An aircraft landing gear assembly (50) comprising: a first structural member (52); a second structural member (54) pivotally coupled to the first structural member at an apex pivot point so as to be movable between a first angular condition and a second angular condition; a downward locking spring having a first end region pivotally coupled to the mounting structure and arranged under tension to bias the first and second structural members to assume the first angular condition; and a linkage assembly including: an arm member (58) pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having a first end region pivotally coupled to a second end region of the downward lock spring; a control link (56) pivotally coupled to one of the first and second structural members at a first control link pivot point, and pivotally coupled to the arm member at a second control link pivot point, the first control link pivot point is configured such that as the first and second structural members move relative to each other from a first angular condition toward a second angular condition, the first control link pivot point moves over a center, through an axis or plane bisecting the apex pivot point and the second control link pivot point.
一种飞行器起落架组件(50),包括:第一结构构件(52);第二结构构件(54),其在顶点枢转点处枢转地联接到第一结构构件,从而在第一角度状况与第二角度状况之间可运动;向下锁定弹簧,其具有枢转地联接到安装结构的第一端区域,并且在张力下布置成偏置第一结构构件和第二结构构件,从而呈现所述第一角度状况;以及连杆系组件,该连杆系组件包括:臂构件(58),其在臂枢转点处枢转地联接到第一结构构件和第二结构构件中的一个,臂具有枢转地联接到向下锁定弹簧的第二端区域的第一端区域;控制连杆(56),其在第一控制连杆枢转点处枢转地联接到第一结构构件和第二结构构件中的一个,并且在第二控制连杆枢转点处枢转地联接到臂构件,使得随着第一结构构件和第二结构构件相对于彼此从第一角度状况朝向第二角度状况运动,第一控制连杆枢转点运动过中心,穿过平分顶点枢转点和第二控制连杆枢转点的轴线或平面。
Aircraft landing gear assembly
飞行器起落架组件
2024-04-16
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |