PROBLEM TO BE SOLVED: To eliminate, in a hydraulic cylinder for a landing gear of an aircraft, various defects caused by having a snubber ring formed with slits.SOLUTION: A hydraulic cylinder 1 comprises a cylinder tube 2, a piston 3, a piston rod 32, end covers 41, 42, and snubbing mechanisms 71, 72 which reduce a moving speed of the piston after the piston reaches near the end of a stroke. The snubbing mechanisms have supply/discharge ports 412, 422 formed in the end covers, valve elements 51, 52 for opening and closing the supply/discharge ports, connection parts 61, 62 connecting the valve elements and the piston 3 to each other, and recesses (cutouts 414, 424) recessed from the edges of the supply/discharge ports. When the piston approaches the end of a stroke, the valve element closes the supply/discharge port to form an orifice flow passage so that hydraulic oil is discharged through the orifice flow passage and the moving speed of the piston is reduced.SELECTED DRAWING: Figure 4

    【課題】航空機の降着装置用油圧シリンダにおいて、スナビング機構が、スリットが形成されたスナバーリングを備えることに起因する様々な不都合を解消する。【解決手段】油圧シリンダ1は、シリンダチューブ2と、ピストン3と、ピストンロッド32と、エンドカバー41、42と、ピストンがストロークの終端近くに到達したとき以降に、ピストンの移動速度を低減させるスナビング機構71、72と、を備える。スナビング機構は、エンドカバーに設けられた給排口412、422と、給排口を開閉する弁体51、52と、弁体とピストン3とを互いに連結する連結部61、62と、給排口の縁部から凹陥する凹部(切り欠き414、424)と、を有する。ピストンがストロークの終端に近づいたときに、弁体が給排口を閉じて絞り流路が形成され、作動油が絞り流路を通じて排出されることで、ピストンの移動速度が低下する。【選択図】図4


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    Title :

    HYDRAULIC CYLINDER FOR LANDING GEAR OF AIRCRAFT


    Additional title:

    航空機の降着装置用油圧シリンダ


    Contributors:

    Publication date :

    2017-04-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    F15B SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL , Druckmittelbetriebene Systeme allgemein / B64C AEROPLANES , Flugzeuge



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