A pitch control system configured to vary a pitch angle of a plurality of propeller blades of a propeller system is provided including a motor having a motor shaft configured to rotate about an axis. A rotary switch having a tab protruding generally outwardly is coupled to the motor shaft and is configured to move between a first position and a second position. The pitch control system also includes a position sensor configured to monitor the position of the rotary switch. The position of the rotary switch is proportional to the pitch angle of the plurality of propeller blades.


    Access

    Download


    Export, share and cite



    Title :

    Pitch control system for an aircraft


    Contributors:
    CYR MARK M (author) / GRADZKI KARL (author)

    Publication date :

    2020-06-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    Rotary wing aircraft pitch control system

    BREDENBECK JR KEVIN L / COTTON BRYAN S / WILSON MARK K | European Patent Office | 2020

    Free access

    PROPELLER PITCH CONTROL SYSTEM FOR AIRCRAFT TURBOPROP ENGINES

    FUTA JR PAUL W / TILLICH SAMMUEL / LEWIS STEVEN ALAN et al. | European Patent Office | 2020

    Free access

    AIRCRAFT PITCH CONTROL SYSTEM WITH ELECTRONICALLY GEARED ELEVATOR

    AHN THOMAS / TANNER CLINTON ERIC / NELSON THOMAS et al. | European Patent Office | 2017

    Free access

    AIRCRAFT PITCH CONTROL SYSTEM WITH ELECTRONICALLY GEARED ELEVATOR

    AHN THOMAS / TANNER CLINTON ERIC / NELSON THOMAS et al. | European Patent Office | 2021

    Free access

    Propeller pitch control system for aircraft turboprop engines

    FUTA JR PAUL W / TILLICH SAMMUEL / LEWIS STEVEN ALAN et al. | European Patent Office | 2020

    Free access