CN114243947A - Direct-current voltage stabilizing circuit of airplane power distribution system, design method and application - Google Patents

Direct-current voltage stabilizing circuit of airplane power distribution system, design method and application Download PDF

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Publication number
CN114243947A
CN114243947A CN202111520342.2A CN202111520342A CN114243947A CN 114243947 A CN114243947 A CN 114243947A CN 202111520342 A CN202111520342 A CN 202111520342A CN 114243947 A CN114243947 A CN 114243947A
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China
Prior art keywords
coupler
circuit
power distribution
distribution system
current voltage
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CN202111520342.2A
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Chinese (zh)
Inventor
于丰玮
白志强
刘卫芳
张静
秦亚南
高鹏飞
史超
隋政
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Commercial Aircraft Corp of China Ltd
Beijing Aeronautic Science and Technology Research Institute of COMAC
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Commercial Aircraft Corp of China Ltd
Beijing Aeronautic Science and Technology Research Institute of COMAC
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Priority to CN202111520342.2A priority Critical patent/CN114243947A/en
Publication of CN114243947A publication Critical patent/CN114243947A/en
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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
    • 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
    • H02J50/001—Energy harvesting or scavenging
    • 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
    • H02J50/50—Circuit arrangements or systems for wireless supply or distribution of electric power using additional energy repeaters between transmitting devices and receiving devices
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
    • H02M3/00—Conversion of dc power input into dc power output
    • H02M3/22—Conversion of dc power input into dc power output with intermediate conversion into ac
    • H02M3/24—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters
    • H02M3/28—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac
    • H02M3/325—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal
    • H02M3/335—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
    • Y02B70/00—Technologies for an efficient end-user side electric power management and consumption
    • Y02B70/10—Technologies improving the efficiency by using switched-mode power supplies [SMPS], i.e. efficient power electronics conversion e.g. power factor correction or reduction of losses in power supplies or efficient standby modes

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Inverter Devices (AREA)

Abstract

The invention provides a direct-current voltage stabilizing circuit of an airplane power distribution system, a design method and application, relates to the technical field of airplane power distribution, does not need communication and feedback between a load and a power supply, does not need a complex control means, and can realize direct-current voltage stabilizing output of the airplane power distribution system when the load jumps; the direct current voltage stabilizing circuit comprises a direct current power supply, a high-frequency inverter circuit, a first coupler, a resonance compensation loop, a second coupler, a rectifying circuit and a load; the direct-current power supply, the high-frequency inverter circuit and the first coupler are sequentially connected; the first end of the resonance compensation loop is coupled with the first coupler, and the second end of the resonance compensation loop is coupled with the second coupler; the second coupler, the rectifying circuit and the load are connected in sequence; the optimal dislocation range of the coupling coil between the first coupler and the resonance compensation loop and between the second coupler and the resonance compensation loop is 0-25 cm.

Description

Direct-current voltage stabilizing circuit of airplane power distribution system, design method and application
Technical Field
The invention relates to the technical field of airplane power distribution, in particular to a direct-current voltage stabilizing circuit of an airplane power distribution system without feedback, a design method and application.
Background
The multi-electric airplane using electric energy to replace hydraulic energy and air energy can effectively reduce the weight of an airplane power system, reduce oil consumption and improve the reliability and economy of the system, and is a necessary trend of future airplane development. With the continuous maturity and perfection of power electronic technology, the electrical system of the aircraft is gradually developing towards the direction of power electronization, and the boeing 787 aircraft applies a large number of power electronic technologies and devices, including variable frequency alternating current generators, variable voltage rectifiers, static converters, electric brake power supplies and the like. However, the output characteristics of the system become very complicated due to the application of a large number of nonlinear power electronic circuits, wherein a small variation of a certain parameter may cause a large variation in the electric quantities such as the system output voltage, current and the like, so in order to ensure stable output of the direct current voltage in the aircraft power distribution system during load jump, components such as INV, E-BPSU, SPU and the like in the aircraft are stabilized by using DC/DC circuits.
The basic principle of the DC/DC circuit used for the direct current voltage stabilization of the airplane power distribution system in the prior art is as follows: utilize divider resistance to gather output end voltage, transmit the sampling result to VFB end (feedback end), the signal that the feedback end will gather compares with given voltage, exports the result through operational amplifier, adjusts the carrier and produces corresponding PWM signal to this duty cycle that changes the switch tube, thereby realizes constant voltage closed-loop control. The method is characterized in that the switching tube is adjusted according to the target of reducing the difference value between the acquisition voltage and the given voltage, a relatively complex control strategy is needed, once the communication circuit is interfered, the feedback output end possibly delays or even cannot receive the acquisition signal, so that the output voltage overshoots, and the output voltage gradually tends to be stable after a plurality of cycles. Therefore, the DC/DC circuit has the problems of complicated control, low reliability of the feedback communication circuit, high cost, and the like.
Accordingly, there is a need to develop a feedback-free dc voltage regulator circuit, design method and application for an aircraft power distribution system that address the deficiencies of the prior art and solve or mitigate one or more of the problems set forth above.
Disclosure of Invention
In view of the above, the invention provides a direct current voltage stabilizing circuit of an aircraft power distribution system, a design method and an application thereof, which do not need communication and feedback between a load and a power supply, do not need a complex control means, and can realize direct current voltage stabilizing output of the aircraft power distribution system when the load jumps.
On one hand, the invention provides a direct current voltage stabilizing circuit of an airplane power distribution system, which comprises a direct current power supply, a high-frequency inverter circuit, a first coupler, a resonance compensation loop, a second coupler, a rectifying circuit and a load;
the direct-current power supply, the high-frequency inverter circuit and the first coupler are sequentially connected;
the first end of the resonance compensation loop is coupled with the first coupler, and the second end of the resonance compensation loop is coupled with the second coupler;
the second coupler, the rectifying circuit and the load are connected in sequence.
The above aspect and any possible implementation manner further provide an implementation manner that the high-frequency inverter circuit is a single-phase bridge inverter circuit composed of four high-frequency switching tubes.
The above aspects and any possible implementations further provide an implementation, where the first coupler includes a first coupling inductor and a first resonant capacitor connected in parallel; the second coupler comprises a second coupling inductor and a second resonance capacitor which are connected in series.
The above-mentioned aspect and any possible implementation manner further provide an implementation manner, where the resonant compensation loop includes a third coupling inductor, a fourth coupling inductor, and a third resonant capacitor, and the third coupling inductor, the third resonant capacitor, and the fourth coupling inductor are sequentially connected in parallel;
the third coupling inductor is coupled with the first coupling inductor; the fourth coupling inductor is coupled with the second coupling inductor.
The above-described aspect and any possible implementation manner further provide an implementation manner, and the optimal misalignment ranges of the coupling coils between the first coupler and the resonance compensation loop and between the second coupler and the resonance compensation loop are both 0-25 cm.
The above-mentioned aspect and any possible implementation manner further provide an implementation manner that, by adjusting the duty ratio of the second coupler, the voltage received by the load is made to be a certain value and the stability of the voltage at the time of load jump is improved.
The above aspect and any possible implementation further provide an implementation in which the high-frequency inverter circuit converts a direct current into an alternating current, and the frequency of the alternating current is the same as the resonant frequency of the first coupler, the resonant frequency of the resonance compensation circuit, and the resonant frequency of the second coupler.
The above-mentioned aspect and any possible implementation manner further provide an implementation manner, where the coupling inductors in the first coupler and the second coupler each use an inductor core with a rounded rectangular structure, and a coil material is wound around the inductor core.
The above-described aspects and any possible implementations further provide an implementation in which the coil material is litz wire wound from thousands of thin wires.
The above aspect and any possible implementation further provide an implementation in which the resonant compensation loop employs a bipolar DD coil, enabling decoupling of the two inductances L4, L5 of the intermediate loop.
In another aspect, the present invention provides a method for designing a dc voltage stabilizing circuit of an aircraft power distribution system, where the method includes the steps of:
s1, selecting device parameters: respectively determining the switching frequency of a switching tube in the high-frequency inverter circuit according to the resonant frequency to be realized by the direct-current voltage stabilizing circuit; determining parameters of coupling inductance and resonance capacitance in the first coupler, the resonance compensation loop and the second coupler by taking the resonance frequency as the resonance frequency of the first coupler, the resonance compensation loop and the second coupler;
s2, analyzing mutual inductance values of the coils at different dislocation distances, and determining the optimal dislocation range of the coupled coils between the first coupler and the resonance compensation loop and between the second coupler and the resonance compensation loop;
s3, simulating the direct current voltage stabilizing circuit according to the device parameters determined in S1 and the optimal dislocation range determined in S2, and determining the optimal duty ratio of the direct current voltage stabilizing circuit;
the condition of the optimal duty ratio is that the voltage received by the load can be kept stable when the load jumps;
and S4, building a real direct current voltage stabilizing circuit according to the device parameters determined in S1, the optimal dislocation range determined in S2 and the optimal duty ratio of S3.
In a further aspect, the invention provides an application of the direct current voltage stabilizing circuit of the aircraft power distribution system, wherein the direct current voltage stabilizing circuit is applied to a DC/DC power conversion scene of each element in the aircraft power distribution system.
The above aspects and any possible implementation further provide an implementation in which the elements are INV, E-BPSU or SPU elements, and may be in other scenarios requiring DC/DC power conversion.
Compared with the prior art, one of the technical schemes has the following advantages or beneficial effects: the direct-current voltage stabilizing circuit of the airplane power distribution system, provided by the invention, can realize direct-current voltage stabilizing output of the airplane power distribution system when the load changes without communication and feedback between the load and a power supply and without a complicated control means aiming at the problems of more complicated control, low reliability of a feedback communication circuit, higher cost and the like existing in the process of stabilizing the voltage by adopting a DC/DC circuit;
another technical scheme in the above technical scheme has the following advantages or beneficial effects: the design method provided by the invention is used for DC/DC power conversion in elements such as INV (static inverter), E-BPSU (electric brake power supply unit), SPU (start power unit) and the like in the airplane power distribution system, can effectively solve the problems of complex control of a DC/DC conversion circuit, low reliability of a feedback circuit, high cost and the like in the elements, realizes voltage-stabilized output when a load jumps, and ensures high transmission efficiency.
Of course, it is not necessary for any one product in which the invention is practiced to achieve all of the above-described technical effects simultaneously.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a topology diagram of a rectifying voltage regulator circuit according to one embodiment of the present invention;
FIG. 2 is a diagram of a model of a coupling coil provided in accordance with an embodiment of the present invention;
FIG. 3 is a graph of mutual inductance versus misalignment distance provided by an embodiment of the present invention;
FIG. 4 is a schematic diagram of a horizontal offset of a mutual inductor according to an embodiment of the present invention;
FIG. 5 is a diagram of a simulation model provided by one embodiment of the present invention;
fig. 6 is voltage and current waveforms of different jumps of the load according to an embodiment of the present invention, where the upper part of each waveform is a voltage waveform, and the lower part is a current waveform.
Detailed Description
For better understanding of the technical solutions of the present invention, the following detailed descriptions of the embodiments of the present invention are provided with reference to the accompanying drawings.
It should be understood that the described embodiments are only some embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In order to enable the aircraft power distribution system to output stable direct-current voltage when the load jumps, the invention provides a design method of a direct-current voltage stabilizing circuit of the aircraft power distribution system without feedback. The DC/DC power conversion circuit in the elements such as INV, E-BPSU, SPU and the like in the aircraft power distribution system is selected as an application scene. The whole circuit structure is composed of three parts, and is coupled together by two groups of mutual inductors, and a compensation capacitor is added in the system to make the system work in a resonance state. The circuit is modeled by using the principles of kirchhoff law, fundamental wave analysis method and the like, and the characteristic that the output voltage of the circuit is independent of load change can be obtained. The topology and design flow of the circuit is shown in fig. 1.
The circuit comprises three parts. The first part comprises a direct current power supply, a high-frequency inverter circuit and a coupler, wherein the direct current provided by the power supply is converted into alternating current with the same frequency as the resonant frequency of the coupler (namely the first coupler) formed by L3 and Cp through the high-frequency inverter circuit and then is transmitted to the coupler; the first coupler comprises a capacitor Cp and an inductor L3 which are arranged in parallel, the positive pole of the coupler is connected with the second positive pole end of the high-frequency inverter circuit through an inductor L2, and the negative pole of the coupler is directly connected with the second negative pole end of the high-frequency inverter circuit; a first positive terminal and a first negative terminal of the high-frequency inverter circuit are respectively connected with the positive pole and the negative pole of the direct-current power supply; an inductor L1 is connected in series between the first positive terminal of the high-frequency inverter circuit and the positive electrode of the direct-current power supply; the high-frequency inverter circuit is composed of four switching tubes. The second part is an intermediate resonance compensation loop and comprises an inductor L4, a capacitor Cd and an inductor L5 which are sequentially connected in parallel; where inductor L4 is coupled to the first section and inductor L5 is coupled to the following third section. The third part is a load end, energy is received by a coupler (namely an inductor L6 and a capacitor Cs which are connected in series in the figure 1) formed by L6 and Cs and is input into a subsequent rectifying circuit, and the duty ratio of the coupler at the load end is adjusted, so that the voltage received by the load end is a certain value and is kept stable when the load jumps.
The design method of the airplane power distribution system direct-current voltage stabilizing circuit without feedback comprises the following steps:
1) and (5) selecting the types of the components. A switching tube of the inverter circuit selects a high-frequency-resistant power MOSFET, and the parameter range of the inductance and the capacitance is determined according to the upper limit of the switching frequency which can be borne by the switching tube of the inverter; in the selection of the coupler, because the magnetic field at the corner of the conventional rectangular structure is extremely uneven, the coupling coil is prepared by adopting a novel rounded rectangular structure and winding litz wires, and meanwhile, the dislocation distance of the coupling coil is ensured not to exceed 25 cm. The invention adopts litz wire made by winding thousands of thin wires as coil material to reduce skin effect. The coupling coil with the round-corner rectangular structure is suitable for a first coupler and a second coupler; the middle resonance compensation loop adopts a bipolar DD coil, so that the two inductances L4 and L5 of the middle loop can be decoupled.
2) When the coupling inductance and the resonance capacitance in the coupler are designed, the parameters are determined according to the resonance frequency of the system. The resonant frequency of the system is calculated as follows:
Figure BDA0003408433830000061
in the formula L3、CpThe inductance and capacitance of the first coupler; l is6、CsThe inductance and capacitance of the second coupler.
3) A circuit is built according to the topological graph of FIG. 1, and the building process is as follows: the circuit is input by a direct current power supply, a single-phase bridge type inverter circuit is connected, the output frequency of the inverter circuit is the system resonance frequency, the output is output to an intermediate loop through a coupler composed of L3 and Cp, the intermediate loop is composed of three elements of Ld1, Cd and Ld2 which are connected in parallel, electric energy is output to a receiving loop through Ld2, the receiving loop receives energy through the coupler composed of L6 and Cs, then the receiving loop is connected with a single-phase bridge type uncontrolled rectifying circuit and a filter capacitor, power is supplied to a load, and a load resistor is switched to control the input circuit through a switching tube.
The invention determines the on-off frequency of the switching tube of the inverter circuit according to the resonant frequency of the system, and ensures that the current output by the inverter can enable the system to work in a resonant state.
4) According to the circuit structure, the circuit is modeled by a fundamental component method and kirchhoff law, and the output characteristic that the output voltage is independent of load change can be obtained. Specifically, the method comprises the following steps:
setting the DC power supply voltage as
Figure BDA0003408433830000071
Receiving input voltage and current of loop rectifier bridge
Figure BDA0003408433830000072
Output voltage, current are set to
Figure BDA0003408433830000073
Then there are:
Figure BDA0003408433830000074
Figure BDA0003408433830000075
is provided with L3And L4Mutual inductance between M1，L5And L6Mutual inductance between M2Through L2、L3、L4、L5Respectively at a current value of
Figure BDA0003408433830000076
Then there are:
Figure BDA0003408433830000077
Figure BDA0003408433830000078
Figure BDA0003408433830000079
Figure BDA00034084338300000710
Figure BDA00034084338300000711
simultaneous equations, one can obtain:
Figure BDA00034084338300000712
the method for determining the optimal dislocation range of the coupler applied to the direct-current voltage stabilizing circuit of the airplane power distribution system without feedback (namely the method for determining the dislocation distance of the coupling coil in the step 1) is as follows:
in practical application, the coupling coil is difficult to align without deviation, once the coil is dislocated, the transmission performance of the system is reduced, and therefore after a circuit topology is designed, the optimal dislocated range of the coupler needs to be determined. The coupled coil model is shown in fig. 2.
The calculation results of the mutual inductance of the coils obtained under different dislocation distances are shown in the following table:
offset distance 0cm 5cm 10cm 15cm 20cm 25cm 30cm
Mutual inductance/. mu.H 68.72 64.07 58.65 52.77 46.12 39.25 30.98
TABLE 1
The variation trend of the mutual inductance variation of the coil with the offset distance is calculated by taking 5cm as 1 unit and is shown in figure 3.
Analysis shows that after the horizontal offset distance of the coil exceeds 25cm, the change amplitude of the mutual inductance value of the coil is obviously increased, which is unfavorable for the transmission of the circuit power and efficiency, and on the other hand, because the power supply is a constant voltage source, the coupling coefficient is reduced when the coil is dislocated, the reflection impedance of the middle resonance compensation loop to the input loop is reduced, which causes the current of the input loop to be increased, and the thermal stability of the system is damaged, so that the optimal dislocation range of the coupling coil is determined to be 0-25 cm. The misalignment range refers to misalignment between the mutual coils L3 and L4 and misalignment between L5 and L6. The horizontal offset diagram is shown in fig. 4.
The invention further verifies the design content by using a simulink simulation model. The simulation model is shown in fig. 5. The load jumps at 0.3s and the resulting load voltage (up) and current (down) waveforms are shown in figure 6. As can be seen from the waveform diagram of fig. 5: when the load jumps by 0.3s, the output voltage is almost free of fluctuation under the condition of no feedback communication circuit and can be stabilized at 28V.
Therefore, the change of the load has no influence on the output voltage, and the output stability of the circuit is proved.
The novel voltage stabilizing circuit does not need a complex control strategy and feedback communication of an input end and an output end, can realize the voltage recovery immediately after the load jumps, and can effectively solve the problems.
The method for designing the direct-current voltage stabilizing circuit of the aircraft power distribution system without feedback provided by the embodiment of the application is described in detail. The above description of the embodiments is only for the purpose of helping to understand the method of the present application and its core ideas; meanwhile, for a person skilled in the art, according to the idea of the present application, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present application.
It is also noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a good or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such good or system. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a commodity or system that includes the element. "substantially" means within an acceptable error range, and a person skilled in the art can solve the technical problem within a certain error range to substantially achieve the technical effect.
The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in the examples of the present invention and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.

Claims (10)

1. A direct current voltage stabilizing circuit of an aircraft power distribution system is characterized by comprising a direct current power supply, a high-frequency inverter circuit, a first coupler, a resonance compensation loop, a second coupler, a rectifying circuit and a load;
the direct-current power supply, the high-frequency inverter circuit and the first coupler are sequentially connected;
the first end of the resonance compensation loop is coupled with the first coupler, and the second end of the resonance compensation loop is coupled with the second coupler;
the second coupler, the rectifying circuit and the load are connected in sequence.
2. The aircraft power distribution system direct current voltage stabilizing circuit of claim 1 wherein the high frequency inverter circuit is a single phase bridge inverter circuit consisting of four high frequency switching tubes.
3. The aircraft power distribution system direct current voltage regulation circuit of claim 1 wherein the first coupler comprises a first coupling inductance and a first resonant capacitance connected in parallel; the second coupler comprises a second coupling inductor and a second resonance capacitor which are connected in series.
4. The aircraft power distribution system direct current voltage stabilizing circuit of claim 3, wherein the resonant compensation loop comprises a third coupling inductor, a fourth coupling inductor and a third resonant capacitor, and the third coupling inductor, the third resonant capacitor and the fourth coupling inductor are connected in parallel in sequence;
the third coupling inductor is coupled with the first coupling inductor; the fourth coupling inductor is coupled with the second coupling inductor.
5. The aircraft power distribution system direct current voltage stabilizing circuit of claim 1, wherein the optimal misalignment ranges of the coupling coils between the first coupler and the resonant compensation loop and between the second coupler and the resonant compensation loop are both 0-25 cm.
6. The aircraft power distribution system DC voltage regulator circuit of claim 1 wherein the high frequency inverter circuit converts DC power to AC power having a frequency that is the same as the resonant frequency of the first coupler, the resonant frequency of the resonant compensation circuit, and the resonant frequency of the second coupler.
7. The aircraft power distribution system direct current voltage stabilizing circuit of claim 1, wherein the coupling inductors of the first coupler and the second coupler are inductor cores with rounded rectangular structures, and coil materials are wound on the inductor cores.
8. An aircraft power distribution system DC voltage regulator circuit according to claim 7 wherein the coil material is litz wire wound from thousands of thin wires.
9. A method of designing an aircraft power distribution system dc voltage regulator circuit according to any of claims 1 to 8, the method comprising the steps of:
s1, selecting device parameters: respectively determining the switching frequency of a switching tube in the high-frequency inverter circuit according to the resonant frequency to be realized by the direct-current voltage stabilizing circuit; determining parameters of coupling inductance and resonance capacitance in the first coupler, the resonance compensation loop and the second coupler by taking the resonance frequency as the resonance frequency of the first coupler, the resonance compensation loop and the second coupler;
s2, analyzing mutual inductance values of the coils at different dislocation distances, and determining the optimal dislocation range of the coupled coils between the first coupler and the resonance compensation loop and between the second coupler and the resonance compensation loop;
s3, simulating the direct current voltage stabilizing circuit according to the device parameters determined in S1 and the optimal dislocation range determined in S2, and determining the optimal duty ratio of the direct current voltage stabilizing circuit;
the condition of the optimal duty ratio is that the voltage received by the load can be kept stable when the load jumps;
and S4, building a real direct current voltage stabilizing circuit according to the device parameters determined in S1, the optimal dislocation range determined in S2 and the optimal duty ratio of S3.
10. Use of a direct current voltage regulator circuit according to any one of claims 1 to 8 in the context of DC/DC power conversion of components in an aircraft power distribution system.
CN202111520342.2A 2021-12-13 2021-12-13 Direct-current voltage stabilizing circuit of airplane power distribution system, design method and application Pending CN114243947A (en)

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