公开(公告)号：US20190056734A1

公开(公告)日：2019-02-21

申请号：US16032928

申请日：2018-07-11

Applicant: Bell Helicopter Textron Inc.

Inventor： Robert Earl Worsham, II ,  Luke Dafydd Gillett ,  Troy Sheldon Caudill ,  Bradley Paul Regnier ,  Joshua Robert O'Neil ,  Brandon Jeffrey Thomas

IPC: G05D1/00 ,  B64C13/50

Abstract: In an embodiment, a rotorcraft includes a rotor system including a plurality of blades; two or more engines operable to rotate the plurality of blades; a control assembly operable to receive commands from a pilot; a flight control computer (FCC) in signal communication with the two or more engines, the FCC being operable to generate engine data indicating whether the two or more engines are functional; and a flight management system (FMS) in signal communication with the control assembly and the FCC, the FMS being operable to receive a takeoff type and a plurality of takeoff parameters input into the FMS by the pilot; generate a guidance profile for a Category A (Cat-A) takeoff procedure based on the takeoff type and the plurality of takeoff parameters, the Cat-A takeoff procedure including one or more decision points for performing a takeoff procedure based on whether all engines are operable or one engine is inoperable; receive a command to engage in a takeoff procedure from the control assembly; in response to the command to engage in the takeoff procedure, provide guidance cues to a pilot of the rotorcraft; receive the engine data from the FCC during operation of the rotorcraft; and update the guidance profile based on the engine data during operation of the rotorcraft.

公开(公告)号：US20190225349A1

公开(公告)日：2019-07-25

申请号：US15876298

申请日：2018-01-22

Applicant: Bell Helicopter Textron Inc.

Inventor： Eric A. Sinusas ,  Bradley Paul Regnier ,  Aaron Alexander Acee ,  Charles Hubert Speller ,  Marc Ouellet

IPC: B64D47/00 ,  H02J4/00

Abstract: A power system for an aircraft includes a plurality of power consumers each operable to consume power in a range from zero to maximum power demand and collectively capable of consuming a combined maximum power demand, a power source operable to output power to the power consumers and a power allocation system operable to allocate power from the power source to the power consumers based on an operational parameter of the aircraft. The power allocated by the power allocation system is less than the combined maximum power demand of the power consumers, thereby allowing the power source to have a maximum power output less than the combined maximum power demand of the power consumers.