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公开(公告)号：US20200348332A1
公开(公告)日：2020-11-05
申请号：US16400916
申请日：2019-05-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Vincent Louis , Daniel Bryan Robertson , Matthew Edward Louis
Abstract: A pitot-static array system for a tail-sitting aircraft has a disk with a plurality of edge ports arrayed about an edge of the disk. Each of a plurality of pressure transducers is configured to measure air pressure at one of the edge ports. The edge ports are arrayed about an axis parallel to a pitch axis of the aircraft.
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公开(公告)号：US11286036B2
公开(公告)日：2022-03-29
申请号：US16159178
申请日：2018-10-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk L. Groninga , Daniel B. Robertson , Matthew Edward Louis , Robert Glenn Vaughn , Michael J. Ryan , Brent Randal Achttien
Abstract: A rotor system is provided in one example embodiment and may include a rotor duct; at least one rotor blade, wherein the at least one rotor blade comprises a tip end; and a tip extension affixed at the tip end of the at least one rotor blade, wherein the tip extension is comprised, at least in part, of a flexible material and the rotor blade has a fixed extended length based on the tip extension. The tip extension may provide a clearance distance between the tip extension and the rotor duct.
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公开(公告)号：US10884015B2
公开(公告)日：2021-01-05
申请号：US16400916
申请日：2019-05-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Vincent Louis , Daniel Bryan Robertson , Matthew Edward Louis
Abstract: A pitot-static array system for a tail-sitting aircraft has a disk with a plurality of edge ports arrayed about an edge of the disk. Each of a plurality of pressure transducers is configured to measure air pressure at one of the edge ports. The edge ports are arrayed about an axis parallel to a pitch axis of the aircraft.
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公开(公告)号：US11286037B2
公开(公告)日：2022-03-29
申请号：US16159208
申请日：2018-10-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Robert Glenn Vaughn , Michael J. Ryan , Brent Randal Achttien , Kirk L. Groninga , Daniel B. Robertson , Matthew Edward Louis
Abstract: A rotor system is provided in one example embodiment and may include a rotor duct; at least one rotor blade, wherein the at least one rotor blade comprises a tip end; and a tip extension affixed at the tip end of the at least one rotor blade, wherein the tip extension comprises a plurality of flexible elements and the rotor blade has a fixed extended length based on the tip extension. The tip extension may provide a clearance distance between the tip extension and the rotor duct.
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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：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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