PROBLEM TO BE SOLVED: To provide a telescoping strut (1) for a retractable landing gear (LG) in an aircraft (A).SOLUTION: The telescoping strut (1) comprises a pre-pressurized and central extension chamber (12) extending along the telescoping strut (1) and a surrounding retraction chamber (13). For retraction, a hydraulic generation architecture of the aircraft (A) feeds a single input/output passage (24) of the surrounding retraction chamber (13) with an overcoming fluid pressure that overwhelms an extension positive pressure in the central extension chamber (12) and opposes the effect of the pre-pressurizing. The retraction system (S) is for instance for a rotorcraft.SELECTED DRAWING: Figure 3

    【課題】航空機(A)における格納式ランディングギア(LG)用の伸縮自在ストラット(1)を提供する。【解決手段】伸縮自在ストラット(1)は、伸縮自在ストラット(1)及び包囲格納チャンバ(13)に沿って延出する予加圧された中央伸長チャンバ(12)を具備する。格納のために、航空機(A)の油圧発生アーキテクチャが、中央伸長チャンバ(12)内の伸長正圧を圧倒し、且つ予加圧の効果を妨害する克服流体圧を包囲格納チャンバ(13)の単一の入力/出力通路(24)にフィードする。格納システム(S)は、例えば回転翼機用である。【選択図】図3


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    Title :

    RETRACTION/EXTENSION OF LANDING GEAR IN AIRCRAFT


    Additional title:

    航空機におけるランディングギアの格納/伸長


    Contributors:

    Publication date :

    2017-11-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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