The invention discloses a magneto-rheological buffer of a helicopter undercarriage and a magneto-rheological vibration reduction control system and method. The magneto-rheological buffer comprises a high-pressure air cavity, a low-pressure air cavity, a coil, a piston, an oil cavity, a wire and a piston valve. The control system comprises a helicopter undercarriage, a magneto-rheological buffer, a sensor, a main controller, a current driver and a Hall element. The control method comprises the following steps: measuring data of the height and the body posture of the helicopter and the damping force of the buffer through the sensor, and transmitting the data to the main controller; the main controller calculates the current required by the coil in the rising and falling process of the helicopter; the main controller outputs PWM waves to the current driver, and the current driver outputs actual current to the coil to change the damping force of the coil; meanwhile, actual current is sensed through a Hall element and fed back to the main controller, and the main controller tracks the actual current through a self-adaptive control algorithm. The damping device is simple in structure, damping force can be adjusted in real time according to changes of the helicopter attitude, vibration of the helicopter during landing can be effectively reduced, and therefore the stability and safety of the helicopter during landing are improved.

    本发明公开了一种直升机起落架磁流变缓冲器及磁流变减振控制系统和方法,磁流变缓冲器包括高压气腔、低压气腔、线圈、活塞、油腔、导线和活塞阀门;控制系统包括直升机起落架、磁流变缓冲器、传感器、主控制器、电流驱动器和霍尔元件。控制方法包括:通过传感器测得直升机的高度和机身姿态及缓冲器阻尼力的数据,并传输至主控制器;主控制器计算在直升机起落过程中线圈所需电流;主控制器输出PWM波至电流驱动器中,电流驱动器输出实际电流至线圈中改变其阻尼力;同时通过霍尔元件感测实际电流并将其反馈至主控制器,主控制器通过自适应控制算法对实际电流进行跟踪。本发明结构简单且能根据直升机姿态的变化而实时调整阻尼力,能够有效减小直升机在起落时的振动,从而增加直升机起落时的平稳性和安全性。


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    Titel :

    Helicopter undercarriage magneto-rheological buffer and magneto-rheological vibration reduction control system and method


    Weitere Titelangaben:

    一种直升机起落架磁流变缓冲器及磁流变减振控制系统和方法


    Beteiligte:
    RUI XIAOTING (Autor:in) / XU XIUCAI (Autor:in) / ZHU WEI (Autor:in) / YANG FUFENG (Autor:in) / RUI XUE (Autor:in) / WANG LINGYUN (Autor:in) / XIN XIN (Autor:in) / QIANG RAN (Autor:in)

    Erscheinungsdatum :

    29.04.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    F16F SPRINGS , Federn / B64C AEROPLANES , Flugzeuge



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