CN113394741B - Protection method for DC power supply system of multi-electric aircraft - Google Patents
Protection method for DC power supply system of multi-electric aircraft Download PDFInfo
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- CN113394741B CN113394741B CN202110639788.0A CN202110639788A CN113394741B CN 113394741 B CN113394741 B CN 113394741B CN 202110639788 A CN202110639788 A CN 202110639788A CN 113394741 B CN113394741 B CN 113394741B
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H3/00—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection
- H02H3/08—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection responsive to excess current
- H02H3/087—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection responsive to excess current for dc applications
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Abstract
The invention discloses a protection method for a direct-current power supply system of a multi-electric airplane, which adopts a novel direct-current solid-state circuit breaker to realize short-circuit protection of the direct-current power supply system of the multi-electric airplane. The novel direct current solid-state circuit breaker mainly comprises a first thyristor, a second thyristor, a first transformer, a second transformer, a first capacitor and a second capacitor; the circuit breaker has the advantages that the typical short-circuit fault of the system can be quickly responded without an additional detection and control circuit, the protection effect on a multi-electric airplane direct-current power supply system is realized, the structure is simple, fewer elements are adopted, current can flow to a load side only by flowing through a primary coil of a transformer and a thyristor, and the on-state loss is low.
Description
The technical field is as follows:
the invention belongs to the field of protection of a direct-current power supply system of a multi-electric aircraft, and particularly relates to a novel direct-current solid-state circuit breaker topological structure.
Background art:
with the continuous development of aviation industry, the multi-electric aircraft technology MEA has become the development trend of future advanced aircrafts, and is superior to the traditional aircrafts in various aspects such as structure, weight, reliability, maintainability, use cost and the like, so that new requirements are provided for the multi-electric aircraft electrical system, and the multi-electric aircraft MEA has the characteristics of high reliability and strong fault protection capability in the aspect of direct-current power supply system protection.
At present, corresponding protection devices are arranged on an airplane for short circuit faults, overvoltage faults, undervoltage faults, overcurrent faults and the like. The current protection device mainly protects against short-circuit faults or overcurrent faults, and commonly used current protection devices include fuses, circuit breakers and the like. The simplest and most-used protection device in a fuse direct-current system belongs to single-use equipment, and the protection device must be replaced after being fused and cannot be reused, and a circuit breaker can be reused, so that the current protection device is high in reliability and strong in practicability.
The direct current circuit breaker can be divided into a mechanical type, an all-solid-state type and a hybrid type, but the switching speed of the mechanical type and the all-solid-state type direct current circuit breaker is influenced by a mechanical switch, and the switching speed is slow. The all-solid-state dc circuit breaker has an excellent structure in the dc circuit breaker because of its advantages of high switching speed, capability of cutting off faults without arcing, light and sound, etc., and has been developed in recent years.
Application number cn202010301027.x discloses a bidirectional dc solid-state circuit breaker, which replaces a hall current sensor with an existing shunt, reducing production cost. The voltage and current conversion rate detection directly enters the system controller without isolation, and the fault rapid detection effect is realized. However, the circuit breaker still needs to be processed by a control system to complete the opening of the circuit breaker, and in addition, the circuit breaker needs to be additionally provided with a current detection circuit to complete the detection of fault current.
Application number CN201810446025.2 discloses a bidirectional dc solid-state circuit breaker, which can be applied in protection of dc power supply systems. The circuit breaker adopts a three-coil transformer to realize bidirectional energy flow, does not need a current detection and circuit breaker control circuit, uses less semiconductor switching elements and reduces the complexity of the circuit breaker. The use of a three coil transformer, however, increases the complexity of the circuit calculations.
The novel direct current solid-state circuit breaker protection device is provided for solving the problems that an existing direct current solid-state circuit breaker is complex in structure and high in on-state loss.
Disclosure of Invention
The invention aims to provide a method for protecting a multi-electric-aircraft direct-current power supply system based on a direct-current solid-state circuit breaker, which ensures the safe operation of the power supply system and mainly solves the problems of complex structure and high on-state loss of the existing direct-current solid-state circuit breaker. In particular, the present invention aims to improve the following aspects: novel direct current solid state circuit breaker protection device adopts the component less, and simple structure need not extra control circuit, and the current only flows through transformer primary and thyristor flow direction load side during the steady state, and the on-state loss is lower.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the bidirectional direct-current solid-state circuit breaker is connected in series in a multi-electric-aircraft direct-current power supply system, and when a typical short-circuit fault occurs in the multi-electric-aircraft direct-current power supply system, the bidirectional direct-current solid-state circuit breaker responds in time and is disconnected within microsecond time to isolate the fault; the bidirectional direct current solid-state circuit breaker mainly comprises a first thyristor, a second thyristor, a first transformer, a second transformer, a first capacitor and a second capacitor;
the bidirectional direct-current solid-state circuit breaker structure comprises a direct-current power supply (9), a first thyristor (1), a second thyristor (2), a first transformer primary coil (3), a first transformer secondary coil (4), a second transformer primary coil (5), a second transformer secondary coil (6), a first capacitor (7), a second capacitor (8), a first leading-out terminal (14), a second leading-out terminal (21), a third leading-out terminal (25) and a fourth leading-out terminal (26), wherein the anode of the first thyristor (1) and the synonym end of the first transformer primary coil (3) are connected to a connection point 17, and the cathode of the first thyristor (1) and the synonym end of the first transformer secondary coil (4) are connected to a connection point 18; the dotted terminal of the first transformer secondary coil (4) and the anode of the second capacitor (8) are connected to a connection point 24, and the cathode of the second capacitor (8) is used as a fourth leading-out terminal (26); the anode of the second thyristor (2) and the synonym terminal of the second transformer primary coil (5) are connected to a connection point 20, the connection point 20 and the connection point 18 intersect at the second leading-out terminal (21), the cathode of the second thyristor (2) and the synonym terminal of the second transformer secondary coil (6) are connected to a connection point 16, the connection point 16 and the connection point 15 intersect at the first leading-out terminal (14), the synonym terminal of the second transformer secondary coil (6) and the anode of the first capacitor (7) are connected to a connection point 23, the cathode of the first capacitor (7) is used as the third leading-out terminal (25), the anode of the direct current power supply (9) is connected with the first leading-out terminal (14), and the cathode of the direct current power supply (9) is connected with the third leading-out terminal (25) and the fourth leading-out terminal (26), a power supply system load is connected to the second lead-out terminal (21) and the fourth lead-out terminal (26).
The bidirectional direct current solid-state circuit breaker realizes bidirectional flow of energy through the first thyristor (1) and the second thyristor (2) which are arranged in opposite directions, wherein in a steady state, current flows to a load side through a primary coil of a transformer and the thyristors; when short circuit occurs, the first capacitor (7) and the second capacitor (8) are rapidly discharged, the secondary coil of the transformer is connected with the capacitors in series, fault transient current is gradually increased, the direction of induced current of the primary coil of the transformer is opposite to that of steady-state current, and thyristor current is gradually reduced to zero; a first resistor (10) and a first diode (11) are connected in series and then are connected in parallel to two sides of a primary coil (3) of the first transformer to form a follow current loop; a second resistor (13) and a second diode (12) are connected in series and then are connected in parallel to two sides of the primary coil (5) of the second transformer to form a follow current loop; after the bidirectional direct current solid-state circuit breaker is disconnected, the follow current loop is used for buffering energy of the primary coil of the inductor;
a protection method for a direct-current power supply system of a multi-electric airplane is characterized in that the direct-current solid-state circuit breaker device is connected in series in the power supply system, when the system has a short-circuit fault, the short-circuit current is increased instantly, and the circuit breaker detects the fault change of the system current and is disconnected in time, so that the safe operation of the power supply system is protected.
Compared with the prior art, the invention has the beneficial effects that:
1. from the short-circuit protection of a direct-current power supply system of a multi-electric airplane, the direct-current solid-state circuit breaker device effectively plays the advantage of rapidity of a solid-state circuit breaker and guarantees safe operation of the power supply system.
2. From the breaker structure, this circuit breaker uses the component fewly, and simple structure to adopt two transformers to replace the inductance, effectively reduced the circuit breaker volume.
3. In terms of system on-state loss, current can be transmitted to the load side only by flowing through the primary coil of the transformer and the thyristor, and the increased on-state loss caused by more semiconductor elements is effectively reduced.
The foregoing description is only an overview of the technical solutions of the present invention, and in order to make the technical means of the present invention more clearly understood, the present invention may be implemented in accordance with the content of the description, and in order to make the above description and other objects, features, and advantages of the present invention more clearly understandable, preferred embodiments are specifically described below.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a schematic diagram of the protection of a DC power supply system for a multi-electric aircraft;
fig. 2 is a structural diagram of a bidirectional dc solid-state circuit breaker designed according to the present invention;
FIG. 3 is a second capacitor positive discharge voltage waveform;
FIG. 4 is a first thyristor current waveform;
FIG. 5 is a first thyristor voltage waveform;
FIG. 6 is a load voltage waveform;
FIG. 7 is a side current waveform of a DC power supply system for a multi-electric aircraft;
in fig. 2, 1-first thyristor, 2-second thyristor, 3-primary coil of first transformer, 4-secondary coil of first transformer, 5-primary coil of second transformer, 6-secondary coil of second transformer, 7-first capacitor, 8-second capacitor, 14-first leading-out terminal, 21-second leading-out terminal, 25-third leading-out terminal, 26-fourth leading-out terminal, 15, 16, 17, 18, 20, 24-connection point
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
In the description of the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be connected or detachably connected or integrated; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The invention provides a method for protecting a direct current power supply system of a multi-electric aircraft, and a protection schematic diagram of the method is shown in figure 1. The direct-current solid-state circuit breaker is connected in series in a direct-current power supply system of the multi-power plane, when the system has short-circuit faults, the circuit breaker detects the faults in time and is disconnected in microsecond time, and the whole direct-current power supply system is protected.
The circuit topology of the bidirectional direct current solid-state circuit breaker for protecting the direct current power supply system is shown in figure 2.
The dotted terminal of the primary coil of the first transformer is connected with the anode of the direct current supply system, and the unlike terminal is connected with the anode of the first thyristor, so that a current forward circulation path is formed when the system energy flows in the forward direction. Therefore, in a steady state operation condition, a current is transmitted to the load side of the power supply system through the primary coil of the first transformer and the first thyristor.
The cathode of the second thyristor is connected with the anode of the direct current power supply system, and the anode of the second thyristor is connected with the synonym end of the primary coil of the second transformer, so that a current reverse circulation path when the system energy reversely flows is formed. Therefore, under the condition of steady-state operation, the current flows through the second thyristor and the primary coil of the second transformer and is transferred to the load side of the power supply system.
Through the two forward and reverse current circulation paths, the circuit breaker can be ensured to work normally in a bidirectional direct current power supply system.
When the circuit breaker works in an energy forward flow system, the first capacitor and the second capacitor immediately discharge in a fault transient state, discharge current flows through the secondary coil of the first transformer, and at the moment, the current induced by the primary coil of the first transformer is opposite to the current direction under the steady-state working condition of the primary coil, so that the current flowing through the first thyristor can gradually drop to zero, then the first thyristor is switched off, and the solid-state circuit breaker successfully isolates the system short-circuit fault. After the first thyristor is switched off, the primary coil of the first transformer completes residual energy dissipation through a freewheeling circuit formed by a resistor and a diode which are connected in parallel with the primary coil of the first transformer.
When the circuit breaker works in an energy reverse flow system, the first capacitor and the second capacitor discharge immediately in a fault transient state, discharge current flows through the secondary coil of the second transformer, at the moment, the current induced by the primary coil of the second transformer is opposite to the current direction under the steady-state working condition, therefore, the current flowing through the second thyristor can gradually drop to zero, then the second thyristor is switched off, and the solid-state circuit breaker successfully isolates the system short-circuit fault. After the second thyristor is disconnected, the primary coil of the second transformer completes residual energy dissipation through a freewheeling circuit formed by a resistor and a diode which are connected in parallel with the primary coil of the second transformer.
Aiming at a protection example of a multi-electric airplane direct-current power supply system, a multi-electric airplane direct-current power supply circuit and a breaker circuit are built in Saber simulation software, the novel direct-current solid-state breaker provided by the patent is connected between the power supply circuit and a load in series, then short-circuit fault occurrence is simulated, and the correctness and the reliability of the protection method are verified according to the response of the solid-state breaker when the system is in short-circuit fault.
The simulation experiment takes the forward flow of system energy as an example, in the experiment, when the short-circuit fault of the simulation system occurs when t is 0.5s, the short-circuit fault resistance is set to be Rf0.02 Ω. The direct-current power supply system of the multi-electric-aircraft adopts a high-voltage direct-current power supply system, the output voltage is 270V, the system is provided with a resistive load, and the resistance value of a resistor is 10 omega. Through simulation experiments, the transient response voltage and current waveforms of the relevant elements during the fault transient are shown in fig. 3 to 7.
As can be seen from fig. 3, when the system has a short-circuit fault, the second capacitor 8 is rapidly discharged, and the current induced in the primary winding 3 of the first transformer is opposite to the steady-state current of the first thyristor 1. Thus, as can be seen from fig. 4, the current of the first thyristor 1 drops rapidly to zero at the moment of the fault, and the voltage is reverse biased, as shown in fig. 5, and is thus completely switched off.
As can be seen from the load voltage waveform shown in fig. 6, the load voltage drops to zero rapidly within 10us, so that damage to the dc power supply system of the multi-level aircraft due to overvoltage caused by short-circuit fault is avoided. Fig. 7 is a current waveform of the side of the dc power supply system of the multi-electric aircraft, and it can be seen from the diagram that at the time of a fault, the circuit breaker does not cause a short-circuit current to return to the side of the dc power supply system of the multi-electric aircraft, thereby causing overcurrent damage to the system and effectively ensuring the safe operation of the power supply system.
The invention has the advantages that: the novel direct-current solid-state circuit breaker device has the advantages that the number of used elements of the circuit breaker is small, the structure is simple, two transformers are adopted to replace inductors, the size of the circuit breaker is effectively reduced, the advantage of rapidity of the solid-state circuit breaker is effectively played, the safe operation of a power supply system is guaranteed, meanwhile, no current can be transmitted to a load side only through a primary coil and a thyristor of the transformer, and the on-state loss increased by more semiconductor elements flowing through the circuit breaker is effectively reduced
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (1)
1. A protection method for a multi-electric airplane direct-current power supply system is characterized in that a bidirectional direct-current solid-state circuit breaker is connected in series in the multi-electric airplane direct-current power supply system, and when a typical short-circuit fault occurs in the multi-electric airplane direct-current power supply system, the bidirectional direct-current solid-state circuit breaker responds in time and is disconnected within microsecond time to isolate the fault; the bidirectional direct current solid-state circuit breaker mainly comprises a first thyristor, a second thyristor, a first transformer, a second transformer, a first capacitor and a second capacitor;
the bidirectional direct-current solid-state circuit breaker structure specifically comprises a first thyristor (1), a second thyristor (2), a first transformer primary coil (3), a first transformer secondary coil (4), a second transformer primary coil (5), a second transformer secondary coil (6), a first capacitor (7) and a second capacitor (8), a first leading-out terminal (14), a second leading-out terminal (21), a third leading-out terminal (25) and a fourth leading-out terminal (26), wherein the anode of the first thyristor (1) and the synonym end of the first transformer primary coil (3) are connected to a connection point 17, and the cathode of the first thyristor (1) and the synonym end of the first transformer secondary coil (4) are connected to a connection point 18; the dotted terminal of the first transformer secondary coil (4) and the anode of the second capacitor (8) are connected to a connection point 24, and the cathode of the second capacitor (8) is used as a fourth leading-out terminal (26); the anode of the second thyristor (2) and the synonym terminal of the second transformer primary coil (5) are connected to a connection point 20, the connection point 20 and the connection point 18 intersect at the second leading-out terminal (21), the cathode of the second thyristor (2) and the synonym terminal of the second transformer secondary coil (6) are connected to a connection point 16, the connection point 16 and the connection point 15 intersect at the first leading-out terminal (14), the synonym terminal of the second transformer secondary coil (6) and the anode of the first capacitor (7) are connected to a connection point 23, the cathode of the first capacitor (7) is used as the third leading-out terminal (25), the anode of the direct current power supply (9) is connected with the first leading-out terminal (14), and the cathode of the direct current power supply (9) is connected with the third leading-out terminal (25) and the fourth leading-out terminal (26), a power supply system load is connected to the second lead-out terminal (21) and the fourth lead-out terminal (26).
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