公开(公告)号：US10435149B2

公开(公告)日：2019-10-08

申请号：US15620317

申请日：2017-06-12

Applicant: Bell Helicopter Textron Inc.

Inventor： Levi Charles Hefner ,  Danielle Lynn Moore ,  Sung Kim

IPC: B64C27/52 ,  B64C27/605 ,  B64C39/02 ,  B64C29/02 ,  B64C11/48 ,  B64C27/10 ,  B64C3/54

Abstract: An Unmanned Aerial Vehicle (UAV) has a first blade assembly configured to rotate in a first direction about an axis of rotation and a second blade assembly configured to rotate in a second direction opposite the first direction about the axis of rotation, wherein the second blade assembly can be selectively cocked relative to the axis of rotation.

公开(公告)号：US20190118942A1

公开(公告)日：2019-04-25

申请号：US15792430

申请日：2017-10-24

Applicant: Bell Helicopter Textron Inc.

Inventor： Sung Kim ,  Jouyoung Jason Choi ,  Frank Bradley Stamps

IPC: B64C29/00 ,  B64C27/26 ,  B64C27/28 ,  B64C27/605 ,  B64C11/30 ,  B64C13/16

Abstract: Systems and methods of operating a tiltrotor aircraft include providing a control system that includes sensors and/or gauges that provide feedback regarding hub shear forces in rotor systems of the aircraft that produce aeroelastic instability known as whirl flutter. Feedback from the sensors and/or gauges is communicated to a flight control subsystem that includes an algorithm that provides a cascading set of responses to control whirl flutter and a failsafe that adjusts operational characteristics of the aircraft in response to the continuation or excitation of the whirl flutter.

公开(公告)号：US09886039B2

公开(公告)日：2018-02-06

申请号：US14623382

申请日：2015-02-16

Applicant: Bell Helicopter Textron Inc.

Inventor： Luke D. Gillett ,  Joseph M. Schaeffer ,  Christopher M. Bothwell ,  Robert Worsham ,  Jillian Alfred ,  Sung Kim

IPC: G05D1/08 ,  G05D1/06 ,  B64C27/10 ,  B64C27/16 ,  B64C27/605

CPC classification number: G05D1/0607 ,  B64C27/10 ,  B64C27/16 ,  B64C27/605

Abstract: A flight control system having a control law, the control law operable to generate a modified pitch command, the modified pitch command representing a greater amount of collective pitch compared to an amount of collective pitch generated by a first pitch command, the modified pitch command being generated because a vertical descent speed of the rotorcraft at a given forward airspeed is greater than a threshold. A method of avoiding entry into an undesired vertical descent speed region during operation of a rotorcraft, including measuring a forward airspeed; evaluating a vertical descent of the rotorcraft; and generating a modified collective pitch command in respond to a first collective pitch command having a collective pitch value that would cause the rotorcraft to experience a vertical descent rate greater than a threshold value at the forward airspeed of the rotorcraft.

公开(公告)号：US20200172237A1

公开(公告)日：2020-06-04

申请号：US16206088

申请日：2018-11-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Carlos Fenny ,  Sung Kim ,  Kip Campbell ,  Jouyoung Jason Choi

IPC: B64C29/00 ,  B64C19/00 ,  F04D25/06

Abstract: An electric reaction control system that can selectively expel a “burst” or “puff” of air to alter the orientation of the aircraft during flight. An aircraft incorporating ducting, an air compressor, an electric motor, and a plurality of nozzles can facilitate in-flight trajectory modifications. When an air burst is needed to provide thrust for the purposes of reaction control, nozzles are selectively opened and closed to provide roll, pitch, and yaw of the aircraft. The ERCS can facilitate an electric aircraft that would be very agile and very light, utilizing electric power, as opposed to jet power.

公开(公告)号：US20180354612A1

公开(公告)日：2018-12-13

申请号：US15620317

申请日：2017-06-12

Applicant: Bell Helicopter Textron Inc.

Inventor： Levi Charles Hefner ,  Danielle Lynn Moore ,  Sung Kim

IPC: B64C27/605 ,  B64C39/02 ,  B64C29/02 ,  B64C25/52 ,  B64C9/00

CPC classification number: B64C27/605 ,  B64C3/546 ,  B64C11/48 ,  B64C27/10 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/165

Abstract: An Unmanned Aerial Vehicle (UAV) has a first blade assembly configured to rotate in a first direction about an axis of rotation and a second blade assembly configured to rotate in a second direction opposite the first direction about the axis of rotation, wherein the second blade assembly can be selectively cocked relative to the axis of rotation.

公开(公告)号：US20150232176A1

公开(公告)日：2015-08-20

申请号：US14623382

申请日：2015-02-16

Applicant: Bell Helicopter Textron Inc.

Inventor： Luke D. Gillett ,  Joseph M. Schaeffer ,  Christopher M. Bothwell ,  Robert Worsham ,  Jillian Alfred ,  Sung Kim

IPC: B64C27/605 ,  B64C27/16 ,  B64C27/10

CPC classification number: G05D1/0607 ,  B64C27/10 ,  B64C27/16 ,  B64C27/605

Abstract: A flight control system having a control law, the control law operable to generate a modified pitch command, the modified pitch command representing a greater amount of collective pitch compared to an amount of collective pitch generated by a first pitch command, the modified pitch command being generated because a vertical descent speed of the rotorcraft at a given forward airspeed is greater than a threshold. A method of avoiding entry into an undesired vertical descent speed region during operation of a rotorcraft, including measuring a forward airspeed; evaluating a vertical descent of the rotorcraft; and generating a modified collective pitch command in respond to a first collective pitch command having a collective pitch value that would cause the rotorcraft to experience a vertical descent rate greater than a threshold value at the forward airspeed of the rotorcraft.

Abstract translation: 一种具有控制规则的飞行控制系统，所述控制规则可操作以产生修正的俯仰指令，所述修正的俯仰指令表示与由第一俯仰指令产生的总音调量相比较大的总音调， 这是因为在给定的前进空速下旋翼飞机的垂直下降速度大于阈值。 一种在旋翼航空器操作期间避免进入不期望的垂直下降速度区域的方法，包括测量前进空速; 评估旋翼航空器的垂直下降; 以及响应于具有共同音调值的第一集体音调命令来产生修正的集体音调命令，所述集体音调值将导致旋翼航空器在所述旋翼航空器的前进空速下经历大于阈值的垂直下降速率。