The invention relates to the technical field of flight control vibration reduction, in particular to a flight control device with a vibration reduction structure, an aircraft and an installation method. The flight control device with the vibration reduction structure comprises an inertial measurement unit, a mounting frame and the vibration reduction structure, the inertial measurement unit is mounted in the mounting frame; the vibration reduction structure comprises a first vibration reduction part and a second vibration reduction part, the inertial measurement unit is suspended in the mounting frame through the first vibration reduction part, and the second vibration reduction part is mounted on the mounting frame, so that vibration reduction of the inertial measurement unit is realized through vibration reduction of the mounting frame. The damping device has the beneficial effects that the layout is compact and reasonable, the occupied space is reduced, and the damping effect is improved.
本发明涉及飞控减振技术领域,特别是涉及一种具有减振结构的飞控装置、飞行器及安装方法。该具有减振结构的飞控装置包括惯性测量单元、安装框架和减振结构;所述惯性测量单元安装于所述安装框架内;所述减振结构包括第一减振件和第二减振件,所述惯性测量单元通过所述第一减振件悬挂于所述安装框架内,所述第二减振件安装于所述安装框架上,以通过减振所述安装框架对所述惯性测量单元实现减振。本发明的有益效果是:布局紧凑合理,减小了占用空间,提高了减振效果。
Flight control device with vibration reduction structure, aircraft and installation method
具有减振结构的飞控装置、飞行器及安装方法
08.07.2022
Patent
Elektronische Ressource
Chinesisch
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