IMPROVED EXTERNAL POWER SUPPLY MODULE FOR AIRCRAFT.

Abstract

The invention relates to an aircraft power supply module (APSM) for powering an aircraft (AC), comprising at least one first input (I1) configured to make an electrical connection to a first AC power distribution network (GPU1) and a power converter (C1). The APSM is external to the aircraft (AC), and the power converter (C1) is configured to deliver a direct current supply voltage (HVDCN1) to the aircraft (AC) from at least the first AC power distribution network (GPU1) via an output (O1) configured for a connection to the aircraft (AC). Advantageously, this makes it possible to power an aircraft parked on an airport apron without requiring complex logistics and without having to use its auxiliary power unit. Fig. 1

Description

Title of the invention: IMPROVED EXTERNAL POWER SUPPLY MODULE FOR AIRCRAFT. Technical field

[0001] The present invention relates to an improved external aircraft power supply module for supplying electrical power to an aircraft positioned on a parking area of ​​an airport facility. PREVIOUS STATE OF THE ART

[0002] Aircraft architectures are evolving, particularly with the aim of substantially reducing carbon dioxide emissions. Recent and future architectures are therefore more electrified, and the electrical power density required on board aircraft is greater, both on the ground and in flight. When an aircraft is parked at an airport, the electrical power it needs is generally supplied by its auxiliary power unit (APU) or by a ground-based power source in the form of a limited-power 115V AC power grid, for example, from a fixed or mobile generator. Electrical power requirements are now increased for aircraft parked on the ground, and the introduction of onboard power converters, adjusted accordingly, would be detrimental to the aircraft's weight.Furthermore, the provision of new, appropriately sized sources of electrical power in airport facilities would lead to the need for more complex logistics with a significant financial impact.

[0003] The situation can be improved. Description of the invention

[0004] An object of the present invention is to reconcile as best as possible the environmental needs for carbon dioxide reduction and the electrical energy needs of aircraft parked on the ground, while avoiding the need to carry additional weight in the aircraft for this purpose, and avoiding complex and costly ground logistics.

[0005] To this end, a power supply module is proposed for powering an aircraft, comprising at least a first input configured to operate an electrical connection to a first AC power distribution network and a power converter, the power supply module being external to the aircraft, and the power supply module being such that the power converter is configured to deliver to the aircraft a supply voltage at current continuous, from at least the first AC power network connected to the first input, via a first output configured for connection to the aircraft.

[0006] According to one embodiment, the aircraft power supply module comprises at least the first input connected to said first AC power distribution network, a second input configured to operate a connection to a second AC power distribution network, and an internal synchronization and joining module for two AC power supply lines respectively connected to said first and second inputs and of which a synchronization output is connected to an input of the power converter configured to deliver, via said first output, said DC power supply voltage from said two synchronized and joined power supply lines.

[0007] According to one embodiment, the aircraft power supply module comprises at least the first input connected to said first AC power distribution network, a second input configured to operate a connection to a second AC power distribution network, and a second power converter, which second power converter is configured to deliver, in parallel and jointly with the first power converter, via the first output, the DC supply voltage from at least the first AC power network and the second AC power network.

[0008] According to one embodiment, the aircraft power supply module is configured to be connected to a plurality of fixed or mobile 115V AC power sources. These power sources are those commonly found in airport infrastructure (non-exhaustive list): 115VAC ground-accessible outlets, generators, mobile battery banks, etc.

[0009] Advantageously, the power supply module is arranged in a mobile monobloc unit.

[0010] According to one embodiment, the power supply module is arranged on or in a motorized land vehicle.

[0011] According to one embodiment, the aircraft power supply module is such that its input(s) are each configured for connection to a network having an alternating voltage of 115V and operating at a frequency of 400Hz, and its output is configured to deliver a direct voltage between 270V and 1000V, preferably equal to 540V or 800V.

[0012] According to one embodiment, the output of the power supply module is configured to deliver a DC voltage adjustable via a user interface for controlling the aircraft power supply module. Brief description of the drawings

[0013] [Fig. 1] schematically illustrates an aircraft power supply module according to one embodiment;

[0014] [Fig.2] schematically illustrates details of the module implementation power supply already represented on [Fig.1] according to a first variant of embodiment;

[0015] [Fig.3] schematically illustrates details of the module implementation of power supply already shown in [Fig. 1] according to a second embodiment; and,

[0016] [Fig.4] illustrates an example of the architecture of an internal controller of a module feeding according to a particular embodiment.

[0017] DETAILED STATEMENT OF IMPROVEMENTS

[0018] Figure 1 schematically represents a power supply system (PSS) for an AC aircraft according to one embodiment. The PSS is an AC aircraft power supply system in the sense that it is designed to supply the AC aircraft with electrical power. According to the example described, the PSS comprises an APSM power supply module and connection elements for electrical power sources, which constitute inputs II and 12, hereinafter referred to as input interfaces II and 12. Inputs II and 12 are each configured for connection to an AC power supply network. According to the non-limiting example described, input II is configured to be connected to a first AC power supply network GPU1, and input 12 is configured to be connected to a second AC power supply network GPU2.According to one embodiment, the GPU1 and GPU2 power supply networks deliver effective AC voltages of 115V at a frequency of 400Hz. In one example, these networks are supplied by mobile generator sets located on an aircraft parking area. Cleverly, the APSM power supply module is configured to deliver, on an output 01, a DC voltage, also referred to here as the HVDCN1 DC network, between 270V and 1000V, preferably equal to 540V or 800V, from the electrical energy supplied by the GPU1 and GPU2 networks. According to a first, preferred embodiment, illustrated in [Fig.[2] The APSM power supply module comprises a first power converter module Cl, connected to input 11 and configured to perform internal rectification and voltage boosting within the APSM module, and a second power converter module C2, connected to input 12 and configured to perform internal rectification and voltage boosting within the APSM module. The outputs of the power converter modules Cl. and C2 are connected in parallel, ensuring they are regulated to the same voltage level, and joined to deliver the resulting electrical energy in the form of the HVDCN1 network, of the HVDC (High Voltage Direct Current) type, on output 01, so as to be able to power the AC aircraft or another aircraft connected to output 01. The parallel connection of the converted sources into a DC power supply is made ensuring that the voltage amplitudes of the DC sources are equal. The internal circuits of the power converters C1 and C2 are not detailed here as this is not necessary for understanding the invention. A person skilled in the art will be able to determine a voltage rectifier circuit and a voltage booster circuit calibrated to meet the specific requirements, for example, in voltage or power, which are specific to a given aircraft or a given range of aircraft. [Fig.Figure 3 illustrates another embodiment of the APSM module, in which the AC networks GPU1 and GPU2 are first synchronized at the input of the APSM power supply module by means of an ACSM synchronization circuit or module. This circuit is controlled by an internal CTRL controller connected to inputs II and 12, which then drives a SYN synchronization signal to control the ACSM synchronization circuit or module. This ensures that the AC sources are regulated to the same voltage level (115VAC), the same frequency (400 Hz), and the same phase sequence (e.g., PhA, PhB, PhC). A SACN output of the ACSM synchronization circuit or module connected to input 12, which is connected to the GPU2 network, is then synchronized with the GPU1 network applied to input II and can be joined to this input II.The synchronization and paralleling of the AC power sources is achieved by ensuring that all sources operate with the same phase sequence (e.g., phase A, then phase B, then phase C), at the same frequency (e.g., 400 Hz), and with the same amplitude (e.g., 115 VAC). These last two conditions are easily met because all airport power sources conform to the same 115 VAC, 400 Hz standard. The synchronization output is connected to an input of the power converter, also known as a rectifier, which converts and regulates the AC voltage into a DC voltage. The converter is configured to deliver, via this first output, the DC supply voltage from the two synchronized and connected power lines.

[0019] According to one embodiment, the internal CTRL controller is also used to operate internal configurations of the ACSM module, for example, to configure the output voltage level applied to output 01. According to this second embodiment, the synchronized SACN output is connected to the input of the power converter Cl, which then performs rectification and voltage boosting to provide the DC voltage HVDCN1 at output 01. The internal circuits of the module The synchronization methods are not described in further detail here, as they are not essential to understanding the invention. Again, a person skilled in the art will be able to select a synchronization module for two analog networks with varying voltages of the same amplitude, in order to then power a rectification and voltage boosting circuit to meet the specific requirements, for example, in terms of voltage or power, for a given aircraft or family of aircraft.

[0020] In one embodiment, the DC voltage supplied to output 01 by the APSM power supply module is configurable by a user via a control interface directly accessible on the APSM module or accessible remotely. In one embodiment, the control interface is a keypad or a multi-position switch implemented directly on the APSM module. In another variant, the power supply module can be configured via a wireless communication interface, using radio waves, for example from a control center at an airport facility.

[0021] Advantageously, the APSM power supply module is monobloc and is configured to be carried on or in a motor vehicle, or on a trailer that can be towed or pushed by a motor vehicle, which makes it easily mobile and allows it to be brought as close as possible to one or more generator sets, in the vicinity of an aircraft.

[0022] According to one embodiment, the internal CTRL controller is configured to automatically detect the presence or absence of each of the GPU1 and GPU2 power networks at the input of the APSM power supply module so as to be able to operate, even with a lower output power, if only one network among the GPU 1 and GPU2 networks is connected to the APSM module.

[0023] Fig. 4 schematically illustrates an example of the internal architecture of the CTRL control and synchronization control device internal to the APSM power supply module.

[0024] According to the hardware architecture example shown in [Fig. 4], the CTRL control device internal to the APSM power supply module then comprises, connected by a CTRLB communication bus: a processor or CPU (Central Processing Unit) CTRL1; a RAM (Random Access Memory) CTRL2; a ROM (Read Only Memory) CTRL3; a storage unit such as a hard drive (or a storage media reader, such as an SD (Secure Digital) card reader) CTRL4; a power and communication interface module CTRL5 enabling the CTRL control device internal to the APSM power supply module to communicate with remote devices, such as sensors, actuators or remote devices, including in particular one or more aircraft devices.

[0025] The CTRL1 processor of the avionics trim control device is capable of executing instructions loaded into CTRL2 RAM from CTRL3 ROM, external memory (not shown), a storage medium (such as an SD card), or a communication network. When the CTRL control device internal to the APSM power supply module is powered on, the CTRL1 processor is capable of reading instructions from CTRL2 RAM and executing them. These instructions form a computer program that causes the CTRL1 processor of the CTRL control device internal to the APSM power supply module to implement all or part of a method for synchronizing the electrical networks applied to inputs II and 12.

[0026] All or part of such a synchronization method can then be implemented in software form by executing a set of instructions by a programmable machine, for example a DSP (Digital Signal Processor) or a microcontroller, or be implemented in hardware form by a dedicated machine or component, for example a FPGA (Field-Programmable Gate Array) or an ASIC (Application-Specific Integrated Circuit). In general, the CTRL control device internal to the APSM power supply module includes electronic circuitry configured to implement a synchronization control method for AC-type power networks.Of course, the CTRL control device internal to the APSM power supply module also includes or is coupled to all the elements usually present in an electronic system comprising a control unit and its peripherals, such as, a power supply circuit, a power supply monitoring circuit, one or more clock circuits, a reset circuit, input / output ports, interrupt inputs, bus drivers, this list being non-exhaustive.

[0027] The invention is not limited to the examples and embodiments described, but more generally to any aircraft power supply module comprising one or more inputs intended to be powered by AC power sources and comprising circuitry for delivering a direct current (HVDC) power source suitable for powering a parked aircraft. In particular, the power supply module may comprise more than two inputs configured to be connected to an AC power supply network, for example, 2, 3, 4, or 5 inputs, or even more.

Claims

Demands

1. Power supply module (APSM) for the power supply of an aircraft (AC) comprising at least: a first input (II) configured to operate an electrical connection to a first AC power distribution network (GPU1) and a power converter (Cl), the power supply module (APSM) being characterized in that: it is external to an aircraft, and in that: the power converter (Cl) is configured to deliver to said aircraft (AC) a DC supply voltage (HVDCN1), from at least said first AC power distribution network (GPU1), via an output (01) configured for a connection to said aircraft (AC).

2. Aircraft (AC) power supply module (APSM) according to claim 1, comprising at least said first input (II) configured to operate an electrical connection to said first AC power distribution network (GPU1), a second input (12) configured to operate a connection to a second AC power distribution network (GPU2), and a synchronization and junction module (ACSM) of two AC power supply lines (II, 12) respectively connected to said inputs (II, 12) of which a synchronized output (SACN) is connected to an input of said power converter (Cl) configured to deliver, via said output (01), said DC power supply voltage (HVDCN1) from said two synchronized and joined power supply lines (II, 12).

3. Aircraft power supply module according to claim 1 comprising at least said first input (II) to said first AC power distribution network (GPU1), a second input (12) configured to operate a connection to a second AC power distribution network (GPU2), and a second power converter (C2), the second power converter (C2) being configured to deliver, in parallel and jointly with said first power converter (C1), via said output (01), said DC supply voltage (HVDCN1), from at least the first AC power supply (GPU1) and the second AC power supply (GPU2).

4. Aircraft (AC) power supply module (APSM) according to any one of claims 2 to 3, said module (APSM) being configured to be connected to a plurality of fixed or mobile generator sets.

5. Aircraft power supply module (APSM) according to any one of claims 1 to 4, said power supply module (APSM) being arranged in a mobile monobloc unit.

6. Aircraft power supply module (APSM) according to any one of claims 1 to 5, said power supply module being arranged on or in a motorized land vehicle.

7. Aircraft power supply module (APSM) according to any one of claims 1 to 6, wherein the (II) or the inputs (II, 12) are configured for connection to a network having an alternating voltage of 115V and operating at a frequency of 400Hz, and said output (01) being configured to deliver a direct voltage between 500V and 1000V, preferably equal to 540V or 800V.

8. Power supply module (APSM) according to any one of claims 1 to 7, wherein said output (01) is configured to deliver an adjustable DC voltage via a user interface for controlling said module (APSM).

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