Provided is a high-lift actuation system having independent actuation control. A high-lift actuation system for differentially actuating a plurality of high-lift surfaces of an aircraft is disclosed.An exemplary high-lift actuation system includes a plurality of independent drive devices for individually actuating the plurality of high-lift surfaces. The independent drive devices may include a power drive unit (PDU) arranged between an inboard actuator and an outboard actuator of a respective high-lift surface and an interconnecting driveline. The PDU of at least one independent drive devicemay include two motors having a respective motor output coupled together in a torque summing arrangement. A controller may be implemented with two independent control channels respectively coupled toone of the two motors.
具有独立致动控制的高升力致动系统。本文公开了一种用于对飞机的多个高升力表面进行差速致动的高升力致动系统。一种示例性高升力致动系统包括多个独立的驱动装置,以单独致动所述多个高升力表面。所述独立的驱动装置可包括布置在相应的高升力表面的内侧致动器和外侧致动器之间的动力驱动单元(PDU)并且包括互连驱动系。至少一个独立驱动装置的PDU可包括两个马达,所述两个马达具有在扭矩加和布置中联接在一起的相应的马达输出部。一种控制器可实现为具有分别联接到两个马达中的一个的两个独立控制通道。
High-lift actuation system having independent actuation control
具有独立致动控制的高升力致动系统
2020-05-26
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
HIGH-LIFT ACTUATION SYSTEM HAVING INDEPENDENT ACTUATION CONTROL
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