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公开(公告)号：US20220250755A1
公开(公告)日：2022-08-11
申请号：US17173989
申请日：2021-02-11
发明人： Michael Raymond Hull , Steven Loveland , Yue Fan
IPC分类号： B64D27/24 , B60L50/60 , B64D31/06 , B60L58/10 , B60L50/70 , B60L50/10 , B64C29/00 , B60L53/50
摘要： A configurable electrical architecture for an eVTOL aircraft having a takeoff and landing power mode and a cruise power mode. The configurable electrical architecture includes a power-optimized power source including a high-power battery array and an energy-optimized power source selected from a plurality of interchangeable energy-optimized power sources including a high-energy battery array, a hydrogen fuel cell system and a turbo-generator system. A distribution system is electrically coupled to the power-optimized power source and the energy-optimized power source. At least one electric motor is electrically coupled to the distribution system. In the takeoff and landing power mode, both the power-optimized power source and the energy-optimized power source provide electrical power to the at least one electric motor. In the cruise power mode, the energy-optimized power source provides electrical power to the at least one electric motor and to the power-optimized power source to recharge the high-power battery array.
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公开(公告)号：US20220222346A1
公开(公告)日：2022-07-14
申请号：US17584248
申请日：2022-01-25
发明人： Michael Kevin McNair
摘要： A decentralized trust assessment system, comprising a neural network, a trust module, and a local subsystem, wherein the trust module controls whether a plurality of inputs to the local subsystem are trustworthy. The decentralized trust assessment system provides rotorcraft and tiltrotor aircraft with airborne systems able to detect bad and spoofed data from a wide variety of data streams.
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公开(公告)号：US11319056B2
公开(公告)日：2022-05-03
申请号：US16788888
申请日：2020-02-12
发明人： Jeffrey Matthew Williams , George Ryan Decker , Michael Edwin Rinehart , Andrew G. Baines , James Elbert King
摘要： A propulsion and lift system of a tiltrotor aircraft includes a wing having an outboard end, a wing tip assembly having an inboard end, a fixed nacelle coupled to the wing tip assembly and a wing-nacelle splice assembly having inboard and outboard sides. The inboard side of the wing-nacelle splice assembly is coupled to the outboard end of the wing, and the outboard side of the wing-nacelle splice assembly is coupled to the inboard end of the wing tip assembly, thereby coupling the fixed nacelle to the wing.
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公开(公告)号：US11319055B2
公开(公告)日：2022-05-03
申请号：US16558071
申请日：2019-08-31
摘要： A compliant tail structure for a rotorcraft having rotating components and a fuselage. The tail structure includes a tail assembly having first and second oppositely disposed tail members. A tail joint connects the tail assembly to an aft portion of the fuselage. The tail joint includes at least four tail mounts configured to establish a nodding axis for the tail assembly. At least two of the tail mounts are resilient tail mounts that are configured to establish a nodding degree of freedom for the tail assembly relative to the fuselage about the nodding axis, thereby detuning dynamic fuselage responses from excitation frequencies generated by the rotating components.
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公开(公告)号：US11312487B2
公开(公告)日：2022-04-26
申请号：US16840292
申请日：2020-04-03
IPC分类号： B64C29/02 , B64C29/00 , B64C11/28 , B64D35/00 , B64C27/50 , B64C39/02 , B64C39/06 , B64D1/08 , B64D25/12
摘要： An aircraft has an airframe with first and second wings having first and second pylons extending therebetween. A distributed propulsion system attached to the airframe includes at least first, second, third and fourth propulsion assemblies that are independently controlled by a flight control system. A pod assembly is coupled to the airframe. In a VTOL flight mode, the first and second propulsion assemblies are forward of the pod assembly and the third and fourth propulsion assemblies are aft of the pod assembly. In a forward flight mode, the first and second propulsion assemblies are below the pod assembly and the third and fourth propulsion assemblies are above the pod assembly. In both the VTOL and forward flight modes, the first and fourth propulsion assemblies generate thrust having a first direction while the second and third propulsion assemblies generate thrust having a second direction that is different from the first direction.
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公开(公告)号：US11312482B2
公开(公告)日：2022-04-26
申请号：US16449373
申请日：2019-06-22
发明人： Bruce Bennett Bacon
摘要： A component alignment system for an aircraft includes a first component having a first surface including first shaped projections that repeat in at least two directions along the first surface. The component alignment system also includes a second component having a second surface including second shaped projections that repeat in at least two directions along the second surface. The first shaped projections are complementary to the second shaped projections such that the first surface is translationally and rotationally constrained relative to the second surface when the first and second shaped projections are in an interlocked position.
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公开(公告)号：US11279479B2
公开(公告)日：2022-03-22
申请号：US16833638
申请日：2020-03-29
IPC分类号： B64C29/00 , B64D27/16 , B64C11/48 , B64D35/06 , B64C11/00 , B64D35/02 , B64C27/22 , B64D33/04 , B64D35/04 , B64C3/10 , B64C19/00 , B64C27/26 , B64C27/30 , B64C9/20 , B64C21/08 , B64C27/78 , B64C21/04 , B64C39/10 , B64C9/18 , B64C15/02 , B64C15/14 , B64C21/00
摘要： An active flow control system for generating yaw control moments for an aircraft during hover flight. The system includes right and left yaw effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.
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公开(公告)号：US11279476B2
公开(公告)日：2022-03-22
申请号：US17102552
申请日：2020-11-24
发明人： Kyle Thomas Cravener
IPC分类号： B64C27/32
摘要： A passive hub flapping lock including: one or more lever arms, each lever arm rotatably coupled to a pivot and comprising a first lever arm end and a second lever arm end; one or more stop wedges; one or more frames coupled to the one or more stop wedges, each frame coupled to the first lever arm end of one of the one or more lever arms; one or more weight sets, each weight set comprising one or more weights coupled to the second lever arm end of one of the one or more lever arms; and one or more pivot torsion springs, each pivot torsion spring positioned at the pivot.
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公开(公告)号：US20220073198A1
公开(公告)日：2022-03-10
申请号：US17245010
申请日：2021-04-30
IPC分类号： B64C29/00
摘要： One example of a tiltrotor aircraft includes a rotor system, a pylon coupled to the rotor system, a spindle coupled to the pylon, an actuator arm coupled to the spindle, and an actuator. The actuator can cause the actuator arm to rotate, thereby causing the spindle to rotate the pylon and the rotor system. In an example, the actuator is in front of a forward spar of the wing of the tiltrotor aircraft and the actuator arm is about one-half (0.5) of an inch to about five (5) inches from the wing.
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公开(公告)号：US11260982B2
公开(公告)日：2022-03-01
申请号：US16297179
申请日：2019-03-08
发明人： Michael R. Smith , Cheng-Ho Tho
摘要： An apparatus comprising a float bag comprising an air bladder configured to inflate when an aircraft lands in the water, a girt coupled to the air bladder and configured to attach the air bladder to the aircraft via at least one airframe fitting, and a load attenuator coupled to the girt and configured to be positioned between the girt and the airframe fitting when the float bag is attached to the aircraft, wherein the plurality of load attenuators are configured to mechanically deform in a progressive failure fashion from a first effective length to a second effective length greater than the first length in response to an applied tensile load on the load attenuators coupled to the plurality of girts and the aircraft airframe, wherein the load attenuators are selected to reduce the force with a total length that minimizes buoyancy depth of the aircraft.
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