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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：US20190225334A1
公开(公告)日：2019-07-25
申请号：US16371375
申请日：2019-04-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga , Carlos Alexander Fenny
Abstract: A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. At least two wings are supported by the forward portion of the fuselage. A distributed propulsion system includes at least one propulsion assembly operably associated with each fixed wing and is operable to provide forward thrust during forward flight and vertical thrust during vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of rotatably mounted tail arms having control surfaces and landing members. In a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces. In a landing configuration, the tail arms are radially extended relative to the fuselage axis to form a stable ground contact base with the landing members.
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公开(公告)号：US10293931B2
公开(公告)日：2019-05-21
申请号：US15253449
申请日：2016-08-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga
Abstract: A tri-wing aircraft includes a fuselage having a longitudinally extending fuselage axis. Three wings extend generally radially outwardly from the fuselage axis and are circumferentially distributed generally uniformly about the fuselage at approximately 120-degree intervals. The wings have airfoil cross-sections including first and second surfaces having chordwise channels therebetween. A distributed propulsion system includes a plurality of propulsion assemblies. Each propulsion assembly includes a variable thrust cross-flow fan disposed within one of the chordwise channels of one of the wings. At least two variable thrust cross-flow fans are disposed within the chordwise channels of each of the wings. A flight control system is operably associated with the distributed propulsion system such that the flight control system and the distributed propulsion system are operable to generate a triaxial dynamic thrust matrix.
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公开(公告)号：US20190055016A1
公开(公告)日：2019-02-21
申请号：US15680501
申请日：2017-08-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk Landon Groninga , Daniel Bryan Robertson
Abstract: An unmanned aircraft system has a vertical takeoff and landing flight mode and a forward flight mode. The unmanned aircraft system includes an airframe, a rotor assembly rotatably coupled to the airframe and a propeller rotatably coupled to the airframe. The rotor assembly including at least two rotor blades having tip jets that are operably associated with a compressed gas power system. The propeller is operably associated with an electric power system. In the vertical takeoff and landing flight mode, compressed gas from the compressed gas power system is discharged through the tip jets to rotate the rotor assembly and generate vertical lift. In the forward flight mode, the electric power system drives the propeller to generate forward thrust and autorotation of the rotor assembly generates vertical lift.
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公开(公告)号：US10118687B1
公开(公告)日：2018-11-06
申请号：US16103770
申请日：2018-08-14
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga , Frank Bradley Stamps
Abstract: An inflight connection system for aircraft having at least one wing with a wingtip includes, for each aircraft, a primary connector selectively extendable from the wingtip, an alignment connector selectively extendable from the wingtip and a male and female connector assembly disposed proximate the wingtip. The primary connectors extend a greater distance from the wingtips than the alignment connectors such that the primary connectors form a first connection between the aircraft when the aircraft are flying in a connection pattern. Thereafter, retraction of the primary connectors reduces wingtip separation of the aircraft such that the alignment connectors form a second connection between the aircraft establishing coarse alignment therebetween. Thereafter, retraction of the primary and alignment connectors further reduces wingtip separation of the aircraft such that the male and female connector assemblies form a third connection between the aircraft establishing fine alignment therebetween.
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Patent Agency Ranking
公开(公告)号：US20180050792A1
公开(公告)日：2018-02-22
申请号：US15241436
申请日：2016-08-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga , Carlos Alexander Fenny
CPC classification number: B64C25/16 , B64C9/02 , B64C11/006 , B64C13/503 , B64C25/24 , B64C29/02
Abstract: A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. A main lifting surface is supported by the forward portion of the fuselage. A propulsion system is operably associated with the main lifting surface and operable to provide thrust during forward flight, vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of rotatably mounted tail arms having control surfaces and landing members wherein, in a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces and, wherein, in a landing configuration, the tail arms are radially extended relative to one another about the fuselage axis to form a stable ground contact base with the landing members.
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公开(公告)号：US20200339252A1
公开(公告)日：2020-10-29
申请号：US16398106
申请日：2019-04-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Daniel Bryan Robertson
IPC: B64C27/82
Abstract: According to one implementation of the present disclosure, a tail rotor system of a rotorcraft includes an electric motor, a swiveling actuator, a spindle, and a hub assembly. The hub assembly may be configured to position two or more blades. Also, in response to a control signal, the swiveling actuator may be configured to actuate swivel rotation of the spindle around a vertical axis such that the hub assembly turns from a first horizontal directional axis to a second horizontal directional axis.
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公开(公告)号：US10414492B2
公开(公告)日：2019-09-17
申请号：US15251128
申请日：2016-08-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga , 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. The tailboom assembly includes a plurality of landing members. In a vertical takeoff and landing mode of the aircraft, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode of the aircraft, the first rotor assembly rotates about the fuselage to provide forward thrust and the second rotor assembly is non-rotatable about the fuselage forming wings to provide lift.
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公开(公告)号：US20190031333A1
公开(公告)日：2019-01-31
申请号：US15662257
申请日：2017-07-27
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk Landon Groninga , Daniel Bryan Robertson
CPC classification number: B64C29/0033 , B64C39/008 , B64C39/08 , B64D27/24 , B64D2027/026
Abstract: An aircraft having a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes a fuselage and a dual tiltwing assembly having a vertical lift orientation and a forward thrust orientation relative to the fuselage. The dual tiltwing assembly includes a forward wing and an aft wing coupled together and to the fuselage by a quadrilateral linkage. A distributed propulsion system is coupled to the dual tiltwing assembly and includes a plurality of forward propulsion assemblies coupled to the forward wing and a plurality of aft propulsion assemblies coupled to the aft wing. A flight control system is operably associated with the distributed propulsion system and the dual tiltwing assembly. The flight control system is operable to independently control each of the propulsion assemblies and is operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation.
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公开(公告)号：US20180354615A1
公开(公告)日：2018-12-13
申请号：US15619765
申请日：2017-06-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk Landon Groninga , Daniel Bryan Robertson
CPC classification number: B64C29/0033 , B64C3/385 , B64C15/12 , B64C27/28 , B64C39/08 , B64D27/24 , B64D2027/026
Abstract: An aircraft having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes a fuselage and an X-tiltwing that is rotatable relative to the fuselage between a vertical lift orientation and a forward thrust orientation. The X-tiltwing has oppositely disposed V-wing members each having first and second wing sections. In the vertical lift orientation, the first and second wing sections of each V-wing member are generally in the same horizontal plane. In the forward thrust orientation, the first and second wing sections of each V-wing member are generally in the same vertical plane. A distributed propulsion system is attached to the X-tiltwing such that a plurality of propulsion assemblies is attached to each wing section. A flight control system is operably associated with the distributed propulsion system to independently control each of the propulsion assemblies.
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