An aircraft uses trajectory-based control algorithms for blade pitch (or twist). This approach greatly enhances the ability of the actuator to accurately achieve the desired blade pitch and to track the commanded pitch position. An actuator includes an electronic rotor blade controller that converts communicated or desired changes in pitch (or similar parameter) to actual physical effects that match the desired changes as closely as possible. The controller preferably includes a motor drive circuit, such as an h-bridge, a communication circuit for connection to external commands, and a processor with associated enabling circuitry (e.g. memory, I/O) to coordinate and implement the control.


    Access

    Download


    Export, share and cite



    Title :

    Rotor blade pitch trajectory control



    Publication date :

    2023-08-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    Rotor Blade Pitch Trajectory Control

    BERGER THOMAS KARL / MILANES DAVID WADE / ROBERTSON JAMES STEWART | European Patent Office | 2023

    Free access

    ROTOR BLADE PITCH TRAJECTORY CONTROL

    BERGER THOMAS KARL / MILANES DAVID WADE / ROBERTSON JAMES STEWART | European Patent Office | 2023

    Free access

    ROTOR BLADE PITCH HORN ASSEMBLY

    HALCOM LANCE / D'ANNA FRANK P / DOOLIN LEONARD J | European Patent Office | 2017

    Free access

    Rotor blade pitch horn assembly

    HALCOM LANCE / D'ANNA FRANK P / DOOLIN LEONARD J | European Patent Office | 2020

    Free access

    ROTOR BLADE PITCH HORN ASSEMBLY

    HALCOM LANCE / D ANNA FRANK P / DOOLIN LEONARD J | European Patent Office | 2016

    Free access