Electrical power generation and distribution system for aircraft, and aircraft comprising such system

By using differential mode current and common mode current to define the adjustment set points of the engine and generator in the electric power generation and distribution system of the hybrid electric propulsion aircraft, the servo control of the turbojet engine and the aircraft distribution network is decoupled, and the system complexity and efficiency problems are solved, and more efficient electrical power management is achieved.

CN119768986APending Publication Date: 2025-04-04SAFRAN ELECTRICAL & POWER
4 Cites 0 Cited by

Patent Information

Application Number
CN202380061330.9
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Priority Date
2022-07-28
Filing Date
2023-07-25
Publication Date
2025-04-04

AI Technical Summary

Technical Problem

The existing hybrid electric power generation and distribution systems of electric power generation and distribution systems of hybrid electric propulsion vehicles are difficult to avoid dynamic and static interactions, resulting in increased system complexity and reduced efficiency when regulating the operating point of the turbojet engine and supplying the electric load of the aircraft.

Method used

An electric power generation and distribution system is proposed, including at least one turbojet engine, a plurality of distribution networks and a power generation channel associated with each distribution network. The engine adjustment set point is limited by the differential mode current, and the generator adjustment set point is limited by the common mode current. In this way, the servo control function is decoupled to avoid interaction.

Benefits of technology

Decoupling between the servo control of the turbojet engine and the aircraft distribution network is achieved, dynamic and static interactions are avoided, system design is simplified, and system stability and efficiency are improved.

✦ Generated by Eureka AI based on patent content.
Patent Text Reader

Abstract

The invention relates to an electrical power generation and distribution system 1 for a hybrid electric propulsion aircraft powered by at least one turbojet engine (10). The system comprises at least N > = 2 (N is an integer) distribution networks (30), and at least M > = 1 (M is an integer) power generation channels (20) associated with each distribution network. An electric machine (22) provided on each power generation channel controls the power supply parameters of the distribution network based on a generator control setpoint (Cg) defined by a common mode current IC resulting from the current IN, M generated in the power generation channel. The turbojet engine comprises a high-pressure shaft, a low-pressure shaft, and a control module (16) for controlling the power delivered between the shafts based on an engine regulation setpoint (Cm) defined by a differential mode current Id resulting from the distribution of the power drawn between the power generation channels.
Need to check novelty before this filing date? Find Prior Art