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公开(公告)号：US20190351999A1
公开(公告)日：2019-11-21
申请号：US15982420
申请日：2018-05-17
Applicant: Bell Helicopter Textron Inc.
Inventor： Frank Bradley Stamps , Michael K. McNair , John Richard McCullough
Abstract: A propulsion assembly for a rotorcraft includes a blade assembly, a drive shaft coupled to the blade assembly and an electric motor coupled to the drive shaft and operable to provide rotational energy to the drive shaft to rotate the blade assembly. The propulsion assembly includes a landing assistance turbine coupled to the drive shaft and operable to selectively provide rotational energy to the drive shaft during an underpowered descent to rotate the blade assembly and provide upward thrust, thereby reducing a descent rate of the rotorcraft prior to landing.
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公开(公告)号：US20190263516A1
公开(公告)日：2019-08-29
申请号：US16413572
申请日：2019-05-15
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
Abstract: An aircraft has a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe with first and second M-wings having first and second pylons extending therebetween, each M-wing forming a pair of leading apexes with swept forward and swept back portions extending therefrom at a swept angle. A propulsion system includes a plurality of propulsion assemblies each attached to the airframe proximate one of the leading apexes. Each of the propulsion assemblies includes a rotor assembly having a tilting degree of freedom. A flight control system is operable to control the propulsion assemblies including tilting the rotor assemblies to generate variable thrust vectors. In the vertical takeoff and landing fight mode, the aircraft operates responsive to thrust-borne lift from the propulsion system. In the forward flight mode, the aircraft operates responsive to wing-borne lift in a biplane orientation.
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公开(公告)号：US10329014B2
公开(公告)日：2019-06-25
申请号：US15606213
申请日：2017-05-26
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
Abstract: An aircraft has a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe with first and second M-wings each having a pair of leading apexes with swept forward and swept back portions extending therefrom at a swept angle. A propulsion system includes a plurality of propulsion assemblies each attached to the airframe proximate one of the leading apexes. Each of the propulsion assemblies includes a rotor assembly having a tilting degree of freedom. A flight control system is operable to control the propulsion assemblies including tilting the rotor assemblies to generate variable thrust vectors that have a maximum angle that is generally congruent with the swept angles of the M-wings.
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公开(公告)号：US10315761B2
公开(公告)日：2019-06-11
申请号：US15200261
申请日：2016-07-01
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
Abstract: In some embodiments, a propulsion assembly for an aircraft includes a nacelle, at least one self-contained fuel tank disposed within the nacelle operable to contain a liquid fuel, an engine disposed within the nacelle operable to run on the liquid fuel, a drive system mechanically coupled to the engine and operable to rotate responsive to rotation of the engine, a rotor hub mechanically coupled to the drive system operable to rotate responsive to rotation of the drive system and a proprotor mechanically coupled to the rotor hub and operable to rotate therewith.
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公开(公告)号：US20190092458A1
公开(公告)日：2019-03-28
申请号：US15718592
申请日：2017-09-28
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd , Brett Rodney Zimmerman
IPC: B64C27/00 , B64C27/473 , B64C27/06
Abstract: An inertia weight assembly positionable within a receiving portion of a rotor blade for use on a rotorcraft. The inertia weight assembly includes a weighted core and a casing having a closed outboard end and forming a cavity. The weighted core is disposed in the cavity such that the casing at least partially encloses the weighted core. The weighted core is formed from a first material and the casing is formed from a second material that is dissimilar to the first material. The casing provides an interface between the weighted core and the receiving portion of the rotor blade. The second material is more bondable to the receiving portion of the rotor blade than the first material.
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Patent Agency Ranking
公开(公告)号：US10232950B2
公开(公告)日：2019-03-19
申请号：US15200273
申请日：2016-07-01
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
Abstract: In some embodiment, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flight control system is operable to independently control the propulsion assemblies. The flight control system is also operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.
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公开(公告)号：US10227133B2
公开(公告)日：2019-03-12
申请号：US15200230
申请日：2016-07-01
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
Abstract: In some embodiments, a transportation method includes coupling a flying frame to a passenger pod assembly; lifting the passenger pod assembly into the air in a vertical takeoff and landing mode with the passenger pod assembly in a generally horizontal attitude; transitioning from the vertical takeoff and landing mode to a forward flight mode by rotating the flying frame relative to the passenger pod assembly, which remains in the generally horizontal attitude; transporting the passenger pod assembly toward a second location in the forward flight mode; transitioning the flying frame from the forward flight mode to the vertical takeoff and landing mode by rotating the flying frame relative to the passenger pod assembly, which remains in the generally horizontal attitude; landing the flying frame at the second location in the vertical takeoff and landing mode; and releasing the passenger pod assembly.
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公开(公告)号：US10214285B2
公开(公告)日：2019-02-26
申请号：US15200211
申请日：2016-07-01
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
Abstract: In some embodiments, an aircraft includes a flying frame having an airframe with first and second wing members having a plurality of pylons extending therebetween, a distributed propulsion system including a plurality of propulsion assemblies securably attached to the airframe and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode with the wing members disposed in generally the same horizontal plane and a forward flight mode with the wing members disposed in generally the same vertical plane. The flight control system is operable to command the propulsion assemblies responsive to at least one of remote flight control, autonomous flight control and combinations thereof.
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公开(公告)号：US20190031336A1
公开(公告)日：2019-01-31
申请号：US16154207
申请日：2018-10-08
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
IPC: B64C29/00 , B64C27/26 , B64C27/28 , B64C27/30 , B64C29/02 , B64C39/02 , B64C39/08 , B64D27/06 , B64D27/24 , B64D27/26
Abstract: Systems and methods for automated configuration of mission specific aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. A method includes receiving mission parameters including flight parameters and payload parameters; configuring an airframe based upon the mission parameters including selecting a flight control system, first and second wings and first and second pylons operable for coupling between the first and second wings, the first and second wings each having first and second inboard nacelle stations and first and second outboard nacelle stations; determining thrust requirements based upon the mission parameters; configuring a two-dimensional distributed thrust array based upon the thrust requirements including selecting inboard propulsion assemblies operable for coupling to the inboard nacelle stations of the first and second wings and selecting outboard propulsion assemblies operable for coupling to the outboard nacelle stations of the first and second wings.
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公开(公告)号：US20190031334A1
公开(公告)日：2019-01-31
申请号：US16154173
申请日：2018-10-08
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
Abstract: A mission configurable aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons extending therebetween. A two-dimensional distributed thrust array is attached to the airframe. The thrust array including a plurality of inboard propulsion assemblies coupled to first and second inboard nacelle stations of the first and second wings. The thrust array also includes a plurality of outboard propulsion assemblies coupled to first and second outboard nacelle stations of the first and second wings. A flight control system is operable to independently control each of the propulsion assemblies. A payload is coupled to the airframe. The inboard propulsion assemblies have a thrust type that is different from the thrust type of the outboard propulsion assemblies.
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