Airplane ground power supply equipment power control device and method

Abstract

The invention belongs to the technical field of power supply control, and particularly relates to a power control device and method for aircraft ground power supply equipment. The equipment comprises a direct-current power supply subsystem, an alternating-current power supply subsystem, a power control system and at least one liquid crystal screen operation unit, the direct current power supply subsystem comprises a first working power supply, a direct current side power unit and two paths of direct current output plugs which are electrically connected in sequence; the alternating current power supply subsystem comprises a second working power supply, an alternating current side power unit and two paths of alternating current output plugs which are electrically connected in sequence; the power control system is in communication connection with the direct-current power supply subsystem and the alternating-current power supply subsystem, and the liquid crystal screen operation unit is electrically connected with the power control system. According to the technical scheme, the problem of airplane power supply failure caused by low network casting rate, single power supply system type and large instantaneous current disturbance of a conventional ground power supply is solved, and the method is more environment-friendly.

Description

Technical Field

[0001] The present invention belongs to the technical field of power supply control, and in particular relates to a power control device and method for aircraft ground power supply equipment. Background Art

[0002] When an aircraft is being maintained on the ground, the existing technology generally uses power supply vehicles and other equipment to provide ground working power. The disadvantage is that the ground working power supply type is relatively single, only providing one DC power supply or one AC power supply, and usually one power supply vehicle can only provide ground working power for one aircraft. When multiple models and multiple flights of aircraft need power supply at the same time, multiple power supply vehicles are required, which reduces the working efficiency of the equipment.

[0003] The existing power supply vehicle can only meet the power demand of the normal maintenance work of the aircraft, and has no power backup function. That is, when the power module of the power supply vehicle fails, it cannot meet the power supply demand of the aircraft. The fault must be resolved before the ground working power can be provided to the aircraft again, which reduces work efficiency.

[0004] In the prior art, a Chinese invention patent document with publication number CN101902661A and publication date December 1, 2010 is proposed, which discloses a power supply system, including a power supply part, which includes: A plurality of power supply modules for providing a power supply voltage signal; A power supply output part, connected to the power supply part, for integrating and processing the power supply voltage signals provided by the multiple power supply modules and outputting them to the load, so that each power supply module can supply power to the multiple loads; A power detection part, connected to the power supply output part, used to detect the output power of the power supply output part to obtain output power information; The control part is connected between the power detection part and the power supply part, and is used to receive the output power information and control the on / off status of the multiple power modules according to the output power information.

[0005] The above technical solution cannot be used for the power supply of some aircraft (here refers to aircraft with high requirements for power supply). In actual use, the following problems may occur: First of all, it is impossible to provide the steady-state and transient power supply quality required by such aircraft. The ground power supply equipment of the above technical solution is mostly used for city power, the circuit is stable, and the power supply parameters generally do not fluctuate much in an instant. However, the ground power supply equipment of some aircraft has special requirements for steady-state voltage range testing, sudden load addition and subtraction testing, transient voltage characteristic testing, load starting output characteristic testing, etc. When the ground power supply equipment supplies power to the aircraft, different aircraft models and different states may cause instantaneous disturbance changes in the ground power supply parameters, causing a surge process in voltage and frequency. Once the power supply indicators do not meet the aircraft requirements, the ground power supply control and protection device will immediately switch the ground power supply. In particular, when the engines of some aircraft are started, the output current of the ground power supply will increase suddenly, and the short-term high-power output may affect the generator set, causing the instantaneous power supply quality to deteriorate, resulting in power supply failure.

[0006] Secondly, it is impossible to provide ground power with multiple power supply systems required by some aircraft. The ground power supply equipment of the above technical solution is generally used for 220V / 50Hz AC power for city power, while different types of aircraft in the aviation field require different types of power. Some aircraft power supply systems include aviation AC power supply system and aviation DC power supply system, while the ground power supply equipment of the above technical solution or other conventional ground power supply equipment in the aviation field are all single-system power supply equipment, that is, they can only output city power (220V / 50Hz AC power) or one of the aviation AC power supply system and aviation DC power supply system. However, with the rapid development of the aviation field, there are more and more cases where multiple flights and aircraft with different power supply systems (aviation AC power and aviation DC power) are maintained at the same time. At this time, the use of single-system ground power supply equipment requires multiple people to operate the ground power supply equipment at the same time or one person repeatedly moves between multiple workstations to operate multiple ground power supply equipment, resulting in a waste of resources.

[0007] Finally, the power module grid connection rate of the above technical solution cannot meet the requirements of the aircraft. Due to the high overload and high power requirements of the aircraft, when the aircraft power demand increases or the power module of the ground power supply equipment fails, the backup power module of the ground power supply equipment used in the above technical solution cannot meet the power supply requirements of the aircraft, and cannot be quickly connected to the grid. There is a risk of abnormal power failure of the aircraft causing damage to the relevant airborne products. Summary of the invention

[0008] The present invention aims to solve the technical problem and provides a power control device and method for aircraft ground power supply equipment. A power supply cabin is specially designed for aircraft to solve the problems of low grid connection rate, single power supply system type and large instantaneous current disturbance of conventional ground power supply leading to power supply failure of aircraft, and it is more environmentally friendly.

[0009] The technical solutions adopted to achieve the above purpose are as follows: A power control device for aircraft ground power equipment comprises a power cabin and a dual-system power supply system; the dual-system power supply system is arranged inside the power cabin and comprises a direct current power subsystem, an alternating current power subsystem, a power control system and at least one liquid crystal screen operating unit.

[0010] The DC power supply subsystem includes a first working power supply, a DC side power unit, a I-way DC output plug and a II-way DC output plug; the first working power supply is electrically connected to the DC side power unit through an input control contactor K1; the I-way DC output plug and the II-way DC output plug are electrically connected to the DC side power unit through output control contactors K3 and K4, respectively.

[0011] The AC power subsystem includes a second working power supply, an AC side power unit, an AC output plug I and an AC output plug II; the second working power supply is electrically connected to the AC side power unit through an input control contactor K2; the AC output plug I and the AC output plug II are electrically connected to the AC side power unit through output control contactors K5 and K6, respectively.

[0012] The power control system is communicatively connected to the DC power subsystem and the AC power subsystem respectively, and is used to collect the actual power usage information of the aircraft and the working signals of the DC power subsystem and the AC power subsystem, and control the power supply output of the DC power subsystem and the AC power subsystem based on the actual power usage information and the working signals.

[0013] The LCD screen operation unit is electrically connected to the power control system, and is used to display and collect working signals of the DC power subsystem and the AC power subsystem, and cooperate with the power control system to query the working status of the DC power subsystem and the AC power subsystem and control power supply.

[0014] Preferably, the DC side power unit includes a DC online main circuit and a plurality of DC power modules. The input ends of all DC power modules are electrically connected to the first working power supply respectively; the output ends of all DC power modules are electrically connected to the DC online main circuit respectively, and all DC power modules are communicatively connected to the power control system through the first matrix relay; the I-way DC output plug and the II-way DC output plug are electrically connected to the DC online main circuit respectively. The DC online main circuit is communicatively connected to the power control system, and is used to select a corresponding number of DC power modules to be connected to participate in the power supply output to the I-way DC output plug and / or the II-way DC output plug according to the module number selection instruction issued by the power control system.

[0015] Preferably, the AC side power unit includes an AC online main circuit and a plurality of AC power modules. The input ends of all AC power modules are electrically connected to the second working power supply respectively; the output ends of all AC power modules are electrically connected to the AC online main circuit respectively; all AC power modules are communicatively connected to the power control system through the second matrix relay; the I-way AC output plug and the II-way AC output plug are electrically connected to the AC online main circuit respectively. The AC online main circuit is communicatively connected to the power control system, and is used to select a corresponding number of AC power modules to be connected to participate in power supply to the I-way AC output plug and / or the II-way AC output plug according to the module number selection instruction issued by the power control system.

[0016] Preferably, the second working power supply is provided with an AC input and EMI filter module II, and the AC power module includes a rectifier soft start module II, a rectifier two-stage filter module II, a power inverter module II, a medium frequency isolation transformer module, and a medium frequency two-stage filter module which are electrically connected in sequence; wherein, the rectifier soft start module II is connected to the output end of the AC input and EMI filter module II; the rectifier soft start module II and the power inverter module II are respectively communicated with the power control system, and a drive module II is connected between the power inverter module II and the power control system.

[0017] Preferably, the power control system includes two sets of control subsystems corresponding to the DC power subsystem and the AC power subsystem, and each control subsystem includes a power control unit, a data signal acquisition unit, an output data acquisition unit and an online control unit. The data signal acquisition unit is connected to the power control unit for communication, and is used to collect power output signals and obtain information about the actual power used on the aircraft, and send the collected power output signals and the actual power used on the aircraft to the power control unit. The output data acquisition unit is connected to the power control unit for communication, and is used to collect power output information in real time, send the power output information to the power control unit, and cooperate with the power control unit to complete power on / off control; wherein the power output information includes on / off information, voltage information and current information. The power control unit is used to determine the system fault according to the power output signal, and control the power output in combination with the power output information and the actual power used on the aircraft. The online control unit is connected to the output data acquisition unit and the power control unit for communication through the online interface to establish conditions for the DC power subsystem and the AC power subsystem to mutually query the working status and control the power supply.

[0018] Preferably, the first working power supply is provided with an AC input and EMI filter module I, and the DC power module includes a rectifier soft start module I, a rectifier two-stage filter module I, a power inverter module I, a high-frequency isolation transformer module, and a high-voltage rectifier two-stage filter module which are electrically connected in sequence; wherein, the rectifier soft start module I is connected to the output end of the AC input and EMI filter module I; the rectifier soft start module I and the power inverter module I are respectively communicated with the power control system, and a drive module I is connected between the power inverter module I and the power control system.

[0019] Preferably, two LCD screen operating units are included, and the two LCD screen operating units are respectively connected to the power control units in the two control subsystems in a one-to-one correspondence.

[0020] Based on the above-mentioned aircraft ground power supply equipment power control device, the present technical solution proposes an aircraft ground power supply equipment power control method, comprising the following steps: S1, start the dual-system power supply system and connect the target aircraft end load to the dual-system power supply system; S2, according to the access position of the target aircraft end load, using the LCD screen operation unit to start the corresponding power supply subsystem; wherein the power supply subsystem refers to the DC power supply subsystem and the AC power supply subsystem; S3, according to the position where the load at the target aircraft end is connected, using the LCD screen operation unit to control the corresponding power output plugs to be electrically connected; wherein the power output plugs refer to a first-channel DC output plug, a second-channel DC output plug, a first-channel AC output plug and a second-channel AC output plug; S4, for the started power supply subsystem, the power control system detects the on / off information of the two power supply output plugs in the same power supply subsystem in real time; S5, judging whether the two power output plugs have a target aircraft end load connected to them one by one based on the on-off information; if so, the power control system controls the corresponding power supply subsystem to supply power to the power output plug according to the location where the target aircraft end load is connected and the actual power usage on the aircraft; if not, the power output plug is not supplied with power; S6, for each single target aircraft load connected, determine whether the power supply is completed; if so, proceed to step S7, if not, the power control system controls the corresponding power supply subsystem to maintain the power supply state for the target aircraft load; S7, operating through the LCD operating unit, cooperating with the power control system to control the corresponding power supply subsystem to disconnect the power output to the power output plug connected to the load at the target aircraft end; S8, for the started power supply subsystem, determine whether its two power output plugs are both in the disconnected state according to the on-off information; if so, the current power supply task of the power supply subsystem is completed and the power supply subsystem is turned off; if not, return to step S6.

[0021] Preferably, in step S5, the power control system controls the power supply subsystem to supply power to the power output plug based on a matrix shared data processing method, that is, the power control system cooperates with the matrix relay to share data between the power modules, and controls the switching output of each power module based on the shared data; in the DC power subsystem, the power module refers to the DC power module, and in the AC power subsystem, the power module refers to the AC power module.

[0022] Preferably, in step S5, the power control system controls the power supply subsystem to supply power to the power output plug, and also includes trying to detect the fault condition of each power module, and according to the fault condition of the power module, controls the switching output of each power module in combination with the matrix shared data processing method.

[0023] Beneficial effects of the present invention: 1) This technical solution proposes a power control device and method for aircraft ground power equipment. Aiming at the problem of single power supply type of conventional ground power supply, a dual-system power supply system is set up. The dual-system power supply system includes a DC power subsystem with two power outputs and an AC power subsystem with two power outputs, which supports powering two DC aircraft and two AC aircraft at the same time. The DC power subsystem and the AC power subsystem are connected, and only one ground maintenance personnel is required to efficiently complete the power supply control task of a large number of aircraft, breaking the working mode that the traditional power supply vehicle can only provide support for a single power supply system of one aircraft; at the same time, in terms of energy consumption, it directly reduces the gasoline consumption, the number of drivers and maintenance personnel required for the conventional power supply vehicle to drive from the garage to the aircraft to complete the support task, and also reduces the waiting time and driving time in the middle. In today's domestic and foreign aviation fields, the frequency of simultaneous maintenance of multiple flights and multiple models of aircraft is increasing. The dual-system power supply method greatly improves the use efficiency of the power supply cabin, has strong innovation and demonstration, and has broad application prospects and high promotion value in the power supply field of various types of aircraft.

[0024] 2) This technical solution proposes a power control device and method for aircraft ground power supply equipment, which adopts a matrix-type shared data processing method. It does not require each DC / AC power module to collect the power consumption of the aircraft separately. It only requires each power module to directly maintain data interaction to complete the work switching between operation and backup. When the aircraft power demand increases or the operating power module fails, the backup power module can be quickly and automatically put into the aircraft power grid with a nanosecond response time to prevent the aircraft from abnormal power failure and damage to the onboard finished products. After the power supply task is completed, the corresponding faulty power module is repaired, avoiding the problem of having to solve the ground power supply equipment failure before the aircraft can be powered again, greatly improving work efficiency and ensuring the safety, continuity and reliability of aircraft power use.

[0025] 3) Both the DC power subsystem and the AC power subsystem of this technical solution adopt three-level protection including AC input circuit, full-bridge DC / DC conversion circuit and control and display circuit, which can solve the problem of power supply failure to the aircraft due to sudden increase / decrease of aircraft load or large instantaneous circuit fluctuations during the power supply process, and ensure the power output stability of the power supply cabin. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is the basic principle block diagram of the dual-system power supply system of this technical solution; Figure 2 This is the basic principle block diagram of the DC power subsystem of this technical solution; Figure 3 This is the basic principle block diagram of the AC power subsystem of this technical solution; Figure 4 This is a schematic diagram of matrix-based shared data; Figure 5 This is the anti-interference principle block diagram of the DC power supply subsystem; Figure 6 It is a schematic diagram of an anti-interference circuit for a DC power supply subsystem; Figure 7 This is the anti-interference principle block diagram of the AC power subsystem. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings in the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments.

[0028] Therefore, the following detailed description of the invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0029] Example 1 This embodiment discloses a power control device for aircraft ground power supply equipment, as a preferred implementation scheme of this technical solution, such as Figure 1 As shown, it includes a power supply cabin and a dual-system power supply system. The dual-system power supply system is arranged inside the power supply cabin, including a DC power subsystem, an AC power subsystem, a power control system and at least one LCD screen operation unit.

[0030] The DC power supply subsystem includes a first working power supply, a DC side power unit, a DC output plug I and a DC output plug II. The first working power supply is electrically connected to the DC side power unit through the input control contactor K1, wherein the first working power supply is connected to the mains, and the input control contactor K1 is used to control the power supply on and off. The DC output plug I and the DC output plug II are electrically connected to the DC side power unit through the output control contactor K3 and the output control contactor K4, respectively, wherein the output control contactor K3 and the output control contactor K4 are program-controlled, and are used to control the on and off of the DC output plug I and the DC output plug II, respectively, that is, to control the electrical connection and electrical disconnection of the aircraft end load.

[0031] The AC power supply subsystem includes a second working power supply, an AC side power unit, an AC output plug I and an AC output plug II. The second working power supply is electrically connected to the AC side power unit through the input control contactor K2, wherein the second working power supply is connected to the mains, and the input control contactor K2 is used to control the power supply on and off. The AC output plug I and the AC output plug II are electrically connected to the AC side power unit through the output control contactor K5 and the output control contactor K6, respectively, wherein the output control contactor K5 and the output control contactor K6 are program-controlled, and are used to control the on and off of the AC output plug I and the AC output plug II, respectively, that is, to control the electrical connection and electrical disconnection of the aircraft end load.

[0032] The power control system is communicatively connected to the DC power subsystem and the AC power subsystem respectively, and is used to collect the actual power usage information of the aircraft and the working signals of the DC power subsystem and the AC power subsystem, and control the power supply output of the DC power subsystem and the AC power subsystem based on the actual power usage information and the working signals.

[0033] The LCD screen operation unit is electrically connected to the power control system, and is used to display and collect working signals of the DC power subsystem and the AC power subsystem, and cooperate with the power control system to query the working status of the DC power subsystem and the AC power subsystem and control power supply.

[0034] In this technical solution, in order to solve the problem of single power supply type of conventional ground power supply, a dual-system power supply system is set up. The dual-system power supply system includes a DC power subsystem and an AC power subsystem, and the DC power subsystem includes two outputs, namely, an AC output plug I and an AC output plug II, and the AC power subsystem includes two outputs, namely, an AC output plug I and an AC output plug II. In this way, this technical solution can supply power to two DC aircraft and two AC aircraft at the same time. In actual use, power can be distributed to the DC power subsystem and the AC power subsystem according to actual needs, such as setting up an aviation DC power subsystem and an aviation AC power subsystem.

[0035] Example 2 This embodiment discloses a power control device for aircraft ground power supply equipment, as a preferred implementation scheme of this technical solution, combined with Figure 1 , Figure 2 and Figure 3 The DC power subsystem and AC power subsystem of the technical solution are connected through the power control system, support mutual query of working status, and the power supply control operation is completed uniformly by the LCD screen operation unit. Specifically: the power control system includes two sets of control subsystems corresponding to the DC power subsystem and the AC power subsystem, and each set of control subsystems includes a power control unit, a data signal acquisition unit, an output data acquisition unit and an online control unit.

[0036] The data signal acquisition unit is connected to the power control unit for communication, and is used to collect the power output signal and obtain the actual power information used on the aircraft, and send the power output signal and the actual power information used on the aircraft to the power control unit. Based on this, in actual application of this technical solution, it is necessary to connect the target aircraft end load with the data signal acquisition unit so that the data signal acquisition unit can obtain the actual power information used on the aircraft in real time.

[0037] The output data acquisition unit is communicatively connected with the power control unit, and is used to collect power supply output information in real time, and send the power supply output information to the power control unit, and cooperate with the power control unit to complete power supply on-off control; wherein, the power supply output information includes on-off information, voltage information and current information. Based on this, in actual application of this technical solution, after the target aircraft end load is connected one-to-one to the Ⅰ-way AC output plug and / or the Ⅱ-way AC output plug, the output control contactor K3 and / or the output control contactor K4 are connected to the connection position of the target aircraft end load through the LCD screen operation unit. The principle is: after the operation is implemented through the LCD screen operation unit, the power control unit sends a connection signal to the output data acquisition unit, and the output data acquisition unit controls the output control contactor K3 and / or the output control contactor K4 to be turned on based on the connection signal (that is, 2 and Figure 3 On this basis, the output data acquisition unit respectively collects the power supply output information (an electrical signal) between the AC output plug I and the AC output plug II and the online control unit and sends it to the power control unit. The power control unit can judge the on and off of the AC output plug I and / or the AC output plug II based on the power supply output information, so that the power control unit can control the corresponding power supply subsystem to only conduct power to the power output plug.

[0038] The power control unit is used to determine system fault conditions based on the power output signal, and to control the power output in combination with the power output information and the actual power used on the aircraft.

[0039] The online control unit is respectively connected to the output data acquisition unit and the power control unit for communication, and is used to connect the two control subsystems through the online interface to establish conditions for the DC power subsystem and the AC power subsystem to query each other's working status and control each other's power supply.

[0040] When there is only one LCD screen operation unit in the dual-system power supply system, the LCD screen operation unit is connected to the power control unit in any control subsystem. In this way, based on the online structure of the two control subsystems, the working status of the DC power subsystem and the AC power subsystem can be queried, and the power supply of the DC power subsystem and the AC power subsystem can be controlled through only one LCD screen operation unit.

[0041] Furthermore, in order to meet the docking conditions of multiple aircraft, four power supply ports (I-way AC output plug, II-way AC output plug, I-way AC output plug and II-way AC output plug) can be arranged in different positions of the power supply cabin. In this way, based on the principle of proximity operation, a liquid crystal screen operation unit can be set based on the DC power subsystem and the AC power subsystem respectively, that is, two liquid crystal screen operation units are set in the dual-system power supply system, and the two liquid crystal screen operation units are respectively connected to the power control units in the two control subsystems in a one-to-one correspondence. In this way, based on the online structure of the two control subsystems, the two liquid crystal screen operation units can query the working status of the DC power subsystem and the AC power subsystem, and control the power supply work of the DC power subsystem and the AC power subsystem, that is, mutual query of working status and mutual control of power supply work are realized.

[0042] More specifically, this technical solution takes the aviation DC power subsystem and the aviation AC power subsystem as examples, and the display interface of the LCD screen operation unit includes the I-way interface and the II-way interface. Taking the I-way interface as an example, the I-way output and the II-way output of the DC power subsystem (including voltage display and current display), as well as the I-way output and the II-way output of the AC power subsystem (including voltage display and current display) are displayed. In addition, the I-way operation interface of the aviation DC power subsystem and the aviation AC power subsystem is also presented. Specifically: for the aviation AC power subsystem, there are start and stop buttons for the AC power supply, and there are on and off buttons for the I-way power supply output; for the aviation DC power subsystem, there are start and stop buttons for the DC power supply, and there are on and off buttons for the I-way power supply output. In addition, by clicking on the alarm query, the corresponding fault record can be retrieved; the historical power supply data of the DC power subsystem and the AC power subsystem can be retrieved through the motor data record; by clicking on the parameter setting, the voltage value, frequency value or the control signal sent by the power control unit can be output.

[0043] Example 3 This embodiment discloses a power control device for aircraft ground power supply equipment. As a preferred implementation of this technical solution, based on Example 2, the DC side power unit includes a DC online main circuit and a plurality of DC power modules. The number of DC power modules is set according to actual needs. This embodiment takes the aviation DC power supply subsystem as an example, and can be configured with 8 sets of DC power modules, such as Figure 2 shown.

[0044] The input terminals of all DC power modules are electrically connected to the first working power supply. Figure 2Among them, K11~K18 are contactors, which are respectively used to control the input on and off of 8 sets of DC power modules, and can be respectively communicated with the power control system to realize program control. Based on the control subsystem corresponding to the DC power supply subsystem, the contactors K11~K18 are respectively communicated with its power control unit, and program control is realized based on the power control unit. The output ends of all DC power modules are respectively electrically connected to the DC online main circuit, and all DC power modules are communicated with the power control system through the first matrix relay; the I-way DC output plug and the II-way DC output plug are respectively electrically connected to the DC online main circuit. Figure 2 As shown, there are labels ①, ②, ③ and ⑧ in the figure, and labels ④, ⑥ and ⑦ are hidden. The same labels are connected together, that is, taking the first DC power module as an example: its control end is labeled ① and the output end is labeled ①, the port corresponding to it on the value flow online main circuit is labeled ①, and the corresponding power control unit and data signal acquisition unit are also labeled ① respectively. These ports labeled ① are electrically connected.

[0045] Based on the above connection structure, the DC online main circuit of the technical solution is communicated with the power control system (specifically, the power control unit of the control subsystem corresponding to the DC power supply subsystem) to select a corresponding number of DC power modules to be connected according to the module number selection instruction issued by the power control system (power control unit) to participate in the power supply output to the DC output plug I and / or the DC output plug II.

[0046] This technical solution can support the power supply control of DC aircraft through a matrix-type shared data processing method. Specifically: For several DC power modules in the present technical solution, in actual use, a part is put into operation, and the remaining part is in backup state. On this basis, the data signal acquisition unit collects the power output signal in real time (specifically the power output signal at the output end of each DC power module in operation); the power control unit determines whether the corresponding DC power module is faulty through the power output information; when any DC power module fails, the power control unit cuts off the faulty DC power module. At this time, based on the matrix sharing data adopted by each DC power module, the power module in the backup state can be quickly and automatically randomly put into the aircraft power grid with a nanosecond response time (that is, quickly participate in the power supply work). At the same time, the output data acquisition unit samples the power supply output information (including voltage and current) at the output end of the DC online main circuit in real time, and displays the corresponding power supply output information on the LCD screen operation unit through the power control unit. If the power control unit detects based on the power supply output information that the DC power module currently in operation does not meet the actual power requirement of the aircraft, the power control unit will calculate the number of DC power modules that need to be added to the operation based on the actual power information of the aircraft and the corresponding power supply output information, and control the corresponding number of power modules in the backup state to automatically start and automatically match the output current balance with a nanosecond response time, thereby completely and reliably ensuring the normal power supply of the equipment.

[0047] To sum up, in the DC side power unit of the present technical solution, based on the matrix-type shared data processing method, each DC power module can not only back up each other but also work and supply power at the same time, and automatically balance the current, thereby improving the load capacity of the equipment and ensuring the safety, continuity and reliability of the aircraft's electricity use.

[0048] Example 4 This embodiment discloses a power control device for aircraft ground power supply equipment. As a preferred implementation of this technical solution, based on Embodiment 2 or 3, the AC side power unit includes an AC online main circuit and a plurality of AC power modules. The number of AC power modules is set according to actual needs. This embodiment takes the aviation AC power subsystem as an example, and can be configured with 8 sets of AC power modules, such as Figure 3 shown.

[0049] The input ends of all AC power modules are electrically connected to the second working power supply respectively; the output ends of all AC power modules are electrically connected to the AC online main circuit respectively; all AC power modules are communicatively connected to the power control system through the second matrix relay; the I-way AC output plug and the II-way AC output plug are electrically connected to the AC online main circuit respectively; The input terminals of the AC power modules are electrically connected to the second working power supply. Figure 3In the figure, K21~K28 are contactors, which are used to control the input on and off of 8 sets of AC power modules respectively. They can be connected to the power control system for program control. Based on the control subsystem corresponding to the AC power subsystem, contactors K21~K28 are connected to the power control unit for program control. The output ends of all AC power modules are electrically connected to the AC online main circuit respectively. All AC power modules are connected to the power control system through the second matrix relay. The Ⅰ-way AC output plug and the Ⅱ-way AC output plug are electrically connected to the AC online main circuit respectively. Figure 3 As shown, there are labels D-1, D-8, C-1, C-8, E-1, E-8 and ⑧ in the figure, and labels D-2~ D-7, C-2~ C-7 and E-2~ E-7 are hidden. The same labels are connected together, that is, taking the first AC power module as an example: its control end is labeled D-1 and C-1, and the corresponding ports set on the corresponding power control unit are labeled D-1 and C-1 respectively; the output end of the AC power module is labeled E-1, and the corresponding port on the AC online main circuit is labeled E-1, and the data signal acquisition unit is also labeled E-1. These ports with the same labels are electrically connected.

[0050] Based on the above connection structure, the AC online main circuit of the present technical solution is communicatively connected with the power control system (specifically, the power control unit of the control subsystem corresponding to the AC power supply subsystem), and is used to select a corresponding number of AC power modules to be connected according to the module number selection instruction issued by the power control system (power control unit) to participate in supplying power to the Ⅰ-way AC output plug and / or the Ⅱ-way AC output plug.

[0051] This technical solution can support the power supply control of AC aircraft through a matrix-type shared data processing method. Specifically: For several AC power modules in the present technical solution, in actual use, a part is put into operation, and the remaining part is in a backup state. On this basis, the data signal acquisition unit collects the power output signal in real time (specifically the power output signal at the output end of each AC power module in operation); the power control unit determines whether the corresponding AC power module is faulty through the power output information; when any AC power module fails, the power control unit cuts off the faulty AC power module. At this time, based on the matrix sharing data adopted by each AC power module, the power module in the backup state can be quickly and automatically randomly put into the aircraft power grid with a nanosecond response time (that is, quickly participate in the power supply work). At the same time, the output data acquisition unit samples the power supply output information (including voltage and current) at the output end of the AC online main circuit in real time, and displays the corresponding power supply output information on the LCD screen operation unit through the power control unit. If the power control unit detects based on the power supply output information that the AC power module currently in operation does not meet the actual power requirement of the aircraft, the power control unit will calculate the number of AC power modules that need to be added to the operation based on the actual power information of the aircraft and the corresponding power supply output information, and control the corresponding number of power modules in the backup state to automatically put into operation and automatically match the output current balance with a nanosecond response time, thereby completely and reliably ensuring the normal power supply of the equipment.

[0052] To sum up, in the AC side power unit of the present technical solution, based on the matrix-type shared data processing method, each AC power module can not only back up each other but also work and supply power at the same time, and automatically balance the current, thereby improving the load capacity of the equipment and ensuring the safety, continuity and reliability of the aircraft's electricity use.

[0053] Example 5 This embodiment discloses a power control device for aircraft ground power supply equipment. As a preferred implementation scheme of this technical solution, in view of the problem that the instantaneous current disturbance that may exist in the conventional ground power supply during the power supply process is too large, resulting in the failure of power supply to the aircraft, this technical solution adopts three-level protection for the DC power supply subsystem, including AC input circuit, full-bridge DC / DC conversion circuit and control and display circuit. Specifically, based on embodiment 3 or 4, in the DC power supply subsystem, an AC input and EMI filter module I is provided in the first working power supply, and the DC power module includes a rectifier soft start module I (AC / DC1), a rectifier two-stage filter module I (LC1 and LC2), a power inverter module I (DC / AC1), a high-frequency isolation transformer module (AC / AC1), and a high-voltage rectifier two-stage filter module (AC / DC2, LC3 and LC4) that are electrically connected in sequence; wherein, the rectifier soft start module I is connected to the output end of the AC input and EMI filter module I; the rectifier soft start module I and the power inverter module I are respectively connected to the power control system in communication, and a drive module I is connected between the power inverter module I and the power control system. wherein, the drive module I adopts a rectifier drive board.

[0054] This technical solution takes the aviation DC power subsystem as an example, and its anti-interference principle block diagram is as follows Figure 5 As shown, Figure 6 correspond Figure 5 A schematic diagram of an anti-interference circuit is presented. The working principle is as follows: First, the AC input circuit includes AC input and EMI filter module I, rectifier soft start module I and rectifier double-stage filter module I. Its main function is to effectively prevent the interference of the external power grid to the power supply cabin. Specifically: AC input and EMI filter module I refers to the electromagnetic interference filter circuit, which is used to suppress electromagnetic interference and can weaken or block the interference signal in the AC input power supply. Rectifier soft start module I (corresponding to Figure 6 The ZL in the figure is used to support the power control unit to control the AC input of the mains. When the input is over-voltage or under-voltage, the power control unit outputs a low level and the DC power module is in the off state; otherwise, the power control unit outputs a high level and the DC power module is turned on, thereby avoiding excessive starting voltage and frequency. The rectifier dual-stage filter module I corresponds to Figure 6 The inductor filter circuit composed of the inductor L1 and the resistor R1 converts the AC power output by the front stage (rectifier soft start module I) into a relatively pure DC high voltage with AC harmonic components through the rectifier double-stage filter module I.

[0055] Secondly, the full-bridge DC / DC conversion circuit includes a power inverter module I, a high-frequency isolation transformer module, and a high-voltage rectifier two-stage filter module. It is a "DC-AC-DC" conversion circuit. The DC voltage output by the rectifier two-stage filter module I is converted, and a high-frequency AC square wave voltage is output under the control of the voltage control signal of the power control unit; the high-frequency AC square wave voltage is safely isolated by the high-frequency isolation transformer, and then the high-frequency AC square wave voltage is converted into a high-frequency AC square wave voltage. Figure 6 As shown in the figure, a high-voltage rectifier secondary filter circuit including inductor L2, inductor L3, capacitor C3 and capacitor C4 is used for filtering, and a flat DC voltage is obtained on resistors R2 and R3, and finally the aviation DC power required by the aircraft load is output. Among them, the power inverter module I (including Figure 6 The rectifier bridge 1 and rectifier bridge 2 in the figure refer to circuit modules that use high-frequency rectifier bridge circuits to convert direct current into alternating current. The high-frequency isolation transformer module is a circuit module that safely isolates the front end of the circuit from the back end of the circuit and plays a protective role. It can ensure that when a fault occurs in the back end of the circuit, the power supply and inverter modules at the front end of the circuit will not be affected. The high-voltage rectifier secondary filter module is used to convert high-frequency AC voltage into DC voltage with smaller voltage ripples, that is, to convert the AC output of the front stage (high-frequency isolation transformer module) into the aviation DC power required by the aircraft.

[0056] Finally, the control and display circuit specifically refers to the LCD operation unit, which is mainly used to monitor the working status and various information of the entire dual-system power supply system, and display them on the LCD screen. It can also view the records of fault data in real time, and at the same time, set the output voltage value and frequency value according to the LCD operation panel or control the system output voltage according to the control signal sent by the power control unit, thereby ensuring the stability of the power supply output and improving the overall reliability and durability of the power supply.

[0057] Furthermore, for the attached Figure 6 A schematic diagram of an anti-interference circuit of a disclosed DC power supply subsystem is provided. In a power control unit, the power control unit is powered through terminal J1; terminal J2 provides an interface for the power control unit to connect to a voltage Hall and a current shunt, and sends the voltage value collected by the voltage Hall and the current value collected by the current shunt to the power control unit. In a rectifier bridge driver board, the rectifier bridge driver board is powered through terminal J1; terminal J3 and terminal J4 correspond to connection terminal 1, connection terminal 2, connection terminal 3 and connection terminal 4 connecting rectifier bridge 1 and rectifier bridge 2, respectively, and are used for the power control unit to drive rectifier bridge 1 and rectifier bridge 2 through the rectifier bridge driver board.

[0058] Example 6 This embodiment discloses a power control device for aircraft ground power supply equipment. As a preferred implementation scheme of this technical solution, in order to solve the problem that the instantaneous current disturbance that may exist in the conventional ground power supply during the power supply process is too large, resulting in the failure of power supply to the aircraft, this technical solution corresponds to Example 5, and adopts three levels of protection for the AC power supply subsystem, namely, AC input circuit, full-bridge DC / DC conversion circuit and control and display circuit. That is, based on Example 4, as Figure 7 As shown, the second working power supply is provided with an AC input and EMI filter module II, and the AC power module includes a rectifier soft start module II (AC / DC2), a rectifier two-stage filter module II (LC5 and LC6), a power inverter module II (three-way DC / AC2), an intermediate frequency isolation transformer module (three-way AC / AC2), and an intermediate frequency two-stage filter module (AC / AC3 and three-way LC7) which are electrically connected in sequence; wherein the rectifier soft start module II is connected to the output end of the AC input and EMI filter module II; the rectifier soft start module II and the power inverter module II are respectively connected to the power control system in communication, and a drive module II is connected between the power inverter module II and the power control system. wherein the drive module II adopts a rectifier drive board.

[0059] Example 7 This embodiment discloses a power control method for aircraft ground power supply equipment. As a preferred implementation scheme of this technical solution, a power control device for aircraft ground power supply equipment disclosed in this technical solution is adopted, including the following steps: S1, start the dual-system power supply system, and connect the target aircraft-end load to the dual-system power supply system. Among them, at most two DC aircraft-end loads and two AC aircraft-end loads can be connected at one time. The DC aircraft-end load is connected through the I-way DC output plug or the II-way DC output plug, and the AC aircraft-end load is connected through the I-way AC output plug or the II-way AC output plug.

[0060] S2, according to the access position of the target aircraft end load, use the LCD screen operation unit to start the corresponding power supply subsystem; wherein, the power supply subsystem refers to the DC power supply subsystem and the AC power supply subsystem. Specifically, when the target aircraft end load is connected to the I-way DC output plug and / or the II-way DC output plug, the DC power supply subsystem is started; if the target aircraft end load is connected to the I-way AC output plug and / or the II-way AC output plug, the AC power supply subsystem is started; the DC power supply subsystem and the AC power supply subsystem can be started at the same time.

[0061] S3, according to the position of the target aircraft end load, use the LCD screen operation unit to control the corresponding power supply output plug to be electrically connected; wherein, the power supply output plug refers to the I-way DC output plug, the II-way DC output plug, the I-way AC output plug and the II-way AC output plug. Specifically, taking the DC power supply subsystem as an example: if the target aircraft end load is connected to the I-way DC output plug, the operation is implemented through the LCD screen operation unit, and the corresponding power control unit controls the output control contactor K3 to be turned on through the output data acquisition unit, so that the I-way DC output plug is electrically connected to the DC connection main circuit; if the target aircraft end load is connected to the II-way DC output plug, the operation is implemented through the LCD screen operation unit, and the corresponding power control unit controls the output control contactor K4 to be turned on through the output data acquisition unit, so that the II-way DC output plug is electrically connected to the DC connection main circuit; the output control contactor K3 and the output control contactor K4 can be turned on at the same time. Correspondingly, the AC power supply subsystem is also the same principle.

[0062] S4, for the started power supply subsystem, for the two power supply output plugs in the same power supply subsystem, the power control system detects the on-off information in real time, that is, detects whether there is an electrical signal between the power supply output plug and the DC side power unit.

[0063] S5, based on the on-off information, determine whether the two power output plugs have the target aircraft end load connected; if so, the power control system controls the corresponding power supply subsystem to supply power to the power output plug according to the location where the target aircraft end load is connected and the actual power usage on the aircraft; if not, the power output plug is not supplied with power. Specifically, take the I-way DC output plug of the DC power subsystem as an example: if there is an electrical signal between the I-way DC output plug and the DC connection main circuit, it is determined that the I-way DC output plug is connected to the DC connection main circuit, indicating that the target aircraft end load is connected and power needs to be supplied to the I-way DC output plug; otherwise, it indicates that there is no target aircraft end load connected and power does not need to be supplied to the I-way DC output plug. The same principle applies to the II-way DC output plug. The power control unit can control the DC side power unit to supply power to the I-way DC output plug and the II-way DC output plug at the same time. The same principle applies to the AC power subsystem.

[0064] S6, for each single connected target aircraft-end load, determine whether its power supply is completed; if so, proceed to step S7, if not, the power control system controls the corresponding power supply subsystem to maintain the power supply state to the target aircraft-end load until it is determined that its power supply has been completed, and then proceed to step S7.

[0065] S7, operate through the LCD screen operation unit, cooperate with the power control system to control the corresponding power supply subsystem to disconnect the power output of the power supply output plug connected to the target aircraft end load. Take the Ⅰ-way DC output plug as an example, in the Ⅰ-way interface, corresponding to the Ⅰ-way control interface of the DC power subsystem, click the "disconnect button", and the power control unit can control the output control contactor K3 to disconnect through the output data acquisition unit. The same principle applies to the Ⅱ-way DC output plug, Ⅰ-way AC output plug and Ⅱ-way AC output plug.

[0066] S8, for the started power supply subsystem, determine whether its two power supply output plugs are both in the disconnected state according to the on-off information; if so, the current power supply task of the power supply subsystem is completed, and the power supply subsystem is turned off; if not, return to step S6. Specifically, taking the DC power supply subsystem as an example: when the DC output plug Ⅰ and the DC output plug Ⅱ are connected to the aircraft end load, only when the aircraft end load is electrically disconnected from the DC side power unit when the aircraft end load is electrically disconnected from the DC side power unit, the power supply subsystem can be turned off by the "stop button"; when the DC output plug Ⅰ and the DC output plug Ⅱ are both connected to the aircraft end load, the power supply subsystem can be turned off by the "stop button" after both the aircraft end loads are electrically disconnected from the DC side power unit.

[0067] Example 8 This embodiment discloses a power control method for aircraft ground power supply equipment. As a preferred implementation scheme of the present technical solution, in order to solve the problem of low grid connection rate of conventional ground power supply, the present technical solution adopts a matrix shared data processing method, that is, on the basis of Example 7, in step S5, the power control system controls the power supply subsystem to supply power to the power supply output plug based on the matrix shared data processing method, that is, the power control system cooperates with the matrix relay to share data between the power modules, and controls the switching output of the power modules based on the shared data; in the DC power supply subsystem, the power module refers to the DC power module, and in the AC power supply subsystem, the power module refers to the AC power module.

[0068] Specific, combined Figure 2 , Figure 3 and Figure 4 As shown in the figure, take the DC power subsystem as an example: in actual use, part of all the DC power modules in the DC side power unit are put into operation (called the operating power module), and the remaining part is in the backup state (called the backup power module). On this basis, the operating power module and the backup power module share data and switch output according to the control data. The principle of matrix data sharing is as follows Figure 4As shown, it is composed of multiple matrix switch modules (provided by the first matrix relay). Each matrix switch controls a signal input, output or selects a signal as a ground line. When multiple matrices work at the same time, the channels are isolated from each other and do not interfere with each other. The main function of the matrix-type shared data processing method is to distribute different loads from the same power supply to different ports, or to distribute different loads from different power supplies to one port. It can also keep the load on a port unchanged and redistribute the loads of other ports.

[0069] exist Figure 4 In the figure, r0, r1, r2, and r3 represent DC power modules respectively, and the number of r represents the number of DC power modules; c0~c2…c27~c31 represent the signal interfaces of each DC power module, and the number of c is equal to the number of r, and c and r are in a matrix symmetrical form. After the DC power subsystem is powered on, each DC power module (r0, r1, r2, and r3) is connected through the first matrix relay (see Figure 4 The enlarged part of the circle in the middle communicates with the power control unit by closing the first matrix relay switch to make the "+" circuit and the "-" circuit form a complete path). The module control unit monitors the working status of each DC power module in real time, such as output voltage, output current and output power. When the module control unit collects the total output current and output voltage, it automatically compares the power of each DC power module, and the total output power is equal to the sum of the powers of all operating power modules. When the total power consumption is low, the module control unit automatically disconnects the low-power operating power module according to the usage of each operating power module, disconnects the operating power module, and puts it in standby mode, that is, it becomes a backup power module. In summary, if there is a sudden increase or decrease in the load on the aircraft end, the backup power module can be put into operation quickly based on the matrix-based shared data processing method described in this technology.

[0070] Example 9 This embodiment discloses a power control method for aircraft ground power equipment, as a preferred implementation scheme of this technical scheme, that is, on the basis of Example 8, the power control system controls the power supply subsystem to supply power to the power supply output plug, and also includes trying to detect the fault condition of each power module, and according to the fault condition of the power module, controls each power module to switch output in combination with the matrix shared data processing method. Also taking the DC power supply subsystem as an example, specifically: the power control unit monitors whether the row power module is faulty in real time through the data signal acquisition unit. If so, the faulty row power module is cut off. Because the matrix shared data is adopted between the DC power modules, the power control unit can control the backup power module to be quickly and automatically randomly put into the aircraft power grid with a nanosecond response time, and become the operating power module. At the same time, the output data acquisition unit samples the voltage signal and current signal output by the DC online main circuit in real time, and the corresponding voltage value and current value are displayed on the LCD screen operation unit through the power control unit. If it is checked that the current operating power module does not meet the aircraft output requirements, the power control unit calculates the number of backup power modules to be added or the number of operating power modules to be reduced, and controls the backup power module to be quickly and automatically randomly put into the aircraft power grid with a nanosecond response time, or controls the connection of the operating power module to be cut off.

Claims

1. A power control device for aircraft ground power supply equipment, characterized in that: It includes a power supply cabin and a dual-system power supply system; the dual-system power supply system is arranged inside the power supply cabin, and includes a DC power supply subsystem, an AC power supply subsystem, a power control system and at least one liquid crystal screen operation unit; The DC power supply subsystem includes a first working power supply, a DC side power unit, a I-way DC output plug and a II-way DC output plug; the first working power supply is electrically connected to the DC side power unit through an input control contactor K1; The Ⅰ-way DC output plug and the Ⅱ-way DC output plug are electrically connected to the DC side power unit through the output control contactor K3 and the output control contactor K4 respectively; The AC power subsystem includes a second working power supply, an AC side power unit, a first-way AC output plug, and a second-way AC output plug; the second working power supply is electrically connected to the AC side power unit through an input control contactor K2; the first-way AC output plug and the second-way AC output plug are electrically connected to the AC side power unit through output control contactors K5 and K6, respectively; The power control system is respectively connected to the DC power subsystem and the AC power subsystem for communication, and is used to collect the actual power information used by the aircraft and the working signals of the DC power subsystem and the AC power subsystem, and control the power supply output of the DC power subsystem and the AC power subsystem based on the actual power information and the working signals; The LCD screen operation unit is electrically connected to the power control system, and is used to display and collect working signals of the DC power subsystem and the AC power subsystem, and cooperate with the power control system to query the working status of the DC power subsystem and the AC power subsystem and control power supply.

2. The power control device for aircraft ground power supply equipment according to claim 1, characterized in that: The DC side power unit includes a DC online main circuit and a plurality of DC power modules; The input ends of all DC power modules are electrically connected to the first working power supply respectively; the output ends of all DC power modules are electrically connected to the DC online main circuit respectively, and all DC power modules are communicatively connected to the power control system through the first matrix relay; the I-way DC output plug and the II-way DC output plug are electrically connected to the DC online main circuit respectively; The DC online main circuit is communicatively connected with the power control system, and is used to select a corresponding number of DC power modules to be connected to participate in the power supply output to the I-way DC output plug and / or the II-way DC output plug according to the module number selection instruction issued by the power control system.

3. The power control device for aircraft ground power supply equipment as claimed in claim 2, characterized in that: The AC side power unit includes an AC online main circuit and a plurality of AC power modules; The input ends of all AC power modules are electrically connected to the second working power supply respectively; the output ends of all AC power modules are electrically connected to the AC online main circuit respectively; all AC power modules are communicatively connected to the power control system through the second matrix relay; the I-way AC output plug and the II-way AC output plug are electrically connected to the AC online main circuit respectively; The AC online main circuit is in communication connection with the power control system, and is used to select a corresponding number of AC power modules to be connected to participate in supplying power to the I-way AC output plug and / or the II-way AC output plug according to the module number selection instruction issued by the power control system.

4. A power control device for aircraft ground power supply equipment as claimed in claim 3, characterized in that: The second working power supply is provided with an AC input and EMI filter module II, and the AC power module includes a rectifier soft start module II, a rectifier two-stage filter module II, a power inverter module II, a medium frequency isolation transformer module, and a medium frequency two-stage filter module which are electrically connected in sequence; wherein, the rectifier soft start module II is connected to the output end of the AC input and EMI filter module II; the rectifier soft start module II and the power inverter module II are respectively communicated with the power control system, and a drive module II is connected between the power inverter module II and the power control system.

5. The power control device for aircraft ground power supply equipment as claimed in claim 3, characterized in that: The power control system includes two sets of control subsystems corresponding to the DC power subsystem and the AC power subsystem, and each set of control subsystem includes a power control unit, a data signal acquisition unit, an output data acquisition unit and an online control unit; The data signal acquisition unit is in communication connection with the power control unit, and is used to collect the power output signal and obtain the actual power information used on the aircraft, and send the collected power output signal and the actual power information used on the aircraft to the power control unit; The output data acquisition unit is connected to the power control unit for real-time acquisition of power supply output information, and sends the power supply output information to the power control unit, and cooperates with the power control unit to complete power supply on-off control; wherein the power supply output information includes on-off information, voltage information and current information; The power control unit is used to determine the system fault condition according to the power output signal, and control the power output in combination with the power output information and the actual power used on the aircraft; The online control unit is respectively connected to the output data acquisition unit and the power control unit for communication, and is used to connect the two control subsystems through the online interface to establish conditions for the DC power subsystem and the AC power subsystem to query each other's working status and control each other's power supply.

6. The power control device for aircraft ground power supply equipment as claimed in claim 2, characterized in that: The first working power supply is provided with an AC input and EMI filter module I, and the DC power module includes a rectifier soft start module I, a rectifier two-stage filter module I, a power inverter module I, a high-frequency isolation transformer module, and a high-voltage rectifier two-stage filter module which are electrically connected in sequence; wherein, the rectifier soft start module I is connected to the output end of the AC input and EMI filter module I; the rectifier soft start module I and the power inverter module I are respectively communicated with the power control system, and a drive module I is connected between the power inverter module I and the power control system.

7. The power control device for aircraft ground power supply equipment as claimed in claim 2, characterized in that: It comprises two liquid crystal screen operating units, and the two liquid crystal screen operating units are respectively connected with the power control units in the two sets of control subsystems in a one-to-one correspondence.

8. A method for controlling power of aircraft ground power equipment as claimed in claim 2, characterized in that: A power control device for aircraft ground power supply equipment as claimed in any one of claims 2 to 7 is used, comprising the following steps: S1, start the dual-system power supply system and connect the target aircraft end load to the dual-system power supply system; S2, according to the access position of the target aircraft end load, using the LCD screen operation unit to start the corresponding power supply subsystem; wherein the power supply subsystem refers to the DC power supply subsystem and the AC power supply subsystem; S3, according to the position where the load at the target aircraft end is connected, using the LCD screen operation unit to control the corresponding power output plugs to be electrically connected; wherein the power output plugs refer to a first-channel DC output plug, a second-channel DC output plug, a first-channel AC output plug and a second-channel AC output plug; S4, for the started power supply subsystem, the power control system detects the on / off information of the two power supply output plugs in the same power supply subsystem in real time; S5, judging whether the two power output plugs have a target aircraft end load connected to them one by one based on the on-off information; if so, the power control system controls the corresponding power supply subsystem to supply power to the power output plug according to the location where the target aircraft end load is connected and the actual power usage on the aircraft; if not, the power output plug is not supplied with power; S6, for each single target aircraft load connected, determine whether the power supply is completed; if so, proceed to step S7, if not, the power control system controls the corresponding power supply subsystem to maintain the power supply state for the target aircraft load; S7, operating through the LCD operating unit, cooperating with the power control system to control the corresponding power supply subsystem to disconnect the power output to the power output plug connected to the load at the target aircraft end; S8, for the started power supply subsystem, determine whether its two power output plugs are both in the disconnected state according to the on-off information; if so, the current power supply task of the power supply subsystem is completed and the power supply subsystem is turned off; if not, return to step S6.

9. A power control method for aircraft ground power equipment as claimed in claim 8, characterized in that: In step S5, the power control system controls the power supply subsystem to supply power to the power output plug based on a matrix shared data processing method, that is, the power control system cooperates with the matrix relay to share data between the power modules, and controls the switching output of each power module based on the shared data; in the DC power subsystem, the power module refers to the DC power module, and in the AC power subsystem, the power module refers to the AC power module.

10. A power control method for aircraft ground power equipment as claimed in claim 9, characterized in that: In step S5, the power control system controls the power supply subsystem to supply power to the power output plug, and also includes trying to detect the fault condition of each power module. According to the fault condition of the power module, the power modules are controlled to switch output in combination with the matrix shared data processing method.

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