Providing energy in an aircraft using droop control
AssigneeSafran
InventorsVictor Dos Santos, Florent Rougier, Isabelle Florent
Life of this patent
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Abstract
An apparatus for providing energy in an aircraft, including a DC bus; at least one low-pressure electrical source and at least one high-pressure electrical source. The apparatus further includes a system for calculating a droop gain for each electrical source, based on at least one operating characteristic of the turbine engine; and for each electrical source, a model for controlling the electrical source in question, which module is designed to implement a droop setting based on the droop gain calculated for the electrical source in question.
Claims10
An apparatus for providing energy in an aircraft, comprising:
- a DC bus to which at least one electrical load is intended to be connected;
- several electrical sources including:
- at least one electrical source referred to as low-pressure electrical source designed to draw power from a low-pressure body of a turbomachine of the aircraft, in order to provide a current to the DC bus, and
- at least one electrical source referred to as high-pressure electrical source designed to draw power from a high-pressure body of the turbomachine of the aircraft, in order to provide a current to the DC bus;
- wherein the apparatus further comprises:
- a system for calculating a droop gain for each low-pressure electrical source and each high-pressure electrical source, on the basis of at least one operating characteristic of the turbomachine;
- and
- for each low-pressure electrical source and each high-pressure electrical source, a module for controlling the electrical source under consideration, designed to implement a droop regulation on the basis of the droop gain calculated for the electrical source under consideration.
A method for providing energy in an aircraft, wherein said method comprises:
- calculating, from at least one measurement of at least one operating characteristic of a turbomachine, a droop gain for:
- each electrical source referred to as low-pressure electrical source designed to draw power from a low-pressure body of the turbomachine of the aircraft, in order to provide a current to a DC bus to which at least one electrical load is intended to be connected, and
- each electrical source referred to as high-pressure electrical source designed to draw power from a high-pressure body of the turbomachine of the aircraft, in order to provide a current to the DC bus;
- and
- for each low-pressure electrical source and each high-pressure electrical source, a droop regulation is implemented on the basis of the droop gain calculated for the electrical source under consideration.
Dependencies are inferred from the claim text.