An aircraft (1) with hybrid thermal/electric propulsion comprising at least one turbomachine (3), at least one first electrical source (12, 31, 32), at least one second electrical source (13, 45) provided with at least one means for storing electrical energy, a non-propulsive electrical distribution network (6) and a low-voltage electrical distribution network (7). It further comprises a propulsive electrical distribution network (8), the three electrical distribution networks (6, 7, 8) being supplied electrically by the first and second electrical sources (12, 31, 32, 13, 45) and electrically interconnected by static converters (20, 21, 44).
一种具有混合热/电气推进的飞行器(1),包括至少一个涡轮机(3)、至少第一电气源(12,31,32)、配备有电能储存装置的至少第二电气源(13,45)、非推进配电网(6)和低电压配电网(7)。它还包括推进配电网(8),这三个配电网(6,7,8)由第一和第二电气源(12,31,32,13,45)供电并通过静态转换器(20,21,44)电互连。
ELECTRIC ARCHITECTURE FOR HYBRID PROPULSION
用于混合推进的电气架构
2021-06-18
Patent
Elektronische Ressource
Chinesisch
A H‐type architecture for electric/hybrid‐electric aircraft propulsion systems
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