A control system (6) of an aircraft (1) includes a computer (15) that controls flight based on either a flight control law (20) that controls flight by controlling the deflection angles of control surfaces (3) or a control surface/thrust integrated flight control law (22) that controls flight by controlling the deflection angles of the control surfaces (3) and engine thrust, and a control surface failure/damage detection device (18) that detects that at least one of the control surfaces (3) is malfunctioning. If malfunctioning of the control surface(s) (3) is detected, the deflection angles and the rates of change of the deflection angles of the control surfaces (3) that are necessary for realization of desired flight characteristics are calculated based on the detection result, and the necessity of switching from the flight control law (20) to the control surface/thrust integrated flight control law (22) is judged by judging whether or not the calculated deflection angles or rates of change of the deflection angles exceed an acceptable range of change.


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    Title :

    航空機の制御システム、航空機、航空機の制御プログラム、及び航空機の制御方法


    Publication date :

    2015-11-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen



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