公开(公告)号：US20180275684A1

公开(公告)日：2018-09-27

申请号：US15465417

申请日：2017-03-21

Applicant: Bell Helicopter Textron Inc.

Inventor： Luke Dafydd Gillett ,  Robert Earl Worsham II

IPC: G05D1/10 ,  B64C27/06 ,  B64C27/82 ,  B64D43/02 ,  B64C17/06 ,  G01C21/18 ,  B64C13/50

Abstract: A rotorcraft includes airspeed sensors, inertial sensors, and a flight control computer (FCC) operable to provide a longitudinal control for the rotorcraft. The FCC receives a first indication of longitudinal airspeed from the airspeed sensors and receives a first indication of longitudinal acceleration from the inertial sensors. The FCC generates a filtered indication of longitudinal airspeed from the first indication of longitudinal airspeed and generates a scaled and filtered indication of longitudinal acceleration from the first indication of longitudinal acceleration. The FCC combines the filtered indication of longitudinal airspeed with the scaled and filtered indication of longitudinal acceleration to generate a determined longitudinal airspeed. The FCC generates a flight control signal to control operation of the rotorcraft, the flight control signal based on the determined longitudinal airspeed.

公开(公告)号：US20180290733A1

公开(公告)日：2018-10-11

申请号：US15480152

申请日：2017-04-05

Applicant: Bell Helicopter Textron Inc.

Inventor： Robert Earl Worsham II ,  Thomas Wayne Brooks

IPC: B64C13/50 ,  B64C27/06 ,  B64C27/82 ,  B64C27/14

Abstract: A rotorcraft 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, thereby returning the rotorcraft 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 engaged in flight operations at airspeeds between 0 knots (e.g., a hover) and about 60 knots. The control laws are further operable to permit the rotorcraft to operate with Instrument Meteorological Conditions (IMC) approval at substantially all airspeeds within a normal flight envelope of the rotorcraft.