A rotorcraft (100) with a fly-by-wire system includes a computing device having control laws. The control laws are operable to engage a stabilization maneuver in response to a perturbation of an otherwise stable operating condition of the rotorcraft (100), thereby returning the rotorcraft (100) to the stable operating condition without requiring input from the pilot. One or more control laws are further operable to increase or decrease pitch angle, roll angle, yaw rate, or collective pitch angle. In representative aspects, perturbation of the stable operating condition may occur as a result of transient meteorological conditions ( e.g., wind shear, wind gust, turbulence) experienced by a rotorcraft (100) engaged in flight operations at airspeeds between o knots ( e.g., a hover) and about 60 knots. The control laws are further operable to permit the rotorcraft (100) to operate with Instrument Meteorological Conditions (IMC) approval at substantially all airspeeds within a normal flight envelope of the rotorcraft (100).
ROTORCRAFT FLY-BY-WIRE STABILIZATION
FLY-BY-WIRE-STABILISIERUNG FÜR DREHFLÜGLER
STABILISATION DES COMMANDES DE VOL ÉLECTRIQUE DE GIRAVION
2020-03-18
Patent
Electronic Resource
English