The present invention provides a landing device including a magneto-rheological (MR) fluid damper for an aircraft. According to an embodiment of the present invention, the landing device including the MR fluid damper for an aircraft can change a damping force by changing viscosity of an MR fluid by a magnetic field formed around a piston by applying an electric current to the piston on which a coil is wound. The landing device including the MR fluid damper for an aircraft also can maintain the damping force by using a metering pin and a structure of an orifice unit when a magnetic force generating unit is abnormal. According to the embodiment of the present invention, the landing device including the MR fluid damper for an aircraft includes: a cylinder unit having an open lower end of a tubular shape including a space inside, wherein an upper end of the cylinder unit is closed; a piston formed in the tubular shape by corresponding to the inner side of the cylinder unit to perform a linear motion by being inserted along the inner surface of the cylinder unit, wherein a side of the piston unit is connected to the lower end of the cylinder unit; the magnetic force generating unit on which the coil is wound to generate the magnetic force by being installed on one side of the inside of the piston unit; the MR fluid positioned in the cylinder unit and the piston unit to flow in the cylinder unit and the piston unit, wherein the viscosity of the MR fluid is changed by the magnetic force generated from the magnetic force generating unit; the metering pin protruding from the lower surface of an upper end of the cylinder unit to an upper end of the piston unit, wherein the metering pin is formed in a tapered shape to change the damping force of the piston unit in accordance with the length of a stroke; and an orifice unit installed in a plate shape having a hole in order for the metering pin to be inserted into the upper end of the piston unit, wherein the hole is installed in the orifice unit at fixed intervals from the outer circumference of the metering pin so that the piston unit can have the damping force as the MR fluid flows.

    본 발명의 일 실시 예는 코일이 권취된 피스톤에 전류를 인가하여 피스톤 주변으로 형성된 자기장을 통해 엠알유체의 점성을 변화시켜 감쇠력을 가변시키고, 자기력생성부의 이상시에도 미터링핀 및 오리피스부의 구조로 감쇠력을 유지할 수 있는 항공기용 엠알유체 댐퍼를 포함하는 착륙장치를 제공한다. 본 발명의 실시 예에 따른 항공기용 엠알유체 댐퍼를 포함하는 착륙장치는, 내부에 공간이 형성된 관형상으로 하단이 개방되고, 상단은 폐쇄된 실린더부, 상기 실린더부의 하단과 측면이 결합되고, 상기 실린더부의 내면을 따라 삽입되어 직선운동을 수행하도록 상기 실런더부의 내면과 대응하여 관형상으로 형성된 피스톤부, 상기 피스톤부 내부의 일측에 배치되어 자기력을 생성하도록 코일이 권취된 자기력생성부, 상기 실린더부 및 상기 피스톤부의 내부에 유동되도록 상기 실린더부 및 상기 피스톤부의 내부에 위치되고, 상기 자기력생성부로부터 생성된 자기력에 의해서 점도가 변화되는 엠알유체, 상기 실린더부 상단의 하면에는 상기 피스톤부의 상단을 향해 돌출되고, 스트로크의 길이에 따라 상기 피스톤부의 감쇠력을 변화시키도록 테이퍼진 형상으로 형성된 미터링핀 및 상기 피스톤부의 상단에 상기 미터링핀이 삽입되도록 홀이 형성된 플레이트 형상으로 배치되고, 상기 엠알유체가 유동되어 상기 피스톤부가 감쇠력을 갖도록 상기 홀이 상기 미터링핀의 외주와 일정한 간격을 두고 구비된 오리피스부를 포함한다.


    Access

    Download


    Export, share and cite



    Title :

    LANGING GEAR HAVING MAGNETO RHEOLOGICAL FLUID DAMPER FOR AIRCRAFT


    Additional title:

    항공기용 엠알유체 댐퍼를 포함하는 착륙장치


    Contributors:
    CHOI SEUNG BOK (author) / HAN CHUL HEE (author) / KIM BO GYU (author) / NAM KYOUNG JAE (author) / HWANG JAI HYUK (author) / HONG YEH SUN (author) / TAK JUN MO (author)

    Publication date :

    2019-05-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Korean


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn




    Control method for magneto-rheological shimmy damper of aircraft landing gear

    REN NIANDONG / LIU AOTIAN | European Patent Office | 2020

    Free access

    Magneto-Rheological (MR) Damper for Landing Gear System

    Khani, Mahboubeh / Stiharu, Ion / Sedaghati, Ramin | AIAA | 2009


    Study on Magneto-rheological Damper Control of Aircraft Landing Gear Based on LADRC

    Dong, Lei / Chen, Zengqiang / Sun, Mingwei et al. | Springer Verlag | 2021


    MR Magneto Rheological Damper

    European Patent Office | 2019

    Free access