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公开(公告)号：US10906520B2
公开(公告)日：2021-02-02
申请号：US16041687
申请日：2018-07-20
IPC分类号： B60V3/08 , B64C27/08 , B64B1/62 , B64D9/00 , B64C39/04 , B64C3/30 , B64C1/34 , B64C39/02 , B64C37/00
摘要： Systems and methods include providing vertical takeoff and landing (VTOL) aircraft with a cargo pod having a selectively inflatable bladder system that firmly secures a payload disposed within the cargo pod when the bladder system is pressurized. The bladder system also controls the location, position, and/or orientation of the payload in order to adjust, control, and/or maintain the center of gravity of the aircraft during flight. The aircraft includes an impact protection system that further pressurizes the bladder system to protect the payload and/or that disperses a flame-retardant fluid into the cargo pod to protect electrical components of the aircraft. The aircraft is fully autonomous and self-directed via a preprogrammed location-based guidance system to allow for accurate delivery of the payload to its intended destination. The bladder system is depressurized in response to a landing event to allow for e f the payload from the cargo pod.
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公开(公告)号：US20200023829A1
公开(公告)日：2020-01-23
申请号：US16041687
申请日：2018-07-20
摘要： Systems and methods include providing vertical takeoff and landing (VTOL) aircraft with a cargo pod having a selectively inflatable bladder system that firmly secures a payload disposed within the cargo pod when the bladder system is pressurized. The bladder system also controls the location, position, and/or orientation of the payload in order to adjust, control, and/or maintain the center of gravity of the aircraft during flight. The aircraft includes an impact protection system that further pressurizes the bladder system to protect the payload and/or that disperses a flame-retardant fluid into the cargo pod to protect electrical components of the aircraft. The aircraft is fully autonomous and self-directed via a preprogrammed location-based guidance system to allow for accurate delivery of the payload to its intended destination. The bladder system is depressurized in response to a landing event to allow for e f the payload from the cargo pod.
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公开(公告)号：US10322799B2
公开(公告)日：2019-06-18
申请号：US16001925
申请日：2018-06-06
IPC分类号： B64D1/10 , B64D1/22 , G08G5/00 , G08G5/02 , B64C11/28 , B64C25/04 , B64C25/10 , B64C27/30 , B64C29/02 , B64C37/00 , B64C39/02 , B64C39/04 , B64D17/02 , B64D17/80
摘要： 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：US10220944B2
公开(公告)日：2019-03-05
申请号：US15200197
申请日：2016-07-01
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：US20190039718A1
公开(公告)日：2019-02-07
申请号：US15667499
申请日：2017-08-02
CPC分类号： B64C3/26 , B64C3/18 , B64C3/187 , B64C3/34 , B64C29/0033
摘要： A wing airframe for a wing of a tiltrotor aircraft includes a wing airframe core assembly and a wing skin assembly disposed on the wing airframe core assembly. The wing skin assembly includes a lower wing skin assembly disposed on the bottom side of the wing airframe core assembly. The tiltrotor aircraft includes a fuselage underneath the wing. The lower wing skin assembly has one or more buckle zones outboard of the fuselage. The buckle zones are locally susceptible to buckling in response to an impact of the tiltrotor aircraft, thereby protecting the fuselage from being crushed by the wing.
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公开(公告)号：US20190031361A1
公开(公告)日：2019-01-31
申请号：US16154326
申请日：2018-10-08
IPC分类号： B64D31/06 , B64D31/14 , B64C27/57 , B64C29/02 , B64C29/00 , B64C27/52 , B64C39/02 , B64D27/24 , B64D27/26 , G05D1/00 , B64C11/46
摘要： A propulsion assembly for an aircraft includes a nacelle having a rapid connection interface, at least one battery disposed within the nacelle, a speed controller coupled to the battery and a propulsion system coupled to the speed controller and the battery. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that are rotatable with the output drive of the electric motor in a rotational plane to generate thrust. The electric motor is operable to rotate responsive to power from the battery at a speed responsive to the speed controller. The rapid connection interface of the nacelle is couplable to a rapid connection interface of an airframe nacelle station to provide structural and electrical connections therebetween that are operable for rapid in-situ assembly.
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公开(公告)号：US20190031331A1
公开(公告)日：2019-01-31
申请号：US16154359
申请日：2018-10-08
IPC分类号： B64C27/57 , B64C29/02 , B64C29/00 , B64C27/52 , B64C39/02 , B64D27/24 , B64D27/26 , B64D31/06 , G05D1/00 , B64C11/46
摘要： An aircraft includes an airframe having first and second wings with first and second pylons extending therebetween and having a two-dimensional distributed thrust array of outboard propulsion assemblies attached thereto. A flight control system is coupled to the airframe and is operable to independently control a rotor speed and a thrust vector of each propulsion assembly. In a low thrust to weight configuration, transitions from the VTOL orientation to the biplane orientation include establishing a pitch down flight attitude while engaging in collective thrust vectoring of the outboard propulsion assemblies to maintain hover stability followed collectively reducing the thrust vector angles to initiate forward flight. In a high thrust to weight configuration, transitions from the VTOL orientation to the biplane orientation include maintaining a level flight attitude while collectively increasing the thrust vector angles of the outboard propulsion assemblies to initiate forward flight.
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公开(公告)号：US20180339772A1
公开(公告)日：2018-11-29
申请号：US15606197
申请日：2017-05-26
CPC分类号： B64C29/0033 , B64C25/04 , B64C25/36 , B64C39/04 , B64C39/08
摘要： An aircraft having omnidirectional ground maneuver capabilities. The aircraft includes an airframe and a plurality of propulsion assemblies attached to the airframe. Each of the propulsion assemblies includes a nacelle having a mast axis, a rotor assembly having a tilting degree of freedom relative to the mast axis and a tail assembly rotatable about the mast axis. The tail assembly includes at least one wheel having a rotational axis. A flight control system is operable to independently control each of the propulsion assemblies including tilting each rotor assembly and rotating each tail assembly. For each propulsion assembly, the rotor assembly and the tail assembly have complementary configurations in which a thrust vector generated by the rotor assembly has a horizontal component that is generally perpendicular to the rotational axis of the wheel, thereby enabling omnidirectional ground maneuvers.
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公开(公告)号：US20180339771A1
公开(公告)日：2018-11-29
申请号：US15606163
申请日：2017-05-26
CPC分类号： B64C5/02 , B64C3/10 , B64C11/46 , B64C29/0033 , B64C29/02 , B64C2201/088 , B64C2201/108
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：US20180297712A1
公开(公告)日：2018-10-18
申请号：US15972431
申请日：2018-05-07
摘要： An aircraft has an airframe with a two-dimensional distributed thrust array attached thereto having a plurality of propulsion assemblies that are independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto that is operable to tilt about first and second axes responsive to first and second actuators. 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. Responsive to a thrust vector error of a first propulsion assembly, the flight control system commands at least a second propulsion assembly, that is symmetrically disposed relative to the first propulsion assembly, to counteract the thrust vector error, thereby providing redundant directional control for the aircraft.
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