Electric power-assisted towing integrated aircraft ground power supply control system and method

Abstract

The invention discloses an electric power-assisted towing integrated aircraft ground power supply control system and method, belonging to the technical field of aircraft ground static variable power supply, comprising an electric chassis vehicle and an aircraft ground power supply mounted on the electric chassis vehicle, wherein the electric chassis vehicle comprises a power assembly and a power supply unit, one end of the power supply unit is connected to the aircraft ground power supply, and the other end is connected to the power assembly, and the power assembly is provided with a mode switching switch for switching the power assembly between neutral and non-neutral gears, and the system further comprises a power supply controller, which is respectively connected to the aircraft ground power supply, the power supply unit and the power assembly for communication, and realizes free switching of a mobile power supply between an electric power-assisted mode and a towing mode according to the gear state of the power assembly in the electric chassis vehicle for different use scenarios, so as to achieve the purpose of greatly improving the use efficiency of the aircraft ground power supply unit, effectively reducing the pollution of the aircraft APU to the environment and greatly reducing the cost.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft ground static variable power supply, and in particular, relates to an electric power-assisted towing integrated aircraft ground power supply control system and method. Background Art

[0002] At present, the airport's movable aircraft static power sources mainly include internal combustion engine-mounted aircraft ground power sources and towed vehicle-mounted aircraft ground power sources, both of which have shortcomings. Among them, the internal combustion engine-mounted aircraft ground power source uses the internal combustion engine to provide power, which pollutes the environment, wastes energy and is noisy; the towed vehicle-mounted aircraft ground power source requires a dedicated trailer to provide power, especially for airport close-range use occasions. Since the use of power sources and trailers belongs to different departments, the coordination efficiency is low and manpower is wasted. Summary of the invention

[0003] In view of this, in order to solve the above-mentioned problems existing in the prior art, the purpose of the present invention is to provide an electric power-assisted towing integrated aircraft ground power control system and method so as to greatly improve the utilization efficiency of the aircraft ground power unit, effectively reduce the pollution of the aircraft APU to the environment and greatly reduce the cost.

[0004] The technical solution adopted by the present invention is: an electric power-assisted towing integrated aircraft ground power control system, including an electric chassis vehicle and an aircraft ground power installed on the electric chassis vehicle, the electric chassis vehicle includes a power assembly and a power supply unit, one end of the power supply unit is connected to the aircraft ground power supply, and the other end is connected to the power assembly, and the power assembly is equipped with a mode switching switch for switching it between neutral and non-neutral. The system also includes a power controller, which is respectively communicated with the aircraft ground power supply, the power supply unit and the power assembly.

[0005] Furthermore, the aircraft ground power supply includes an input module, an energy storage battery and an output module. The input module and the output module are both communicatively connected to the power controller, and the energy storage battery is electrically connected to the power converter. On the one hand, the aircraft ground power supply can directly supply power to the aircraft through the power conversion device; on the other hand, the energy storage battery can also directly supply power to the aircraft through the 400HZ output socket. When the aircraft ground power supply ends and the energy storage battery is out of power, the power grid can charge the energy storage battery.

[0006] Furthermore, the output module includes a 400HZ output socket, which is equipped with a 400Hz limit switch, the 400Hz limit switch is connected to the power controller, and the 400Hz limit switch is interlocked with the power supply and the aircraft; when the 400Hz plug is not taken out of the power plug box, the 400Hz limit switch does not operate, and the power supply can operate at this time, but the 400Hz power cannot be output.

[0007] Furthermore, it also includes an auxiliary power supply and a main switch, the main switch includes at least two paths and each path is connected or disconnected at the same time, one path is connected between the power supply unit and the power assembly, and the other path is connected between the auxiliary power supply and the power controller, so as to realize power supply to the power assembly and the power controller.

[0008] Furthermore, the power supply unit includes a power converter, a battery and a charging conversion unit. One end of the power converter is connected to the ground power supply of the aircraft, and the other end is connected to the charging conversion unit. The other end of the charging conversion unit is connected to the battery. When the battery power of the electric chassis vehicle is sufficient, the battery supplies power to the powertrain; when the battery power is insufficient, the energy storage battery charges the battery through the power converter, the charging conversion unit, etc.

[0009] Furthermore, it also includes a charging switch, which is connected between the auxiliary power supply and the power controller, and the charging switch and the main switch are not turned on at the same time to realize the charging protection function, thereby achieving interlocking of charging and aircraft ground power movement, and aircraft ground power supply to the aircraft.

[0010] Furthermore, the power supply unit includes a DC / DC converter, one end of which is connected to the ground power supply of the aircraft, and the other end of which is connected to the power assembly through a main switch and supplies power to the power assembly to ensure that the electric chassis vehicle has sufficient endurance and avoid damage to the power battery.

[0011] Furthermore, the power assembly includes a controller, a backstop and a reducer unit connected in sequence, the reducer unit is connected to the mode switching switch, the controller is powered by a power supply unit and the controller is communicatively connected to a power supply controller.

[0012] Furthermore, the electric chassis vehicle also includes a body and a handle hinged on the body, the handle is provided with an operating component and the operating component is connected to the controller, and also includes a first limit switch and a second limit switch, the first limit switch and the second limit switch are respectively connected to the controller and the check valve, and the vertical state and horizontal state of the handle respectively trigger the first limit switch and the second limit switch to act, and the second limit switch can prevent the control circuit in the powertrain from burning out due to misoperation.

[0013] Furthermore, the operating component includes a rotary gear lever, a gear position switch and a power display meter respectively connected to the controller, so that the operator can operate the electric chassis vehicle well.

[0014] Furthermore, it also includes a safety device component, and the auxiliary power supply supplies power to the safety device component through a main switch. The safety device component includes a combination of one or more of a reversing radar, a reversing image and a driving recorder to improve the operating safety of the mobile power supply.

[0015] The present invention also discloses a method for controlling a ground power supply of an electric power-assisted towing integrated aircraft, which is applied to the ground power supply control system of the electric power-assisted towing integrated aircraft described in any one of the above items. The method comprises:

[0016] Get the gear status of the powertrain in the electric chassis vehicle. If it is neutral, enter the towing mode; if it is not neutral, enter the electric power assist mode;

[0017] When entering the towing mode, the electric chassis vehicle is moved by towing the trailer;

[0018] When entering the electric power-assist mode, it is determined whether the aircraft ground power supply is in working state. If it is "yes", the electric chassis vehicle is kept in a stopped state. If it is "no", the electric chassis vehicle is started to move forward or backward.

[0019] The beneficial effects of the present invention are:

[0020] 1. The electric power-assisted towing integrated aircraft ground power control system provided by the present invention receives the signals transmitted by the aircraft ground power and the electric chassis vehicle in real time through the power controller, and can realize the free switching of the aircraft ground power between the electric power-assisted mode and the towing mode. Compared with the traditional technology, on the one hand, it does not have the disadvantages of polluting the environment, wasting energy, and making loud noise of the traditional internal combustion engine vehicle-mounted aircraft ground power; on the other hand, it does not have the disadvantages of low cross-departmental coordination efficiency and waste of manpower of the towing vehicle-mounted aircraft ground power, and the disadvantages are obvious in the case of close aircraft positions. At the same time, the power controller controls the aircraft ground power to charge the power supply unit, which can improve the endurance performance of the electric chassis vehicle.

[0021] 2. The electric-assisted towing integrated aircraft ground power control system provided by the present invention has an electric-assisted mode suitable for use at close range at the airport, with simple operation and high efficiency; its towing mode can be used at long distances at the airport and can also quickly reach the designated location, thereby improving the use efficiency; the aircraft ground power supply including these two modes can well solve the problems existing in the current use of mobile power supplies at airports. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is the overall system architecture diagram of the electric power-assisted towing integrated aircraft ground power control system provided by the present invention;

[0023] Figure 2 It is a working logic diagram of the charging function in the ground power supply control system of the electric power-assisted towing integrated aircraft provided by the present invention;

[0024] Figure 3It is a working logic diagram of the electric power-assisting mode and the towing mode in the ground power supply control system of the electric power-assisting towing integrated aircraft provided by the present invention;

[0025] Figure 4 It is a schematic diagram of the overall structure of the electric power-assisted towing integrated aircraft ground power control system provided by the present invention;

[0026] Figure 5 It is a partial structural schematic diagram of the electric chassis vehicle in the electric power-assisted towing integrated aircraft ground power control system provided by the present invention;

[0027] Figure 6 It is an overall system architecture diagram of another embodiment of the electric power-assisted towing integrated aircraft ground power control system provided by the present invention;

[0028] The following are marked in the attached figure:

[0029] 1-cabinet; 2-charging indicator light; 3-output module; 4-400HZ output socket; 5-electric chassis vehicle; 6-power converter; 7-energy storage battery; 8-grid socket; 9-input module; 21-body; 22-battery box; 23-controller; 24-battery; 25-rotary gear lever; 26-main switch; 27-gear shift switch; 28-handle; 29-connecting pin; 30-fixed connector; 31-front tire; 32-reducer unit; 33-rear tire. DETAILED DESCRIPTION

[0030] Embodiments of the present application are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar modules or modules with the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present application, and cannot be construed as limitations on the present application. On the contrary, the embodiments of the present application include all changes, modifications and equivalents that fall within the spirit and connotation of the appended claims.

[0031] Example 1

[0032] like Figure 1 , Figure 4As shown, in this embodiment, a ground power control system for an electric power-assisted towing integrated aircraft is specifically provided, including an electric chassis vehicle 5 and an aircraft ground power supply installed on the electric chassis vehicle 5, wherein the aircraft ground power supply includes a cabinet 1 and an input module 9, an energy storage battery 7 and an output module 3 installed inside the cabinet 1, wherein the cabinet 1 is installed on the electric chassis vehicle 5 by bolt connection, wherein the input module 9 and the output module 3 are both communicatively connected with the power controller, and are used to feed back signals of whether the input module 9 is connected to the AC power grid and whether the output module 3 is connected to the aircraft to the power controller, wherein the power controller can be installed in the cabinet 1 or can be separately provided, which is not limited here; wherein the input module 9 can adopt an AC / DC module and the AC / DC module is connected to a power grid socket 8, and the output module 3 can adopt a DC / AC module and the DC / AC module is connected to a 400HZ output socket 4, and the 400HZ output socket 4 finally provides 115V / 400Hz AC power to the aircraft. The working principle of the aircraft ground power supply is as follows: the aircraft ground power supply is mainly used for parking positions and self-sliding positions with small power distribution capacity, or as a support equipment when the traditional power supply at the airport fails. The aircraft ground power supply can be powered by the power grid and the energy storage battery together, or by the energy storage battery alone. When the power supply is finished, the aircraft ground power supply is pulled back to the designated area, and then connected to the power grid to charge the energy storage battery 7; the external power grid supplies power to the aircraft ground power supply through the power grid socket 8. On the one hand, it can directly power the aircraft through the power conversion device; on the other hand, the energy storage battery 7 can also directly power the aircraft through the 400HZ output socket 4. When the aircraft ground power supply is finished and the energy storage battery 7 is low on power, the power grid can charge the energy storage battery 7.

[0033] The electric chassis vehicle 5 includes a powertrain and a power supply unit, one end of which is connected to the energy storage battery 7 via a power converter 6, and the other end is connected to the powertrain, and the powertrain is equipped with a mode switch for switching it between neutral and non-neutral. The powertrain and the power supply unit are designed as follows:

[0034] The powertrain includes a controller 23, a backstop and a reducer unit 32 connected in sequence. The reducer unit 32 is connected to a mode switch, and the mode switch is used to switch the reducer unit 32 to neutral or working gear (non-neutral). The reducer unit 32 adopts an existing electric drive assembly on the market, which is composed of a reduction box, a drive motor, a power electronics box and an electric shift system. It can switch between forward gear, reverse gear and neutral gear. The forward gear and reverse gear are working gears. The controller 23 is powered by a battery and the controller 23 is connected to the power controller in communication, so that the power controller can grasp the working status of the controller 23 in real time. In this embodiment, the main control chip of the power controller adopts an MCU+FPGA architecture; the controller in the electric chassis vehicle 5 is a motor controller with DC input.

[0035] To achieve effective operation of the electric chassis vehicle 5, Figure 5 As shown, the electric chassis vehicle 5 also includes a vehicle body 21 and a handle 28 hinged on the vehicle body 21, the wheels on the vehicle body 21 are transmission-connected to the reducer unit 32, and a towing traction rod is installed on the handle 28, so as to realize the towing operation of the electric chassis vehicle 5 through the towing traction rod; the vehicle body 21 is provided with a front tire 31 and a rear tire 33, and the handle 28 is hinged to a fixed connection member 30 through a connecting pin 29, and the fixed connection member 30 is provided on the vehicle body 21. The handle 28 is provided with an operating component and the operating component is connected to the controller 23, and the operating component includes a rotary gear lever 25, a gear position switching switch 27 and a power display meter respectively connected to the controller 23. A first limit switch and a second limit switch are also provided at the hinged portion of the handle 28 and the vehicle body 21. The first limit switch and the second limit switch are connected to the controller 23 and the backstop, respectively. The vertical state and the horizontal state of the handle 28 trigger the first limit switch and the second limit switch to act, respectively. The trigger signals of the first limit switch and the second limit switch are used to determine whether the current mobile power supply is in the electric assist mode or the towing mode. The backstop is designed for the following purposes:

[0036] (1) When an erroneous operation occurs (the gear position of the reducer unit 32 is not neutral, but the electric chassis vehicle 5 is being towed), high-speed towing will cause the motor in the reducer unit 32 to generate electricity. The large current is likely to burn out the controller 23. To prevent this from happening, a check valve is designed. Since a second limit switch is installed at the hinge between the handle 28 and the vehicle body 21, when in the towing state, the handle 28 must be placed flat. The second limit switch is actuated, and the second limit switch controls the check valve to disconnect. At this time, the circuit from the controller 23 to the reducer unit 32 will be disconnected, and there will be no risk of burning out the controller 23.

[0037] (2) When the handle 28 is in a vertical state, the first limit switch is actuated, and the first limit switch feeds back a signal to the controller 23. The controller 23 feeds back a signal to the power controller, and the power controller controls the output module 3. The output module 3 can then supply power to the aircraft. At the same time, the controller 23 receives a signal and is in a locked state. At this time, the electric chassis vehicle 5 cannot move.

[0038] The power supply unit includes a power converter 6, a battery 24 and a charging conversion unit. A battery box 22 for placing the battery 24 is provided on the vehicle body 21. One end of the charging conversion unit is electrically connected to the power converter 6, and the other end is connected to the battery 24. The power converter 6 converts the electric energy of the energy storage battery 7 and supplies power to the charging conversion unit. The charging conversion unit charges the battery 24. Alternatively, the charging conversion unit is electrically connected to the power grid socket, and the power grid socket can be connected to the power grid to directly charge the battery through alternating current to ensure that the electric chassis vehicle 5 has good endurance. The battery 24 is connected to the controller 23 through the main switch 26 and supplies power to the controller 23, so that the controller 23 can be in a working state in the initial state.

[0039] It also includes an auxiliary power supply and a main switch 26. The auxiliary power supply is mainly used to supply power to the controller 23 and the power controller. The main switch 26 includes three paths and each path is connected or disconnected at the same time, that is, each path of the main switch 26 is linked. The first path is connected between the battery and the controller 23, and the second path is connected between the auxiliary power supply and the power controller.

[0040] In order to realize the charging protection function of the electric chassis vehicle 5, a charging switch is set, and the charging switch is connected between the auxiliary power supply and the power controller, and the charging switch and the main switch 26 are not turned on at the same time (for not being turned on at the same time, for example, the simplest design of the main switch 26 and the charging switch: a switch similar to a single-pole double-throw is adopted, and three ways of the main switch 26 are provided on one side of the switch, and the three ways are connected after the knife is thrown into this side, and two ways of the charging switch are provided on the other side, and the charging circuit is connected after the knife is thrown into this side. When the knife is in the middle position, the charging switch and the main switch 26 are both in the disconnected state), thereby realizing the interlocking of charging and the movement of the mobile power supply, and the interlocking of the mobile power supply to the aircraft (when charging, the charging signal is received by the power controller, and the output module is controlled not to work, and the energy storage battery is not allowed to supply power to the aircraft). That is to say, when the battery of the electric chassis vehicle 5 is charging, the mobile power supply cannot move; when the mobile power supply moves, it cannot be charged, such as Figure 2 As shown, the specific working principle is as follows:

[0041] By observing the power display on the electric chassis vehicle 5, when the power of the battery in the power supply unit is low, operate the charging switch. When the charging switch is turned on, the main switch 26 is disconnected (cannot be turned on). At this time, the controller 23 is not powered, the electric chassis vehicle 5 cannot be operated and remains in a stopped state. The power controller is powered and controls the power converter 6, so that the energy storage battery 7 charges the battery in the power supply unit through the power converter 6 until it is charged to the set value. The charging indicator light 2 of the charging conversion unit in the power supply unit is activated (from red during charging to full green), and charging is automatically stopped. The charging switch is manually reset. At this time, the charging switch and the main switch 26 are both disconnected; conversely, when it is needed To move the power source, operate the main switch 26. When the main switch 26 is turned on, the charging switch is turned off. At this time, the controller 23 and the power controller are both powered, and the electric chassis vehicle 5 can be operated and freely switched between the electric power-assist mode and the towing mode. However, the charging control terminal in the power controller does not obtain the corresponding level (the simplest relay control can also be used here, and the path end of the relay is set between the power converter 6 and the energy storage battery 7, and the control end of the relay is connected to the charging switch. Of course, other control logics inside the power controller can also be used), then the power converter 6 will not be connected to the energy storage battery 7. At this time, the power converter 6 remains in an inoperative state and the battery is not charged.

[0042] To further realize double protection, the output module 3 includes a 400HZ output socket, which is equipped with a 400Hz limit switch. The 400Hz limit switch is connected to the power controller to realize the interlock between the mobile power supply to the aircraft and charging. When the 400HZ plug is taken out of the 400HZ output socket and plugged into the aircraft, the 400HZ limit switch is actuated and a signal is input to the power controller, and charging is not allowed. The simplest way is to connect the 400HZ limit switch and the charging switch in series. Only when both are turned on can the battery be charged. Of course, this circuit is the simplest implementation method in theory. In actual application, considering the actual situation, the power converter 6 can also be controlled not to work through the logic circuit inside the power controller to realize the protection function. At the same time, when the 400Hz limit switch is activated, if the main switch 26 is in the on state at this time, the power controller receives the signal of the 400Hz limit switch and feeds the signal back to the controller 23. The controller 23 is in a locked state and cannot operate the electric chassis vehicle 5, and the electric chassis vehicle 5 cannot move.

[0043] like Figure 3 As shown, in order to realize the protection function of the mobile power supply during operation, the following design is adopted:

[0044] The input module 9, the output module 3, the power converter 6 and the power assembly are respectively connected to the power controller for communication. The working principle of the protection is as follows:

[0045] (1) When the electric chassis 5 is moving, the ground power supply of the aircraft shall not be output. The specific implementation process is as follows: the circuit of the main switch 26 is turned on, the power controller and the controller 23 are powered on, the forward and reverse switching buttons in the receiving operation component of the controller 23 must be placed in the "stop" gear, and the signal is fed back to the power controller. The power controller controls the 400Hz output contactor in the output module 3 to be turned on, and then power can be supplied to the aircraft; otherwise, it is disconnected, and the ground power supply of the aircraft shall not be output.

[0046] (2) When the aircraft ground power supplies power to the aircraft, the electric chassis vehicle 5 must not move. The specific implementation process is as follows: after the aircraft plug is inserted into the aircraft, the output module 3 feeds back a signal to the power controller, and the power controller outputs a signal to the controller 23 of the chassis vehicle. The controller 23 is in a locked state and cannot operate the electric chassis vehicle 5, so that the electric chassis vehicle 5 cannot move.

[0047] (3) The mode switch is interlocked with the electric power assist function of the chassis vehicle. When the mode switch switches the reducer unit 32 to neutral, the controller 23 cuts off the control signal of the operating component, and the corresponding function of the electric power assist mode cannot be operated;

[0048] In order to realize the safe operation of the mobile power supply during operation, a safety device component is also included. The auxiliary power supply supplies power to the safety device component through the main switch 26. The safety device component includes a reversing radar, a reversing image and a driving recorder. Among them, the reversing radar, the reversing image and the driving recorder are all mature products that can be directly purchased on the market. According to actual needs, the reversing radar, the reversing image and the driving recorder can be installed in an appropriate position, and the reversing radar, the reversing image and the driving recorder are all powered by the auxiliary power supply. The third circuit in the main switch 26 is used to connect or disconnect the power supply to the reversing radar, the reversing image and the driving recorder. When the reversing radar, the reversing image and the driving recorder are powered on, they can work normally respectively, so that the operator can control the surrounding environment and conditions of the mobile power supply in real time during the movement. Take the reversing radar as an example: add a certain number of reversing radar probes behind the electric chassis and on the left and right sides. When an obstacle is detected, the alarm bell rings to remind the operator to operate carefully.

[0049] Example 2

[0050] like Figure 6As shown, on the basis of Example 1, another electric power-assisted towing integrated aircraft ground power control system is provided in this embodiment, in which the corresponding charging switch circuit is cancelled, and the power supply unit is designed in the following manner: including a DC / DC converter, one end of the DC / DC converter is connected to the energy storage battery in the aircraft ground power supply, and the other end is connected to the controller in the power assembly through a main switch and supplies power to the power assembly. In this embodiment, the movement of the electric chassis vehicle in the electric power-assisted mode is converted by the energy storage battery of the aircraft ground power supply through the DC / DC converter and input into the power assembly to directly supply power to the power assembly, and it is unnecessary to charge the electric chassis vehicle separately, so as to avoid damage to the power battery of the electric chassis vehicle, and at the same time, it has good endurance.

[0051] In this embodiment, only the power supply unit is replaced and the corresponding circuit is optimized. The working principle and control logic thereof can be referred to the description in Embodiment 1 and will not be described again here.

[0052] Example 3

[0053] In this embodiment, a method for controlling ground power supply of an electric power-assisted towing integrated aircraft is specifically provided, which is applied to the ground power supply control system of the electric power-assisted towing integrated aircraft described in the above embodiment 1. The method comprises:

[0054] Obtain the gear state of the powertrain in the electric chassis vehicle 5, if it is neutral, enter the towing mode; if it is not neutral, enter the electric power assist mode;

[0055] When entering the towing mode, the electric chassis vehicle 5 is moved by towing the trailer; at this time, the mode switching switch is placed in neutral, the handle 28 is laid flat, and the second limit switch is actuated, so that the check valve disconnects the circuit from the controller 23 to the reducer unit 32, and the trailer is towed and moved.

[0056] When entering the electric power-assist mode, it is determined whether the aircraft ground power supply is in working state. If it is "yes", the electric chassis vehicle 5 is kept in a stopped state. If it is "no", the electric chassis vehicle 5 is started to move forward or backward. The details are as follows: a single person operates, the mode switch is placed in the working gear (not neutral), the operating handle 28 is in a tilted state, the controller 23 is connected to the reducer unit circuit through the check valve, and the rotating handle is manually turned to operate the mobile power supply to move; in this state, the mode switch is placed in the working gear, the first limit switch and the second limit switch on the handle 28 do not act (the handle is tilted), the 400HZ limit switch acts (the aircraft plug is in the plug box), and the rotating handle is turned. The controller 23 detects the analog value given by the rotating handle and controls the reducer unit 32 to act, so that the mobile power supply moves forward or backward.

[0057] Preferably, in order to realize automatic switching of operating modes and avoid manual operation of buttons to realize mode switching, the following method is adopted: an angle sensor is provided at the hinge of the handle 28 to detect the rotation angle of the handle 28 in real time, and the detection signal is transmitted to the controller 23 in real time. When the handle 28 is in a vertical or completely horizontal state, the default drag mode is set; when the handle 28 is tilted at a certain angle (for example, 15° to 75°), it is in the electric power assist mode.

[0058] It should be noted that, in the description of this application, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. In addition, in the description of this application, unless otherwise specified, the meaning of "plurality" refers to at least two.

[0059] Any process or method description in a flowchart or otherwise described herein may be understood to represent a module, segment or portion of code that includes one or more executable instructions for implementing the steps of a specific logical function or process, and the scope of the preferred embodiments of the present application includes alternative implementations in which functions may not be performed in the order shown or discussed, including performing functions in a substantially simultaneous manner or in the reverse order depending on the functions involved, which should be understood by technicians in the technical field to which the embodiments of the present application belong.

[0060] It should be understood that the various parts of the present application can be implemented by hardware, software, firmware or a combination thereof. In the above-mentioned embodiments, multiple steps or methods can be implemented by software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented by hardware, as in another embodiment, it can be implemented by any one of the following technologies known in the art or their combination: a discrete logic circuit having a logic gate circuit for implementing a logic function for a data signal, a dedicated integrated circuit having a suitable combination of logic gate circuits, a programmable gate array (PGA), a field programmable gate array (FPGA), etc.

[0061] A person skilled in the art may understand that all or part of the steps in the method for implementing the above-mentioned embodiment may be completed by instructing related hardware through a program, and the program may be stored in a computer-readable storage medium, which, when executed, includes one or a combination of the steps of the method embodiment.

[0062] In addition, each functional unit in each embodiment of the present application may be integrated into a processing module, or each unit may exist physically separately, or two or more units may be integrated into one module. The above-mentioned integrated module may be implemented in the form of hardware or in the form of a software functional module. If the integrated module is implemented in the form of a software functional module and sold or used as an independent product, it may also be stored in a computer-readable storage medium.

[0063] The storage medium mentioned above can be a read-only memory, a magnetic disk or an optical disk, etc.

[0064] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0065] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. An electric power-assisted towing integrated aircraft ground power control system, comprising an electric chassis vehicle and an aircraft ground power supply mounted on the electric chassis vehicle, characterized in that: The electric chassis vehicle includes a powertrain and a power supply unit, one end of the power supply unit is connected to the aircraft ground power supply, and the other end is connected to the powertrain, and the powertrain is equipped with a mode switching switch for switching it between neutral and non-neutral gears; the system also includes a power controller, which is respectively connected to the aircraft ground power supply, the power supply unit and the powertrain in communication; the aircraft ground power supply includes an input module, an energy storage battery and an output module, the output module includes a 400HZ output socket, the 400HZ output socket is equipped with a 400Hz limit switch, and the 400Hz limit switch is connected to the power controller; it also includes an auxiliary power supply and a main switch; the power supply unit includes a power converter, a battery and a charging conversion unit, one end of the power converter is connected to the aircraft ground power supply, and the other end is connected to the power supply. The first end of the electric chassis vehicle is connected to a power supply, and the other end is connected to a charging conversion unit, the other end of the charging conversion unit is connected to a battery, the battery is connected to the power assembly through a main switch and supplies power to the power assembly; the power assembly includes a controller, a check valve and a reducer unit connected in sequence, the reducer unit is connected to the mode switching switch, the controller supplies power to it through a power supply unit and the controller is communicatively connected to the power controller; the electric chassis vehicle also includes a body and a handle hinged on the body, the handle is provided with an operating component and the operating component is connected to the controller, and also includes a first limit switch and a second limit switch, the first limit switch and the second limit switch are respectively connected to the controller and the check valve, and the vertical state and horizontal state of the handle respectively trigger the first limit switch and the second limit switch to act.

2. The electric power-assisted towing integrated aircraft ground power control system according to claim 1, characterized in that: The input module and the output module are both connected to the power controller for communication, and the energy storage battery is electrically connected to the power converter.

3. The electric power-assisted towing integrated aircraft ground power control system according to claim 1, characterized in that: The main switch includes at least two paths and each path is connected or disconnected at the same time, one path is connected between the power supply unit and the power assembly, and the other path is connected between the auxiliary power supply and the power controller.

4. The electric power-assisted towing integrated aircraft ground power control system according to claim 3, characterized in that: It also includes a charging switch, which is connected between the auxiliary power supply and the power controller, and the charging switch and the main switch are not turned on at the same time.

5. The electric power-assisted towing integrated aircraft ground power control system according to claim 1, characterized in that: It also includes a safety device component, and the auxiliary power supply supplies power to the safety device component through a main switch. The safety device component includes a combination of one or more of a reversing radar, a reversing image and a driving recorder.

6. A method for controlling ground power supply of an electric power-assisted towing integrated aircraft, characterized in that: Applied to the ground power supply control system of the electric power-assisted towing integrated aircraft according to any one of claims 1 to 5, the method comprises: Get the gear status of the powertrain in the electric chassis vehicle. If it is neutral, enter the towing mode; if it is not neutral, enter the electric power assist mode; When entering the towing mode, the electric chassis vehicle is moved by towing the trailer; When entering the electric power-assist mode, determine whether the aircraft ground power supply is in working state. If it is "yes", keep the electric chassis vehicle in a stopped state. If it is "no", start the electric chassis vehicle to move forward or backward.

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