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公开(公告)号：US10442522B2
公开(公告)日：2019-10-15
申请号：US15606163
申请日：2017-05-26
摘要： An aircraft operable to transition between a forward flight mode and a vertical takeoff and landing flight mode. The aircraft includes an airframe having first and second wings. A plurality of propulsion assemblies is attached to the airframe with each of the propulsion assemblies including a nacelle and a tail assembly having at least one active aerosurface. A flight control system is operable to independently control each of the propulsion assemblies. For each of the propulsion assemblies, the tail assembly is rotatable relative to the nacelle such that the active aerosurface has a first orientation generally parallel to the wings and a second orientation generally perpendicular to the wings.
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公开(公告)号：US20190276145A1
公开(公告)日：2019-09-12
申请号：US16421371
申请日：2019-05-23
IPC分类号： B64C27/605 , B64C29/00 , B64C27/54
摘要： A rotor assembly for an aircraft operable to generate a variable thrust output at a constant rotational speed. The rotor assembly includes a mast rotatable at the constant speed about a mast axis. A rotor hub is coupled to and rotatable with the mast. The rotor hub includes a plurality of spindle grips extending generally radially outwardly. Each of the spindle grips is coupled to one of a plurality of rotor blades and is operable to rotate therewith about a pitch change axis. A collective pitch control mechanism is coupled to and rotatable with the rotor hub. The collective pitch control mechanism is operably associated with each spindle grip such that actuation of the collective pitch control mechanism rotates each spindle grip about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating the variable thrust output.
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公开(公告)号：US20190031339A1
公开(公告)日：2019-01-31
申请号：US16154342
申请日：2018-10-08
摘要： An 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. The first and second wings each having first and second outboard nacelle stations. A two-dimensional distributed thrust array is attached to the airframe. The thrust array including a plurality of outboard propulsion assemblies coupled to the first and second outboard nacelle stations of the first and second wings. A flight control system is coupled to the airframe and is operable to independently control each of the propulsion assemblies. A cargo hook module is coupled to the airframe. The cargo hook module is operable for external load operations.
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公开(公告)号：US20180339773A1
公开(公告)日：2018-11-29
申请号：US15606275
申请日：2017-05-26
摘要： A rotor assembly for an aircraft is operable to generate a variable thrust vector. The rotor assembly includes a mast that is rotatable about a mast axis. A ball joint is positioned about and non rotatable with the mast. A tilt control assembly is positioned on and has a tilting degree of freedom relative to the ball joint. The tilt control assembly is non rotatable with the mast. A rotor hub is rotatably coupled to the tilt control assembly. The rotor hub is rotatable with the mast in a rotational plane and tiltable with the tilt control assembly. The rotor hub includes a plurality of grips each coupled to a rotor blade. Actuation of the tilt control assembly changes the rotational plane of the rotor hub relative to the mast axis, thereby generating the variable thrust vector.
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公开(公告)号：US20180339769A1
公开(公告)日：2018-11-29
申请号：US15606257
申请日：2017-05-26
CPC分类号： B64C27/605 , B64C27/54 , B64C29/0016 , B64C29/0033 , B64C2201/086 , B64C2201/108
摘要： A rotor assembly for an aircraft operable to generate a variable thrust output at a constant rotational speed. The rotor assembly includes a mast rotatable at the constant speed about a mast axis. A rotor hub is coupled to and rotatable with the mast. The rotor hub includes a plurality of spindle grips extending generally radially outwardly. Each of the spindle grips is coupled to one of a plurality of rotor blades and is operable to rotate therewith about a pitch change axis. A collective pitch control mechanism is coupled to and rotatable with the rotor hub. The collective pitch control mechanism is operably associated with each spindle grip such that actuation of the collective pitch control mechanism rotates each spindle grip about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating the variable thrust output.
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公开(公告)号：US20180339761A1
公开(公告)日：2018-11-29
申请号：US15606213
申请日：2017-05-26
CPC分类号： B64C29/0033 , B64C3/10 , B64C3/32 , B64C5/10 , B64C11/46 , B64C2201/108
摘要： 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：US20180257761A1
公开(公告)日：2018-09-13
申请号：US15972461
申请日：2018-05-07
CPC分类号： B64C11/32 , B64C11/46 , B64C15/12 , B64C29/02 , B64C39/024 , B64C2201/042 , B64C2201/104 , B64C2201/108 , B64D27/24 , B64D31/06
摘要： An aircraft has an airframe with a distributed thrust array attached thereto that includes a plurality of propulsion assemblies each of which is independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto and operable to tilt about a single axis. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that rotate in a rotational plane to generate thrust having a thrust vector with a magnitude in the longitudinal direction. Actuation of each gimbal is operable to tilt the respective propulsion system relative to the airframe in the longitudinal direction to change the rotational plane of the respective rotor assembly relative to the airframe, thereby controlling the magnitude of the respective thrust vector in the longitudinal direction.
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公开(公告)号：US20180002027A1
公开(公告)日：2018-01-04
申请号：US15200273
申请日：2016-07-01
摘要： 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：US20180002013A1
公开(公告)日：2018-01-04
申请号：US15200197
申请日：2016-07-01
CPC分类号： B64C29/02 , B64C39/024 , B64D1/08 , B64D17/02 , G05D1/0011
摘要： In some embodiment, an aircraft includes an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system. A pod assembly is selectively attachable to the flying frame. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flying frame has a manned flight mode and an unmanned flight mode.
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公开(公告)号：US20180002012A1
公开(公告)日：2018-01-04
申请号：US15200182
申请日：2016-07-01
CPC分类号： B64C29/0033 , B64C11/28 , B64C11/46 , B64C25/10
摘要： In some embodiments, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, a flight control system operably associated with the distributed propulsion system and a pod assembly selectively attachable to the flying frame. The distributed propulsion system includes a plurality of propulsion assemblies that are independently controlled by the flight control system, thereby enabling the flying frame to have a vertical takeoff and landing mode and a forward flight mode.
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