# US 12,214,896 B2 · Electrical supply system of an aircraft

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- Number: US 12,214,896 B2
- Document ID: US12214896B2
- Status: Granted
- Kind: B2
- Application number: 18/352,511
- Filed: 2023-07-14
- Published: 2024-01-25
- Granted: 2025-02-04
- Earliest claimed: 2022-07-19
- Assignees: Airbus Operations GmbH
- Applicants: Airbus Operations (S.A.S.)
- Inventors: Matthieu Bradier; Mohamed Khaled Kahalerras
- Web page: https://patentgrep.com/patent/US12214896B2

## CPC

- B64D 33/00: Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D 41/00: Power installations for auxiliary purposes
- H02J 3/46: Controlling the sharing of generated power between the generators, sources or networks
- H02J 4/00: Circuit arrangements for mains or distribution networks not specified as AC or DC; Circuit arrangements for mains or distribution networks combining AC and DC sections or sub-networks (arrangements using intermediate DC-AC-DC conversion H02J1/002; arrangements using high-voltage DC [HVDC] links H02J3/36)
- B64D 2221/00: Electric power distribution systems onboard aircraft
- H02J 7/34: Parallel operation in networks using both storage and other DC sources, e.g. providing buffering (H02J7/14 takes precedence)
- H02J 2105/32: {for aircrafts}
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- H02J: ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY

## Abstract

An electrical supply system (10) with first and second electrical sourced (S1, S2), coupled together to electrically supply electrical loads (Z1, Z2, Z3 . . . Zn) of an aircraft. The first electrical source (S1) is mechanically coupled to a primary energy source (12), to which at least one other energy consumer (16) is coupled. A controller (30) controls the first and second electrical sources (S1, S2) so that the power drawn by the first electrical source from the primary energy source (12) corresponds to a difference between an instantaneous nominal power capable of being delivered by the primary energy source and an instantaneous power drawn by the energy consumer (16), and an electrical power delivered by the second electrical source is a sum of an electrical power delivered by the first and second electrical sources which corresponds to an instantaneous electrical consumption of the electrical loads.

## Claims

### Claim 1

An electrical supply system for an aircraft comprising:
a first electrical source, wherein the first electrical source is mechanically coupled to a primary energy source which is coupled to at least one energy consumer other than the first electrical source,
a second electrical source coupled to the first electrical source and configured to electrically supply electrical power a group of electrical loads in the aircraft, and
a controller configured to:
determine an instantaneous electrical consumption consumed by the group of electrical loads;
determine an instantaneous nominal power capable of being delivered by the primary energy source;
determine an instantaneous power drawn by the at least one energy consumer from the primary energy source; and
control the first electrical source and the second electrical source so that:
the power drawn by the first electrical source from the primary energy source corresponds to a difference between the instantaneous nominal power capable of being delivered by the primary energy source and the instantaneous power drawn by the at least one energy consumer, so as to ensure that the mechanical power drawn by the first electrical source and by the at least one energy user is never greater than the instantaneous nominal power capable of being delivered by the primary energy source, and
an electrical power delivered by the second electrical source is such that a sum of an electrical power delivered by the first electrical source and the electrical power delivered by the second electrical source corresponds to the instantaneous electrical consumption.

### Claim 2 (depends on 1)

The electrical supply system according to claim 1, wherein the first electrical energy source is controlled in a voltage regulation mode and the second electrical energy source is controlled in a current regulation mode.

### Claim 3 (depends on 2)

The electrical supply system according to claim 2, wherein the controller is further configured to:
determine a current setpoint to be delivered by the second electrical source, and
apply the current setpoint to the second electrical source,
wherein the controller determines the current setpoint is determined based on a sum of an electrical power corresponding to the current setpoint and the electrical power delivered by the first electrical source corresponding to the instantaneous electrical consumption.

### Claim 4 (depends on 1)

The electrical supply system according to claim 1, wherein the primary energy source corresponds to a propulsion engine of the aircraft or to an emergency turbine of a ram air turbine type.

### Claim 5 (depends on 1)

The electrical supply system according to claim 1, wherein the at least one energy consumer comprises a hydraulic pump of a hydraulic circuit of the aircraft.

### Claim 6 (depends on 1)

The electrical supply system according to claim 1, wherein the instantaneous nominal power capable of being delivered by the primary energy source corresponds to an instantaneous maximum power capable of being delivered by the primary energy source.

### Claim 7 (depends on 1)

The electrical supply system according to claim 1, wherein the instantaneous nominal power capable of being delivered by the primary energy source corresponds to an optimal operation of the primary energy source.

### Claim 8 (depends on 1)

The electrical supply system according to claim 1, wherein the second electrical energy source comprises an electrical battery or a supercapacitor.

### Claim 9 (depends on 8)

The electrical supply system according to claim 8, wherein the primary energy source corresponds to a propulsion engine of the aircraft, and
the controller is further configured to request an increase in an idle speed of the propulsion engine when the electrical battery or the supercapacitor is not sufficiently charged to allow the second electrical source to deliver the required electrical power.

### Claim 10 (depends on 1)

The electrical supply system according to claim 1, wherein part of the power drawn by the first electrical source from the primary energy source corresponds to the difference between the instantaneous nominal power capable of being delivered by the primary energy source and the instantaneous power drawn by the at least one energy consumer, less a margin.

### Claim 11 (depends on 1)

An aircraft comprising the electrical supply system according to claim 1.