公开(公告)号：US10457417B2

公开(公告)日：2019-10-29

申请号：US16171672

申请日：2018-10-26

Applicant: Bell Helicopter Textron Inc.

Inventor： Erik John Oltheten ,  Thomas Wayne Brooks

IPC: G08B23/00 ,  B64D45/08 ,  B64D43/02 ,  B64D45/00

Abstract: Embodiments are directed to flight instrument warnings that are configured to automatically adjust a low airspeed warning band on an airspeed indicator based on available torque margin and radar altimeter height. Warnings may be presented on a primary flight display or on flight instruments when a low airspeed band is entered.

公开(公告)号：US20200003908A1

公开(公告)日：2020-01-02

申请号：US16022455

申请日：2018-06-28

Applicant: Bell Helicopter Textron Inc.

Inventor： Robert Earl Worsham, II ,  Charles Eric Covington ,  Thomas Wayne Brooks

IPC: G01S19/52 ,  B64C13/50 ,  G01C21/16 ,  G01S19/14

Abstract: A rotorcraft includes a flight control computer (FCC), a GPS receiver configured to calculate a groundspeed based on a first carrier signal, and an attitude and heading reference system (AHRS) configured to determine an acceleration of the rotorcraft. The AHRS is operable to receive an indication of the groundspeed from the GPS receiver and to calculate a velocity of the rotorcraft based on the indication of the groundspeed and the acceleration. The FCC is operable to receive an indication of the velocity from the AHRS, to generate the flight control device control signal according to the indication of velocity, and to send a flight control device control signal to one or more flight control devices.

公开(公告)号：US20190127082A1

公开(公告)日：2019-05-02

申请号：US16171672

申请日：2018-10-26

Applicant: Bell Helicopter Textron Inc.

Inventor： Erik John Oltheten ,  Thomas Wayne Brooks

IPC: B64D45/08 ,  B64D43/02

CPC classification number: B64D45/08 ,  B64C27/006 ,  B64D43/02 ,  B64D2045/0085 ,  G01C23/00

Abstract: Embodiments are directed to flight instrument warnings that are configured to automatically adjust a low airspeed warning band on an airspeed indicator based on available torque margin and radar altimeter height. Warnings may be presented on a primary flight display or on flight instruments when a low airspeed band is entered.

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.