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
Estimating the term…
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.
Claims26
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 pilot command of the ailerons, the pilot command of the ailerons having a characteristic that will cause the pilot command of the ailerons to excite the structural flexible mode of the aircraft;
- and then
- executing the pilot command of the ailerons in conjunction with a mitigating command of the rudder configured to mitigate the effect of the excitation of the structural flexible mode of the aircraft:
- wherein:
- the mitigating command is of zero magnitude and duration when the pilot command is not susceptible to excite the structural flexible mode of the aircraft;
- the mitigating command is generated through an application of transfer functions for applying a criterion, the criterion comprising a predetermined frequency susceptible of exciting the structural flexible mode of the aircraft;
- and
- the pilot command of the ailerons is oscillatory and the characteristic includes the predetermined frequency of the criterion for the pilot command of the ailerons.
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 pilot command of one or more first flight control surfaces, the pilot command of the one or more first flight control surfaces having a characteristic that will cause the pilot command of the one or more first flight control surfaces to excite the structural flexible mode of the aircraft;
- and then
- executing the pilot command of the one or more first flight control surfaces in conjunction with a mitigating 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;
- wherein:
- the mitigating command is of zero magnitude and duration when the pilot command is not susceptible to excite the structural flexible mode of the aircraft;
- the mitigating command is generated through an application of transfer functions for applying a criterion, the criterion comprising a predetermined frequency susceptible of exciting the structural flexible mode of the aircraft;
- and
- the pilot command of the one or more first flight control surfaces is oscillatory and the characteristic includes the predetermined frequency of the criterion for the pilot command of the one or more first flight control surfaces.
Dependencies are inferred from the claim text.