Airplane ground static power supply with direct current compensation function

Abstract

This utility model discloses an aircraft ground static voltage converter with DC compensation function. It includes an aircraft ground static voltage converter and a DC compensation device. The aircraft ground static voltage converter includes an AC input interface, an input contactor, a rectifier module, an inverter module, an output contactor, and an output interface. The AC input interface is connected to the rectifier module via the input contactor. The rectifier module is connected to the inverter module via a DC bus. The inverter module is connected to the output interface via the output contactor. The DC compensation device includes a charging module, an energy storage module, and a DC / DC module. The AC input interface is connected to the charging module, the charging module is connected to the energy storage module, the energy storage module is connected to the DC / DC module, and the DC / DC module is connected to the DC bus. This utility model has advantages such as ensuring continuous and stable output of high-quality AC power and meeting the power requirements of aircraft.

Description

Technical Field

[0001] This utility model relates to the field of aircraft ground static power supply technology, specifically an aircraft ground static power supply with DC compensation function. Background Technology

[0002] Voltage sag refers to the phenomenon where the effective value of the supply voltage suddenly drops and then rises back to the normal voltage level within a short period of time. The duration is generally no more than 2 seconds. With the significant increase in the complexity and uncertainty of airport power systems, voltage sag occurs frequently, posing a severe challenge to the safety and stability of some important and sensitive loads (equipment).

[0003] The 115V / 200V, 400Hz aircraft ground static power supply is currently the mainstream ground power equipment used by civil aircraft at home and abroad. Its working principle is: it uses three-phase mains power as the input source, and after rectification, inversion and filtering, it outputs high-quality 115V / 200V, 400Hz three-phase four-wire AC power to meet the power needs of multiple aircraft models.

[0004] The aircraft ground static power supply is a power electronic conversion device that does not generate energy itself. However, when a voltage dip occurs (the residual voltage is less than 90% of the power system voltage), the power system will not be able to provide enough energy, and the coil-like components inside the device will not be able to remain engaged, thus causing the aircraft ground static power supply to stop working.

[0005] When an aircraft is powered by a ground-based static voltage converter, if the input voltage of the power supply experiences a temporary drop, the power supply will shut down as a protective measure. However, airport power supply networks are complex, and multiple ground power supplies are often operating simultaneously on a single line. This can easily lead to localized, large-scale power failure alarms, which not only affect the aircraft's normal power supply but also cause damage to onboard equipment, thereby affecting the normal operation of flights and causing economic losses to users.

[0006] Aircraft ground static variable power supplies have a large power capacity and require high stability of the grid supply voltage. Upgrading existing airport power grids to eliminate the impact of voltage dips on sensitive equipment is not only difficult but also very costly. Therefore, it is necessary to invent an aircraft ground static variable power supply that can still operate normally when voltage dips occur in the power system, thus addressing the adverse effects of voltage dips on aircraft from within the power supply itself. Utility Model Content

[0007] The purpose of this invention is to overcome the shortcomings of the prior art and provide an aircraft ground static power supply with DC compensation function that ensures continuous and stable output of high-quality AC power and meets the power needs of aircraft.

[0008] The technical solution adopted by this utility model to solve its technical problem is: An aircraft ground static power supply with DC compensation function is characterized in that: it is provided with an aircraft ground static power supply and a DC compensation device. The aircraft ground static power supply includes a mains input interface, an input contactor, a rectifier module, an inverter module, an output contactor, and an output interface. The mains input interface is connected to the rectifier module via the input contactor. The rectifier module is connected to the inverter module via a DC bus. The inverter module is connected to the output interface via the output contactor. The DC compensation device includes a charging module, an energy storage module, and a DC / DC module. The mains input interface is connected to the charging module, the charging module is connected to the energy storage module, the energy storage module is connected to the DC / DC module, and the DC / DC module is connected to the DC bus. When the aircraft ground static power supply is operating normally, the 50Hz three-phase AC power is rectified and inverted, and the output interface outputs high-quality 115V / 220V 400Hz AC power to supply the aircraft. It also charges the energy storage module through the charging module, completing energy storage. When a voltage dip occurs in the mains power, the energy storage module discharges to stabilize the DC bus voltage, ensuring the normal operation of the aircraft ground static power supply inverter circuit. When the voltage returns to normal, the DC compensation device stops outputting, and the aircraft ground static power supply continues to operate using mains power. This ensures that the power supply is unaffected by the mains power, can operate uninterruptedly, and outputs high-quality power, guaranteeing a continuous and normal power supply to the aircraft. It solves the problem of mains voltage dips affecting power supply operation directly from the power supply itself, without needing to address grid instability, thus possessing superior economic and practical value.

[0009] This utility model also includes an auxiliary interface module and a control board. The auxiliary interface module is equipped with a sampling circuit, which collects the mains input voltage and the DC bus voltage. The voltage signal collected by the sampling circuit of the auxiliary interface module is transmitted to the control board, which is connected to the charging module, the energy storage module, and the DC / DC module respectively. The control board receives power index sampling signals from the mains and DC bus. When a voltage dip in the mains is detected, the control board controls the energy storage module to work, quickly responding to adjust the DC bus voltage, maintaining the normal operation of the inverter module, ensuring continuous output of high-quality AC power, and achieving adaptive compensation.

[0010] The aircraft ground static variable power supply of this utility model also includes an input filtering module and an output filtering module. The input filtering module is located between the input contactor and the rectifier module, and the output filtering module is located between the inverter module and the output contactor. The input filtering module suppresses high-frequency interference from the power grid and prevents high-order harmonics generated by the rectifier module from being fed back to the power grid, thereby reducing pollution to the power grid. The output filtering module is used to filter out high-frequency components in the PWM wave output by the inverter, providing pure sinusoidal AC power.

[0011] The input filtering module of this invention uses an input transformer, and the output filtering module uses an output transformer.

[0012] The input transformer described in this invention is a phase-shifting transformer; it transforms the three-phase power from the mains power grid into six-phase or twelve-phase power, achieving multi-phase rectification and significantly reducing input current harmonics.

[0013] The output transformer described in this utility model is an isolation step-down transformer; it achieves electrical isolation and voltage reduction, ensuring that the 115V / 200V 400Hz AC power supply is electrically isolated from the mains power supply, thereby improving electrical safety.

[0014] The aircraft ground static power supply of this utility model also includes a processor module and a user operation module. The user operation module includes a display screen. The auxiliary interface module is connected to the processor module, and the processor module is connected to the display screen.

[0015] The control board of this invention is connected to the processor module via a communication adapter board; data transmission with the processor module is achieved through the communication adapter board.

[0016] The control board and communication adapter board of this utility model transmit data bidirectionally; the processor module and communication adapter board transmit data bidirectionally.

[0017] The aircraft ground static power supply of this utility model also includes a relay module. The user operation module includes a button. The button's start / stop signal is transmitted to the processor module. After processing, the processor module issues a control command to drive the relay module to control the opening and closing of the output contactor K2.

[0018] The beneficial effects of this utility model are as follows: When the aircraft ground static power supply is working normally, the 50Hz three-phase AC power is rectified and inverted, and the output interface outputs high-quality 115V / 220V 400Hz AC power to supply the aircraft. The charging module also charges the energy storage module, completing energy storage. When the mains voltage drops, the energy storage module discharges to stabilize the DC bus voltage, ensuring the normal operation of the aircraft ground static power supply inverter circuit. When the voltage returns to normal, the DC compensation device stops outputting, and the aircraft ground static power supply continues to operate using mains power. This ensures that the power supply is not affected by the mains power, can operate uninterruptedly, and outputs high-quality power, guaranteeing a continuous and normal power supply to the aircraft. It solves the problem of the mains voltage drop affecting the power supply's operation from the power supply itself, without needing to address the problem of grid instability, and has superior economic and practical value. Attached Figure Description

[0019] Figure 1 This is an electrical principle block diagram of an aircraft ground static power supply with DC compensation function.

[0020] Figure 2 This is the electrical schematic diagram of an aircraft ground static power supply with DC compensation function.

[0021] Reference numerals: AC power input interface - X1, input contactor - K1, input transformer - T1, rectifier module - A1, inverter module - A2, output transformer - T2, output contactor - K2, output interface - X2, auxiliary interface module - A5, relay module - A6, processor module - A8, display screen - A13, button and indicator light module - A14; Charging module - A22, Energy storage module - A25, DC / DC module - A21, Control board - A28, Communication conversion board - A12. Detailed Implementation

[0022] The present invention will now be described in conjunction with the accompanying drawings and embodiments.

[0023] As shown in the attached figure, an aircraft ground static power supply with DC compensation function includes an aircraft ground static power supply and a DC compensation device. The aircraft ground static power supply includes a mains input interface X1, an input contactor K1, an input filter module, a rectifier module A1, an inverter module A2, an output filter module, an output contactor K2, and an output interface X2. The mains input interface X1 is connected to the input terminal of the input filter module via the input contactor K1. In this embodiment, the input contactor K1 is controlled to open and close by the main switch of the aircraft ground static power supply. The output terminal of the input filter module is connected to the input terminal of the rectifier module A1. The output terminal of the rectifier module A1 is connected to the input terminal of the inverter module A2 via a DC bus. The output terminal of the inverter module A2 is connected to the input terminal of the output filter module. The output terminal of the output filter module is connected to the output interface X2 via the output contactor K2. The DC compensation device includes a charging module A22, an energy storage module A25, and a DC / DC module A21. The mains input interface X1 is connected to the input terminal of the charging module A22 via an input contactor K1. The output terminal of the charging module A22 is connected to the input terminal of the energy storage module A25. The output terminal of the energy storage module A25 is connected to the input terminal of the DC / DC module A21. The output terminal of the DC / DC module A21 is connected to the DC bus. When the aircraft ground static power supply is operating normally, the 50Hz three-phase AC power is rectified and inverted, and then outputs high-quality 115V / 220V 400Hz three-phase four-wire AC power to the aircraft. It also charges the energy storage module via a charging module, completing energy storage. When a voltage dip occurs in the mains power, the energy storage module discharges, and the DC / DC module provides the required voltage to the DC bus, ensuring the normal operation of the aircraft ground static power supply's inverter circuit. When the voltage returns to normal, the DC compensation device stops outputting, and the aircraft ground static power supply continues to operate using mains power. This ensures that the power supply is unaffected by mains power, can operate uninterruptedly, and outputs high-quality power, guaranteeing a continuous and normal power supply to the aircraft. It solves the problem of mains voltage dips affecting power supply operation directly from the power supply itself, without needing to address grid instability, thus possessing superior economic and practical value.

[0024] In this embodiment, input contactor K1 controls the switching on and off of mains power; the input filter module suppresses high-frequency interference from the power grid and prevents high-order harmonics generated by rectifier module A1 from feeding back to the power grid, reducing pollution to the power grid; rectifier module A1 converts three-phase AC power into DC power, providing a stable DC power supply for the subsequent inverter stage. In this embodiment, PWM rectification technology is used to achieve high power factor and low harmonic distortion; the DC bus serves as a common DC link between the rectifier output and the inverter input, carrying out power transmission and buffering functions; inverter module A2 inverts DC power into 400Hz three-phase AC power. In this embodiment, SPWM or SVPWM technology is used to generate high-quality sinusoidal AC power; the output filter module is used to filter out high-frequency components in the PWM wave output by the inverter, providing pure sinusoidal AC power; output contactor K2 controls the switching on and off of the output circuit; output interface X2 connects to the aircraft power supply system, outputting high-quality AC power.

[0025] In this embodiment, the charging module A22 converts AC mains power into DC power to charge the energy storage module; the energy storage module A25 stores electrical energy and quickly releases it when the AC mains power drops to maintain the stability of the DC bus voltage. In this embodiment, a lithium battery pack is used; the DC / DC module A21 converts the output voltage of the energy storage module A25 into a voltage that matches the DC bus voltage.

[0026] This embodiment also includes an auxiliary interface module A5 and a control board A28. The auxiliary interface module A5 is equipped with a sampling circuit, which collects the mains input voltage and the DC bus voltage. The voltage signal collected by the sampling circuit of the auxiliary interface module A5 is transmitted to the control board A28. The control board A28 is connected to the charging module A22, the energy storage module A25, and the DC / DC module A21 respectively. Control board A28 receives power index sampling signals from the mains power and DC bus. When the power supply is working normally, control board A28 controls charging module A22 to charge energy storage module A25 to store energy. When a voltage dip occurs in the grid, control board A28 controls energy storage module A25 to discharge. Through DC / DC module A21 (control board A28 controls DC / DC module to start and output the target voltage required by inverter module), the DC bus voltage is quickly regulated to maintain normal operation of inverter module and ensure continuous output of high-quality AC power. When the grid voltage returns to normal, control board A28 controls energy storage module A25 to stop discharging and controls charging module A22 to continue charging energy storage module A25, waiting for voltage dips to occur to perform DC compensation on DC bus through DC / DC module A21.

[0027] In this embodiment, the sampling circuit of the auxiliary interface module A5 continuously collects the voltage signals of the mains power and the DC bus and transmits them to the control board A28.

[0028] In this embodiment, the control board A28 controls the charging module A22, the energy storage module A25, and the DC / DC module respectively via CAN communication.

[0029] In this embodiment, the sampling circuit of the auxiliary interface module A5 collects the voltage signal between the input contactor K1 and the input terminal of the input filter module.

[0030] In this embodiment, the input filtering module uses an input transformer T1, and the output filtering module uses an output transformer T2.

[0031] In this embodiment, the input transformer T1 is a phase-shifting transformer; it transforms the three-phase power of the mains grid into 6-phase or 12-phase power, realizes multi-phase rectification, significantly reduces input current harmonics, and outputs high-voltage DC power after rectification by the rectifier module.

[0032] In this embodiment, the output transformer T2 is an isolation step-down transformer; it achieves electrical isolation and voltage reduction, thereby improving electrical safety. In this embodiment, the secondary side of the output transformer T2 adopts a star connection, which can provide 115V phase voltage and 200V line voltage to meet the specific output requirements of 400Hz AC power supply.

[0033] The aircraft ground static power supply also includes a processor module A8, a relay module A6, and a user operation module. The user operation module includes a display screen A13, a button and indicator light module A14, and an auxiliary interface module A5 connected to the processor module A8. The mains voltage and DC bus voltage signals collected by the sampling circuit of the auxiliary interface module A5 are transmitted to the processor module A8. The processor module A8 is connected to the display screen A13, and the display screen A13 displays the system status transmitted by the processor module A8 in real time. The button and indicator light module A14 transmits the start / stop signal to the processor module A8. After processing, the processor module A8 issues a control command to drive the relay module A6 to control the opening and closing of the output contactor K2. The indicator light reflects the power supply's working status. After the aircraft ground static power supply is started, the output contactor K2 closes and the indicator light illuminates, indicating normal operation. When K2 opens, the indicator light goes out.

[0034] The control board A28 is connected to the processor module A8 via the communication adapter board A12; data transmission with the processor module A8 is achieved through the communication adapter board A12.

[0035] The control board A28 and the communication adapter board A12 transmit data bidirectionally; the processor module A8 and the communication adapter board A12 transmit data bidirectionally.

[0036] In this embodiment, the control board A28 uses a high-performance microcontroller (MCU) or digital signal processor (DSP); the processor module A8 can be a PLC controller; the relay module A6 realizes electrical isolation and power amplification, and the relay module can be an electromagnetic relay (EMR) or a solid-state relay (SSR).

[0037] In this embodiment, the charging module uses the REG75050 model, which is existing technology and will not be described in detail here.

[0038] The internal structures of the input transformer T1, rectifier module A1, inverter module A2, output transformer T2, sampling circuit of auxiliary interface module A5, relay module A6, processor module A8, communication adapter board A12, control board A28, charging module A22, energy storage module A25, and DC / DC module A21 in this embodiment are existing technologies and will not be described in detail here.

[0039] In this embodiment, the auxiliary interface module A5 is also provided with an auxiliary power module. The auxiliary power module is connected to the control board A28 and the processor module A8, and provides the required operating power to the control board A28 and the processor module A8. In this embodiment, the auxiliary power module provides 24V DC power.

[0040] When using this utility model: 1. When power is needed for the aircraft, the output interface X2 of the aircraft ground static power supply is connected to the aircraft power interface. Turn on the main switch of the aircraft ground static power supply, the input contactor K1 is closed, and the button is pressed. The button sends the start / stop signal to the processor module A8. After processing, the processor module A8 sends a control command to drive the relay module A6 to control the output contactor K2 to close. The aircraft ground static power supply works normally. The 50Hz three-phase AC power input from the mains is filtered, rectified, inverted, and filtered again before being output through the output interface X2 to supply high-quality 115V / 200V 400Hz AC power to the aircraft. During this process, the DC compensation device is in energy storage standby mode. 2. The sampling circuit of auxiliary interface module A5 collects voltage signals from the mains input sampling point and the DC bus sampling point, and transmits the collected voltage signals to control board A28 and processor module A8. Processor module A8 processes the voltage signals and transmits them to display screen A13. Control board A28 receives the voltage signals transmitted from auxiliary interface module A5 and controls the start and stop of the DC compensation device. When control board A28 detects that the collected voltage is normal (the grid voltage meets the normal operation of the aircraft ground static power supply), control board A28 controls charging module A22 to charge energy storage module A25 and store the energy. Energy is stored in the DC compensation device. When the control board A28 detects a voltage dip, it controls the energy storage module A25 to discharge and controls the DC / DC module A21 to convert and stabilize the stored voltage to the rated voltage of the DC bus, ensuring the normal operation of the aircraft ground static power supply inverter circuit. At this time, the DC compensation device is in DC compensation mode. When the control board A28 detects that the collected voltage has returned to normal, it controls the energy storage module A25 to stop discharging and controls the charging module A22 to continue charging the energy storage module A25. At this time, the DC compensation device is back in energy storage mode. 3. When the aircraft's ground static power supply stops or malfunctions during operation, the control board A28 controls the DC compensation device to stop and enter standby mode.

Claims

1. An aircraft ground static power supply with direct current compensation function, characterized in that: The system includes an aircraft ground static power supply and a DC compensation device. The aircraft ground static power supply includes an AC input interface, an input contactor, a rectifier module, an inverter module, an output contactor, and an output interface. The AC input interface is connected to the rectifier module via the input contactor. The rectifier module is connected to the inverter module via a DC bus. The inverter module is connected to the output interface via the output contactor. The DC compensation device includes a charging module, an energy storage module, and a DC / DC module. The mains input interface is connected to the charging module, the charging module is connected to the energy storage module, the energy storage module is connected to the DC / DC module, and the DC / DC module is connected to the DC bus.

2. The aircraft ground static power supply with DC compensation function according to claim 1, characterized in that: It also includes an auxiliary interface module and a control board. The auxiliary interface module is equipped with a sampling circuit, which collects the mains input voltage and DC bus voltage. The voltage signal collected by the sampling circuit of the auxiliary interface module is transmitted to the control board, which is connected to the charging module, the energy storage module, and the DC / DC module respectively.

3. The aircraft ground static power supply with DC compensation function according to claim 1 or 2, characterized in that: The aircraft ground static power supply also includes an input filtering module and an output filtering module. The input filtering module is located between the input contactor and the rectifier module, and the output filtering module is located between the inverter module and the output contactor.

4. The aircraft ground static power supply with DC compensation function according to claim 3, characterized in that: The input filtering module uses an input transformer, and the output filtering module uses an output transformer.

5. The aircraft ground static power supply with DC compensation function according to claim 4, characterized in that: The input transformer is a phase-shifting transformer.

6. The aircraft ground static power supply with DC compensation function according to claim 4 or 5, characterized in that: The output transformer is an isolation step-down transformer.

7. The aircraft ground static power supply with DC compensation function according to claim 2, characterized in that: The aircraft ground static power supply also includes a processor module and a user operation module. The user operation module includes a display screen. The auxiliary interface module is connected to the processor module, and the processor module is connected to the display screen.

8. The aircraft ground static power supply with DC compensation function according to claim 7, characterized in that: The control board is connected to the processor module via a communication adapter board.

9. The aircraft ground static power supply with DC compensation function according to claim 8, characterized in that: The control board and the communication adapter board transmit data bidirectionally; the processor module and the communication adapter board transmit data bidirectionally.

10. The aircraft ground static power supply with DC compensation function according to claim 7, characterized in that: The aircraft ground static power supply also includes a relay module. The user operation module includes a button. The button's start / stop signal is transmitted to the processor module. After processing, the processor module issues a control command to drive the relay module to control the opening and closing of the output contactor K2.

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