Hybrid DC circuit breaker and control method thereof
By combining the design of hybrid DC circuit breakers and utilizing components such as ultra-fast mechanical switches and thyristors, zero-current and arc-free interruption of the space power station system during faults is achieved, solving the problem of the inability of the space power station system to effectively interrupt faults and ensuring the safety and stability of the power system.
Patent Information
- Application Number
- CN202511153582.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-08-18
- Publication Date
- 2025-11-21
AI Technical Summary
Space power station systems cannot effectively interrupt power failures, and current technologies cannot achieve zero-current, arc-free interruption.
A hybrid DC circuit breaker is adopted, which includes a combination design of main current branch, transfer branch, pre-dissipation branch and energy dissipation branch. It utilizes components such as ultra-fast mechanical switches, insulated gate bipolar transistors and thyristors to achieve fault current transfer and energy dissipation.
It achieves zero-current, arc-free interruption of the space power station system in the event of a fault, ensuring the safe and stable operation of the power system.
Smart Images
Figure CN120999515A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of power transmission technology, and in particular to a hybrid DC circuit breaker and its control method. Background Technology
[0002] Space-based power station systems, unaffected by Earth's atmosphere, seasonal variations, and day-night cycle, can continuously receive stable solar radiation for 99% of the year, making them suitable for large-scale solar power generation. The power transmission system is an indispensable component of a space-based power station system; however, given the space environment, power outages cannot be resolved manually. Summary of the Invention
[0003] The purpose of this application is to provide a hybrid DC circuit breaker and its control method to achieve effective interruption of a space power station system in the event of a fault.
[0004] To achieve the above objectives, this application provides the following solution.
[0005] In a first aspect, this application provides a hybrid DC circuit breaker, which is applied to a space power station system. The hybrid DC circuit breaker includes: a main current branch, a transfer branch, a pre-dissipation branch, and an energy dissipation branch.
[0006] The transfer branch, the pre-dissipation branch, and the energy dissipation branch are all connected in parallel with the main flow branch;
[0007] The main current branch is used for the flow of operating current; the operating current is the current flowing through the hybrid DC circuit breaker when the space power station system is operating normally.
[0008] The transfer branch is used for the transfer and flow of fault current; the fault current is the current flowing through the hybrid DC circuit breaker when a short-circuit fault occurs in the space power station system.
[0009] The pre-dissipation branch is used to generate an energy dissipation turn-on voltage based on the fault current; the energy dissipation turn-on voltage is used to turn on the energy dissipation branch.
[0010] The energy dissipation branch is used to absorb the fault current.
[0011] Optionally, the main current path includes: an ultra-fast mechanical switch, a first insulated-gate bipolar transistor, a second insulated-gate bipolar transistor, a first diode, and a second diode;
[0012] The ultra-fast mechanical switch, the first insulated-gate bipolar transistor (IGBT), and the second IGBT are connected in series in sequence. The first diode is connected in anti-parallel to the first IGBT, and the second diode is connected in anti-parallel to the second IGBT.
[0013] Optionally, when the space power station system is operating normally, the fast mechanical switch, the first insulated gate bipolar transistor, and the second insulated gate bipolar transistor are all turned on;
[0014] In the event of a short-circuit fault in the space power station system, the fast mechanical switch, the first insulated-gate bipolar transistor, and the second insulated-gate bipolar transistor are all turned off.
[0015] Optionally, the transfer branch includes: a third insulated gate bipolar transistor;
[0016] The third insulated gate bipolar transistor is disconnected during normal operation of the space power station system;
[0017] At the initial moment when a short-circuit fault is detected in the space power station system, the third insulated gate bipolar transistor is turned on, and when the opening distance of the ultra-fast mechanical switch of the main flow branch reaches the rated opening distance, the third insulated gate bipolar transistor is turned off.
[0018] Optionally, the transfer branch includes: the pre-dissipation branch includes: a first thyristor, a second thyristor, a fourth insulated gate bipolar transistor, a switching capacitor, and a resistor;
[0019] The first thyristor, the switching capacitor, and the second thyristor are connected in series to form an energy dissipation auxiliary branch.
[0020] The fourth insulated gate bipolar transistor, the switching capacitor, and the resistor are connected in series to form a pre-charge branch;
[0021] The energy dissipation auxiliary branch and the pre-charge branch share the switching capacitor;
[0022] The energy dissipation auxiliary branch is connected in parallel with the main flow branch;
[0023] One end of the pre-charging branch is connected to the input end of the main flow branch, and the other end of the pre-charging branch is grounded.
[0024] Optionally, when the space power station system is operating normally, the fourth insulated gate bipolar transistor is turned on to precharge the switching capacitor using the operating current, and the fourth insulated gate bipolar transistor is turned off when the precharging is complete.
[0025] Optionally, in the event of a short-circuit fault in the space power station system, when the opening distance of the ultra-fast mechanical switch of the main flow branch reaches the rated opening distance, the first thyristor and the second thyristor are turned on. At this time, the fault current flows through the breaking capacitor to charge the breaking capacitor. When the voltage across the breaking capacitor reaches the energy dissipation turn-on voltage, the first thyristor and the second thyristor are turned off.
[0026] Optionally, the energy dissipation branch includes a metal oxide surge arrester.
[0027] Secondly, this application provides a control method for the above-mentioned hybrid DC circuit breaker, the control method comprising the following steps:
[0028] Under normal operation of the space power station system, the main flow branch is controlled to conduct, and the operating current flows through the main flow branch;
[0029] In the event of a short-circuit fault in the space power station system, perform the following steps:
[0030] At the initial moment when a short-circuit fault is detected in the space power station system, the main flow branch is disconnected and the transfer branch is turned on to allow the fault current to flow through the transfer branch.
[0031] When the opening distance of the ultra-fast mechanical switch in the main flow branch reaches the rated opening distance, the transfer branch is controlled to disconnect and the pre-dissipation branch is controlled to conduct, so that the fault current flows through the pre-dissipation branch and the fault current is used to charge the switching capacitor in the pre-dissipation branch.
[0032] When the voltage across the switching capacitor reaches the energy dissipation turn-on voltage, the pre-dissipation branch is disconnected, and the energy dissipation branch is put into use.
[0033] Optionally, the control method further includes:
[0034] When the space power station system is operating normally, when the voltage across the switching capacitor in the pre-dissipation branch is less than a preset voltage threshold, the fourth insulated gate bipolar transistor in the pre-dissipation branch is turned on, and the operating current is used to pre-charge the switching capacitor in the pre-dissipation branch. When the pre-charging is completed, the fourth insulated gate bipolar transistor is turned off.
[0035] According to the specific embodiments provided in this application, this application has the following technical effects.
[0036] This application provides a hybrid DC circuit breaker and its control method. The combination of the main current branch, transfer branch, pre-dissipation branch and energy dissipation branch in this application can realize zero-current arc-free interruption of the space power station system when a fault occurs. Attached Figure Description
[0037] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0038] Figure 1 This is a circuit diagram of a hybrid DC circuit breaker provided in one embodiment of this application.
[0039] Figure 2 A flowchart illustrating a control method for a hybrid DC circuit breaker provided in one embodiment of this application.
[0040] Figure 3 This is a schematic diagram of the current path of a hybrid DC circuit breaker in a space power station system provided in an embodiment of this application during normal operation.
[0041] Figure 4 This is a schematic diagram of the current path of a hybrid DC circuit breaker at the initial moment of fault detection, provided as an embodiment of this application.
[0042] Figure 5 This is a schematic diagram of the current path of a hybrid DC circuit breaker when the opening distance of an ultra-fast mechanical switch in a main flow branch reaches the rated opening distance, as provided in an embodiment of this application.
[0043] Figure 6 This is a schematic diagram of the current path of a hybrid DC circuit breaker when the voltage across the switching capacitor reaches the energy dissipation turn-on voltage, as provided in an embodiment of this application. Detailed Implementation
[0044] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0045] To make the above-mentioned objectives, features and advantages of this application more apparent and understandable, the application will be further described in detail below with reference to the accompanying drawings and specific embodiments.
[0046] In one exemplary embodiment, such as Figure 1 As shown, a hybrid DC circuit breaker is provided, including: a main current flow branch, a transfer branch, a pre-dissipation branch, and an energy dissipation branch;
[0047] The transfer branch, the pre-dissipation branch, and the energy dissipation branch are all connected in parallel with the main flow branch;
[0048] The main current branch is used for the flow of operating current; the operating current is the current flowing through the hybrid DC circuit breaker when the space power station system is operating normally.
[0049] The transfer branch is used for the transfer and flow of fault current; the fault current is the current flowing through the hybrid DC circuit breaker when a short-circuit fault occurs in the space power station system.
[0050] The pre-dissipation branch is used to generate an energy dissipation turn-on voltage based on the fault current; the energy dissipation turn-on voltage is used to turn on the energy dissipation branch.
[0051] The energy dissipation branch is used to absorb the fault current.
[0052] In another exemplary embodiment, the aforementioned main current branch is connected in series with an ultra-fast mechanical switch and a load transfer switch. The main current branch is used for current flow during normal operation of the space power station system; the transfer branch is used to conduct in the event of a short-circuit fault in the power station, transferring the fault current flowing through the main current branch to the transfer branch; the pre-dissipation branch is used to pre-charge the switching capacitor therein, attract the fault current flowing through the main current branch to the energy dissipation auxiliary branch, and generate an energy dissipation conduction voltage based on the fault current; the energy dissipation branch is used to conduct under the energy dissipation conduction voltage, absorbing the fault current and dissipating it in the form of heat.
[0053] Furthermore, such as Figure 1 As shown, the main current branch includes: an ultra-fast mechanical switch (UFD), a first insulated-gate bipolar transistor (IGBT) T1, a second IGBT T2, a first diode D1, and a second diode D2; the transfer branch includes: a third IGBT T3; the pre-dissipation branch includes a pre-charge branch and an energy dissipation auxiliary branch, wherein the pre-charge branch includes: a fourth IGBT T6, a breaking capacitor C, and a resistor R; the energy dissipation auxiliary branch includes: a first thyristor T4, a second thyristor T5, and a breaking capacitor C, and the pre-charge branch and the energy dissipation auxiliary branch share the breaking capacitor C; the energy dissipation branch includes: a metal oxide surge arrester (MOV).
[0054] In one exemplary embodiment, a control method for the hybrid DC circuit breaker of the above embodiments is provided, such as... Figure 2 As shown, the control method executes steps 101 and 102 when the space power station system is operating normally, and executes steps 103-105 when a short circuit fault occurs in the space power station system.
[0055] Step 101: Control the main current flow branch to conduct, so that the operating current can flow through the main current flow branch.
[0056] Step 102: When the voltage across the switching capacitor in the pre-dissipation branch is less than a preset voltage threshold, the fourth insulated gate bipolar transistor in the pre-dissipation branch is turned on to pre-charge the switching capacitor in the pre-dissipation branch using the operating current, and the fourth insulated gate bipolar transistor is turned off when the pre-charging is completed.
[0057] Step 103: At the initial moment when the space power station system detects a short circuit fault, the main flow branch is disconnected and the transfer branch is turned on to allow the fault current to flow through the transfer branch.
[0058] Step 104: When the opening distance of the ultra-fast mechanical switch in the main flow branch reaches the rated opening distance, control the transfer branch to disconnect and control the pre-dissipation branch to conduct, so that the fault current flows through the pre-dissipation branch and the fault current is used to charge the switching capacitor in the pre-dissipation branch.
[0059] Step 105: When the voltage across the switching capacitor reaches the energy dissipation turn-on voltage, the pre-dissipation branch is controlled to disconnect, and at this time, the energy dissipation branch is put into use.
[0060] In another exemplary embodiment, the specific implementation principle of the above control method is as follows:
[0061] When the space power station system is operating normally, the current path is as follows: Figure 3 As shown, the switching capacitor C can be pre-charged during this stage, triggering the fourth insulated-gate bipolar transistor T6. The space power station system pre-charges the switching capacitor C, and the charging current path is as follows. Figure 3 As shown, the quad insulated-gate bipolar transistor T6 is turned off after charging is complete.
[0062] Let time t0 be the time of fault occurrence. At this time, a short-circuit fault occurs on the right side of the hybrid DC circuit breaker. At time t1, the space station system detects the fault and sends a trip command to the hybrid DC circuit breaker. This triggers the third insulated-gate bipolar transistor T3, turning off the fast mechanical switch UFD, the first insulated-gate bipolar transistor T1, and the second insulated-gate bipolar transistor T2. The fault current is transferred from the main current path to the transfer path, allowing the fast mechanical switch UFD to complete zero-current interruption. The fast mechanical switch UFD takes 2ms to complete the entire disconnection process. The current path during the transfer phase is as follows... Figure 4 As shown.
[0063] At time t2, the fast mechanical switch UFD reaches its rated opening distance, triggering the first thyristor T4 and the second thyristor T5, and turning off the third insulated-gate bipolar transistor T3. At this time, the switching capacitor C continues to charge under the action of the fault current, and the current path is as follows. Figure 5 As shown, the voltage charged to the space power station system at time t3 will peak during fault current and then gradually decrease.
[0064] At time t4, the charge reaches the operating voltage of the metal oxide surge arrester (MOA), i.e., the energy dissipation turn-on voltage. The MOA then begins operation, dissipating the fault energy. The current path is as follows: Figure 6 As shown. At time t5, the fault current decays to 0, the fault interruption is completed, and the thyristors in the circuit turn off naturally.
[0065] This application provides a hybrid DC circuit breaker, which is a forced-commutation hybrid high-voltage DC circuit breaker that uses IGBTs and thyristors as the main switching elements. It can disconnect various faults in a space power station system and realize arc-free breaking of the ultra-fast mechanical switches under zero current.
[0066] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.
[0067] This document uses specific examples to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. Furthermore, those skilled in the art will recognize that, based on the ideas of this application, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this application.
Claims
1. A hybrid DC circuit breaker, characterized in that, The hybrid DC circuit breaker is applied to a space power station system. The hybrid DC circuit breaker includes: a main flow branch, a transfer branch, a pre-dissipation branch, and an energy dissipation branch. The transfer branch, the pre-dissipation branch, and the energy dissipation branch are all connected in parallel with the main flow branch; The main current branch is used for the flow of operating current; the operating current is the current flowing through the hybrid DC circuit breaker when the space power station system is operating normally. The transfer branch is used for the transfer and flow of fault current; the fault current is the current flowing through the hybrid DC circuit breaker when a short-circuit fault occurs in the space power station system. The pre-dissipation branch is used to generate an energy dissipation turn-on voltage based on the fault current; the energy dissipation turn-on voltage is used to turn on the energy dissipation branch. The energy dissipation branch is used to absorb the fault current.
2. The hybrid DC circuit breaker according to claim 1, characterized in that, The main circuit includes: an ultra-fast mechanical switch, a first insulated-gate bipolar transistor, a second insulated-gate bipolar transistor, a first diode, and a second diode; The ultra-fast mechanical switch, the first insulated-gate bipolar transistor (IGBT), and the second IGBT are connected in series in sequence. The first diode is connected in anti-parallel to the first IGBT, and the second diode is connected in anti-parallel to the second IGBT.
3. The hybrid DC circuit breaker according to claim 2, characterized in that, Under normal operating conditions of the space power station system, the fast mechanical switch, the first insulated gate bipolar transistor, and the second insulated gate bipolar transistor are all turned on; In the event of a short-circuit fault in the space power station system, the fast mechanical switch, the first insulated-gate bipolar transistor, and the second insulated-gate bipolar transistor are all turned off.
4. The hybrid DC circuit breaker according to claim 1, characterized in that, The transfer branch includes: a third insulated-gate bipolar transistor; The third insulated gate bipolar transistor is disconnected during normal operation of the space power station system; At the initial moment when a short-circuit fault is detected in the space power station system, the third insulated gate bipolar transistor is turned on, and when the opening distance of the ultra-fast mechanical switch of the main flow branch reaches the rated opening distance, the third insulated gate bipolar transistor is turned off.
5. The hybrid DC circuit breaker according to claim 1, characterized in that, The transfer branch includes: the pre-dissipation branch includes: a first thyristor, a second thyristor, a fourth insulated gate bipolar transistor, a switching capacitor, and a resistor; The first thyristor, the switching capacitor, and the second thyristor are connected in series to form an energy dissipation auxiliary branch. The fourth insulated gate bipolar transistor, the switching capacitor, and the resistor are connected in series to form a pre-charge branch; The energy dissipation auxiliary branch and the pre-charge branch share the switching capacitor; The energy dissipation auxiliary branch is connected in parallel with the main flow branch; One end of the pre-charging branch is connected to the input end of the main flow branch, and the other end of the pre-charging branch is grounded.
6. The hybrid DC circuit breaker according to claim 5, characterized in that, When the space power station system is operating normally, when the voltage across the switching capacitor in the pre-dissipation branch is less than a preset voltage threshold, the fourth insulated gate bipolar transistor is turned on, and the operating current is used to pre-charge the switching capacitor. When the pre-charging is completed, the fourth insulated gate bipolar transistor is turned off.
7. The hybrid DC circuit breaker according to claim 5, characterized in that, In the event of a short circuit fault in the space power station system, when the opening distance of the ultra-fast mechanical switch of the main flow branch reaches the rated opening distance, the first thyristor and the second thyristor are turned on. At this time, the fault current flows through the interrupting capacitor to charge the interrupting capacitor. When the voltage across the interrupting capacitor reaches the energy dissipation turn-on voltage, the first thyristor and the second thyristor are turned off.
8. The hybrid DC circuit breaker according to claim 1, characterized in that, The energy dissipation branch includes: a metal oxide surge arrester.
9. A control method for a hybrid DC circuit breaker according to any one of claims 1-8, characterized in that, The control method includes the following steps: Under normal operation of the space power station system, the main flow branch is controlled to conduct, and the operating current flows through the main flow branch; In the event of a short-circuit fault in the space power station system, perform the following steps: At the initial moment when a short-circuit fault is detected in the space power station system, the main flow branch is disconnected and the transfer branch is turned on to allow the fault current to flow through the transfer branch. When the opening distance of the ultra-fast mechanical switch in the main flow branch reaches the rated opening distance, the transfer branch is controlled to disconnect and the pre-dissipation branch is controlled to conduct, so that the fault current flows through the pre-dissipation branch and the fault current is used to charge the switching capacitor in the pre-dissipation branch. When the voltage across the switching capacitor reaches the energy dissipation turn-on voltage, the pre-dissipation branch is disconnected, and the energy dissipation branch is put into use.
10. The control method according to claim 9, characterized in that, The control method further includes: When the space power station system is operating normally, when the voltage across the switching capacitor in the pre-dissipation branch is less than a preset voltage threshold, the fourth insulated gate bipolar transistor in the pre-dissipation branch is turned on, and the operating current is used to pre-charge the switching capacitor in the pre-dissipation branch. When the pre-charging is completed, the fourth insulated gate bipolar transistor is turned off.