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公开(公告)号：US10889366B2
公开(公告)日：2021-01-12
申请号：US16138672
申请日：2018-09-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Chad Lewis Jarrett , Frank Bradley Stamps , Daniel Bryan Robertson , Kirk Landon Groninga , Matthew Edward Louis
Abstract: An aircraft comprising a pair of ducted thrusters. Each of the ducted thrusters comprises a duct surrounding a rotor assembly with a rotor hub having a plurality of rotor blades extending therefrom, wherein the plurality of rotor blades have a modulated angular distribution about a central longitudinal axis of the duct. Each of the ducted thrusters further comprises a stator assembly having a stator hub with a plurality of stator vanes extending from the stator hub to an interior surface of the duct, wherein each of the plurality of the stator vanes are angularly modulated around the stator hub such that angular spacing between pairs of adjacent vanes of the plurality of stator vanes varies for each pair of the adjacent vanes.
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公开(公告)号：US20200094942A1
公开(公告)日：2020-03-26
申请号：US16138672
申请日：2018-09-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Chad Lewis Jarrett , Frank Bradley Stamps , Daniel Bryan Robertson , Kirk Landon Groninga , Matthew Edward Louis
Abstract: An aircraft comprising a pair of ducted thrusters. Each of the ducted thrusters comprises a duct surrounding a rotor assembly with a rotor hub having a plurality of rotor blades extending therefrom, wherein the plurality of rotor blades have a modulated angular distribution about a central longitudinal axis of the duct. Each of the ducted thrusters further comprises a stator assembly having a stator hub with a plurality of stator vanes extending from the stator hub to an interior surface of the duct, wherein each of the plurality of the stator vanes are angularly modulated around the stator hub such that angular spacing between pairs of adjacent vanes of the plurality of stator vanes varies for each pair of the adjacent vanes.
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公开(公告)号：US10384776B2
公开(公告)日：2019-08-20
申请号：US15438972
申请日：2017-02-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Daniel Bryan Robertson , Kirk Landon Groninga , Frank Bradley Stamps , Matthew Edward Louis
IPC: B64C39/00 , B64C3/32 , B64C3/14 , B64D27/12 , B64D27/26 , B64C29/00 , B64C27/26 , B64C27/28 , B64C27/52 , B64C23/02
Abstract: A tiltrotor aircraft has a fuselage and a wing having upper and lower surfaces with a plurality of channels extending therebetween, each with a cycloidal rotor mounted therein. At least two pylon assemblies are rotatably coupled to the wing to selectively operate the tiltrotor aircraft between helicopter and airplane flight modes. Each pylon assembly includes a mast and a proprotor assembly operable to rotate with the mast to generate thrust. At least one engine provides torque and rotational energy to the proprotor assemblies and the propulsion assemblies. Each of the cycloidal rotors has a plurality of blades that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.
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公开(公告)号：US20180237136A1
公开(公告)日：2018-08-23
申请号：US15438972
申请日：2017-02-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Daniel Bryan Robertson , Kirk Landon Groninga , Frank Bradley Stamps , Matthew Edward Louis
IPC: B64C39/00 , B64C3/32 , B64C3/14 , B64D27/12 , B64D27/26 , B64C29/00 , B64C27/26 , B64C27/28 , B64C27/52
CPC classification number: B64C39/005 , B64C3/14 , B64C3/32 , B64C23/02 , B64C27/26 , B64C27/28 , B64C27/52 , B64C29/0033 , B64C39/003 , B64C2003/143 , B64D27/12 , B64D27/26 , B64D2027/262 , Y02T50/12
Abstract: A tiltrotor aircraft has a fuselage and a wing having upper and lower surfaces with a plurality of channels extending therebetween, each with a cycloidal rotor mounted therein. At least two pylon assemblies are rotatably coupled to the wing to selectively operate the tiltrotor aircraft between helicopter and airplane flight modes. Each pylon assembly includes a mast and a proprotor assembly operable to rotate with the mast to generate thrust. At least one engine provides torque and rotational energy to the proprotor assemblies and the propulsion assemblies. Each of the cycloidal rotors has a plurality of blades that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.
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公开(公告)号：US20180044009A1
公开(公告)日：2018-02-15
申请号：US15233897
申请日：2016-08-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel Bryan Robertson , Dudley Smith , Mark Dreier , Steve Ray Ivans , Kirk Landon Groninga
CPC classification number: B64C27/82 , B64C11/006 , B64C27/06 , B64C39/008 , B64C2027/8245 , B64C2027/8254 , F04D17/04 , F04D29/362 , F05D2220/90
Abstract: In some embodiments, a rotorcraft includes a fuselage, a tailboom, a drive system and a variable thrust cross-flow fan system. The cross-flow fan system includes a cross-flow fan assembly that is mechanically coupled to a drive shaft and operable to rotate with the drive shaft about a longitudinal axis. The cross-flow fan assembly includes first and second driver plates having a plurality of blades rotatably mounted therebetween. The blades are disposed radially outwardly from the longitudinal axis and have a generally circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis. The blades are moveable between a plurality of pitch angle configurations. A control assembly is coupled to the blades. The control assembly is operable to change the pitch angle configuration of the blades to generate variable thrust at a substantially constant rotational speed of the cross-flow fan assembly.
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Patent Agency Ranking
公开(公告)号：US20200239134A1
公开(公告)日：2020-07-30
申请号：US16257696
申请日：2019-01-25
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel Bryan Robertson , Matthew Edward Louis , Kirk Landon Groninga
Abstract: A rotorcraft featuring a fuselage, a forward fuselage ducted fan located in the fuselage, and an aft fuselage ducted fan located in the fuselage. The rotorcraft is directly powered by electricity and can be supplemented with additional powers sources. Two sets of pivoting ducted fans provide additional lift and thrust as needed to control the rotorcraft.
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公开(公告)号：US10717526B2
公开(公告)日：2020-07-21
申请号：US15620310
申请日：2017-06-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Levi Charles Hefner , Danielle Lynn Moore , Andrea Chavez , Kirk Landon Groninga , John Lloyd , Daniel Bryan Robertson
IPC: B64C39/02
Abstract: An Unmanned Aerial Vehicle (UAV) has a fuselage, a rotor system, and a wing configured for selective positioning during flight of the UAV to a deployed position, a stowed position, and to positions between the deployed position and the stowed position. The UAV has a flexible wing skin at least partially carried by a leading arm and the leading arm is rotatable relative to the fuselage.
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公开(公告)号：US10562618B2
公开(公告)日：2020-02-18
申请号：US15477582
申请日：2017-04-03
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga
Abstract: A helicopter has a fuselage, a main rotor system connected to the fuselage and configured to rotate in a rotor direction, the main rotor system comprising a retreating rotor blade side and an opposing advancing rotor blade side, and a first wing extending from the fuselage on the retreating rotor blade side. The helicopter comprises no tail rotor system and comprises no counter-rotating rotor system coaxial with the main rotor system.
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公开(公告)号：US10407169B2
公开(公告)日：2019-09-10
申请号：US15251110
申请日：2016-08-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk Landon Groninga , Daniel Bryan Robertson , Frank Bradley Stamps
Abstract: A tail sitter aircraft includes a fuselage having a forward portion and an aft portion. The forward portion of the fuselage includes first and second rotor stations. A first rotor assembly is positioned proximate the first rotor station. A second rotor assembly is positioned proximate the second rotor station. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of landing members. A pusher propeller extends from the tailboom assembly. In a vertical takeoff and landing mode, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode, rotation of the pusher propeller provides forward thrust and the first and second rotor assemblies are non-rotatable about the fuselage forming a dual wing configuration to provide lift.
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公开(公告)号：US20190144126A1
公开(公告)日：2019-05-16
申请号：US15815513
申请日：2017-11-16
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk Landon Groninga , Daniel Bryan Robertson
IPC: B64D33/08
Abstract: A stacked motor assembly for an aircraft includes a forward motor having an exhaust port and an aft motor disposed aft of the forward motor, the aft motor having an intake port. The stacked motor assembly includes an exhaust conduit originating from the exhaust port of the forward motor and disposed at least partially around the aft motor such that exhaust from the forward motor bypasses the aft motor. The stacked motor assembly also includes an intake conduit terminating at the intake port of the aft motor and disposed at least partially around the forward motor such that intake air for the aft motor bypasses the forward motor.
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