The invention relates to a tilt actuation system of a tilt-rotor aircraft. The tilt actuation system comprises a tilt actuation unit, an active power input unit and a backup power input unit, the tilting actuation unit comprises a ball screw and a screw nut used in cooperation with the ball screw. The driving power input unit comprises a driving power input unit shell, driving power input equipment, a planetary gear train in transmission connection with an input shaft of the driving power input equipment and a first triple gear in transmission connection with the planetary gear train. The backup power input unit comprises a backup power input unit shell, backup power input equipment, a second triple gear in transmission connection with an input shaft of the backup power input equipment, and a worm and gear mechanism in transmission connection with the second triple gear; the problems that an existing tilting actuation system of the tilting rotor aircraft is poor in operability, low in control efficiency, poor in stability and prone to system failure, and consequently the flight safety cannot be guaranteed are solved.
本发明涉及一种倾转旋翼飞行器倾转作动系统,包括倾转作动单元、主动功率输入单元以及备份功率输入单元;倾转作动单元包括滚珠丝杠以及与滚珠丝杠配合使用的丝杠螺母;主动功率输入单元包括主动功率输入单元壳体、主动功率输入设备、与主动功率输入设备输入轴传动连接的行星轮系以及与行星轮系传动连接的第一三联齿轮;备份功率输入单元包括备份功率输入单元壳体、备份功率输入设备、与备份功率输入设备的输入轴传动连接的第二三联齿轮以及与第二三联齿轮传动连接的蜗轮蜗杆机构;解决目前倾转旋翼飞行器倾转作动系统,存在操作性差、控制效率低、稳定性差以及容易出现系统失效,导致飞行安全性不能得到保障的问题。
Tilt actuation system of tilt-rotor aircraft
一种倾转旋翼飞行器倾转作动系统
02.05.2025
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |