A hydraulic directional lock for an aircraft steering wheel comprises a shell, a piston, a lining and a screw plug, the lining and the screw plug are each of a stepped shaft structure provided with an axial through hole, the lining is clamped in an inner cavity in the right end of the shell, the screw plug is in threaded connection with the inner cavity of the shell, and the left end of the screw plug abuts against the end face of the lining; the piston is of a stepped shaft structure with the diameter of the middle larger than the diameters of the two sides and is arranged in an inner cavity of the shell, the middle section of the piston is attached to the inner cavity of the shell and divides the inner cavity of the shell into a left cavity and a right cavity, a compression spring is arranged on the piston located in the left cavity, and the right end of the piston extends out of the shell through an axial through hole. The left end of the piston extends out of the shell and is provided with a lock pin mounting hole; two mounting holes are formed in the shell, each mounting hole is of a stepped structure, the two mounting holes are communicated with the left cavity and the right cavity respectively, filler necks are connected to the mounting holes, and buffer mechanisms are arranged at the joints of the mounting holes and the filler necks. The impact force is effectively relieved, and the problem that the service life is short due to the fact that the piston is not centered is solved.
一种飞机转向轮液压定向锁,包括壳体、活塞、衬套和螺塞,衬套和螺塞均为设有轴向通孔的阶梯轴结构,衬套卡设在壳体右端内腔中,螺塞与壳体内腔螺纹连接,左端抵靠在衬套端面上;活塞为中部直径大于两侧直径的阶梯轴状结构,设置在壳体内腔中,活塞中段与壳体内腔贴合设置,并将壳体内腔分隔成左右两个腔室,位于左侧腔室的活塞上设有压缩弹簧,活塞右端通过轴向通孔延伸至壳体外,活塞左端延伸至壳体外设有锁销安装孔;壳体上设有两个安装孔,安装孔为阶梯状结构,两个安装孔分别与左右两个腔室连通,安装孔上连接有接管嘴,且安装孔与接管嘴连接处设有缓冲机构。本发明有效缓解撞击力度且避免活塞不对中引起的寿命低的问题。
Hydraulic directional lock for aircraft steering wheel
一种飞机转向轮液压定向锁
2023-08-01
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |