CN217183040U - A DC voltage regulator circuit for aircraft power distribution system - Google Patents

Abstract

The utility model provides an aircraft power distribution system direct current voltage stabilizing circuit, which relates to the technical field of aircraft power distribution, does not need communication and feedback between a load and a power supply, does not need complex control means, and can realize the direct current voltage stabilizing output of the aircraft 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

A DC voltage regulator circuit for aircraft power distribution system

technical field

The utility model relates to the technical field of aircraft power distribution, in particular to a DC voltage stabilizer circuit of an aircraft power distribution system without feedback.

Background technique

The use of electric energy instead of hydraulic energy and gas energy for multi-electric aircraft can effectively reduce the weight of the aircraft power system, reduce fuel consumption, and improve the reliability and economy of the system, which is an inevitable trend of future aircraft development. With the continuous maturity and improvement of power electronic technology, the electrical system of the aircraft is gradually developing in the direction of power electronics. The Boeing 787 aircraft has applied a large number of power electronic technologies and devices, including variable frequency alternators, transformer rectifiers, static Inverter, electric brake power supply, etc. However, the application of a large number of nonlinear power electronic circuits will make the output characteristics of the system very complicated. A small change in a certain parameter may cause a large change in the output voltage, current and other electrical quantities of the system. Therefore, in order to ensure that the load jumps When the stable output of the DC voltage in the aircraft power distribution system is used, the components in the aircraft such as INV, E-BPSU, and SPU all use DC/DC circuits to stabilize the voltage.

The basic principle of the DC/DC circuit used in the DC voltage regulation of the aircraft power distribution system in the prior art is to use the voltage dividing resistor to collect the output terminal voltage, transmit the sampling result to the VFB terminal (feedback terminal), and the feedback terminal will collect the collected voltage. The obtained signal is compared with the given voltage, the result is output through the operational amplifier, and the carrier is adjusted to generate the corresponding PWM signal, so as to change the duty cycle of the switch tube, thereby realizing constant voltage closed-loop control. This method is essentially that the switch is adjusted according to the goal of reducing the difference between the acquisition voltage and the given voltage, which requires a relatively complex control strategy, and once the communication circuit is disturbed, the feedback output may be delayed or even unable to receive the acquisition. signal, so that the output voltage overshoot occurs, and it can gradually become stable after a few cycles. Therefore, the DC/DC circuit has problems such as complicated control, low reliability of the feedback communication circuit, and high cost.

Therefore, it is necessary to study a DC voltage regulator circuit for an aircraft power distribution system without feedback to deal with the deficiencies of the prior art, so as to solve or alleviate one or more of the above problems.

Utility model content

In view of this, the utility model provides a DC voltage stabilizer circuit for an aircraft power distribution system, which does not require communication and feedback between the load and the power source, and does not require complex control means, which can realize the aircraft power distribution system when the load jumps. regulated DC output.

In one aspect, the present invention provides a DC voltage regulator circuit for an aircraft power distribution system, the DC voltage regulator circuit includes a DC power supply, a high-frequency inverter circuit, a first coupler, a resonance compensation circuit, a second coupler, and a rectifier circuit and load;

the DC power supply, the high frequency inverter circuit and the first coupler are connected in sequence;

The first end of the resonance compensation loop is coupled and connected to the first coupler, and the second end is coupled and connected to the second coupler;

The second coupler, the rectifier circuit and the load are connected in sequence.

According to the above aspect and any possible implementation manner, an implementation manner is further provided, wherein the high-frequency inverter circuit is a single-phase bridge inverter circuit composed of four high-frequency switch tubes.

In the above aspect and any possible implementation manner, an implementation manner is further provided, wherein the first coupler includes a first coupled inductor and a first resonant capacitor connected in parallel; the second coupler includes a second coupler connected in series A coupled inductor and a second resonant capacitor.

In the above aspect and any possible implementation manner, an implementation manner is further provided, wherein the resonance compensation loop includes a third coupled inductor, a fourth coupled inductor, and a third resonance capacitor, the third coupled inductor, the The third resonance capacitor and the fourth coupling inductor are connected in parallel in sequence;

The third coupled inductor is coupled and connected to the first coupled inductor; the fourth coupled inductor is coupled and connected to the second coupled inductor.

The above-mentioned aspects and any possible implementation manners further provide an implementation manner, the coupling between the first coupler and the resonance compensation circuit and between the second coupler and the resonance compensation circuit The optimal dislocation range of the coils is 0-25cm.

The above aspects and any possible implementation manners further provide an implementation manner, by adjusting the duty cycle of the second coupler to make the voltage received by the load to be a certain value and to increase the voltage at the load Stability during transitions.

The above aspect and any possible implementation manner further provide an implementation manner, wherein the high-frequency inverter circuit converts direct current into alternating current, and the frequency of the alternating current is the same as the resonant frequency of the first coupler, the The resonant frequency of the resonant compensation circuit and the resonant frequency of the second coupler are the same.

In the above aspect and any possible implementation manner, an implementation manner is further provided, wherein the coupled inductors in the first coupler and the second coupler both use inductor cores with a rounded rectangular structure, and in all the coupled inductors A coil material is wound on the inductor core.

According to the above aspect and any possible implementation manner, an implementation manner is further provided, wherein the coil material is a Litz wire wound by thousands of thin wires.

According to the above aspect and any possible implementation manner, an implementation manner is further provided, wherein the resonant compensation loop adopts a bipolar DD coil, which can decouple the two inductances L4 and L5 of the intermediate loop.

On the other hand, the present invention provides a method for designing a DC voltage regulator circuit of an aircraft power distribution system as described above, wherein the steps of the method include:

S1. Device parameter selection: Determine the switching frequency of the switch tube in the high-frequency inverter circuit according to the resonant frequency to be realized by the DC voltage regulator circuit; use the above resonant frequency as the first coupler, the resonant compensation circuit and the second coupler. Resonant frequency, determine the parameters of the coupling inductance and resonant capacitance in the first coupler, the resonant compensation circuit and the second coupler;

S2, analyze the mutual inductance value of the coil under different dislocation distances, and determine the optimal dislocation range of the coupling coil between the first coupler and the resonance compensation circuit and between the second coupler and the resonance compensation circuit;

S3. According to the device parameters determined in S1 and the optimal dislocation range determined in S2, simulate and simulate the DC voltage regulator circuit as described above, and determine the optimal duty cycle of the DC voltage regulator circuit;

The condition of the optimal duty cycle is that the voltage received by the load can remain stable when the load jumps;

S4. According to the device parameters determined in S1, the optimal dislocation range determined in S2, and the optimal duty cycle of S3, build a physical DC voltage regulator circuit.

On the other hand, the present invention provides an application of the DC voltage stabilizer circuit in an aircraft power distribution system as described above, and the DC voltage stabilizer circuit is applied to the scene of DC/DC power conversion of each element in the aircraft power distribution system. .

The above aspects and any possible implementation manners further provide an implementation manner, where each element is an INV, E-BPSU or SPU element, and may also be other scenarios requiring DC/DC power conversion.

Compared with the prior art, one of the above-mentioned technical solutions has the following advantages or beneficial effects: the DC voltage-stabilizing circuit of the aircraft power distribution system provided by the present utility model is more complicated for the control that adopts the DC/DC circuit to stabilize the voltage. In addition, the feedback communication circuit has problems such as low reliability and high cost, which can realize the communication and feedback between the load and the power supply, and does not require complex control methods, and can realize the DC voltage stabilized output of the aircraft power distribution system when the load changes. ;

Another technical solution in the above technical solutions has the following advantages or beneficial effects: a design method proposed by the present invention for the DC voltage stabilizer circuit topology in the aircraft power distribution system can be applied to the INV (static transformer) in the aircraft power distribution system. DC/DC power conversion in components such as current transformer), E-BPSU (electric brake power supply unit), SPU (starting power unit), etc., can effectively solve the problem that the control of the DC/DC conversion circuit in the above components is complicated and the reliability of the feedback circuit is low. , the problem of high cost, realize the regulated output when the load jumps, and ensure high transmission efficiency.

Of course, any product implementing the present invention does not necessarily need to achieve all the above-mentioned technical effects at the same time.

Description of drawings

In order to illustrate the technical solutions of the embodiments of the present invention more clearly, the accompanying drawings required in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can also be obtained from these drawings without any creative effort.

1 is a topology diagram of a rectifier and voltage regulator circuit provided by an embodiment of the present invention;

2 is a model diagram of a coupling coil provided by an embodiment of the present invention;

Fig. 3 is the variation trend of mutual inductance with dislocation distance provided by an embodiment of the present utility model;

4 is a schematic diagram of horizontal dislocation of the mutual inductance coil provided by an embodiment of the present invention;

5 is a simulation model diagram provided by an embodiment of the present utility model;

6 is a voltage and current waveform diagram under different load jump conditions provided by an embodiment of the present invention, wherein the upper part of each group of waveform diagrams is a voltage waveform diagram, and the lower part is a current waveform diagram.

Detailed ways

In order to better understand the technical solutions of the present invention, the embodiments of the present invention are described in detail below with reference to the accompanying drawings.

It should be clear that the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present invention.

In order to make the aircraft power distribution system output a stable DC voltage when the load jumps, the utility model proposes a design method of the DC voltage regulator circuit of the aircraft power distribution system without feedback. The DC/DC power conversion circuit in the INV, E-BPSU, SPU and other components in the aircraft power distribution system is selected as the application scenario. The whole circuit structure consists of three parts, which are coupled together through two sets of mutual inductance coils, and a compensation capacitor needs to be added to the system to make it work in a resonant state. Using Kirchhoff's law and fundamental wave analysis method to model the circuit, the characteristics of its output voltage independent of load variation can be obtained. The topology and design flow of the circuit are shown in Figure 1.

The circuit consists of three parts. The first part includes a DC power supply, a high-frequency inverter circuit and a coupler. The DC power provided by the power source is converted into an AC power with the same frequency as the resonant frequency of the coupler (ie, the first coupler) formed by L3 and Cp through the high-frequency inverter circuit. It is then sent to the coupler; the first coupler includes a capacitor Cp and an inductor L3, which are arranged in parallel, the positive pole of the coupler is connected to the second positive pole of the high-frequency inverter circuit through the inductor L2, and the negative pole of the coupler is directly connected to the high The second negative terminal of the high frequency inverter circuit is connected to the second negative terminal of the high frequency inverter circuit; the first positive terminal and the first negative terminal of the high frequency inverter circuit are respectively connected to the positive and negative terminals of the DC power supply; the first positive terminal of the high frequency inverter circuit is connected to the positive terminal of the DC power supply An inductor L1 is connected in series between them; the high-frequency inverter circuit is composed of four switch tubes. The second part is an intermediate resonance compensation loop, including an inductance L4, a capacitor Cd and an inductance L5 connected in parallel in sequence; the inductance L4 is coupled with the first part, and the inductance L5 is coupled with the third part behind. The third part is the load end, which receives the energy through the coupler formed by L6 and Cs (ie, the inductance L6 and the capacitor Cs in series in Figure 1) and inputs it into the rectifier circuit behind to adjust the duty cycle of the coupler at the load end. It can make the voltage received by the load side to a certain value and keep stable when the load jumps.

The steps of the design method of the DC voltage stabilizer circuit of the aircraft power distribution system without feedback of the present invention include:

1) Carry out the selection of each component. The switch tube of the inverter circuit is made of high-frequency power MOSFET, and the parameter range of the inductance and capacitance is determined according to the upper limit of the switching frequency that the switch tube of the inverter can withstand. It is extremely uneven, so the utility model adopts a new type of rounded rectangular structure and uses Litz wire to prepare a coupling coil, and at the same time, it is necessary to ensure that the dislocation distance of the coupling coil does not exceed 25cm. The utility model adopts the Litz wire wound by thousands of thin wires as the coil material to reduce the skin effect. The coupling coil of the rounded rectangular structure is suitable for the first coupler and the second coupler; the middle resonance compensation loop adopts a bipolar DD coil, which can decouple the two inductances L4 and L5 of the middle loop.

2) When designing the coupling inductance and resonant capacitor in the coupler, its parameters are determined according to the resonant frequency of the system. The formula for calculating the resonant frequency of the system is as follows:

In the formula, L ₃ and C _p are the inductance and capacitance values of the first coupler; L ₆ and C _s are the inductance and capacitance values of the second coupler.

3) Build the circuit according to the topology diagram in Figure 1. The construction process is as follows: the circuit is input by a DC power supply, connected to a single-phase bridge inverter circuit, and the output frequency of the inverter circuit is the system resonant frequency. The coupler is output to the intermediate circuit. The intermediate circuit is composed of three elements Ld1, Cd, and Ld2 in parallel. The power is output to the receiving circuit through Ld2. The receiving circuit receives the energy through the coupler composed of L6 and Cs, followed by a single-phase bridge. The rectifier circuit and filter capacitor are not controlled, and finally power is supplied to the load, and the load resistance is switched to control the input circuit through the switch tube.

The utility model determines the breaking frequency of the switching tube of the inverter circuit according to the resonance frequency of the system, so as to ensure that the current output by the inverter can make the system work in the resonance state.

4) According to the above circuit structure, the circuit is modeled by the fundamental wave component method and Kirchhoff's law, and the output characteristics of the output voltage independent of the load change can be obtained. specifically:

接收回路整流桥的输入电压、电流设为

输出电压、电流设为

则有：Let the DC power supply voltage be

The input voltage and current of the receiving loop rectifier bridge are set to

The output voltage and current are set to

Then there are:

则有：Let the mutual inductance between L ₃ and L ₄ be M ₁ , the mutual inductance between L ₅ and L ₆ be M ₂ , and the current values flowing through L ₂ , L ₃ , L ₄ , and L ₅ are respectively

Then there are:

Simultaneous equations, we can get:

The content of the method for determining the optimal dislocation range of the coupler (that is, the method for determining the dislocation distance of the coupling coil that does not exceed 25cm in the above-mentioned step 1) applied to the DC voltage stabilizer circuit of the aircraft power distribution system without feedback of the present invention) is as follows:

Since the above-mentioned DC voltage stabilizer circuit is used in practical applications, it is difficult for the coupling coil to align without deviation. Once the coil is misaligned, the transmission performance of the system will be degraded. Therefore, after designing the circuit topology, it is necessary to determine the optimal misalignment of the coupler. The method is to use Ansys Maxwell to analyze the mutual inductance value of the coil under different dislocation distances, and to analyze the change trend of the system mutual inductance when the dislocation distance is 0-30cm with a change of 5cm as a unit. The coupled coil model is shown in Figure 2.

The calculation results of the coil mutual inductance obtained under different dislocation distances are as follows:

offset distance 0cm 5cm 10cm 15cm 20cm 25cm 30cm Mutual inductance/μH 68.72 64.07 58.65 52.77 46.12 39.25 30.98

Table 1

Taking 5cm as a unit, the change trend of the coil mutual inductance change with the dislocation distance is calculated as shown in Figure 3.

The analysis shows that when the horizontal offset distance of the coil exceeds 25cm, the change range of the mutual inductance value of the coil will increase significantly, which is unfavorable for the transmission of power and efficiency of the circuit. When dislocation occurs, the coupling coefficient decreases, and the reflected impedance of the intermediate resonance compensation loop to the input loop decreases, which will lead to an increase in the input loop current and destroy the thermal stability of the system. Therefore, the optimal dislocation range of the coupling coil is determined to be 0-25cm. The range of misalignment refers to the misalignment between mutual inductance coils L3 and L4 and the misalignment between L5 and L6. The schematic diagram of horizontal dislocation is shown in Figure 4.

The utility model further verifies the above design content by using the simulink simulation model. The simulation model is shown in Figure 5. The load jumps at 0.3s, and the obtained load voltage (upper) and current (lower) waveforms are shown in Figure 6. It can be seen from the waveform diagram in Figure 5 that when the load jumps for 0.3s, the output voltage has almost no fluctuation and can be stabilized at 28V without the feedback communication circuit.

It can be seen that the change of the load has no effect on the output voltage, which proves the output stability of the circuit of the present invention.

The novel voltage stabilizing circuit of the utility model does not need complicated control strategies and feedback communication of the input and output terminals, and can realize the immediate voltage recovery after the load jumps, which can effectively solve the above problems.

The design method of a DC voltage regulator circuit of an aircraft power distribution system without feedback provided by the embodiments of the present application has been described in detail above. The description of the above embodiment is only used to help understand the method of the present application and its core idea; meanwhile, for those of ordinary skill in the art, according to the idea of the present application, there will be changes in the specific embodiment and the scope of application, In conclusion, the content of this specification should not be construed as a limitation on the present application.

It should also be noted that the terms "comprising", "comprising" or any other variation thereof are intended to encompass non-exclusive inclusion, such that a commodity or system comprising a list of elements includes not only those elements, but also includes not explicitly listed other elements, or elements inherent to the commodity or system. Without further limitation, an element defined by the phrase "comprising a..." does not preclude the presence of additional identical elements in the article or system that includes the element. "Approximately" means that within an acceptable error range, those skilled in the art can solve the technical problem within a certain error range, and basically achieve the technical effect.

The terms used in the embodiments of the present invention are only for the purpose of describing specific embodiments, and are not intended to limit the present invention. As used in the embodiments of the present invention and the appended claims, the singular forms "a," "the," and "the" are intended to include the plural forms as well, unless the context clearly dictates otherwise.

Claims (8)

1. an aircraft power distribution system DC voltage regulator circuit, is characterized in that, described DC voltage regulator circuit comprises DC power supply, high frequency inverter circuit, first coupler, resonance compensation circuit, second coupler, rectifier circuit and load; the DC power supply, the high frequency inverter circuit and the first coupler are connected in sequence; The first end of the resonance compensation loop is coupled and connected to the first coupler, and the second end is coupled and connected to the second coupler; The second coupler, the rectifier circuit and the load are connected in sequence. 2 . The DC voltage stabilizer circuit of an aircraft power distribution system according to claim 1 , wherein the high-frequency inverter circuit is a single-phase bridge inverter circuit composed of four high-frequency switch tubes. 3 . 3 . The DC voltage regulator circuit of an aircraft power distribution system according to claim 1 , wherein the first coupler comprises a first coupled inductor and a first resonant capacitor connected in parallel; the second coupler comprises a series connected A second coupled inductor and a second resonant capacitor. 4. The DC voltage regulator circuit of an aircraft power distribution system according to claim 3, wherein the resonant compensation loop comprises a third coupled inductor, a fourth coupled inductor and a third resonant capacitor, the third coupled inductor, The third resonance capacitor and the fourth coupling inductor are connected in parallel in sequence; The third coupled inductor is coupled and connected to the first coupled inductor; the fourth coupled inductor is coupled and connected to the second coupled inductor. 5 . The DC voltage stabilizer circuit of an aircraft power distribution system according to claim 1 , wherein the connection between the first coupler and the resonance compensation circuit and between the second coupler and the resonance compensation circuit is 5 . The dislocation range of the inter-coupling coils is 0-25 cm. 6 . The DC voltage regulator circuit of an aircraft power distribution system according to claim 1 , wherein the frequency of the alternating current at the output end of the high-frequency inverter circuit is the same as the resonant frequency of the first coupler and the resonant compensation circuit. 7 . The resonant frequency of and the resonant frequency of the second coupler are the same. 7 . The DC voltage regulator circuit of an aircraft power distribution system according to claim 1 , wherein the coupled inductors in the first coupler and the second coupler are inductance cores with a rounded rectangular structure, and 7 . A coil material is wound around the inductor core. 8 . The DC voltage stabilizer circuit of an aircraft power distribution system according to claim 7 , wherein the coil material is a Litz wire wound from thousands of thin wires. 9 .

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