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公开(公告)号：US20180281943A1
公开(公告)日：2018-10-04
申请号：US16001925
申请日：2018-06-06
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
CPC classification number: B64C29/02 , B64C39/024 , B64D1/10 , B64D1/22 , B64D17/025 , G05D1/0011 , G05D1/102 , G08G5/0034 , G08G5/0039 , G08G5/0052 , G08G5/0056 , G08G5/0065 , G08G5/0069 , G08G5/025
Abstract: In some embodiments, a pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a pod assembly; upload a flight plan to a flight control system of a flying frame including an airframe and a distributed propulsion system coupled to airframe; dispatch the flying frame by air to the current location of the pod assembly; couple the pod assembly to the flying frame; transport the pod assembly by air from the current location of the pod assembly to the destination of the pod assembly including transitioning the flying frame between a vertical takeoff and landing mode and a forward flight mode; and decouple the pod assembly from the flying frame at the destination of the pod assembly.
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公开(公告)号：US10011351B2
公开(公告)日：2018-07-03
申请号：US15200244
申请日：2016-07-01
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
IPC: G05D1/00 , G05D3/00 , G06F7/00 , G06F17/00 , B64C29/02 , G05D1/10 , G08G5/00 , B64D1/22 , B64D1/10 , B64D17/02
CPC classification number: B64C29/02 , B64C11/28 , B64C25/04 , B64C25/10 , B64C27/30 , B64C37/00 , B64C39/024 , B64C39/04 , B64D1/10 , B64D1/22 , B64D17/025 , B64D17/80 , G08G5/0034 , G08G5/0039 , G08G5/0052 , G08G5/0056 , G08G5/0065 , G08G5/0069 , G08G5/025
Abstract: In some embodiments, a passenger pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a passenger pod assembly having a current location and a destination; upload a flight plan to a flight control system of a flying frame including an airframe and a propulsion system; dispatch the flying frame to the current location of the passenger pod assembly; couple the flying frame to the passenger pod assembly at the current location of the passenger pod assembly; transport the passenger pod assembly by air from the current location of the passenger pod assembly to the destination of the passenger pod assembly; and decouple the passenger pod assembly from the flying frame at the destination of the passenger pod assembly.
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公开(公告)号：US20180002016A1
公开(公告)日：2018-01-04
申请号：US15200244
申请日：2016-07-01
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
CPC classification number: B64C29/02 , B64C39/024 , B64D1/10 , B64D1/22 , B64D17/025 , G05D1/0011 , G05D1/102 , G08G5/0034 , G08G5/0039 , G08G5/0052 , G08G5/0056 , G08G5/0065 , G08G5/0069 , G08G5/025
Abstract: In some embodiments, a passenger pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a passenger pod assembly having a current location and a destination; upload a flight plan to a flight control system of a flying frame including an airframe and a propulsion system; dispatch the flying frame to the current location of the passenger pod assembly; couple the flying frame to the passenger pod assembly at the current location of the passenger pod assembly; transport the passenger pod assembly by air from the current location of the passenger pod assembly to the destination of the passenger pod assembly; and decouple the passenger pod assembly from the flying frame at the destination of the passenger pod assembly.
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公开(公告)号：US20180002014A1
公开(公告)日：2018-01-04
申请号：US15200211
申请日：2016-07-01
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
CPC classification number: B64C29/02 , B64C11/46 , B64C15/02 , G05D1/0011 , G05D1/102
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：US20180002009A1
公开(公告)日：2018-01-04
申请号：US15200261
申请日：2016-07-01
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
CPC classification number: B64C27/82 , B64C11/28 , B64C27/08 , B64C29/0033 , B64C2027/8227 , B64D31/06 , B64D35/00 , B64D37/04
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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Patent Agency Ranking
公开(公告)号：US11414199B2
公开(公告)日：2022-08-16
申请号：US16290704
申请日：2019-03-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Joseph Dean Rainville , John Richard McCullough
Abstract: A line-replaceable thrust module includes a nacelle configured to be mechanically connected to an anchoring location of an unmanned aerial vehicle (UAV), an electric motor coupled to the nacelle, an electric speed controller configured to control the speed of the electric motor and configured to be electrically connected to a communication network of the UAV, and a fuel cell system configured to produce electrical energy from an electrochemical reaction between hydrogen and oxygen. The fuel cell system includes a fuel cell, a hydrogen tank, a pressure regulator coupled to the hydrogen tank, and a supply line coupled between the pressure regulator and the fuel cell.
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公开(公告)号：US20200277069A1
公开(公告)日：2020-09-03
申请号：US16290704
申请日：2019-03-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Joseph Dean Rainville , John Richard McCullough
Abstract: A line-replaceable thrust module includes a nacelle configured to be mechanically connected to an anchoring location of an unmanned aerial vehicle (UAV), an electric motor coupled to the nacelle, an electric speed controller configured to control the speed of the electric motor and configured to be electrically connected to a communication network of the UAV, and a fuel cell system configured to produce electrical energy from an electrochemical reaction between hydrogen and oxygen. The fuel cell system includes a fuel cell, a hydrogen tank, a pressure regulator coupled to the hydrogen tank, and a supply line coupled between the pressure regulator and the fuel cell.
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公开(公告)号：US10479497B2
公开(公告)日：2019-11-19
申请号：US15990624
申请日：2018-05-26
Applicant: Bell Helicopter Textron Inc.
Inventor： Robert Patrick Wardlaw , John Richard McCullough , Amarjit Olenchery Kizhakkepat , Tyler Wayne Baldwin
Abstract: A proprotor system for a tiltrotor aircraft having helicopter and airplane flight modes includes a yoke having a plurality of blade arms each having an inboard pocket with an outboard surface. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets with each bearing assembly including a shear bearing and a centrifugal force bearing having an integral shoe with an outboard surface. Each of a plurality of inboard beams is disposed at least partially between one of the centrifugal force bearings and one of the shear bearings. Each of a plurality of proprotor blades is coupled to one of the inboard beams. The integral shoes are coupled to the yoke such that there is a spaced apart relationship between the outboard surfaces of the integral shoes and the outboard surfaces of the pockets to prevent centrifugal force load transfer therebetween.
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公开(公告)号：US20190256205A1
公开(公告)日：2019-08-22
申请号：US15902402
申请日：2018-02-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Maresh , Troy Cyril Schank , Chyausong Tzeng , John Richard McCullough , Robert Wardlaw
Abstract: An inboard bearing attachment for carrying centrifugal force (“CF”) loads in a rotor blade assembly of a rotorcraft includes a CF fitting having a curved surface and a shear bearing retainer aligned with the curved surface. A mounting flange connected to either the CF fitting or the shear bearing retainer is used to mount the inboard bearing attachment to a yoke.
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公开(公告)号：US20190217950A1
公开(公告)日：2019-07-18
申请号：US16361155
申请日：2019-03-21
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
Abstract: An aircraft includes an airframe and a distributed propulsion system including a plurality of propulsion assemblies coupled to the airframe. Each of the propulsion assemblies includes a nacelle, an engine disposed within the nacelle, a proprotor coupled to the engine and a thrust vectoring system. Each thrust vectoring system includes a pivoting plate, a rotary actuator operable to rotate the pivoting plate about a propulsion assembly centerline axis and a linear actuator operable to pivot the pivoting plate about a pivot axis that is normal to the propulsion assembly centerline axis. The engine is mounted on the pivoting plate such that operation of the pivoting plate enables resolution of a thrust vector within a thrust vector cone.
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