An aircraft control surface deployment system (100) for an aircraft structure, such as a spoiler deployment system for an aircraft wing, includes a cam body (300), an actuator (200) and a coupling mechanism (120). The actuator (200) moves the cam body (300) such that the cam body raises and lowers the aircraft control surface (400). The actuator (200) is connected to the cam body (300) by a coupling mechanism (120). The coupling mechanism (120) has a first portion (320) connected to the cam body (300) and a second portion (220) connected to the actuator (200), the first and second portions being configured such that the coupling mechanism (120) allows some free relative movement and rotation of the first and second portions (320, 220). A load transverse to the axis of movement of the actuator (200) caused by the relative movement of the cam body (300) is not transmitted to the actuator (200).
本发明涉及了一种用于飞行器结构的飞行器控制表面部署系统(100)、例如用于飞行器机翼的扰流板部署系统,该飞行器控制表面部署系统包括凸轮本体(300)、致动器(200)和联接机构(120)。致动器(200)移动凸轮本体(300),使得凸轮本体升高和降低飞行器控制表面(400)。致动器(200)通过联接机构(120)连接至凸轮本体(300)。联接机构(120)具有连接至凸轮本体(300)的第一部分(320)和连接至致动器(200)的第二部分(220),第一部分和第二部分构造成使得联接机构(120)允许第一部分(320)和第二部分(220)的一些自由相对运动和旋转。由凸轮本体(300)的相对运动而引起的与致动器(200)的运动轴线横向的载荷不会传递至致动器(200)。
Aircraft control surface deployment system
飞行器控制表面部署系统
28.05.2024
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |