Battery powered floor power unit with improved structure, operability, durability and maintenance

Abstract

An airport ground power unit for supplying electric current to an aircraft parked on the ground, a method of operating the ground power unit, a system for supplying electric current to an aircraft parked on the ground, a method of operating the system, a Y-adapter.

Description

[0001] Technical Field and Background Technology

[0002] This invention relates to a system for supplying current to an aircraft parked on the ground, the system comprising a battery-powered ground power unit (GPU). A battery-powered ground power unit is proposed in the related technology "Referenzbericht: eGPUEnergieversorgung von Flugzeugen" by ARADEX AG of Switzerland. Summary of the Invention

[0003] The inventors desired to improve the structure, operability, durability, and maintainability of such battery-powered GPUs. Therefore, the object of this invention is to provide a GPU with improved structure, operability, durability, and / or maintainability.

[0004] In this application, the term battery GPU generally refers to a GPU comprising one or more batteries. Additionally, it can be a hybrid GPU that further includes an internal combustion engine and a generator.

[0005] The aim of improving the operability of a battery GPU is achieved through a system for supplying current to an aircraft parked on the ground. The system includes a battery GPU for supplying current to an aircraft parked on the ground, preferably a battery GPU according to any embodiment of the battery GPU described herein. The battery GPU includes one or more batteries and an inverter for converting the output current of the one or more batteries into AC output current for supplying to the aircraft. The battery GPU includes an AC input port, and is configured to connect via the AC input port to an AC output connector of an auxiliary GPU to direct the AC output current of the auxiliary GPU to the aircraft via the AC input port.

[0006] The present invention is also implemented by a method of operating a system for supplying current to an aircraft parked on the ground, preferably a system according to the present invention, the system comprising a battery GPU for supplying current to the aircraft parked on the ground using one or more batteries, preferably using a GPU operation method according to any of the GPU operation methods described herein, preferably the battery GPU being a battery GPU according to any embodiment of the battery GPU embodiments described herein, and the system further comprising an auxiliary GPU for supplying current to the aircraft parked on the ground, wherein the method comprises the following steps:

[0007] Connect the auxiliary GPU's AC output connector to the battery GPU's AC input port, and direct the auxiliary GPU's AC output current to the aircraft via the AC input port.

[0008] Therefore, by switching the aircraft's power supply from one or more batteries of the battery GPU to the corresponding power source of the auxiliary GPU (such as a battery or generator), the continuous usage time of the battery GPU can be extended.

[0009] In another preferred system according to the invention, the AC input port includes an aircraft socket configured to connect to an aircraft output connector suitable for connection to an aircraft.

[0010] Therefore, multiple GPUs can be connected to each other using existing GPU aircraft output connectors. Conventional (e.g., diesel) GPUs can be easily used as auxiliary GPUs.

[0011] The aircraft socket is a type of socket integrated into the aircraft fuselage, to which the GPU's aircraft output connector is connected to power the aircraft. It is standardized (6 poles, 400Hz) and is known to those skilled in the art.

[0012] The aircraft socket is preferably embedded in the GPU housing. Alternatively, the GPU's output cable may be configured via a Y-type cable, thus giving the aircraft socket the corresponding features.

[0013] In another preferred system according to the invention, the battery GPU includes a Y-connector having two AC input ports, each including an aircraft socket, and an aircraft output connector, wherein the aircraft output connector of the battery GPU is connected to one of the two AC input ports. Preferably, the Y-connector includes an input coupling switch for each phase to be switched (e.g., four phases).

[0014] Therefore, battery-powered GPUs can be easily equipped with AC input ports.

[0015] In another preferred system according to the invention, the system is configured to synchronize the following with each other:

[0016] - The AC output current of the inverter of the battery GPU, preferably the phase angle and / or frequency and / or amplitude of the output, and

[0017] - The AC output current of the auxiliary GPU, preferably the phase angle and / or frequency and / or amplitude of the output.

[0018] This allows for a smooth switching of power delivery between GPUs. Preferably, the phase angle, frequency, and amplitude are synchronized. However, in practice, the parameter that has the greatest impact on smooth switching is likely the phase angle, because amplitude and frequency can be controlled precisely by each GPU, while the phase angle between the currents of the two GPUs is initially unrelated. Therefore, synchronizing only the phase angle of the output current may be sufficient for smooth switching.

[0019] In another preferred system according to the invention, the system (preferably a battery GPU) includes an input coupling switch, and wherein the system (preferably a battery GPU) is configured to:

[0020] - Detect parameters of the auxiliary GPU's AC output current (e.g., phase angle, frequency, or amplitude—preferably phase angle), and

[0021] - If the difference between the detected parameter and the corresponding parameter of the AC output current of the inverter of the battery GPU is less than or equal to a predetermined threshold, the input coupling switch is closed.

[0022] This enables a smooth switching of power delivery between GPUs. The detection step can be performed as part of the synchronization process.

[0023] In another preferred system according to the invention, the system (preferably a battery GPU) is configured to: translate parameters of the AC output current of the inverter of the battery GPU (e.g., phase angle, frequency, or amplitude – preferably phase angle); and / or translate parameters of the AC output current of the auxiliary GPU (e.g., phase angle, frequency, or amplitude – preferably phase angle) via, for example, a communication channel to the controller or inverter of the auxiliary GPU.

[0024] Therefore, the synchronization of these output currents can be accelerated by actively shifting one or more parameters of the GPU's output current.

[0025] In another preferred system according to the invention, the system (preferably a battery GPU) includes an output decoupling switch, and wherein the system (preferably a battery GPU) is configured to:

[0026] - If the input coupling switch is already switched to the closed state, then disconnect the output decoupling switch.

[0027] Therefore, disconnecting or disabling the inverter for the battery GPU ensures proper power delivery, thereby avoiding unbalanced power draw from both the battery GPU and the auxiliary GPU. Preferably, the output decoupling switch is switched within seconds or milliseconds after the input coupling switch has been switched to the closed state. Preferably, the decoupling switch can be one of the inverter's switches, used to disable the inverter.

[0028] In another preferred system according to the invention, the system further includes an auxiliary GPU, wherein the battery GPU and the auxiliary GPU are connected to each other via an AC input port of the battery GPU and an AC output connector of the auxiliary GPU.

[0029] In another preferred system according to the invention, in order to convert the output current of one or more batteries into the AC output current of an inverter, one or more batteries are connected to the input port of the inverter, and the system is configured to guide the AC output current of the auxiliary ground power supply unit from the AC input port to the aircraft via the input port of the inverter, wherein the system includes an input converter configured to convert the AC output current of the auxiliary ground power supply unit into DC current at the AC input port and output the DC current to the input port of the inverter.

[0030] Therefore, power from the auxiliary GPU can be fed to the DC bus of the battery GPU. The advantage of this topology is that uninterrupted power delivery can be achieved without synchronizing or timing the switching of the auxiliary GPU; however, it requires an input converter as an additional component. The auxiliary GPU can be started at any time because it will take over power initially when the DC voltage from the battery is lower than the output voltage of the input converter. Therefore, the auxiliary GPU only takes over the load when connected and the battery voltage is lower than the rectifier voltage. Additionally, if the auxiliary GPU fails and stops supplying power to the inverter, the battery will take over the load again. Preferably, the input converter is configured to provide a converted output voltage of approximately 15% to 25%, more preferably 20%, and / or approximately 325V dc of the maximum battery charge.

[0031] In another preferred system according to the invention, the input converter includes one or more of the following: a transformer, a rectifier, a filter, a filter diode, and a choke. The transformer and rectifier can be configured in any way, as long as the resulting ripple voltage is below a predetermined level.

[0032] In another preferred method of system operation according to the invention, the method further includes one or more of the steps a) to c):

[0033] a) Preferably, the following are synchronized by shifting the parameters (e.g., phase angle, frequency, amplitude) of the AC output current of the inverter of the battery GPU; and / or, for example, by shifting the parameters (e.g., phase angle, frequency, amplitude) of the AC output current of the auxiliary GPU via a communication channel to the controller of the auxiliary GPU:

[0034] - The AC output current of the inverter of the battery GPU, preferably the phase angle and / or frequency and / or amplitude of the output current, and

[0035] - The AC output current of the auxiliary GPU, preferably the phase angle and / or frequency and / or amplitude of the output current;

[0036] b) Detect parameters of the AC output current of the auxiliary GPU (e.g., phase angle, frequency, amplitude), and if the difference between the detected parameters and the corresponding parameters of the AC output current of the battery GPU inverter is less than or equal to a predetermined threshold, close the input coupling switch; and preferably,

[0037] c) If the input coupling switch is already switched to the closed state, then disconnect the output decoupling switch.

[0038] Preferably, the battery GPU is configured to perform phase angle / frequency / amplitude detection, synchronization, translation, and corresponding switching; and the corresponding hardware is preferably implemented in the battery GPU. Thus, the auxiliary GPU can be a conventional GPU without requiring further intervention for this purpose. However, the scope of the invention also covers solutions in which such tasks are performed (in whole or in part) by the auxiliary GPU or shared between the auxiliary GPU and the battery GPU. The auxiliary GPU and the battery GPU can therefore communicate via a communication channel to allow the desired operation.

[0039] In another preferred method of system operation according to the invention, the AC output current of the auxiliary ground power supply unit is directed from the AC input port to the aircraft via the input port of the inverter. Therefore, without specific synchronization, power delivery from the auxiliary GPU can be more easily enabled / disabled automatically based on power demand. Preferably, the AC output current of the auxiliary ground power supply unit is thus converted to DC current via the input converter of the battery GPU.

[0040] In addition, the operability of the battery GPU is improved by using a Y-connector, which has two AC input ports, each including an aircraft socket, and an aircraft output connector.

[0041] Therefore, battery-powered GPUs can be easily equipped with AC input ports.

[0042] The system according to the invention preferably includes a first embodiment of an airport battery GPU (preferably movable by wheels) for supplying current to an aircraft parked on the ground, the GPU comprising:

[0043] -First battery,

[0044] - An inverter is used to convert the battery's output current into the inverter's AC output current to supply the aircraft.

[0045] One or more first electronic switches are used to connect and disconnect a first battery from an inverter, wherein the one or more first switches are connected in series with the first battery, and wherein the series-connected first battery and the one or more first switches are connected together to the inverter.

[0046] - A first controller unit, used to control at least one of one or more first switches, preferably all of the first switches.

[0047] - Second battery, and

[0048] One or more second electronic switches are used to connect and disconnect the second battery from the inverter, wherein the one or more second switches are connected in series with the second battery, and wherein the series-connected second battery and the one or more second switches are connected together to the inverter so that they are connected in parallel with the series-connected first battery and one or more first switches, wherein at least one, preferably all, of the one or more second switches is controlled by a first digital controller unit or a second digital controller unit.

[0049] In addition to one or more first switches connected in series with the first battery, a first diode is also connected in series, thereby allowing current to flow from the first battery to the inverter and preventing or limiting current from flowing from the inverter or the second battery to the first battery; and wherein, in addition to one or more second switches connected in series with the second battery, a second diode is also connected in series, thereby allowing current to flow from the second battery to the inverter and preventing or limiting current from flowing from the inverter or the first battery to the second battery.

[0050] The method of the operating system according to the present invention preferably includes a first method of operating a GPU to supply current to an aircraft parked on the ground, the GPU including the following steps:

[0051] - One or more first electronic switches are switched via a first digital controller unit to connect and disconnect the GPU's first battery from the GPU's inverter.

[0052] - Convert the output current of the first battery into the AC output current of the inverter.

[0053] - By switching one or more second electronic switches via the first or second controller unit, the GPU's second battery can be connected and disconnected from the inverter.

[0054] - The GPU's first diode allows current to flow from the first battery to the inverter and blocks or limits current flow from the inverter or the second battery to the first battery.

[0055] - The GPU's second diode allows current to flow from the second battery to the inverter and blocks or limits current flow from the inverter or the first battery to the second battery.

[0056] - Convert the output current of the second battery into the AC output current of the inverter.

[0057] This improves the structure, operability, durability, and maintainability of the battery GPU. For example, if one battery disconnects for any reason during load, the remaining batteries (or multiple batteries, see below) can remain unaffected. If needed, fully charged batteries can be kept as backups connected to the inverter during aircraft turns. Diodes thus prevent reverse charging or reverse charging with unlimited current, which would be harmful to the battery and / or cause efficiency degradation.

[0058] Preferably, in the same manner, the GPU includes a third battery having one or more third switches and third diodes, and / or a fourth battery having one or more fourth switches and fourth diodes, and / or other batteries having one or more other switches and other diodes connected in parallel to the first and second batteries and their respective switches. The features described below are preferably used for the first and second battery schemes, and in the case of more than two batteries, are preferably also applicable to the third, fourth, or other battery schemes accordingly.

[0059] The first and second batteries are preferably each configured to maintain 90 kW at the output port of the GPU leading to the aircraft. Preferably, the first and second batteries are constructed in the same manner with the same electrical specifications. The first and / or second batteries are preferably battery packs, each battery pack consisting of multiple battery cells.

[0060] The inverter is preferably configured to output 400Hz AC, preferably 3×200Vac (phase-to-phase), at 400Hz, preferably at least 90kVA.

[0061] The first / second diode is configured to limit current flow from the inverter or from the second / first battery to the first / second battery, for example, by forcing any reverse current through a first / second bypass resistor, which can be a typical quasi-linear resistor or another current-limiting element or circuit. Particularly preferably, the first / second diode is configured to completely limit current flow from the inverter or from the second / first battery to the first / second battery, for example, by implementing a bypass in parallel with the respective diode that allows reverse current flow.

[0062] Preferably, the GPU does not include an internal combustion engine-driven generator set having a continuous electric power output that is 50% higher, preferably 30%, than the GPU's output power rating.

[0063] Preferably, one or more of the first switch and the first diode are implemented in a single element, such as a transistor (preferably an IGBT) or a thyristor. The same is preferred for the second switch and the second first diode.

[0064] Preferably, one or more of the first switch and the first diode are implemented by an electronic relay (electromechanical or solid-state), unless the relay is already unidirectional, in which case it is implemented by a single diode connected in series. The same is preferred for the second switch and the second first diode. Preferably, at least one of the one or more first switches and at least one of the one or more second switches are implemented as electromechanical relays.

[0065] The battery's output current can be directed to the inverter directly or indirectly (e.g., through a filter or another intermediate element).

[0066] Preferably, each battery has a dedicated battery monitoring device, and the GPU is configured to disconnect any one of the batteries by turning off either a first switch or a second switch if the battery monitoring device indicates that the corresponding battery has failed.

[0067] In another preferred second GPU embodiment of the system according to the invention, preferably based on the first GPU embodiment, the total capacity of all batteries powered by the ground is at least 80 kWh.

[0068] Therefore, the battery can store enough energy to sustain the aircraft for several turns using only the energy stored in the battery.

[0069] In another preferred third GPU embodiment of the system according to the invention, preferably based on any of the foregoing GPU embodiments, at least one of the one or more first switches and at least one of the one or more second switches are each configured to disconnect the terminals of the corresponding battery from the inverter. In a preferred method of another operating system according to the invention, the method includes a method of operating the GPU, preferably based on a first or any of the GPU operating methods described herein, wherein the terminals of the corresponding battery are connected to and disconnected from the inverter.

[0070] This improves GPU security. In an emergency, completely disconnecting the battery from other circuitry can be advantageous.

[0071] In another preferred fourth GPU embodiment of the system according to the invention, preferably based on any of the foregoing GPU embodiments, the GPU includes a battery charger configured to charge a first battery and a second battery. In another preferred system operation method according to the invention, the method includes a method of operating the GPU, preferably based on a first or any of the GPU operation methods described herein, wherein the first battery and the second battery are charged simultaneously or alternately by the same charger.

[0072] Preferably, the GPU includes a switch, preferably a two-pole switch.

[0073] a) Used to connect and disconnect the charger from the first / second battery.

[0074] b) Or it can be used to connect and disconnect the charger from the power source, thereby inputting power to the charger.

[0075] Particularly preferably, in case a), the switch is one of one or more first switches / second switches.

[0076] In another preferred fifth GPU embodiment of the system according to the invention, preferably based on any one of the first to third GPU embodiments, the GPU includes a first battery charger configured to charge a first battery and a second battery charger configured to charge a second battery. In another preferred system operation method according to the invention, the method includes a method of operating the GPU, preferably based on a first or any one of the GPU operation methods described herein, wherein the first battery is charged by the GPU's first battery charger and the second battery is charged by the GPU's second battery charger.

[0077] This enables fast and easy charging. By including a charger for each battery in the GPU, the batteries can be charged from a 50 / 60Hz power line, and additionally, the batteries can be charged independently of each other in a fast manner. Equipping each battery with its own charger improves the utilization of the total battery capacity; that is, when the charging of one battery needs to be "slowed down" due to a high cell voltage, the charging of the remaining batteries can continue unaffected.

[0078] Preferably, the first controller is configured to control the first charger, and the second controller is configured to control the second charger. Preferably, the charger is connected to the same or a different connector as the GPU, which is used to connect the charger to mains power.

[0079] Preferably, the GPU includes:

[0080] a) a switch (preferably two-pole) for connecting and disconnecting the first charger from the first battery; and a switch (preferably two-pole) for connecting and disconnecting the second charger from the second battery.

[0081] b) or one or more switches, used together or individually to connect and disconnect the first charger and the second charger from the power source, thereby supplying power to the first charger and the second charger.

[0082] Particularly preferably, in case a), these switches are one of one or more first / second switches.

[0083] Therefore, preferably, at least one of the one or more first switches is configured to disconnect the charger (preferably the first charger) from the first battery, and at least one of the one or more second switches is configured to disconnect the charger (preferably the second charger) from the second battery.

[0084] In another preferred sixth GPU embodiment of the system according to the invention, preferably based on any of the fourth to fifth GPU embodiments, the GPU includes an internal combustion engine-driven generator set or fuel cell having a continuous electrical power output of less than or equal to 50%, preferably 30%, of the GPU's output power rating. The generator set is configured to feed power to a charger or a first and / or a second charger, and / or to feed power directly to a common DC bus (i.e., the battery output and / or the inverter input) via a rectifier. In another preferred system operation method according to the invention, the method includes a method of operating the GPU, preferably based on a first or any of the GPU operation methods described herein, wherein the charger or the first and / or second charger is fed by a corresponding generator set of the GPU.

[0085] Therefore, a cost-effective and compact method is provided to charge the battery using a very small engine or fuel cell, which has insufficient power to support the GPU for its charging rated aircraft, but has sufficient power to charge the battery to a certain state of charge.

[0086] In another preferred seventh GPU embodiment of the system according to the invention, preferably based on any of the fourth to sixth GPU embodiments, at least one of one or more first switches is configured to disconnect the first battery from the inverter, while

[0087] Connect the charger or first battery charger to the first battery.

[0088] - and / or not disconnecting the charger or the first battery charger from the first battery, and wherein at least one of one or more second switches is configured to disconnect the second battery from the inverter, while

[0089] Connect the charger or second battery charger to the second battery.

[0090] - and / or not disconnecting the charger or second battery charger from the second battery. In another preferred system operation method according to the invention, the method includes operating the GPU, preferably based on a first or any of the GPU operation methods described herein, switching at least one of one or more first switches to disconnect the first battery from the inverter while connecting the charger or first battery charger to the first battery and / or not disconnecting the charger or first battery charger from the first battery, and switching at least one of one or more second switches to disconnect the battery from the inverter while connecting the charger or second battery charger to the second battery and / or not disconnecting the charger or second battery charger from the second battery.

[0091] Therefore, the battery can be charged without discharging.

[0092] In another preferred eighth GPU embodiment of the system according to the invention, preferably based on any of the foregoing GPU embodiments, one or more second switches are controlled by a second controller unit, wherein the GPU includes a first battery monitoring device for monitoring the proper functioning of the first battery, the first controller is connected to the first battery monitoring device via a first communication line to communicate with the first battery monitoring device, and is configured to disconnect the first battery, preferably from the inverter and / or charger, by disconnecting at least one of one or more first switches once the first battery monitoring device indicates a failure of the first battery, wherein the GPU includes a second battery monitoring device for monitoring the proper functioning of the second battery, wherein the second controller is connected to the second battery monitoring device via a second communication line to communicate with the second battery monitoring device, and is configured to disconnect the second battery, preferably from the inverter and / or charger, by disconnecting at least one of one or more second switches once the second battery monitoring device indicates a failure of the second battery. In another preferred system operation method according to the invention, the method includes a method of operating the GPU, preferably based on a first or any of the GPU operation methods described herein, correspondingly monitoring the battery and correspondingly switching a switch to disconnect the corresponding battery upon failure.

[0093] Therefore, the security of the GPU is improved because each battery has its own safety cut-off system.

[0094] Preferably, the first battery monitoring device and the second battery monitoring device are battery management controllers, which are configured to monitor one or more of the following parameters:

[0095] - Voltage: Total voltage, voltage of individual battery cells, minimum and maximum battery cell voltages, or voltage of periodic taps.

[0096] - Temperature: Average temperature, coolant inlet temperature, coolant outlet temperature, or temperature of individual battery cells.

[0097] - State of charge (SOC) or depth of discharge (DOD) indicates the battery's charge level.

[0098] -State of Health (SOH), various defined measurements of the overall condition of the battery.

[0099] - Coolant flow: Used for air or fluid cooling of batteries,

[0100] - Current: The current flowing into and out of the battery.

[0101] - Isolation resistor: Creates isolation between the battery terminal and the casing, and is configured to indicate to the respective first and second controllers whether the calculated value of any one of the aforementioned parameters exceeds its permissible boundary, for the purpose of indicating a fault.

[0102] Preferably, the first communication line is electrically isolated from the second communication line. This further improves security.

[0103] Preferably, the first controller and the second controller each communicate with the corresponding battery monitoring device via a communication bus (e.g., CAN bus).

[0104] In another preferred ninth embodiment of the system according to the invention, preferably based on an eighth GPU embodiment, the GPU includes a digital central controller, wherein the central controller is connected to a user interface and configured to be controlled by a user using the user interface, and is connected to a first controller and a second controller via a communication bus. In another preferred system operation method according to the invention, the method includes a method of operating the GPU, preferably based on a first GPU or any of the operation methods described herein, wherein the GPU is accordingly used by a user, and the central controller accordingly communicates with the first and second controllers.

[0105] Therefore, since the user's overall control of the GPU is achieved through a separate central controller, the first and second controllers do not perform these tasks, thus further enhancing security.

[0106] The central controller is preferably configured to send switching commands to a first controller and a second controller for connecting or disconnecting the first battery or the second battery and / or charging it. The first controller and the second controller are configured to receive these commands and accordingly switch one or more first and second switches and / or control the first charger and the second charger. Preferably, the first controller and the second controller are configured to reject commands for connecting or disconnecting the first battery or the second battery and / or charging it if the first battery monitoring device or the second battery monitoring device indicates a malfunction in the first battery or the second battery.

[0107] The central controller is preferably configured to control the inverter.

[0108] Preferably, the communication line of the communication bus between the central controller and the first controller and the second controller is electrically insulated from the first communication line and the second communication line between the first controller and the second controller and the first battery monitoring device and the second battery monitoring device.

[0109] In another preferred tenth GPU embodiment of the system according to the present invention, preferably based on any of the foregoing GPU embodiments, at least one of one or more first switches and a first battery form a first battery module housed in a first housing.

[0110] Furthermore, at least one of the one or more second switches and the second battery form a second battery module housed in the second housing.

[0111] Therefore, the structure, maintainability, and safety have been further improved. This module can be more easily installed in and replaced within the GPU. Furthermore, the impact of malfunctions (e.g., fire) can be limited by the housing. The housing is preferably fire-resistant, for example, because it is made of metal. Preferably, the battery monitoring device (see above) is also formed as part of the battery module.

[0112] In another preferred eleventh GPU embodiment of the system according to the invention, preferably based on a tenth GPU embodiment, the first battery module and the second battery module each include a soft-start device for temporarily limiting the output current of the respective first battery and second battery after they have been connected to the inverter via one or more first switches and second switches. In another system operation method according to the invention, the method includes a method of operating the GPU, preferably based on a first or any of the GPU operation methods described herein, thereby temporarily limiting the output current of the respective first battery and second battery.

[0113] In another preferred twelfth GPU embodiment of the system according to the invention, preferably based on any of the foregoing GPU embodiments, the GPU (preferably each of the first and second housings) includes a heating device configured to automatically turn on or supply power at increased power when the temperature drops below a predetermined temperature (e.g., -20°C), and to automatically turn off or supply power again at reduced power when the temperature reaches a temperature above or equal to the predetermined temperature. In another system operation method according to the invention, the method includes a method of operating the GPU, preferably based on the first or any of the GPU operation methods described herein, correspondingly switching / controlling the heating element.

[0114] In another preferred thirteenth GPU embodiment of the system according to the invention, preferably based on any of the foregoing GPU embodiments, the GPU includes an inductor connected in series between the inverter and the first and second batteries. In another system operation method according to the invention, the method includes a method of operating the GPU, preferably based on the first or any of the GPU operation methods described herein, wherein the inverter's current peak is attenuated by the inductor between the inverter and the first and second batteries.

[0115] This further improves the operability of the ground-based power supply system. Disconnected batteries can be reconnected, even if they have a higher voltage than the others, and in this case, the inductor limits the inrush current to the inverter to an acceptable level. Some battery packs can be charged while others are used to maintain the load (discharge).

[0116] In another preferred system operation method according to the present invention, the method includes a second GPU operation method, preferably based on a first or any of the GPU operation methods described herein, wherein switching of one or more first electronic switches and switching of one or more second electronic switches include:

[0117] - Switch at least one of one or more first electronic switches to connect the first battery to the inverter;

[0118] - Switch at least one of one or more second electronic switches to connect the second battery to the inverter;

[0119] - Switch at least one of one or more first electronic switches to disconnect the first battery from the inverter while continuing to convert the output current of the second battery into the AC output current of the inverter, and then charge the first battery through the GPU's battery charger;

[0120] - After a certain period of time, switch at least one of one or more first electronic switches to reconnect the first battery to the inverter so as to convert the output current of the now recharged first battery into the AC output current of the inverter, while blocking or limiting the current flow from the first battery to the second battery through the second diode.

[0121] In another preferred system operation method according to the present invention, the method includes a third GPU operation method, a first or any of the GPU operation methods described herein, and the switching of one or more first electronic switches and the switching of one or more second electronic switches include:

[0122] - Switch at least one of one or more first electronic switches to connect the first battery to the inverter;

[0123] - Switch at least one of one or more second electronic switches to connect the second battery to the inverter;

[0124] - Switch at least one of one or more first electronic switches to disconnect the first battery from the inverter while continuing to convert the output current of the second battery into the AC output current of the inverter, and then charge the first battery through the GPU's battery charger;

[0125] - After a certain period of time, switch at least one of one or more first electronic switches to reconnect the first battery to the inverter so as to convert the output current of the now recharged first battery into the AC output current of the inverter, while blocking or limiting the current flow from the first battery to the second battery through the second diode.

[0126] In another preferred system operation method according to the present invention, the method includes a fourth GPU operation method, preferably based on the first to third operation methods or any of the GPU operation methods described herein, and the switching of one or more first electronic switches includes:

[0127] - When the first battery monitoring device used to monitor the proper functioning of the first battery indicates that the first battery has malfunctioned, switch at least one of the one or more first electronic switches to disconnect the first battery from the GPU's inverter and / or charger.

[0128] And the switching of one or more second electronic switches includes:

[0129] - When the second battery monitoring device, used to monitor the proper functioning of the second battery, indicates that the second battery has malfunctioned, switch at least one of the one or more second electronic switches to disconnect the second battery from the GPU's inverter and / or charger.

[0130] Preferably, the control scheme is implemented in a central controller. Attached Figure Description

[0131] Embodiments of the invention will now be described by way of example only with reference to the accompanying drawings, wherein:

[0132] Figure 1 This is a conceptual overview diagram of an embodiment of a GPU according to the present invention. Figure 2 This is a schematic diagram of a circuit according to a preferred embodiment of the GPU of the present invention, based on... Figure 2 The embodiment shown, Figure 3A , Figure 3B , Figure 4 , Figure 5 , Figure 6A , Figure 6B , Figure 7 Each illustrates an embodiment of a system according to the invention for supplying electric current to an aircraft parked on the ground, wherein, Figure 3C and Figure 3D Different embodiments of the input converter are shown. Detailed Implementation

[0133] Figure 1 A conceptual overview diagram of one embodiment of a battery GPU according to the present invention is shown. The GPU, an airport GPU 1, is movable by wheels and is used to supply current to an aircraft parked on the ground. GPU 1 includes:

[0134] -First battery 30,

[0135] Inverter 50 is used to convert the output of battery 30 into AC output current to supply the aircraft.

[0136] A first electronic switch 60 is provided for connecting and disconnecting the first battery 30 from the inverter 50, wherein the first switch 60 is connected in series with the first battery 30, and wherein the series-connected first battery 30 and the first switch 60 are together connected to the inverter 50.

[0137] - First controller unit 10, used to control first switch 60.

[0138] GPU 1 further includes:

[0139] -Second battery 31, and

[0140] - A second electronic switch 61 is used to connect and disconnect the second battery 31 from the inverter 50, wherein the second switch 61 is connected in series with the second battery 31, and wherein the series-connected second battery 31 and the second switch 61 are connected together to the inverter 50 so that they are connected in parallel with the series-connected first battery 30 and the first switch 60, wherein the second switch 61 is controlled by a first digital controller unit, wherein in addition to the first switch 60 being connected in series with the first battery 30, a first diode 70 is also connected in series, thereby allowing current to flow from the first battery 30 to the inverter 50 and preventing (in the absence of an optional first bypass resistor 70.1) or limiting current flow from the inverter 50 or the second battery 31 to the first battery 30; and wherein in addition to the second switch 61 being connected in series with the second battery 31, a second diode 71 is also connected in series, thereby allowing current to flow from the second battery 31 to the inverter 50 and preventing (in the absence of an optional second bypass resistor 71.1) or limiting current flow from the inverter 50 or the first battery 30 to the second battery 31.

[0141] Figure 2 It shows the basis Figure 2 The illustrated embodiment is a schematic diagram of a circuit according to a preferred embodiment of the GPU of the present invention. Figure 2 In contrast, a second digital controller unit 11 controls the second switch 61. Furthermore, an additional first switch 80 and an additional second switch 81 are connected in series between the respective batteries 30, 31 and the inverter. The first controller 10 further controls switch 80, and the second controller 11 further controls switch 81. Further, in the same manner, the GPU 1 includes a third battery having one or more third switches and third diodes, and a fourth battery having one or more fourth switches and fourth diodes, which are connected in parallel with the first and second batteries and their respective switches. Features described below that are preferred for the first and second battery configurations (clearly shown in the figures) also apply to the third and fourth battery configurations / parts.

[0142] The diode (is configured to) completely limit the current from the inverter or from any other battery other than the one to which the diode is connected in series.

[0143] The first and second switches are each configured to disconnect the corresponding battery terminals from the inverter.

[0144] The GPU includes a first battery charger configured to charge a first battery and a second battery charger configured to charge a second battery. A first controller 10 is configured to control the first charger 90, and a second controller 11 is configured to control the second charger 91. Chargers 90 and 91 are connected to a common connector 180 of the GPU 1 for connecting the chargers to mains power.

[0145] An additional first switch 80 is configured to disconnect the first battery 30 from the inverter 50 without disconnecting the first battery charger 90 from the first battery 30, and an additional second switch 81 is configured to disconnect the second battery 31 from the inverter 50 without disconnecting the second battery charger 91 from the second battery 31.

[0146] GPU 1 includes a first battery monitoring device 170 for monitoring the proper functioning of a first battery 30, wherein a first controller 10 is connected to the first battery monitoring device 170 via a first communication line 140 to communicate with the first battery monitoring device 170, and is configured to disconnect the first battery 300 from the inverter and charger by opening a first switch once the first battery monitoring device 170 indicates a failure in the first battery 30. GPU 1 includes a second battery monitoring device 171 for monitoring the proper functioning of a second battery 31, wherein a second controller 11 is connected to the second battery monitoring device 171 via a second communication line 141 to communicate with the second battery monitoring device 171, and is configured to disconnect the second battery 31 from the inverter and charger by opening a second switch 61 once the second battery monitoring device 171 indicates a failure in the second battery 31.

[0147] The first controller 10 and the second controller 11 each communicate with their respective battery monitoring devices via a CAN bus. The first communication line 140 and the second connection line 141 are electrically isolated.

[0148] GPU 1 includes a digital central controller 110, wherein the central controller 110 is connected to a user interface 120 and is configured to be controlled by a user using the user interface 120, and is connected to a first controller 10 and a second controller 11 via a communication bus 130.

[0149] The central controller 110 is configured to send switching commands to the first controller 10 and the second controller 11 for connecting or disconnecting the first battery 30 or the second battery 31 and / or charging them. The first controller 10 and the second controller 11 are configured to receive these commands and accordingly switch one or more first switches 60, 61 and second switches 80, 81 and / or control the first charger 90 and the second charger 91. The central controller 110 is configured to control the inverter 50. The communication line of the communication bus 130 between the central controller 110 and the first controller 10 and the second controller 11 is electrically insulated from the first communication line 140 and the second communication line 141 between the first controller 10 and the second controller 11 and the first battery monitoring device 170 and the second battery monitoring device 171.

[0150] The first switch 60 and the first battery 30 form a first battery module 160 housed in a first housing, and the second switch 61 and the second battery 31 form a second battery module 161 housed in a second housing. Battery monitoring devices 170 and 171 are also part of the battery modules 160 and 161 thus formed.

[0151] GPU 1 includes an inductor 100 connected in series between inverter 50 and first battery 30 and second battery 31.

[0152] Figure 3A A system for supplying current to an aircraft parked on the ground is shown. The system includes a battery GPU 1 for supplying current to the aircraft, preferably according to one of the embodiments described above. The battery GPU 1 includes one or more batteries 30, 31 and an inverter 50 for converting the output current of the one or more batteries 30, 31 into AC output current for supplying to the aircraft. The battery GPU 1 includes an AC input port 190, configured to connect via the AC input port 190 to an AC output connector 191' of an auxiliary GPU 1' to direct the AC output current of the auxiliary GPU 1' to the aircraft via the AC input port 190. The AC input port 190 includes an aircraft receptacle configured to connect to aircraft output connectors 191, 191' adapted for connection to the aircraft.

[0153] The system is configured to synchronize the following items with each other:

[0154] -The AC output current of the inverter 50 of the battery GPU 1, and

[0155] -Auxiliary GPU 1' AC output current.

[0156] Here, the battery GPU 1 is configured to synchronize itself with the auxiliary GPU 1' and perform switching from the power supply of one or more batteries 30, 31 to the power delivered by the auxiliary GPU 1'.

[0157] Battery GPU 1 is configured to shift the phase angle of the AC output current of inverter 50. Battery GPU 1 includes an input coupling switch 200, and battery GPU 1 is configured to:

[0158] - Detect the phase angle of the AC output current of the auxiliary GPU 1', and

[0159] If the difference between the detected phase angle and the phase angle of the AC output current of the inverter 50 of the battery GPU 1 is less than or equal to a predetermined threshold, the input coupling switch 200 is closed. The battery GPU 1 includes an output decoupling switch 201, and the battery GPU 1 is configured to:

[0160] - If the input coupling switch 200 has been switched to the closed state, then disconnect the output decoupling switch 201.

[0161] The system operates as follows:

[0162] - Connect the AC output connector 191' of the auxiliary GPU 1' to the AC input port 190 of the battery GPU 1, and direct the AC output current of the auxiliary GPU 1' to the aircraft via the AC input port 190, wherein the connection includes:

[0163] a) Synchronize the following items with each other by shifting the phase angle of the AC output current of the inverter 50 of the battery GPU 1:

[0164] - The AC output current of the inverter 50 of the battery GPU 1, here is the phase angle of the output current, and

[0165] -Auxiliary GPU 1' AC output current, here is the phase angle of the output current;

[0166] b) Detect the phase angle of the AC output current of the auxiliary GPU 1', and if the difference between the detected phase angle and the phase angle of the AC output current of the inverter 50 of the battery GPU 1 is less than or equal to a predetermined threshold, close the input coupling switch 200.

[0167] c) If the input coupling switch 200 has been switched to the closed state, then disconnect the output decoupling switch 201.

[0168] Figure 3B It shows something similar to Figure 3AThe system is shown. However, instead of connecting the auxiliary GPU 1' without voltage / frequency conversion, the AC current of the auxiliary GPU 1' is fed into the DC bus of the battery GPU 1. One or more batteries 30, 31 are connected to the input port of the inverter 50. The system is configured to direct the AC output current of the auxiliary GPU 1' from AC input port 190 to the aircraft via the input port of the inverter 50. The system includes an input converter 210 configured to convert the AC output current of the auxiliary GPU 1' to DC current at AC input port 190 and output the DC current to the input port of the inverter 50. Figure 3A Switches 200 and 201 are not needed.

[0169] Figure 3C and Figure 3D Different embodiments of converter 210 are shown. Figure 3C The converter 210 includes a transformer 211, a 6-pulse rectifier 212, a filter 213 using one or more capacitors, and a filter diode 214. The filter diode 214 prevents battery power from flowing into the filter capacitor. Figure 3D The converter 210 includes a choke 215, a transformer 211, and a 12-pulse rectifier 212.

[0170] Figure 4 It shows something similar to Figure 3A The system shown is an auxiliary GPU 1', but the input coupling switch 200' is implemented in the auxiliary GPU 1'. Furthermore, as an example, the auxiliary GPU 1' is also a battery-powered GPU, preferably based on... Figure 1 and / or Figure 2 The device is a battery GPU with two or more batteries 30', 31'. In this exemplary hardware setup, one possible operation is that the auxiliary GPU 1' performs synchronization (by translating the phase angle of the inverter 50' of the auxiliary GPU 1') and switches the input coupling switch 200'. The auxiliary GPU 1' then switches the decoupling switch 201 to the off state via a communication channel to the battery GPU 1. Another possible operation is that the battery GPU 1 performs synchronization and switching, wherein information about the phase angle of the inverter 50' of the auxiliary GPU 1' is sent from the auxiliary GPU 1' to the battery GPU 1 via a communication channel, and the switch 200' is switched by the battery GPU 1 via the communication channel. As in this setup, when not connected to the auxiliary GPU 1', there will be a charged protruding pin (= a energized pin) at input port 190 during operation of the battery GPU 1, therefore mechanical protection (e.g., a protective cover) or an additional switch is required to enhance safety and prevent the user from contacting the charged protruding pin. For according to Figure 5 and Figure 6AThe same applies to the embodiments, wherein, in Figure 6A In the Y-type adapter 300, the input port 390.2 may have a live protruding pin and require protection.

[0171] Figure 5 It shows something similar to Figure 4 The system shown has an output cable for the battery GPU 1 configured via a Y-shaped cable, which gives the aircraft socket on the input port 190 the corresponding features.

[0172] Figure 6A It shows something similar to Figure 5 The system shown includes a battery GPU 1 comprising a Y-connector 300 having two AC input ports 390.1 and 390.2, each including an aircraft socket, and an aircraft output connector 391, wherein the aircraft output connector 191 of the battery GPU 1 is connected to one of the two AC input ports 390.1. Figure 6B The Y-type adapter 300 is shown separately.

[0173] Figure 7 It shows something similar to Figures 3A to 3D The system shown uses two identical GPUs to perform a switch from one GPU to the other.

[0174] Figure Labels

[0175] 1 Battery ground power supply unit 140 First communication line

[0176] 1' Auxiliary ground power supply unit 141 Second communication line

[0177] 10 First Digital Controller Unit 150 General Purpose Control Signal Circuit

[0178] 11 Second Digital Controller Unit 160 First Battery Module

[0179] 30 First Battery 161 Second Battery Module

[0180] 31 Second battery 170 First battery monitoring device

[0181] 50 Inverter 171 Second Battery Monitoring Device

[0182] 60 First electronic switch 180 Connector to the power line

[0183] 61 Second electronic switch 190 Input port

[0184] 70 First diode 191, 191' output connector

[0185] 70.1 First bypass resistor 200, 200' input coupling switch

[0186] 71 Second Diode 201 Output Decoupling Switch

[0187] 71.1 Second bypass resistor 210 input converter

[0188] 80 First Additional Electronic Switch 211 Transformer

[0189] 81 Second Additional Electronic Switch 212 Rectifier

[0190] 90 First Battery Charger 213 Filter

[0191] 91 Second Battery Charger 214 Filter Diode

[0192] 100 Inductor 215 Choke

[0193] 110 main controller 300 Y-type adapter

[0194] 120 User Interface 390.1, 390.2 Input Ports

[0195] 130 communication bus 391 output connector

Claims

1. A system for supplying electric current to an aircraft parked on the ground, the system comprising: A battery ground power supply unit (1) is configured to supply current to an aircraft parked on the ground. The battery ground power supply unit (1) includes one or more batteries (30, 31) and an inverter (50) for converting the output current of the one or more batteries (30, 31) into an AC output current of the inverter (50) to supply to the aircraft. The battery ground power supply unit (1) includes AC input ports (190, 390.2). The battery ground power supply unit (1) is configured to be connected to the AC output connector (191') of the auxiliary ground power supply unit (1') via the AC input port (190, 390.2) so as to guide the AC output current of the auxiliary ground power supply unit (1') to the aircraft via the AC input port (190, 390.2); The AC input port (190, 390.2) includes an aircraft socket configured to connect to an aircraft output connector (191) and / or the AC output connector (191'), which is adapted to connect to the aircraft.

2. The system according to claim 1, wherein, The battery ground power supply unit (1) includes a Y-type adapter (300) having two AC input ports (390.1, 390.2), each including an aircraft socket, and an aircraft output connector (391), wherein the aircraft output connector (191) of the battery ground power supply unit (1) is connected to one of the two AC input ports (390.1).

3. The system according to claim 1, wherein, The system is configured to synchronize the following: The AC output current of the inverter (50) of the battery ground power supply unit (1), and The AC output current of the auxiliary ground power supply unit (1').

4. The system according to claim 3, wherein, The system includes input coupling switches (200, 200'), and wherein the system is configured to: The parameters of the AC output current of the auxiliary ground power supply unit (1') are detected, and If the difference between the detected parameter and the corresponding parameter of the AC output current of the inverter (50) of the battery ground power supply unit (1) is less than or equal to a predetermined threshold, the input coupling switch (200, 200') is closed.

5. The system according to claim 4, wherein, The system is configured to shift the parameters of the AC output current of the inverter (50) of the battery ground power supply unit (1) and / or shift the parameters of the AC output current of the auxiliary ground power supply unit (1').

6. The system according to claim 5, wherein, The system includes an output decoupling switch (201), and wherein the system is configured to: - If the input coupling switch (200, 200') has been switched to the closed state, then disconnect the output decoupling switch (201).

7. The system according to claim 6, wherein, The system further includes the auxiliary ground power supply unit (1'), wherein the battery ground power supply unit (1) and the auxiliary ground power supply unit (1') are connected to each other via the AC input port (190) of the battery ground power supply unit (1) and the AC output connector (191') of the auxiliary ground power supply unit (1').

8. The system according to claim 7, wherein, In order to convert the output current of the one or more batteries (30, 31) into the AC output current of the inverter (50), the one or more batteries (30, 31) are connected to the input port of the inverter (50), and wherein the system is configured to guide the AC output current of the auxiliary ground power supply unit (1') from the AC input port (190) to the aircraft via the input port of the inverter (50), and wherein the system includes an input converter (210) configured to convert the AC output current of the auxiliary ground power supply unit (1') into DC current at the AC input port (190) and output the DC current to the input port of the inverter (50).

9. The system according to claim 8, wherein, The input converter (210) includes a transformer (211), a rectifier (212), and one or more of the following: a filter (213), a filter diode (214), and a choke (215).

10. The system according to claim 2, wherein, The Y-type adapter (300) has two AC input ports (390.1, 390.2), each including an aircraft socket, and an aircraft output connector (391).

11. The system according to claim 1, the system further comprising a Y-connector (300) including the AC input port (390.2).

12. The system according to claim 11, wherein, The Y-connector (300) includes a second AC input port (390.1) that can be connected to the battery ground power unit (1).

13. A method of operating a system for supplying current to an aircraft parked on the ground, the system comprising a battery ground power supply unit (1) for supplying current to the aircraft parked on the ground using one or more batteries (30, 31), and the system further comprising an auxiliary ground power supply unit (1') for supplying current to the aircraft parked on the ground, wherein, The method includes the following steps: The auxiliary ground power supply unit (1') is connected to the AC input port (190, 390.2) of the battery ground power supply unit (1) via the AC output connector (191'); and The AC output current of the auxiliary ground power supply unit (1') is directed to the aircraft via the AC input ports (190, 390.2). The AC input ports (190, 390.2) include aircraft sockets.

14. The method according to claim 13, wherein, The connection includes one or more of the following steps a) to c): a) Synchronize the following items with each other: -The AC output current of the inverter (50) of the battery ground power supply unit (1), and -The AC output current of the auxiliary ground power supply unit (1'); b) Detect the parameter of the AC output current of the auxiliary ground power supply unit (1'), and if the difference between the detected parameter and the corresponding parameter of the AC output current of the inverter (50) of the battery ground power supply unit (1) is less than or equal to a predetermined threshold, close the input coupling switch (200, 200'). as well as c) If the input coupling switch (200, 200') has been switched to the closed state, then disconnect the output decoupling switch (201).

15. The method according to claim 14, wherein, The AC output current of the auxiliary ground power supply unit (1') is directed to the aircraft from the AC input port (190) via the input port of the inverter (50).

16. A system for supplying electric current to an aircraft parked on the ground, the system comprising: A battery ground power supply unit (1) is configured to supply current to an aircraft parked on the ground. The battery ground power supply unit (1) includes one or more batteries (30, 31) and an inverter (50) for converting the output current of the one or more batteries (30, 31) into the AC output current of the inverter (50) to supply to the aircraft. An AC input port (190, 390.2) is combined with the battery ground power supply unit (1), wherein the battery ground power supply unit (1) is configured to connect via the AC input port (190, 390.2) to the AC output connector (191') of the auxiliary ground power supply unit (1') so as to direct the AC output current of the auxiliary ground power supply unit (1') to the aircraft via the AC input port (190, 390.2); An input coupling switch (200, 200') is combined with the battery ground power supply unit (1), the input coupling switch (200, 200') being configured to connect between the battery ground power supply unit (1) and the auxiliary ground power supply unit (1'); and An output decoupling switch (201) is combined with the battery ground power supply unit (1), wherein the system is configured to disconnect the output decoupling switch (201) if the input coupling switch (200, 200') has been switched to the closed state.

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