising:Energy Transfer module, automatic positioning die piece and core processing module;Described Energy Transfer module links to each other with core processing module, and described Energy Transfer module comprises the energy output that is positioned at the first aircraft and is positioned at the energy receiving terminal of the second aircraft;Described automatic positioning die piece links to each other with core processing module, described automatic positioning die piece is used for the first aircraft of receiving sensor detection and the state of flight of the second aircraft, the locus signal, described automatic positioning die piece is to the state of flight of the first aircraft and the second aircraft, the locus is controlled, and to described core processing module output alignment information, described core processing module is to the energy output and the energy receiving terminal output alignment command that is positioned at the second aircraft of the first aircraft, the energy output of the first aircraft is aimed at the energy receiving terminal that is positioned at the second aircraft, and exported alignment information to described Energy Transfer module;Described Energy Transfer module receives the alignment information of core processing module, and the energy output of described the first aircraft is to the energy receiving terminal output energy of the second aircraft.
- 2. as claimed in claim 1 based on wireless power supply system between the aircraft of induction coupled modes, it is characterized in that: described Energy Transfer module comprises the energy output that is positioned at the first aircraft and is positioned at the energy receiving terminal of the second aircraft;Described energy output 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 links to each other with the mains supply end, be transferred to the high-frequency inversion module after the current processing of described rectifying and wave-filtering power factor correction module with the electrical network input, the output of high-frequency inversion module links to each other with former limit winding;Described energy receiving terminal comprises secondary winding, rectifying and wave-filtering power conditioning module, and described secondary winding receives the energy of former limit winding output, is transferred to power consumption equipment after processing through the rectifying and wave-filtering power conditioning module;Described energy output also comprises the first wireless communication module, described energy receiving terminal comprises the second wireless communication module, the electric weight that described the second wireless communication module needs power consumption equipment and need time tranfer to the first wireless communication module, described the first wireless communication module is controlled quantity and the turn-on time of the sub-winding of working in the winding of former limit, realizes the transmission of corresponding energy.
- 3. as claimed in claim 1 based on wireless power supply system between the aircraft of induction coupled modes, it is characterized in that: the former limit winding of described energy output comprise sub-winding L p1, Lp2 ..., Lpk ..., Lpn, described n is the sub-winding quantity of former limit winding, described n is the positive integer greater than 1, described k=1,2 ..., n, described sub-winding L pk links to each other with switch S k, and described switch S k links to each other with core processing module, by described core processing module control break-make.
- 4. as claimed in claim 1 based on wireless power supply system between the aircraft of induction coupled modes, it is characterized in that: the secondary winding of described energy receiving terminal comprise sub-winding L s1, Ls2 ..., Lsp ..., Lsm, described m is the sub-winding quantity of former limit winding, described m is the positive integer greater than 1, described p=1,2 ..., m, described sub-winding L sp links to each other with switch S p, and described switch S p links to each other with core processing module, by described core processing module control break-make.
- 5. as claimed in claim 1 based on wireless power supply system between the aircraft of induction coupled modes, it is characterized in that: described the first aircraft and the second aircraft all have energy transmitting terminal and energy receiving terminal, when needs output energy, described energy transmitting terminal place in circuit, when the needs received energy, described energy transmitting terminal place in circuit.
- 6. as claimed in claim 1 based on wireless power supply system between the aircraft of induction coupled modes, it is characterized in that: described automatic positioning die piece comprises transducer group and controller, described transducer group is for detection of the state of flight of the first aircraft and the second aircraft, spatial positional information is also given described controller with described communication, described controller is to the state of flight of the first aircraft and the second aircraft, the locus is controlled, the energy output of the first aircraft is aimed at the energy receiving terminal that is positioned at the second aircraft, and to described core processing module output alignment information.
- One kind based on the induction coupled modes aircraft between the wireless power method, it is characterized in that, comprise the steps:S1: build one of claim 1-6 described based on wireless power supply system between the aircraft of induction coupled modes;S2: described automatic positioning die piece receives the first aircraft of navigation system detection and state of flight, the locus signal of the second aircraft, and described state of flight, locus signal be transferred to described core processing module, described core processing module is controlled state of flight, the locus of the first aircraft and the second aircraft, the energy output of the first aircraft is aimed at the energy receiving terminal that is positioned at the second aircraft, and to described Energy Transfer module output alignment information;S3: the Energy Transfer module receives the alignment information of core processing module, and the energy output of described the first aircraft is to the energy receiving terminal output energy of the second aircraft.
- 8. as claimed in claim 7 based on wireless power method between the aircraft of induction coupled modes, it is characterized in that: described Energy Transfer module comprises the energy output that is positioned at the first aircraft and is positioned at the energy receiving terminal of the second aircraft;Described energy output 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 links to each other with the mains supply end, be transferred to the high-frequency inversion module after the current processing of described rectifying and wave-filtering power factor correction module with the electrical network input, the output of high-frequency inversion module links to each other with former limit winding;Described energy receiving terminal comprises secondary winding, rectifying and wave-filtering power conditioning module, and described secondary winding receives the energy of former limit winding output, is transferred to power consumption equipment after processing through the rectifying and wave-filtering power conditioning module;Described energy output also comprises the first wireless communication module, described energy receiving terminal comprises the second wireless communication module, the electric weight that described the second wireless communication module needs power consumption equipment and need time tranfer to the first wireless communication module, described the first wireless communication module is controlled quantity and the turn-on time of the sub-winding of working in the winding of former limit, realizes the transmission of corresponding energy.
- 9. as claimed in claim 7 based on wireless power method between the aircraft of induction coupled modes, it is characterized in that: the former limit winding of described energy output comprise sub-winding L p1, Lp2 ..., Lpk ..., Lpn, described n is the sub-winding quantity of former limit winding, described n is the positive integer greater than 1, described k=1,2 ..., n, described sub-winding L pk links to each other with switch S k, and described switch S k links to each other with core processing module, by described core processing module control break-make;The secondary winding of described energy receiving terminal comprise sub-winding L s1, Ls2 ..., Lsp ..., Lsm, described m is the sub-winding quantity of former limit winding, described m is the positive integer greater than 1, described p=1,2 ..., m, described sub-winding L sp links to each other with switch S p, described switch S p links to each other with core processing module, by described core processing module control break-make.
- 10. as claimed in claim 8 or 9 based on wireless power method between the aircraft of induction coupled modes, it is characterized in that: when the energy output of the first aircraft is exported energy to the energy receiving terminal of the second aircraft, described the second wireless communication module is according to work in the secondary winding quantity of sub-winding of how much controlling of power consumption equipment needs electric weight, described the second wireless communication module is transferred to the first wireless communication module with the electric weight that power consumption equipment needs simultaneously, the quantity that described the first wireless communication module is controlled the sub-winding of working in the winding of former limit realizes the transmission of corresponding energy.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103326479A true CN103326479A (en) | 2013-09-25 |
| CN103326479B CN103326479B (en) | 2015-01-07 |
Family
ID=49195077
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310293587.5A Active CN103326479B (en) | 2013-07-12 | 2013-07-12 | Wireless power supply system between aircrafts based on inductive coupling way and power supply method |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN103326479B (en) |
| WO (1) | WO2015003430A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103580301A (en) * | 2013-10-30 | 2014-02-12 | 青岛大学 | Wireless power transmission power control system and method |
| CN103594749A (en) * | 2013-10-30 | 2014-02-19 | 中国运载火箭技术研究院 | Wireless energy transmission based spacecraft charging method |
| 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 |
| WO2015003430A1 (en) * | 2013-07-12 | 2015-01-15 | 重庆大学 | Inductive coupling mode-based wireless power supply system between aircraft, and power supply method |
| CN106786956A (en) * | 2017-01-11 | 2017-05-31 | 河北省自动化研究所 | Colony's unmanned plane electric supply installation |
| 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 |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3158092U (en) * | 2009-10-23 | 2010-03-18 | 完 森田 | Ecological processing computer vehicle system |
| US20100253156A1 (en) * | 2009-04-07 | 2010-10-07 | Jeffrey Iott | Sensor device powered through rf harvesting |
| 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 |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1996711A (en) * | 2006-12-08 | 2007-07-11 | 广州电器科学研究院 | Inductive coupled wireless power transfer device |
| 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 |
-
2013
- 2013-07-12 CN CN201310293587.5A patent/CN103326479B/en active Active
- 2013-09-30 WO PCT/CN2013/084663 patent/WO2015003430A1/en active Application Filing
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100253156A1 (en) * | 2009-04-07 | 2010-10-07 | Jeffrey Iott | Sensor device powered through rf harvesting |
| 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 |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015003430A1 (en) * | 2013-07-12 | 2015-01-15 | 重庆大学 | Inductive coupling mode-based wireless power supply system between aircraft, and power supply method |
| CN103580301A (en) * | 2013-10-30 | 2014-02-12 | 青岛大学 | Wireless power transmission power control system and method |
| CN103594749A (en) * | 2013-10-30 | 2014-02-19 | 中国运载火箭技术研究院 | Wireless energy transmission based spacecraft charging method |
| CN103580301B (en) * | 2013-10-30 | 2016-04-27 | 青岛大学 | A kind of wireless power transmission power control system and method |
| 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 |
| CN106786956A (en) * | 2017-01-11 | 2017-05-31 | 河北省自动化研究所 | Colony's unmanned plane electric supply installation |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103326479B (en) | 2015-01-07 |
| WO2015003430A1 (en) | 2015-01-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103326479B (en) | Wireless power supply system between aircrafts based on inductive coupling way and power supply method | |
| US9878628B2 (en) | Power supply device, vehicle and non-contact power supply system | |
| US9673664B2 (en) | Wireless power reception apparatus, wireless power transmission apparatus, and wireless power transmission and reception system | |
| CN102197566B (en) | Contactless power receiving device, contactless power transmitting device, contactless power supply system, and vehicle | |
| US10391875B2 (en) | Vehicle alignment for wireless charging | |
| CN106816967B (en) | Resonance coupling system and dynamic charging method for the continuation of the journey of unmanned plane dynamic radio | |
| EP2731231A2 (en) | Wireless power transmitting and charging system, and method for controlling communication and power in the wireless power transmitting and charging system | |
| CN106787233A (en) | Cable tunnel inspection robot and charging method with wireless charging device | |
| CN105958656B (en) | Multi-rotor aerocraft wireless charging device and method | |
| CN206283301U (en) | Cable tunnel inspection robot wireless charging system based on overlapping four transmitting coils | |
| CN106100069B (en) | A kind of unmanned plane wireless radiofrequency charging system | |
| CN109756032B (en) | Spherical wireless charging system | |
| KR20170040961A (en) | wireless charging system for unmaned aircraft and method having the same | |
| CN106505748A (en) | The reverse wireless power supply system of unmanned aerial vehicle onboard energy storage and method of supplying power to | |
| CN105322626A (en) | Wirelessly charged intelligent shopping cart and wireless charging system therefor | |
| CN109515219A (en) | Electric car wireless charging and coil positioning composite array coil design and control | |
| KR101884414B1 (en) | Wireless Power Transmission Apparatus for Drone | |
| US11919406B2 (en) | Power transfer system for electric vehicles and a control method thereof | |
| CN203840065U (en) | An electric sightseeing vehicle electromagnetic resonance type radio electric energy transmission system | |
| CN105914901A (en) | Line patrol robot wireless charging system capable drawing out power via power transmission line induction | |
| CN116317193A (en) | Induction energy taking system for power transmission line | |
| JP2013223301A (en) | Power reception device and power transmission device of contactless power transfer unit | |
| CN201654582U (en) | Wireless temperature control system | |
| CN206619960U (en) | A kind of resonance coupling device continued a journey for unmanned plane dynamic radio | |
| CN114407690B (en) | Concave coupling mechanism and unmanned aerial vehicle charging system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C53 | Correction of patent of invention or patent application | ||
| CB02 | Change of applicant information |
Address after: 400045 Shapingba District, Sha Sha Street, No. 174, Chongqing Applicant after: Chongqing University Address before: 400045 Chongqing street, Shapingba District, No. 174 Applicant before: Chongqing University |
|
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200509 Address after: 400026 6-1, unit 2, building 1, No. 53, Gangcheng West Road, Jiangbei District, Chongqing (room No. 608) Patentee after: Chongqing aipute Electric Co.,Ltd. Address before: Room 307, 3-1, 4-1 (Industrial Design Center), No. 18, Wujiang Road, Jiangbei District, Chongqing Patentee before: Chongqing min Chuang Intellectual Property Agency Co.,Ltd. Effective date of registration: 20200509 Address after: Room 307, 3-1, 4-1 (Industrial Design Center), No. 18, Wujiang Road, Jiangbei District, Chongqing Patentee after: Chongqing min Chuang Intellectual Property Agency Co.,Ltd. Address before: 400045 Shapingba District, Sha Sha Street, No. 174, Chongqing Patentee before: Chongqing University |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200630 Address after: Room 503-1423, unit B1, unit B1, No. 18, Yuetai Road, Tuzhu Town, Shapingba District, Chongqing Patentee after: Chongqing Qianwei radio power transmission Research Institute Co.,Ltd. Address before: 400026 6-1, unit 2, building 1, No. 53, Gangcheng West Road, Jiangbei District, Chongqing (room No. 608) Patentee before: Chongqing aipute Electric Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231009 Address after: 400026 6-1, unit 2, building 1, No. 53, Gangcheng West Road, Jiangbei District, Chongqing (room No. 608) Patentee after: Chongqing aipute Electric Co.,Ltd. Address before: 400037 room 503-1423, 5th floor, unit B1, No.18, platform road, Tuzhu Town, Shapingba District, Chongqing Patentee before: Chongqing Qianwei radio power transmission Research Institute Co.,Ltd. |
|
| TR01 | Transfer of patent right |