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公开(公告)号：US10718810B2
公开(公告)日：2020-07-21
申请号：US15736608
申请日：2016-06-10
IPC分类号： G01R31/315 , G01R31/28 , G01R31/42 , G01R33/022
摘要： A Transistor Resonant Characteristic Sensor (TReCS) includes a sensing element positioned along electronic equipment so that the sensing element is electromagnetically coupled to the electronic equipment. The sensing element includes a coil. The sensing element is configured to detect magnetic oscillations associated with a characteristic signal generated by the electronic equipment. The TReCS sensor further includes an evaluation circuit connected to the sensing element for monitoring health state of the electronic equipment. The evaluation circuit includes one or more processing elements configured to diagnose health state of the electronic equipment based on extracted baseband information associated with the characteristic signal.
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公开(公告)号：US10703472B2
公开(公告)日：2020-07-07
申请号：US15534393
申请日：2015-11-23
发明人： Mark W. Scott
摘要： A rotary winged aircraft includes an airframe and a drive system located at the airframe. A main rotor system is positioned at the airframe and is operably connected to the drive system to provide lift for the rotary winged aircraft. An auxiliary propulsor is located at the airframe and includes a plurality of propeller blades rotatable about a propulsor axis. Collective and cyclic pitch input applied to the auxiliary propeller blades increases yaw performance of the aircraft. A method of operating a rotary wing aircraft includes powering an auxiliary propulsor secured to an airframe of the aircraft and including a plurality of propeller blades rotatable about a propulsor axis. Individual propeller blades are cyclically rotated about their respective propeller blade axes to cyclically change a propeller blade pitch. Rotation of the aircraft about a yaw axis is induced via the collective and cyclic pitch change of the propeller blades.
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公开(公告)号：US10703468B2
公开(公告)日：2020-07-07
申请号：US15756777
申请日：2016-09-13
发明人： Krzysztof Kopanski , Justin Thomas
IPC分类号： B64C27/473
摘要： A blade includes a blade body having a surface and a hole extending through the surface of the blade body. The hole defines a hole axis and a plane perpendicular to the hole axis. The hole has an elongated hole perimeter within the plane. The hole perimeter includes a plurality of non-linear perimeter sections to minimize stress concentration around the elongated hole perimeter while maximizing the usable opening area. A rotor system includes a rotor hub and a blade as recited above. The blade extends radially outward from the rotor hub. The blade defines a root end proximate to the rotor hub, a tip end opposite the root end.
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公开(公告)号：US10689098B2
公开(公告)日：2020-06-23
申请号：US15580204
申请日：2016-06-24
发明人： Peter James Waltner
摘要： An adaptive landing gear assembly for a rotary wing aircraft, the adaptive landing gear assembly including a controller; a first landing gear support having a first ground contact element; and a second landing gear support having a second ground contact element; the controller independently controlling the first landing gear support and the second landing gear support.
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公开(公告)号：US10683106B2
公开(公告)日：2020-06-16
申请号：US15927777
申请日：2018-03-21
摘要： In accordance with at least one aspect of this disclosure, a structure can include a body, and one or more thermal sheet sensors disposed on or within the body. The one or more thermal sheet sensors can be configured to receive heat from the body to allow sensing of thermal flux through the body to monitor and/or determine a condition of the structure.
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公开(公告)号：US10676213B2
公开(公告)日：2020-06-09
申请号：US15519999
申请日：2015-10-16
发明人： Xuchu Ding , Jason C. Derenick , Brendan J. Englot , Igor Cherepinsky , Harshad S. Sane , Christopher Stathis
摘要： According to an aspect of the invention, a method of optimal safe landing area determination for an aircraft includes accessing a probabilistic safe landing area map that includes a plurality of probabilistic indicators of safe landing areas for the aircraft. A processing subsystem that includes one or more processing resources generates a list of candidate safe landing areas based on the probabilistic safe landing area map and one or more constraints. At least two of the candidate safe landing areas are provided to a path planner. The list of candidate safe landing areas is ranked based on results from the path planner indicating an estimated cost to reach each of the candidate safe landing areas. Based on the ranking, an indicator of an optimal safe landing area is output as a desired landing location for the aircraft.
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公开(公告)号：US10676193B2
公开(公告)日：2020-06-09
申请号：US15566282
申请日：2016-04-01
摘要： According to an aspect, a system in an aircraft includes a vehicle management system (VMS) and a load control system (LCS). The LCS includes an LCS processor operable to receive and transmit a plurality of data and load management commands to one or more of: the VMS and a load control interface. The LCS processor is further operable to interact with one or more of: the VMS, one or more LCS sensors, and a load capturing interface of the aircraft to execute the load management commands as a sequence of one or more load management subcommands. The load capturing interface is operable to capture and release an external load relative to the aircraft using a load capture device. The LCS processor is also operable to report a status of execution of the load management commands to the VMS and the load control interface.
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公开(公告)号：US10676181B2
公开(公告)日：2020-06-09
申请号：US15507178
申请日：2015-09-25
IPC分类号： B64C27/10 , B64C27/00 , B64D35/06 , F16F15/02 , B64C27/14 , B64C1/00 , B64C7/00 , B64C13/18 , B64C13/50 , B64C19/00 , B64C27/12 , B64C27/16 , B64C27/32 , B64C27/33 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/78 , B64C27/80 , B64C27/82 , B64D39/00 , B64D39/06 , B64D45/02 , F16H37/02 , G05D1/00 , G05D1/02 , B64C13/04 , G05D1/08 , B64C27/57 , B64C27/467 , B64C27/08 , F02C9/28 , F16D13/52 , F16D13/72 , F16D13/74
摘要： An aircraft is provided including an airframe, an extending tail, a counter-rotating, coaxial main rotor assembly having an upper rotor assembly and a lower rotor assembly, and a translational thrust system including a propeller positioned at the extending tail. The translational thrust system is configured to provide translational thrust to the airframe when the aircraft is in a non-autorotation state and to generate power when in an autorotation state. A gearbox interconnects the propeller and the main rotor assembly to drive the main rotor assembly and the translational thrust system in the non-autorotation state. When the aircraft is in autorotation, the power generated by the propeller drives rotation of the main rotor assembly via the gearbox.
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39.发明授权公开(公告)号：US10674080B2
公开(公告)日：2020-06-02
申请号：US15651567
申请日：2017-07-17
发明人： Carl A. Palmer , Ronald Moffatt , Cody M. Ture , Craig D. Reed
IPC分类号： H04N5/225 , H04N5/232 , H04N5/247 , G03B15/03 , B64D47/08 , B64F5/60 , G03B17/02 , G03B17/38 , G03B15/00 , B64C27/06 , G03B15/05
摘要： An integrated inspection system including at least one surface defining an enclosed space, at least one camera mounted in the enclosed space, and an interrogator device operatively coupled to the at least one camera. The interrogator device provides power to and receives images from the camera.
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公开(公告)号：US10648340B2
公开(公告)日：2020-05-12
申请号：US14915162
申请日：2014-08-07
发明人： David A. Darrow, Jr.
IPC分类号： F01D5/14 , B29D99/00 , B29C70/20 , B29C70/30 , B29K105/10 , B29K307/04 , B29L31/08 , B29K63/00 , B29K105/00
摘要： A composite spar having an upper and lower wall region connected by leading and trailing edge regions is provided including a plurality of first laminates and a plurality of second laminates. The plurality of first laminates includes one or more intermediate modulus graphite plies having an intermediate modulus. The plurality of first laminates is arranged in one or more intermediate modulus layers to form at least a portion of the upper wall region, lower wall region, leading edge region and trailing edge region. The plurality of second laminates includes one or more high modulus graphite plies having a high modulus. The plurality of second laminates is arranged in one or more high modulus layers. The high modulus layers are generally interposed between intermediate modulus layers.
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