发明名称 Electric actuator for aircraft landing gear
摘要 <p>An object of the present invention is to provide an electric actuator having a structure capable of reducing an external force or impact acting on a screw shaft when a piston rod is at a stretched position. An electric actuator (1) includes a first port (6), a second port (7), and a cylinder chamber connecting passage (9), the first port (6) is formed on an inner face of a rod-side cylinder chamber (5a) of a cylinder body (2), the second port (7) is formed on an inner face of a head-side cylinder chamber (5b) of the cylinder body (2), the cylinder chamber connecting passage (9) connects the first port (6) and the second port (7). In the electric actuator (1), a piston part (4a) of a piston rod (4) closes the first port (6) when the piston rod (4) advances.</p>
申请公布号 EP2192041(A2) 申请公布日期 2010.06.02
申请号 EP20090177638 申请日期 2009.12.01
申请人 NABTESCO CORPORATION 发明人 HIRAI, MASANORI
分类号 B64C25/24 主分类号 B64C25/24
代理机构 代理人
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