公开(公告)号：US11072422B2

公开(公告)日：2021-07-27

申请号：US16004375

申请日：2018-06-09

Applicant: Bell Helicopter Textron Inc.

Inventor： Eric Albert Sinusas ,  Albert Gerard Brand

IPC: B64C27/82 ,  B64C5/00

Abstract: Systems and methods include providing an aircraft with a fuselage, a tail boom or empennage extending from the fuselage, a main rotor, a tail rotor, and at least one counter torque device. The counter torque device provides counter torque to the fuselage to prevent rotation of fuselage when the main rotor is operated, particularly in right sideward flight (RSF) for conventional helicopters with a counter-clockwise rotating (when viewed from above the helicopter) main rotor.

公开(公告)号：US20200346732A1

公开(公告)日：2020-11-05

申请号：US16399922

申请日：2019-04-30

Applicant: Bell Helicopter Textron Inc,

Inventor： Albert Gerard Brand

IPC: B64C1/14 ,  B60J1/20 ,  B64C1/06

Abstract: Various implementations described herein are directed to an aircraft. The aircraft includes an airframe; and a windshield system having a transparent canopy coupled to the airframe and a transparent inner panel having a portion thereof disposed within the transparent canopy and coupled to the airframe.

公开(公告)号：US20200156775A1

公开(公告)日：2020-05-21

申请号：US16196950

申请日：2018-11-20

Applicant: Bell Helicopter Textron Inc.

Inventor： Eric Albert Sinusas ,  Thomas C. Parham, Jr. ,  Albert Gerard Brand

IPC: B64C27/20 ,  B64C27/00 ,  B64C27/46

Abstract: A rotor system for a rotorcraft has a hub rotatable about an axis and a plurality of blades coupled to the hub for rotation therewith about the axis. Each blade is capable of rotation about a pitch axis relative to the hub, and a ring couples adjacent blades to each other.

公开(公告)号：US11827333B2

公开(公告)日：2023-11-28

申请号：US16399922

申请日：2019-04-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Albert Gerard Brand

IPC: B64C1/14 ,  B64C1/06 ,  B60J1/20

CPC classification number: B64C1/1492 ,  B60J1/2094 ,  B64C1/062 ,  B60Y2200/50

Abstract: Various implementations described herein are directed to an aircraft. The aircraft includes an airframe; and a windshield system having a transparent canopy coupled to the airframe and a transparent inner panel having a portion thereof disposed within the transparent canopy and coupled to the airframe and to at least a processor.

公开(公告)号：US11148796B2

公开(公告)日：2021-10-19

申请号：US16007666

申请日：2018-06-13

Applicant: Bell Helicopter Textron Inc.

Inventor： Albert Gerard Brand ,  Eric Albert Sinusas

IPC: B64C27/82

Abstract: Systems and methods include providing a helicopter, with a fuselage, a tail boom extending from the fuselage, a main rotor system, and a tail rotor assembly disposed on an aft end of the tail boom. The tail rotor assembly includes a tail rotor housing, at least one normal ducted fan that generate anti-torque thrust to prevent rotation of the fuselage, and at least one canted ducted fan configured to generate both anti-torque thrust to prevent of the fuselage and lift to the tail boom in order to control the pitch of the helicopter. The canted ducted fans generate sufficient lift to prevent a nose-up orientation of the helicopter when the center of gravity of the helicopter is shifted rearward behind the main rotor system, while the normal ducted fans maintain sufficient anti-torque thrust to prevent rotation of the fuselage when the main rotor is operated.

公开(公告)号：US20190382109A1

公开(公告)日：2019-12-19

申请号：US16007666

申请日：2018-06-13

Applicant: Bell Helicopter Textron Inc.

Inventor： Albert Gerard Brand ,  Eric Albert Sinusas

IPC: B64C27/82

Abstract: Systems and methods include providing a helicopter, with a fuselage, a tail boom extending from the fuselage, a main rotor system, and a tail rotor assembly disposed on an aft end of the tail boom. The tail rotor assembly includes a tail rotor housing, at least one normal ducted fan that generate anti-torque thrust to prevent rotation of the fuselage, and at least one canted ducted fan configured to generate both anti-torque thrust to prevent of the fuselage and lift to the tail boom in order to control the pitch of the helicopter. The canted ducted fans generate sufficient lift to prevent a nose-up orientation of the helicopter when the center of gravity of the helicopter is shifted rearward behind the main rotor system, while the normal ducted fans maintain sufficient anti-torque thrust to prevent rotation of the fuselage when the main rotor is operated.