Aircraft power supply system

Abstract

Electrical power system (1) for at least one propulsive or non-propulsive payload of an aircraft (A), the electrical power system (1) comprising: at least one fuel cell (2) configured to be powered by an airflow (FA) and by a hydrogenflow (FH) and at least one control unit (8) arranged to regulate at least one output voltage of the fuel cell (2) from at least one parameter related to the airflow (FA) and / or the hydrogenflow (FH). Aircraft (A) comprising an electrical power system (1). ABBREVIATED FIGURE: Fig. 2

Claims

Demands

1. Power supply system (1) for at least one propulsive or non-propulsive payload of an aircraft (A), the power supply system (1) comprising: - at least one fuel cell (2) configured to be powered by an airflow (FA) and by a hydrogenflow (FH) and - at least one control unit (8) arranged to at least regulate an output voltage of the fuel cell (2) from at least one parameter related to the airflow (FA) and / or the hydrogenflow (FH).

2. System (1) according to claim 1, wherein the parameter is related to the air flow pressure (FA) and / or the hydrogen flow pressure (FH) and / or the stoichiometry of a hydrogen / oxygen mixture present in the fuel cell (2).

3. System (1) according to claim 1 or claim 2, comprising at least one valve (9) arranged to regulate the airflow pressure (FA) and at least one sensor (10) arranged to measure the airflow pressure, the control unit (8) being arranged to control the valve (9), from at least one signal transmitted by the sensor (10), in order to regulate the output voltage of the fuel cell (2).

4. System (1) according to any one of the preceding claims, comprising at least one valve (12) arranged to regulate the hydrogen flow pressure (FH) and at least one sensor (13) arranged to measure the hydrogen flow pressure (FH), the control unit (8) being arranged to control the valve (12) arranged to regulate the hydrogen flow pressure (FH), from at least one signal transmitted by the sensor (13) arranged to measure the hydrogen flow pressure, in order to regulate the output voltage of the fuel cell (2).

5. System (1) according to any one of the preceding claims, comprising a compressor (11) arranged upstream of the fuel cell (2) such that the airflow passes through the compressor (11) before reaching the fuel cell (2) and wherein the control unit (8) is arranged to control said compressor (11) in order to regulate the output voltage of the fuel cell (2).

6. System (1) according to claim 5, wherein the control unit (8) is arranged to modify an operating mode of the compressor (11) in order to regulate the output voltage of the fuel cell (2).

7. System (1) according to any one of the preceding claims, wherein the control unit (8) is configured to maintain the output voltage within a given range, the range being bounded by a minimum output voltage and a maximum output voltage.

8. System (1) according to claim 7, wherein the control unit (8) sets the minimum output voltage via the air flow pressure (FA) and / or the hydrogen flow pressure (FH).

9. System (1) according to any one of claims 7 or 8, wherein the control unit (8) sets the maximum output voltage through the stoichiometry of a hydrogen / oxygen mixture present in the fuel cell (2).

10. Aircraft (A) comprising a system (1) according to any one of the preceding claims.

Images