A high-load low-friction anti-backlash type aircraft steering engine comprises a direct-current servo motor, a base body, a sleeve, a rudder shaft, a rocker arm, a ball screw pair, an angular displacement sensor and the like. An output shaft of the direct-current servo motor and the ball screw pair are coaxially installed, and the sleeve is installed at a joint of the output shaft of the direct-current servo motor and a ball screw. An extending shaft on the side of a ball screw nut is rotatably connected with one end of the rocker arm through a bearing; the other end of the rocker arm is connected with one end of a rudder shaft; the rudder shaft is rotatably connected with the base body through the bearing, and the other end of the rudder shaft extends out of the surface of the base body and is connected with a rudder sheet; an extension rod of the sleeve is mounted on the base body through the bearing and a pin shaft to form a revolute pair; and the angular displacement sensor and therudder shaft are coaxially installed, synchronously rotate and are used for rudder deflection angle signal feedback. The steering engine is simple in structure, small in assembly gap, small in transmission friction, high in transmission accuracy, low in cost and compact in size, and defects that a traditional transmission mechanism is small in bearing, large in friction and prone to clamping stagnation are overcome in the mode that the bearings are installed at movable joints.
一种高负载低摩擦消隙式飞行器舵机,包括直流伺服电机、基体、套筒、舵轴、摇臂、滚珠丝杆副、角位移传感器等;直流伺服电机输出轴与滚珠丝杆副同轴安装,套筒安装在直流伺服电机输出轴和滚珠丝杆连接处;滚珠丝杆螺母侧边的伸出轴通过轴承与摇臂一端转动连接;摇臂另一端与舵轴一端连接,舵轴通过轴承与基体转动连接,舵轴另一端从基体表面伸出并与舵片连接;套筒的伸出杆通过轴承和销轴安装在基体上,形成转动副;角位移传感器与舵轴同轴安装、同步旋转,用于舵偏角度信号反馈。本发明结构简单、装配间隙小、传动摩擦小、传动精确度高、成本低、体积紧凑,通过在活动关节处安装轴承的方式,改善了传统传动机构承载小、摩擦大、易卡滞的缺点。
High-load low-friction anti-backlash type aircraft steering engine
一种高负载低摩擦消隙式飞行器舵机
2020-09-29
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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