System and method for mitigating an effect of an excitation of a structural flexible mode of an aircraft
AssigneeBombardier Inc.
InventorsSylvain THERIEN, David REIST
Life of this patent
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Abstract
Systems and methods for controlling a fixed-wing aircraft during flight are disclosed. The aircraft comprises first and second flight control surfaces of different types. The method comprises determining that a pilot command of the first flight control surface will excite a structural flexible mode of the aircraft and then executing the pilot command of the first flight control surface in conjunction with a command of the second flight control surface to mitigate the effect of the excitation of the structural flexible mode of the aircraft.
Claims27
A method for mitigating an effect of an excitation of a structural flexible mode of an aircraft during flight, the aircraft comprising ailerons for causing movement of the aircraft about a roll axis and a rudder for causing movement of the aircraft about a yaw axis, the method comprising:
- receiving a command of the ailerons, the command of the ailerons having a characteristic that will cause the command of the ailerons to excite the structural flexible mode of the aircraft;
- and then
- executing the command of the ailerons in conjunction with a command of the rudder configured to mitigate the effect of the excitation of the structural flexible mode of the aircraft.
A method for mitigating an effect of an excitation of a structural flexible mode of an aircraft during flight, the aircraft comprising first and second flight control surfaces of different types, the method comprising:
- receiving a command of one or more first flight control surfaces, the command of the one or more first flight control surfaces having a characteristic that will cause the command of the one or more first flight control surfaces to excite the structural flexible mode of the aircraft;
- and then
- executing the command of the one or more first flight control surfaces in conjunction with a command of one or more second flight control surfaces configured to mitigate the effect of the excitation of the structural flexible mode of the aircraft.
-47. (canceled)
Dependencies are inferred from the claim text.