Improved system for supplying power to an aircraft

Abstract

This invention relates to a power supply system (PSS) for an aircraft configured to supply electrical energy to onboard electrical equipment (D1, D2, D3, D4, D5, D6). The power supply system includes at least: - a high-voltage DC type electrical sub-circuit (HVDCN), - a low-voltage AC type electrical sub-circuit (LPACN), and - a low-voltage DC type electrical sub-circuit (LPDCN). The PSS further includes a high-voltage (HVBAT) battery switching circuit (HVBATSW) that ensures each power line of the low-voltage DC sub-circuit is independent of a low-voltage battery, wherein the power lines are independent of the switching circuit (HVBATSW). Advantageously, this avoids battery redundancy that is detrimental to the weight of the aircraft (AC) and leads to a complex electrical system.

Description

Technical Field

[0001] The present invention relates to an improved system for powering an aircraft, the system comprising, in particular, a high-voltage DC electrical circuit and a battery. Background Technology

[0002] Aircraft architecture is evolving, particularly with the goal of significantly reducing carbon emissions. Consequently, recent or upcoming architectures are becoming increasingly electrified, requiring much higher energy densities on aircraft, both on the ground and in flight. This evolution has led to the use of high-voltage DC (High Voltage DC) type electrical circuits, including high-voltage DC batteries capable of supplying high current densities and powering many components of hybrid-electric or electric aircraft, including, for example, the electric propulsion system. Beyond the high-voltage DC circuitry, many aircraft electrical circuits are consistent, either entirely or partially, with standard electrical system architectures, resulting in a degree of redundancy in the use of battery-type energy storage units. This redundancy is therefore disadvantageous in terms of industrialization, weight, cost, maintenance, and, more broadly, the complexity of the aircraft systems involved.

[0003] This situation can be improved. Summary of the Invention

[0004] The purpose of this invention is to propose an improved arrangement for an aircraft electrical system that overcomes at least some of the disadvantages of the prior art, particularly by avoiding redundancy in battery usage, which is particularly detrimental to the weight and simplicity of the system.

[0005] To this end, a power system for the aircraft is proposed, which is configured to supply electrical energy to the onboard electrical equipment in the aircraft. This system includes at least:

[0006] A first electrical sub-circuit of the high-voltage DC type, comprising one or more high-voltage DC batteries.

[0007] A second electrical sub-circuit of low-voltage AC type, which is powered from the first electrical sub-circuit via one or more first power converters, and,

[0008] A third electrical sub-circuit of low-voltage DC type, which is powered by a second sub-circuit via one or more second power converters.

[0009] A battery switching circuit for one or more high-voltage batteries in this system.

[0010] The power system ensures that each power line of the third sub-circuit is free of low-voltage batteries, wherein the power lines are independent of the switching circuit.

[0011] Therefore, it is advantageous to eliminate the need for redundant low-voltage batteries and instead use high-voltage DC batteries as an alternative, since the latter can supply the electrical energy previously provided by the low-voltage DC batteries.

[0012] The power supply system according to the invention may include the following additional features, considered individually or in combination:

[0013] The third electrical circuit includes one or more supercapacitor-type components.

[0014] The power system includes a connection socket configured to connect to an external energy source, which may be located in one of the aforementioned sub-circuits.

[0015] The first electrical sub-circuit is configured to deliver a DC voltage greater than 300 V, the second electrical sub-circuit is configured to deliver an AC voltage equal to 115 V, and the third electrical sub-circuit is configured to deliver a voltage less than 50 V.

[0016] Another subject of the invention is an aircraft that includes a power system as previously described. Attached Figure Description

[0017] Figure 1 An aircraft power system according to one embodiment is schematically shown; and,

[0018] Figure 2 The illustration shows, for example, Figure 1 The power system of the aircraft has already been shown. Detailed Implementation

[0019] Figure 1 An aircraft power supply system (PSS) according to one embodiment is schematically illustrated. The PSS is an aircraft power supply system because it is designed to supply electrical energy to electrical equipment on the aircraft on which it is installed. According to the described example, the PSS includes a high-voltage DC type electrical sub-circuit HVDCN, which includes a high-voltage DC battery HVBAT configured to be supplied with electrical energy via a first power bus HVBB. According to one embodiment, the battery HVBAT is a component of the high-voltage DC battery. The PSS also includes a low-voltage AC type electrical sub-circuit LPACN, which is powered from the electrical sub-circuit HVDCN via one or more first power converters. Figure 1In the exemplary embodiment shown, two inverter-type power converters, INV1 and INV2, are configured to generate a low DC voltage from the grid LPACN and supply this voltage via a second power bus LVBB1. The power system PSS also includes a low-voltage DC type electrical sub-circuit LPDCN, which is powered by the LPACN via one or more second power converters. Figure 1 In the exemplary embodiment shown, two rectifier transformer type power converters TRU1 and TRU2 are configured to generate a low DC voltage from the power grid LPACN and supply this voltage via a third power bus LVBB2. The power system PSS further includes an auxiliary power unit (APU) for the aircraft on which the PSS is installed. The APU's output is connected to the first power bus HVBB. The system PSS also includes a battery switching circuit HVBATSW, which is configured to perform switching or isolation of one or more high-voltage batteries HVBAT within the system PSS via a switch SW and under the control of a control device SWCTR. According to one embodiment, the battery switching circuit HVBATSW includes a battery BAT1 configured to supply power to the battery switching circuit HVBATSW. Battery BAT1 may be, for example, a high-voltage battery of the high-voltage DC subcircuit HVDCN or a low-voltage battery of the low-voltage DC subcircuit LPDCN.

[0020] The power supply system (PSS) arranged in this manner allows for the simultaneous supply of power to electrical components or devices requiring high DC voltage (e.g., aircraft propulsion systems M1 and M2 connected to the power bus HVBB), as well as those requiring low AC voltage (e.g., electrical devices D1, D2, and D3 connected to the power bus LVBB1) and those requiring low DC voltage (e.g., electrical devices D4, D5, and D6 connected to the power bus LVBB2). Here, the term "electrical equipment" refers to any device that requires power to operate, at least in some cases. Therefore, this term is equivalent to purely electrical equipment, electromechanical equipment, hydraulic equipment, electro-pneumatic equipment, etc.

[0021] Ingeniously and advantageously, the power system PSS is configured and arranged such that each power line of the low-voltage DC sub-circuit is battery-free, wherein the power lines are independent of the power supply to the switching circuit HVBATSW.

[0022] According to one embodiment, the low-voltage DC subcircuit of the power system PSS includes one or more supercapacitors configured to store electrical energy. According to the described example, two supercapacitors, SCAP1 and SCAP2, are connected to the low-voltage DC power bus LVBB2, and their dimensions are designed to supply power to the subcircuit LPDCN for a predetermined power duration.

[0023] According to variations of the implementation, battery BAT1 can be installed in other areas of the power system PSS, as long as battery BAT1 can supply power to at least the switching circuit HVBATSW for high-voltage batteries / multiple high-voltage batteries.

[0024] According to one embodiment, the power system PSS includes a power connection or socket EXTPS for power supply outside the aircraft and connected to the switching circuit HVBATSW, and thus eliminates the need for a battery BAT1 for supplying power to the switching circuit HVBATSW to switch the battery HVBAT in the sub-circuit HVDCN.

[0025] According to one implementation, the low-voltage DC sub-circuit LPDCN is a circuit designed to operate normally during all flight phases of the aircraft in which it is installed, and additional low-voltage DC emergency sub-circuits can be implemented in such aircraft.

[0026] According to one implementation, the low-voltage DC subcircuit LPDCN is a circuit designed to operate in predefined emergency situations during flight or on the ground, and additional low-voltage DC subcircuits capable of operating during all other phases of flight are implemented in the aircraft. By way of non-limiting example, the predefined emergency situation can be an aircraft evacuation phase, a failure of one or more components, etc.

[0027] According to one embodiment, the electrical sub-circuit HVDCN is configured to deliver a DC voltage greater than 300 V, the electrical sub-circuit LPACN is configured to deliver an AC voltage equal to 115 V, and the low-voltage DC electrical sub-circuit LPACN is configured to deliver a voltage less than 50 V.

[0028] According to one embodiment, the electrical sub-circuit HVDCN is configured to deliver a DC voltage equal to 540 V or 800 V, and the low-voltage DC electrical sub-circuit LPDCN is configured to deliver a voltage equal to 28 V.

[0029] Figure 2 The diagram schematically illustrates an aircraft AC that advantageously incorporates the aforementioned power system PSS, which enables savings in terms of weight, cost, architectural simplicity, and logistics for use and maintenance.

[0030] The present invention is not limited to the examples and embodiments described herein, but is more generally applicable to any aircraft power system that includes a low-voltage DC power supply circuit in which each power line of such a sub-circuit does not have a battery and the power lines are independent of the high-voltage DC battery switching circuit.

Claims

1. A power supply system (PSS) for an aircraft (AC) configured to supply electrical energy to onboard electrical equipment (D1, D2, D3, D4, D5, D6) in the aircraft (AC), said system (PSS) comprising at least: The first electrical sub-circuit of the high voltage DC type (HVDCN) includes one or more high voltage DC batteries (HVBAT). A second electrical sub-circuit of low-voltage AC type (LPACN), which is powered from the first electrical sub-circuit (HVDCN) via one or more first power converters (INV1, INV2), and, A low-voltage DC type third electrical sub-circuit (LPDCN) is powered by the second sub-circuit (LPACN) via one or more second power converters (TRU1, TRU2). The power system further includes a battery switching circuit (HVBATSW) for the one or more high-voltage batteries (HVBAT) in the system (PSS), wherein each power line of the third sub-circuit has no battery, and wherein the power line is independent of the switching circuit (HVBATSW).

2. The power supply system (PSS) according to claim 1, wherein the third electrical sub-circuit (LPDCN) includes one or more supercapacitor-type components (SCAP1, SCAP2).

3. The power supply system (PSS) according to any one of claims 1 and 2, wherein the first electrical sub-circuit (HVDCN) includes a connection socket (EXTPS) configured to connect to an energy source outside the aircraft (AC) and configured to power the switching circuit (HVBATSW).

4. The power supply system (PSS) according to any one of claims 1 to 3, wherein the first electrical sub-circuit (HVDCN) is configured to deliver a DC voltage greater than 300 V, the second electrical sub-circuit (LPACN) is configured to deliver an AC voltage equal to 115 V, and the third electrical sub-circuit (LPDCN) is configured to deliver a voltage less than 50 V.

5. An aircraft (AC) comprising a power supply system (PSS) according to any one of claims 1 to 4.

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