A vibration control system for a rotorcraft includes at least one of an integrated actuator and an intermediate actuator associated with a first source of vibration, a sensor configured to sense vibration from the first source of vibration, a dedicated actuator configured for association with a fuselage, and a controller configured to receive information from the sensor and configured to control the dedicated actuator and the at least one of the integrated actuator and the intermediate actuator.


    Access

    Download


    Export, share and cite



    Title :

    UNIFIED CONTROL OF MULTIPLE ACTIVE SYSTEMS FOR HELICOPTER VIBRATION SUPPRESSION


    Contributors:

    Publication date :

    2017-03-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



    UNIFIED CONTROL OF MULTIPLE ACTIVE SYSTEMS FOR HELICOPTER VIBRATION SUPRESSION

    HEVERLY DAVID E / SINGH RUPINDER / LEE TAEOH et al. | European Patent Office | 2021

    Free access

    Hybrid Feedforward-Feedback Control for Active Helicopter Vibration Suppression

    Walchko, J. C. / Kim, J. S. / Wang, K. W. et al. | British Library Conference Proceedings | 2007


    Hybrid feedforward-feedback control for active helicopter vibration suppression

    Walchko, Joseph C. / Kim, Jun-Sik / Wang, K.W. et al. | Tema Archive | 2007


    Active control of helicopter vibration

    Pearson, J.T. / Goodall, R.M. / Lyndon, I. | Tema Archive | 1994


    Active Global Vibration Control of Helicopter Fuselage

    Lang, Kai / Xia, Pinqi / Wang, Xiao | AIAA | 2023