An electric aircraft has a fault-tolerant electrical system designed to optimize competing concerns related to cost, performance, and safety. An electrical system in accordance with some embodiments of the present disclosure has a plurality of power sources (e.g., batteries) that are connected to other electrical components, such as motors for driving propellers or flight control surfaces, by a plurality of electrical buses. Each such bus is electrically isolated from the other buses to help the system better withstand electrical faults. Further, one or more of the electrical buses is connected to motors for driving multiple propellers. Selection of the propellers to be powered by energy received from the same bus is optimized so as to limit the effect of an electrical fault on the stability and controllability of the aircraft.
一种电动飞行器具有错误容限电气系统,该错误容限电气系统被设计成优化了与成本、性能和安全性相关的矛盾关注点。根据本公开的一些实施方案,一种电气系统具有多个电源(例如电池),这些电源通过多个电气总线与其他电气部件比如用于驱动螺旋桨或飞行操纵面的电机连接。每个这样的总线与其他总线电气隔离,以帮助系统更好地抵御电气故障。此外,将一个或多个电气总线与用于驱动多个螺旋桨的电机连接。对由从同一总线接收的能量供电的螺旋桨的选择进行优化,以限制电气故障对飞行器的稳定性和可控性的影响。
FAULT-TOLERANT ELECTRICAL SYSTEMS FOR AIRCRAFT
用于飞行器的故障容限电气系统
2020-04-21
Patent
Elektronische Ressource
Chinesisch