To provide an electric hydraulic pressure actuator for an aircraft that can reliably lift up and down a landing gear even when being exposed to a cold environment during flight.SOLUTION: An electric hydraulic pressure actuator A for an aircraft includes: a pump 1; an electric motor 2 for driving the pump 1; an actuator body 3 telescopically operating with supply/discharge of fluid by the driven pump 1; a passage B, 20 for connecting a suction port to a discharge port of the pump 1; and an on-off valve 4 for opening and closing the passage B, 20. The electric hydraulic pressure actuator starts a warm-up operation when a flight altitude becomes equal to or lower than an altitude threshold.SELECTED DRAWING: Figure 1

    【課題】飛行中に寒冷環境に晒されても確実にランディングギアの揚降を行える航空機用電動液圧アクチュエータの提供である。【解決手段】本発明の航空機用電動液圧アクチュエータAは、ポンプ1と、ポンプ1を駆動する電動モータ2と、ポンプ1の駆動による液体の給排で伸縮作動するアクチュエータ本体3と、ポンプ1の吸込口と吐出口とを接続する通路B,20と、通路B,20を開閉する開閉弁4とを備え、飛行高度が高度閾値以下となると暖機運転を開始する。【選択図】図1


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    Title :

    ELECTRIC HYDRAULIC PRESSURE ACTUATOR FOR AIRCRAFT


    Additional title:

    航空機用電動液圧アクチュエータ


    Contributors:
    SATO KOSUKE (author) / OGAWA YOSHIYUKI (author) / ONO FUMIAKI (author) / ARAI RYOHEI (author)

    Publication date :

    2019-09-19


    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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