The invention discloses a fly-by-wire helicopter parallel steering engine mechanism and a working method thereof.The main shaft is sleeved with a torsional spring, the two ends of the torsional spring are connected with a first fixing disc and a second fixing disc respectively, the main shaft extends in the radial direction to form a first adjusting disc, the top end of the main shaft is connected with an anchoring gear through a bearing, and a second adjusting disc is arranged at the bottom of the anchoring gear; the first adjusting disc and the second adjusting disc are both located between the first fixing disc and the second fixing disc. An anchoring shaft is connected with an anchoring gear, an electromagnetic clutch inner ring is fixedly connected to the anchoring shaft, and an electromagnetic clutch outer ring is connected with a parallel steering engine motor; the main shaft gear is connected with a damping transmission shaft and an RVDT transmission shaft, and the RVDT transmission shaft is fixedly connected with the RVDT; the end of the spindle is fixedly connected with a friction device. The damping transmission shaft is fixedly connected with a damper rocker arm, the damper is fixedly connected with a damper shearing rocker arm, and a damper connecting pull rod is hinged between the damper rocker arm and the damper shearing rocker arm. All parts are designed in a centralized mode, the structural layout is compact, and the integration degree is high.

    本发明公开了一种电传直升机并联舵机机构及其工作方法,主轴上套有扭簧,扭簧两端分别连接有固定盘一和固定盘二,主轴径向延伸有第一调整盘,主轴顶端通过轴承连接有锚定齿轮,锚定齿轮底部设置有第二调整盘,第一调整盘和第二调整盘均位于固定盘一和固定盘二之间;锚定轴与锚定齿轮连接,锚定轴上固连有电磁离合器内圈,电磁离合器外圈与并联舵机电机连接;主轴齿轮连接有阻尼传动轴和RVDT传动轴,RVDT传动轴与RVDT固连;主轴端部固连有摩擦装置;阻尼传动轴固连有阻尼器摇臂,阻尼器固连有阻尼器剪切摇臂,阻尼器摇臂和阻尼器剪切摇臂之间铰接有阻尼器连接拉杆。将各个部件集中设计,结构布局紧凑、集成度高。


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    Titel :

    Parallel steering engine mechanism of fly-by-wire helicopter and working method of parallel steering engine mechanism


    Weitere Titelangaben:

    一种电传直升机并联舵机机构及其工作方法


    Beteiligte:
    WANG JINWEI (Autor:in)

    Erscheinungsdatum :

    12.03.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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