A control circuitry includes a propulsor trim prediction circuitry configured to generate a predicted propulsor collective blade pitch trim value for a target state of an aircraft based on an aircraft velocity and a pitch attitude deviation from a reference. The control circuitry further includes an output circuitry configured to output a propulsor collective blade pitch angle command based on the predicted propulsor collective blade pitch trim value. The propulsor collective blade pitch angle command is configured to cause an adjustment in a blade pitch angle of a propulsor of the aircraft. Additionally or alternatively, the control circuitry includes a pitch attitude trim prediction circuitry configured to generate a predicted pitch attitude trim value. The output circuitry is configured to output an aircraft pitch attitude trim command, configured to cause an adjustment in a pitch angle of the aircraft, based on the predicted pitch attitude trim value.


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    Title :

    Pitch and thrust control for compound aircraft


    Contributors:

    Publication date :

    2020-12-29


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / B64C AEROPLANES , Flugzeuge / G05B Steuer- oder Regelsysteme allgemein , CONTROL OR REGULATING SYSTEMS IN GENERAL



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