The invention relates to a control system for controlling flaps and/or slats of an aircraft and the aircraft. The control system has a high lift system (1). The high lift system comprises: a first control module (3) comprising a plurality of first control module computers communicating with each other and configured to be able to implement an automatic driving function of the aircraft; a second control module (4) which is in communication connection with the first control module and is configured to be capable of implementing a manual driving function or a failure-safety function under the condition that the first control module fails; the second control module comprises a plurality of second control module computers, the second control module computers are divided into two groups, wherein the first set of second control module computers is associated with flaps of the aircraft, the second set of second control module computers is associated with slats of the aircraft, and the second control module computers are capable of communicating with each other.
本发明涉及用于控制飞行器的襟翼和/或缝翼的控制系统和飞行器。控制系统具有高升力系统(1),该高升力系统包括:第一控制模组(3),该第一控制模组包括多个互相通信的第一控制模组计算机,并且被配置成能够实施飞行器的自动驾驶功能;第二控制模组(4),该第二控制模组与第一控制模组通信连接,并且被配置成能够在第一控制模组失效的情况下实施手动驾驶功能或失效‑安全功能,第二控制模组包括多个第二控制模组计算机,其中,第二控制模组计算机分成两组,第一组第二控制模组计算机与飞行器的襟翼相关联,第二组第二控制模组计算机与飞行器的缝翼相关联,并且第二控制模组计算机能够彼此通信。
Control system for controlling flaps and/or slats of aircraft and aircraft
用于控制飞行器的襟翼和/或缝翼的控制系统和飞行器
2021-09-14
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
Engineering Index Backfile | 1934
Choice of drive topologies for electrical actuation of aircraft flaps and slats
IET Digital Library Archive | 2004
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