CN110266113B - Wireless power distribution system between spacecrafts and control method - Google Patents
Wireless power distribution system between spacecrafts and control method Download PDFInfo
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- CN110266113B CN110266113B CN201910458265.9A CN201910458265A CN110266113B CN 110266113 B CN110266113 B CN 110266113B CN 201910458265 A CN201910458265 A CN 201910458265A CN 110266113 B CN110266113 B CN 110266113B
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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
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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
- H02J50/70—Circuit arrangements or systems for wireless supply or distribution of electric power involving the reduction of electric, magnetic or electromagnetic leakage fields
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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
Abstract
The invention relates to a wireless power distribution system between spacecrafts, which is improved based on a traditional LCC topological structure, wherein an LCC compensation circuit at a transmitting end comprises a primary side compensation inductor, a primary side first series compensation capacitor and a primary side parallel compensation capacitor, a LCC compensation circuit at a receiving end comprises a secondary side first series compensation capacitor, a secondary side parallel compensation capacitor and a secondary side compensation inductor, a first switch connected with the primary side compensation inductor in series, a second switch and a primary side second series compensation capacitor connected with each other in series, a third switch connected with the secondary side compensation inductor in series, a fourth switch and a secondary side second series compensation capacitor connected with each other in series, a series branch of the second switch and the primary side second series compensation capacitor is connected with the first switch in parallel, a series branch of the primary side compensation inductor and the primary side first series compensation capacitor in series, and a series branch of the fourth switch and the secondary side second series compensation capacitor is connected with the third switch in series, And the series branch of the secondary side compensation inductor and the series branch of the secondary side first series compensation capacitor are connected in parallel, so that the transmission distance and the energy transmission efficiency are considered.
Description
Technical Field
The invention relates to the technical field of wireless power distribution, in particular to a wireless power distribution system between spacecrafts and a control method.
Background
Along with the development of aerospace technology and the increasingly deepened exploration of the unknown field of outer space in China, the functions of various spacecrafts are gradually improved, wireless power distribution systems applied to the spacecrafts are becoming increasingly complicated and diversified, the mode of wireless power distribution or wireless energy transmission technology is gradually one of the power supply modes of the spacecrafts besides the traditional wired power supply mode, the wireless power distribution technology can provide a novel energy supply mode for the spacecrafts besides the high-efficiency energy storage battery technology, and an effective solution is provided for improving the endurance of the spacecrafts.
The wireless power distribution mainly utilizes a wireless charging technology, and converts electric energy into electromagnetic waves or energy in other forms by utilizing special equipment, so that corresponding electric equipment can be charged under the non-contact condition. The prior art generally includes two main types of wireless charging technical solutions: 1) the electromagnetic induction type wireless charging means that alternating current with certain frequency is introduced into a primary coil, and certain current is generated in a secondary coil by utilizing the electromagnetic induction principle, so that wireless transmission of electric energy is realized; 2) the principle of the magnetic resonance type wireless charging is basically similar to the electromagnetic induction principle of the electromagnetic induction type wireless charging, but the electromagnetic resonance type wireless charging only requires that the frequencies of power signals of a transmitting end and a receiving end are consistent, namely the transmitting end and the receiving end work at the same frequency to reach a resonance point, and the wireless transmission of electric energy is realized through the electromagnetic coupling principle. The two wireless charging technical schemes get rid of the trouble of the traditional wired charging mode to enable the charging operation to be convenient and fast, but the two wireless charging technical schemes also have respective defects. In the magnetic resonance type wireless charging technology, an SS type basic resonance compensation structure is generally adopted between a transmitting coil and a receiving coil, so that the magnetic resonance type wireless charging technology is suitable for the condition that the transmission distance is long and the transmission distance is short. In the magnetic induction type wireless charging technology, an LCC type resonance compensation structure is adopted between a transmitting coil and a receiving coil, the condition that the transmission distance is short is adapted, and therefore the transmitting coil and the receiving coil can only be specifically applied to space vehicles meeting the specific transmission distance, and the transmission distance and the energy transmission efficiency cannot be considered at the same time. For some spacecrafts, orbit changing can be carried out according to the space mission condition, or the condition that the spacecrafts with close or far dynamic changing space have the requirement of wireless charging is generated, and the technical schemes of the two spacecrafts are obviously not applicable.
Disclosure of Invention
The invention provides a wireless power distribution system between spacecrafts, aiming at the problem that the transmission distance and the energy transmission efficiency cannot be considered in the existing wireless charging technology, the system is skillfully improved on the basis of the prior art, a switch combination and a compensation capacitor are additionally arranged, an LCC compensation structure and an SS compensation structure are successfully combined, and the switching of two compensation forms can be realized only through the control of the switch combination, so that the transmission distance and the energy transmission efficiency are considered, the structure is simple and reliable, the operation is convenient, the wireless power distribution system can be suitable for the wireless power distribution process between spacecrafts with dynamically changed intervals, and the practicability is high. The invention also provides a control method of the wireless power distribution system between the spacecrafts.
The technical scheme of the invention is as follows:
a wireless power distribution system between spacecrafts comprises a transmitting end power supply, a high-frequency inverter circuit, a transmitting end LCC compensation circuit, a transmitting coil, a receiving end LCC compensation circuit, a rectifying circuit and a receiving end load which are connected in sequence, wherein the transmitting coil and the receiving coil are connected in a non-contact mode, the transmitting end LCC compensation circuit comprises a primary side compensation inductor, a primary side first series compensation capacitor and a primary side parallel compensation capacitor which are coupled in series and parallel, the receiving end LCC compensation circuit comprises a secondary side first series compensation capacitor, a secondary side parallel compensation capacitor and a secondary side compensation inductor which are coupled in series and parallel, the system further comprises a first switch connected in series with the primary side compensation inductor, a second switch connected in series with each other, a primary side second series compensation capacitor, a third switch connected in series with the secondary side compensation inductor, a fourth switch connected in series with each other, and a secondary side second series compensation capacitor, and a series branch formed by the second switch and the primary side second series compensation capacitor is mutually connected in parallel with a series branch formed by the first switch, the primary side compensation inductor and the primary side first series compensation capacitor, and a series branch formed by the fourth switch and the secondary side second series compensation capacitor is mutually connected in parallel with a series branch formed by the third switch, the secondary side compensation inductor and the secondary side first series compensation capacitor.
Preferably, the wireless power distribution system between the spacecrafts further comprises a main controller for monitoring and controlling various state information parameters of the system, the four switches are connected with the main controller, and the main controller manually or automatically sends instructions to control the on and off of the four switches.
Preferably, wireless power distribution system between spacecraft still includes the distance monitoring devices who links to each other with main control unit, the actual distance between two spacecraft of distance monitoring devices monitoring and give main control unit with information data transmission, main control unit controls the closure and the disconnection of four switches according to the automatic instruction of sending of information data of distance monitoring devices, controls first switch, third switch disconnection while second switch, fourth switch and closes when actual distance is greater than apart from the threshold value, controls first switch, third switch closure while second switch, fourth switch disconnection when actual distance is less than apart from the threshold value.
Preferably, the transmitting end power supply is directly supplied with direct current by the spacecraft busbar voltage.
Preferably, the transmitting end and the receiving end wirelessly communicate through a contactless Zigbee wireless communication unit to transmit the operation signal or the status information.
According to the control method of the inter-spacecraft wireless power distribution system, firstly, the power supply state of each spacecraft in an aerospace space is monitored, when electric energy transmission is needed among a plurality of spacecrafts, the distance relation among the spacecrafts is monitored, two inter-spacecraft wireless power distribution systems meeting the distance relation are controlled, when the distance relation is larger than a distance threshold value, a first switch and a third switch are controlled to be switched off, a second switch and a fourth switch are controlled to be switched on, the circuit compensation topology is SS series connection type, and magnetic resonance type wireless energy transmission is achieved; when the distance relation is smaller than the distance threshold, the first switch and the third switch are controlled to be closed, the second switch and the fourth switch are controlled to be opened, the circuit compensation topology is LCC type, and magnetic induction type wireless energy transfer is achieved; the switching of the working mode of the system is controlled by controlling the on and off states of the first switch, the second switch, the third switch and the fourth switch so as to meet the requirements of wireless power transmission at different intervals.
Preferably, the control method further comprises the step of arranging a main controller for monitoring and controlling various state information parameters of the system in the system, and controlling the on and off of the four switches by manually or automatically sending instructions by using the main controller.
Preferably, the control method further comprises a distance monitoring device connected with the main controller, the distance monitoring device is used for monitoring the actual distance between the two spacecrafts and transmitting information data to the main controller, the main controller is used for automatically sending an instruction to control the on and off of the four switches according to the information data of the distance monitoring device, when the actual distance is larger than a distance threshold value, the first switch and the third switch are controlled to be off and the second switch and the fourth switch are controlled to be on and off, the system enters a SS compensation network topology structure mode to work to realize remote wireless power transmission, when the actual distance is smaller than the distance threshold value, the first switch and the third switch are controlled to be on and the second switch and the fourth switch are controlled to be off and on, and the system enters an LCC compensation network topology structure mode to work to realize near wireless power transmission.
Preferably, in the wireless power transmission process, the spacecraft bus voltage is used for carrying out direct current power supply on a transmitting end power supply of the wireless power distribution system.
Preferably, in the wireless power transmission process, the transmitting end and the receiving end of the wireless power distribution system perform wireless communication through the non-contact Zigbee wireless communication unit to transmit the operating signal or the status information.
The invention has the following technical effects:
the invention relates to a wireless power distribution system between spacecrafts, which is suitable for a wireless power distribution scene between the spacecrafts, in particular to a wireless power distribution process between the spacecrafts with dynamically changed space, skillfully improves the prior art, adds a first switch combination, a second switch combination, a third switch combination and a fourth switch combination, a primary side second series compensation capacitor and a secondary side second series compensation capacitor, leads an LCC compensation structure and an SS compensation structure to be perfectly combined, has compact structure, can adapt to resonance coupling, can be used for magnetic induction coupling, can realize the switching of two compensation forms only through the control of the switch combination, has simple and reliable structure and convenient operation, can be applied to the wireless power distribution between long-distance spacecrafts (the long distance is relative to the short distance, and can also correspond to the medium and long distance between the spacecrafts under the actual condition), the system can be applied to wireless power distribution among close-range spacecrafts (close-range space can also be called short-range space), the problem that the transmission distance and the energy transmission efficiency cannot be considered in the existing wireless charging technology is solved, the adaptability is strong, the working quality and the working efficiency of the system are greatly improved on the whole, and the wireless power distribution economic cost under the space environment is effectively reduced.
The invention also relates to a control method of the wireless power distribution system between the spacecrafts, which is suitable for the wireless power distribution scene between the spacecrafts, firstly monitors the power state of the spacecrafts in the aviation space, monitors the distance relationship between the spacecrafts when a plurality of spacecrafts need to transmit electric energy, controls the wireless power distribution system between the two spacecrafts which meets the distance relationship, controls the on-off state of a first switch, a second switch, a third switch and a fourth switch to further control the switching of the working form of the system so as to meet the requirement of wireless electric energy transmission at different intervals, leads an LCC compensation structure and an SS compensation structure to be perfectly combined and freely switched, can realize the switching of two wireless energy transmission modes of resonance coupling and magnetic induction coupling by changing the control mode of the wireless power distribution of the spacecrafts, the system can be applied to wireless power distribution between medium and long distance spacecrafts and between short distance spacecrafts, and has the advantages of considering transmission distance and energy transmission efficiency and greatly improving the working quality and working efficiency of the system on the whole.
Drawings
FIG. 1: the invention relates to a first preferred structure schematic diagram of a wireless power distribution system between spacecrafts.
FIG. 2: the invention is a schematic diagram of a second preferred structure of the wireless power distribution system between spacecrafts.
FIG. 3: the invention is a third preferred structure schematic diagram of the wireless power distribution system between the spacecrafts.
FIG. 4: is a fourth preferred structural schematic diagram of the wireless power distribution system between spacecrafts.
FIG. 5: the invention relates to a preferable flow chart of a control method of a wireless power distribution system between spacecrafts.
The reference numbers are listed below:
1-transmitting end power supply; 2-high frequency inverter circuit; 3-transmitting end LCC compensation circuit; 4-a transmitting coil; 5-a receiving coil; 6-receiving end LCC compensation circuit; 7, a rectification circuit; 8-receiving end load; 9-a main controller; 10-a distance monitoring device; 11-Zigbee wireless communication unit;
Lf1-primary side compensation inductance; c1-a primary side first series compensation capacitor; cf1-a primary side parallel compensation capacitor; l isf2-secondary compensation inductance; c2-a secondary side first series compensation capacitor; cf2-the secondary side is connected in parallel with a compensation capacitor; s1-a first switch; s2-a second switch; c3-a primary side second series compensation capacitor; s3-a third switch; s4-a fourth switch; c4-a secondary second series compensation capacitor.
Detailed Description
The invention relates to a wireless power distribution system between spacecrafts, which comprises a transmitting end power supply, a high-frequency inverter circuit, a transmitting end LCC compensation circuit, a transmitting coil, a receiving end LCC compensation circuit, a rectifying circuit and a receiving end load which are connected in sequence, wherein the transmitting coil is connected with the receiving coil in a non-contact way, the transmitting end LCC compensation circuit comprises a primary side compensation inductor, a primary side first series compensation capacitor and a primary side parallel compensation capacitor which are mutually coupled in series and parallel, the receiving end LCC compensation circuit comprises a secondary side first series compensation capacitor, a secondary side parallel compensation capacitor and a secondary side compensation inductor which are mutually coupled in series and parallel, the system also comprises a first switch which is connected with the primary side compensation inductor in series, a second switch which is connected with each other in series, a primary side second series compensation capacitor, a third switch which is connected with the secondary side compensation inductor in series, a fourth switch which is connected with the secondary side second series compensation capacitor, and the serial branch formed by the second switch and the primary side second serial compensation capacitor is mutually connected in parallel with the serial branch formed by the first switch, the primary side compensation inductor and the primary side first serial compensation capacitor, the serial branch formed by the fourth switch and the secondary side second serial compensation capacitor is mutually connected in parallel with the serial branch formed by the third switch, the secondary side compensation inductor and the secondary side first serial compensation capacitor, and the LCC compensation structure and the SS compensation structure are perfectly combined by utilizing the additional component.
The present invention will be further described in detail with reference to the accompanying drawings.
As shown in fig. 1, a first preferred structure diagram of a wireless power distribution system between spacecrafts provided by the present invention includes a transmitting end power supply 1, a high frequency inverter circuit 2, a transmitting end LCC compensation circuit 3, and a transmitting coil 4 (i.e. a primary side inductance coil L) connected in sequence1) And a receiving coil 5 (i.e., a secondary inductance coil L)2) A receiving end LCC compensating circuit 6, a rectifying circuit 7 and a receiving end load 8, wherein the transmitting coil 4 is in non-contact connection with the receiving coil 5, namely an edge inductance coil L in the figure1And secondary side inductance coil L2The LCC compensation circuit 3 at the transmitting end comprises primary side compensation inductors L which are mutually connected in series and parallel, mutual inductance and self-inductance are generated between the two to transmit energy (M is mutual inductance in the figure), and the primary side compensation inductors L are mutually connected in series and parallelf1Primary side first series compensation capacitor C1And a primary side parallel compensation capacitor Cf1The receiving end LCC compensation circuit 6 comprises secondary side first series compensation capacitors C which are mutually coupled in series and parallel2Secondary side parallel compensation capacitor Cf2And secondary compensation inductance Lf2The system also includes a primary compensation inductor Lf1First switch S connected in series1Second switches S connected in series2And a primary side second series compensation capacitor C3And secondary compensation inductance Lf2Third switch S in series3And a fourth switch S connected in series with each other4And a secondary side second series compensation capacitor C4And a second switch S2And a primary side second series compensation capacitor C3The formed series branch and the first switch S1Primary side compensation inductance Lf1And a primary first series compensation capacitor C1The formed series branches are connected in parallel, and the fourth switch S4And a secondary side second series compensation capacitor C4The formed series branch and the third switch S3Secondary side compensation inductance Lf2And a secondary side first series compensation capacitor C2The formed series branches are mutually connected in parallel, the voltage provided by the power supply 1 at the transmitting end is adjusted and then input into the high-frequency inverter circuit 2, the direct current for adjusting the overvoltage is converted into alternating current conforming to the resonance frequency by the high-frequency inverter circuit 2, and the changed high-frequency alternating current is transmitted to the transmitting coil 4 (namely, the primary side inductance coil L)1) Generates an alternating magnetic field around the receiving coil 5 (i.e., the secondary side inductance coil L)2) The voltage with the same frequency is induced in the high-frequency magnetic field, and is rectified and filtered by the rectifying circuit 7 and then supplied to the load 8 at the receiving end for use. The system is suitable for a wireless power distribution scene among the spacecrafts, in particular to the wireless power distribution process among the spacecrafts with the dynamically changing space, is skillfully improved on the basis of the prior art, and is additionally provided with a first switch S1A second switch S2And a third switch S3And a fourth switch S4These switch combinations and the primary second series compensation capacitor C3And a secondary side second series compensation capacitor C4Make LCC compensation structure and SS compensation structure carry out perfect combination, overall structure is compact, both can adapt to the resonance coupling, can be used to the magnetic induction coupling simultaneously, and just can realize the switching of two kinds of compensation forms through the control of switch combination, simple structure is reliable and the simple operation, both can use wireless distribution between remote spacecraft (long distance is for closely speaking, it also can correspond the medium-long distance between the spacecraft under the actual conditions), can be applied to wireless distribution between closely space spacecraft (closely also can be called as the short distance), when being applied to medium-long distance, control each switch action and make former limit second series compensation capacitance C3And a secondary side second series compensation capacitor C4The circuit is accessed, the circuit compensation topological structure is SS series connection type, the frequency is adjusted to enable the capacitance and the inductance to reach a resonance state, and then the circuit conducts magnetic resonance type wireless energy transmission; when the primary side compensation inductor L is applied to short distance, the primary side compensation inductor L is enabled to be controlled to actf1Primary side first series compensation capacitor C1And a primary side parallel compensation capacitor Cf1And a secondary side first series compensation capacitor C2Secondary side parallel compensation capacitor Cf2And secondary compensation inductance Lf2The access circuit, circuit compensation topological structure is the LCC type, adjustment frequency makes the electric capacity inductance reach the resonant condition and then the circuit carries out the wireless biography energy of magnetic induction formula, also the system adopts the effective switching of long distance and the wireless biography energy of short distance in the digital control mode realization, the problem of transmission distance and energy transmission efficiency can not be compromise among the current wireless charging technology has been solved, a novel energy supply mode is provided for the spacecraft, the suitability is strong, the work quality and the work efficiency of wireless charging process have wholly been promoted greatly, effectively promote the duration of spacecraft, and wireless distribution economic cost under the space environment has effectively been reduced.
As shown in a second preferred structural schematic diagram of fig. 2, the inter-spacecraft wireless power distribution system further includes, in addition to the structure of the embodiment shown in fig. 1, a main controller 9 for monitoring and controlling various state information parameters of the system, four switches are all connected to the main controller 9, the main controller 9 manually or automatically sends an instruction to control the on and off of the four switches, and the main controller 9 of the system can control the switches to perform manual or automatic operation: 1) manual mode: the main controller 9 sends an on or off instruction to each switch, thereby switching the long-distance and short-distance transmission modes; 2) pure automatic mode: the system preferably further comprises a distance monitoring device 10 connected with a main controller 9 as shown in fig. 3, the distance monitoring device 10 monitors the actual distance between the two spacecrafts, transmits the monitored result information data to the main controller 9, and presets a distance threshold value in the main controller 9, the main controller 9 automatically sends an instruction to control the on and off of the four switches according to the information data of the distance monitoring device 10, and controls the first switch S1 and the third switch S3 to be switched off and the second switch S2 and the fourth switch S4 to be switched on when the actual distance is greater than the distance threshold value, so that the primary side second series compensation capacitor C3 and the secondary side second series compensation capacitor C4 are connected to the circuit, the circuit compensation topological structure is an SS series type, and the frequency is adjusted to enable the capacitor to reach a resonance state, thereby the circuit performs magnetic resonance type wireless energy transfer; when the actual distance is smaller than the distance threshold, the first switch S1 and the third switch S3 are controlled to be closed, and the second switch S2 and the fourth switch S4 are controlled to be opened, so that the primary side compensation inductor Lf1, the primary side first series compensation capacitor C1, the primary side parallel compensation capacitor Cf1, the secondary side first series compensation capacitor C2, the secondary side parallel compensation capacitor Cf2 and the secondary side compensation inductor Lf2 are connected into a circuit, the circuit compensation topological structure is of an LCC type, and the frequency is adjusted to enable the capacitor inductor to reach a resonance state, so that the circuit conducts magnetic induction type wireless energy transfer.
Preferably, the transmitting end power supply 1 in the system is directly supplied with direct current by the voltage of a spacecraft bus.
Preferably, as shown in fig. 4, the transmitting end and the receiving end perform wireless communication through the non-contact Zigbee wireless communication unit 11 to transmit the working signal or the status information, and particularly, the system aims to implement wireless charging during non-contact aerospace, and complete electrical isolation needs to be performed between the primary side and the secondary side of the system, so that the primary side and the secondary side cannot be connected by a line, and only a wireless communication mode is adopted, but the non-contact Zigbee wireless communication unit 11 is used to perform wireless communication to transmit the working signal or the status information, and therefore, the power consumption is low, the data transmission is reliable and safe, the compatibility is strong, and the implementation cost is low.
Calculation example:
during long-distance transmission, the first switch S is controlled1And a third switch S3While the second switch S is turned off2And a fourth switch S4Closed so that the primary side second series compensation capacitor C3And a secondary side second series compensation capacitor C4And the circuit is accessed, the circuit compensation topological structure is in an SS series connection type, and the frequency is adjusted to enable the capacitance and the inductance to reach a resonance state, so that the circuit performs a magnetic resonance type wireless energy transmission mode.
The primary and secondary sides of the circuit are subjected to resonant coupling to perfect the functions of the primary and secondary side circuits, so that the system has high-power working capacity, can quickly generate resonance, and can eliminate partial inductive reactance in the circuit by series and parallel coupling capacitance elements and the like. The primary side coupling capacitor is used for balancing primary side leakage inductance and secondary side reaction inductance, so that the apparent power of a system is reduced, the power factor is improved, the secondary side coupling capacitor is used for reducing reactive power, increasing output power and integrally improving the working efficiency.
The operating frequency of the system can be expressed as:
f＝ω/2π (1)
for the SS series compensation topology structure at the moment, when the primary side inductance coil L1Secondary side inductance coil L2When connected in series with the corresponding resonant capacitors, the primary side inductance coil L is used for achieving the optimal performance1And secondary side inductance coil L2The natural resonant angular frequency w generally takes the value:
in the formula, C1A first series compensation capacitor on the primary side, C2A secondary side first series compensation capacitor, L1、L2A primary side inductance coil and a secondary side inductance coil respectively. The inductance of the primary and secondary side inductance coils can be calculated by the following formula:
in the formula, mu0＝4π×10-7H/m, which represents the vacuum permeability; r represents the coil radius; n represents the number of coil turns; a represents the wire cross-sectional radius.
The SS series resonant wireless power distribution system model can be represented by the following matrix equation:
short distanceWhen off-transmission, the first switch S is controlled1And a third switch S3Closing the simultaneous second switch S2And a fourth switch S4Is disconnected, so that the primary side compensates the inductance Lf1Primary side first series compensation capacitor C1And a primary side parallel compensation capacitor Cf1And a secondary side first series compensation capacitor C2Secondary side parallel compensation capacitor Cf2And secondary compensation inductance Lf2The circuit is accessed, the circuit compensation topological structure is of an LCC type, and the frequency is adjusted to enable the capacitance and the inductance to reach a resonance state, so that the circuit conducts magnetic induction type wireless energy transmission.
The LCC type compensation mode has the characteristics that the input impedance angle at the gain intersection point is zero, and the gain intersection point value does not change along with the coupling coefficient of the transformer, and simultaneously, the primary side current is constant, so that the system can work at a certain fixed frequency point to meet the requirement of unit power factor, and the voltage and current stress is small. Primary side inductance coil L1And secondary side inductance coil L2The self-inductance value of (2) can be measured by a multimeter.
Primary side compensation inductance L in LCC type compensation circuitf1Secondary side compensation inductance Lf2The calculation formula of (a) is as follows:
in combination with series resonance type wireless power transmission, when a system generates resonance, the conditions are as follows:
primary side parallel compensation capacitor C of parallel part in LCC type compensation circuitf1A compensation capacitor C connected in parallel with the secondary sidef2The capacity values are calculated as follows:
primary side first series compensation of series part in LCC type compensation circuitCompensated capacitor C1And a secondary side first series compensation capacitor C2Comprises the following steps:
C2＝C1+ΔC2 (9)
the invention also relates to a control method of the wireless power distribution system between the spacecrafts, which aims at the control method of the wireless power distribution system between the spacecrafts in the embodiment shown in the figures 1-4 and is suitable for the wireless power distribution scene between the spacecrafts, as shown in an optimal flow chart of the control method of the wireless power distribution system between the spacecrafts in the figure 5, the method firstly monitors the power state of the spacecrafts in the aerospace, monitors the distance relationship between the spacecrafts when electric energy transmission is needed among a plurality of spacecrafts, namely monitors the actual distance during the spaceflight, controls the wireless power distribution system between two spacecrafts meeting the distance relationship, and controls the first switch S when the actual distance is greater than the distance threshold value1And a third switch S3While the second switch S is turned off2And a fourth switch S4When the circuit is closed, the circuit compensation topology is SS series connection type, the working frequency is adjusted to enable the primary side and the secondary side to reach a resonance state, and magnetic resonance type wireless energy transmission is realized; when the actual distance is less than the distance threshold, the first switch S is controlled1And a third switch S3Closing the simultaneous second switch S2And a fourth switch S4The circuit is disconnected, the circuit compensation topology is of an LCC type, the working frequency is adjusted to enable the primary side and the secondary side to reach a resonance state, and magnetic induction type wireless energy transmission is realized; by controlling the first switch S1A second switch S2And a third switch S3And a fourth switch S4And then the switching of the working mode of the control system is carried out to meet the requirements of wireless power transmission at different intervals. The control method enables the LCC compensation structure and the SS compensation structure to be perfectly combined and freely switched, can realize the switching of two wireless energy transmission modes of resonance coupling and magnetic induction coupling by changing the digital control mode of the wireless power distribution of the spacecraft, and can be applied to medium and long distancesFrom wireless distribution between the spacecraft, can be applied to wireless distribution between the short distance spacecraft again, compromise transmission distance and energy transmission efficiency, promoted system operating mass and work efficiency greatly on the whole.
Preferably, the control method further comprises the step of arranging a main controller 9 for monitoring and controlling various state information parameters of the system in the system, and controlling the on and off of the four switches by manually or automatically sending instructions by utilizing the main controller 9. The main controller 9 can control each switch to perform manual or automatic operation: 1) manual mode: the main controller 9 sends an on or off instruction to each switch, thereby switching the long-distance and short-distance transmission modes; 2) pure automatic mode: the control method is also provided with a distance monitoring device 10 connected with the main controller 9, the distance monitoring device 10 is used for monitoring the actual distance between the two spacecrafts and transmitting the monitored result information data to the main controller 9, a distance threshold value is preset in the main controller 9, then the main controller 9 is utilized to automatically send instructions to control the on and off of the four switches according to the information data of the distance monitoring device 10, controlling the first switch S1 and the third switch S3 to be opened while the second switch S2 and the fourth switch S4 are closed when the actual distance is larger than the distance threshold, the primary side second series compensation capacitor C3 and the secondary side second series compensation capacitor C4 are connected into the circuit, the system enters an SS compensation network topological structure form to work so as to realize remote wireless electric energy transmission, the frequency is adjusted so that the capacitance inductance reaches a resonance state, and then the circuit conducts magnetic resonance type wireless energy transmission; when the actual distance is smaller than the distance threshold, the first switch S1 and the third switch S3 are controlled to be closed, and the second switch S2 and the fourth switch S4 are controlled to be opened, so that the primary side compensation inductor Lf1, the primary side first series compensation capacitor C1, the primary side parallel compensation capacitor Cf1, the secondary side first series compensation capacitor C2, the secondary side parallel compensation capacitor Cf2 and the secondary side compensation inductor Lf2 are connected into the circuit, the system enters an LCC compensation network topological structure to work to achieve near-distance wireless power transmission, and the frequency is adjusted to enable the capacitor inductor to reach a resonance state, so that the circuit conducts magnetic induction type wireless power transmission.
Preferably, in the process of wireless power transmission, the control method utilizes the spacecraft bus voltage to perform direct current power supply on the transmitting end power supply 1 of the wireless power distribution system.
Preferably, in the wireless power transmission process of the control method, the transmitting end and the receiving end of the wireless power distribution system perform wireless communication through the non-contact Zigbee wireless communication unit 11 to transmit the working signal or the status information, and therefore, the power consumption is low, the data transmission is reliable and safe, the compatibility is strong, and the implementation cost is low.
It should be noted that the above-mentioned embodiments enable a person skilled in the art to more fully understand the invention, without restricting it in any way. Therefore, although the present invention has been described in detail with reference to the drawings and examples, it will be understood by those skilled in the art that various changes and modifications can be made therein without departing from the spirit and scope of the invention.
Claims (10)
1. A wireless power distribution system between spacecrafts comprises a transmitting end power supply, a high-frequency inverter circuit, a transmitting end LCC compensation circuit, a transmitting coil, a receiving end LCC compensation circuit, a rectifying circuit and a receiving end load which are connected in sequence, wherein the transmitting coil and the receiving coil are connected in a non-contact mode, the transmitting end LCC compensation circuit comprises a primary side compensation inductor, a primary side first series compensation capacitor and a primary side parallel compensation capacitor which are mutually connected in series and parallel, the receiving end LCC compensation circuit comprises a secondary side first series compensation capacitor, a secondary side parallel compensation capacitor and a secondary side compensation inductor which are mutually connected in series and parallel, the wireless power distribution system is characterized by further comprising a first switch, a second switch, a primary side second series compensation capacitor, a third switch, a fourth switch and a secondary side second series compensation capacitor, wherein the first switch is connected with the primary side compensation inductor in series, the second switch and the primary side second series compensation capacitor are mutually connected in series, a series branch formed by the second switch and the primary side second series compensation capacitor is mutually connected in parallel with a series branch formed by the first switch, the primary side compensation inductor and the primary side first series compensation capacitor, and a series branch formed by the fourth switch and the secondary side second series compensation capacitor is mutually connected in parallel with a series branch formed by the third switch, the secondary side compensation inductor and the secondary side first series compensation capacitor;
when the circuit is applied to medium and long distances, the switching actions are controlled to enable the primary side second series compensation capacitor and the secondary side second series compensation capacitor to be connected into the circuit, the circuit compensation topological structure is in an SS series connection type, the frequency is adjusted to enable the capacitance and the inductance to reach a resonance state, and then the circuit conducts magnetic resonance type wireless energy transmission; when the circuit is applied to short distance, the switch action is controlled to enable the primary side compensation inductor, the primary side first series compensation capacitor, the primary side parallel compensation capacitor, the secondary side first series compensation capacitor, the secondary side parallel compensation capacitor and the secondary side compensation inductor to be connected into the circuit, the circuit compensation topological structure is of an LCC type, and the frequency is adjusted to enable the capacitance inductor to reach a resonance state so that the circuit can conduct magnetic induction type wireless energy transmission.
2. The inter-spacecraft wireless power distribution system according to claim 1, further comprising a main controller for monitoring and controlling various state information parameters of the system, wherein all four switches are connected with the main controller, and the main controller manually or automatically sends instructions to control the on and off of the four switches.
3. The inter-spacecraft wireless power distribution system according to claim 2, further comprising a distance monitoring device connected to the main controller, wherein the distance monitoring device monitors an actual distance between the two spacecraft and transmits information data to the main controller, the main controller automatically sends an instruction to control the four switches to be turned on and off according to the information data of the distance monitoring device, controls the first switch, the third switch to be turned off and the second switch and the fourth switch to be turned on and off simultaneously when the actual distance is greater than a distance threshold, and controls the first switch, the third switch to be turned on and the second switch and the fourth switch to be turned off simultaneously when the actual distance is less than the distance threshold.
4. An inter-spacecraft wireless power distribution system according to any of claims 1 to 3, wherein the transmitting power supply is supplied with direct current from a spacecraft busbar voltage.
5. The inter-spacecraft wireless power distribution system of claim 4, wherein the transmitting end and the receiving end wirelessly communicate through a non-contact Zigbee wireless communication unit to transmit operating signals or status information.
6. A control method of a wireless power distribution system between spacecrafts according to one of the claims 1-5, characterized in that the method firstly monitors the power state of the spacecrafts in the aviation space, when the electric energy transmission is needed among a plurality of spacecrafts, the distance relation between the spacecrafts is monitored, two wireless power distribution systems between the spacecrafts meeting the distance relation are controlled, when the distance relation is larger than the distance threshold value when the distance relation is applied to the medium and long distance, the first switch and the third switch are controlled to be switched off, the second switch and the fourth switch are controlled to be switched on, the circuit compensation topology is SS series connection type, and the magnetic resonance type wireless energy transmission is realized; when the distance relation is smaller than a distance threshold value when the device is applied to short distance, the first switch and the third switch are controlled to be closed, meanwhile, the second switch and the fourth switch are controlled to be opened, the circuit compensation topology is LCC type, and magnetic induction type wireless energy transfer is achieved; the digital control mode of the spacecraft wireless power distribution is changed by controlling the on and off states of the first switch, the second switch, the third switch and the fourth switch, so that the switching of the working modes of the system is controlled to meet the requirements of wireless power transmission at different intervals.
7. The control method according to claim 6, characterized in that a main controller for monitoring and controlling various state information parameters of the system is further arranged in the system, and the main controller is used for manually or automatically sending commands to control the on and off of the four switches.
8. The control method according to claim 7, further comprising a distance monitoring device connected with the main controller, wherein the distance monitoring device is used for monitoring the actual distance between the two spacecrafts and transmitting information data to the main controller, the main controller is used for automatically sending an instruction to control the on and off of the four switches according to the information data of the distance monitoring device, when the actual distance is greater than a distance threshold value, the first switch and the third switch are controlled to be off and the second switch and the fourth switch are controlled to be on and off, the system enters an SS compensation network topology structure to work to realize long-distance wireless power transmission, when the actual distance is less than the distance threshold value, the first switch and the third switch are controlled to be on and the second switch and the fourth switch are controlled to work, and when the actual distance is less than the distance threshold value, the system enters an LCC compensation network topology structure to work to realize short-.
9. The control method according to claim 8, wherein the spacecraft bus voltage is used for DC power supply of a transmitting end power supply of the wireless power distribution system during wireless power transmission.
10. The control method according to claim 8 or 9, wherein during the wireless power transmission, the transmitting end and the receiving end of the wireless power distribution system wirelessly communicate with each other via a non-contact Zigbee wireless communication unit to transmit the operating signal or the status information.
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| CN111146872B (en) * | 2019-12-31 | 2022-04-05 | 华为数字能源技术有限公司 | Wireless power transmission system |
| CN111200372B (en) * | 2020-02-04 | 2022-02-08 | 湖南大学 | Single-phase and three-phase integrated inverter power circuit, power equipment and electrified vehicle |
| CN111817452B (en) * | 2020-07-15 | 2023-11-07 | 国网河北省电力有限公司衡水供电分公司 | Wireless power transmission and reception system and method |
| CN112311106A (en) * | 2020-12-02 | 2021-02-02 | 青岛大学 | Single-stage full-bridge constant-current constant-voltage wireless charging device and control method thereof |
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