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.
FOURNITURE D'ENERGIE DANS UN AERONEF UTILISANT UN CONTRÔLE DE STATISME
PROVIDING ENERGY IN AN AIRCRAFT USING DROOP CONTROL
BEREITSTELLUNG VON ENERGIE IN EINEM FLUGZEUG MIT REGELDIFFERENZSTEUERUNG
2024-10-02
Patent
Electronic Resource
French
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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