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21.发明申请公开(公告)号：US20160159495A1
公开(公告)日：2016-06-09
申请号：US14562100
申请日：2014-12-05
Applicant: Gulfstream Aerospace Corporation
Inventor： Brian Cook , Michael Knight , John Louis , Thomas Van de Ven , Robert M. Vieito
CPC classification number: B64D47/02 , B64C25/001 , B64C25/10 , B64C25/50 , B64C2025/003 , B64D47/04
Abstract: Aircraft landing gear assemblies and aircraft are provided. A landing gear assembly includes a main post and a light element cluster. The main post has a non-rotating portion and a rotatable steering portion. The light element cluster is associated with the non-rotating portion and includes at least two independently illuminating sections.
Abstract translation: 提供飞机起落架组件和飞机。 起落架组件包括主柱和轻组件。 主柱具有非旋转部分和可旋转的转向部分。 光元件簇与非旋转部分相关联并且包括至少两个独立照明部分。
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22.发明申请公开(公告)号：US20150311841A1
公开(公告)日：2015-10-29
申请号：US14264751
申请日：2014-04-29
Applicant: Gulfstream Aerospace Corporation
Inventor： Gary Palfreyman , Michael Knight
IPC: H02P9/02
CPC classification number: H02P9/02
Abstract: A system is provided for engine and generator control. The system includes a compound AC generator, a generator control unit (GCU) module and an engine electronic controller (EEC) module. The compound AC generator includes a shaft, and a permanent magnet generator (PMG) configured to be driven by the shaft to generate an AC power signal. The GCU module is configured to control the compound AC generator. The PMG is coupled to the GCU module and the EEC module such that it is configured to simultaneously supply the AC power signal to the GCU module and to the EEC module.
Abstract translation: 提供一种用于发动机和发电机控制的系统。 该系统包括复合交流发电机，发电机控制单元（GCU）模块和发动机电子控制器（EEC）模块。 复合式交流发电机包括轴和永磁发电机（PMG），永磁发电机（PMG）构造成由轴驱动以产生交流电力信号。 GCU模块配置为控制复合式交流发电机。 PMG耦合到GCU模块和EEC模块，使得它被配置成同时将AC功率信号提供给GCU模块和EEC模块。
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23.发明申请SYSTEMS FOR AVOIDING A COLLISION BETWEEN AN AIRCRAFT ON A GROUND SURFACE AND AN OBSTACLE 审中-公开用于避免地面上的飞机与障碍物之间碰撞的系统公开(公告)号：US20150269847A1
公开(公告)日：2015-09-24
申请号：US14728735
申请日：2015-06-02
Applicant: Gulfstream Aerospace Corporation
Inventor： Michael Knight
CPC classification number: G08G5/04 , B64C25/44 , B64D47/08 , G01S7/24 , G01S7/51 , G01S7/56 , G01S13/08 , G01S13/93 , G01S13/931 , G01S15/08 , G01S15/93 , G01S17/08 , G01S17/93 , G01S17/933 , G01S2013/9335 , G01S2013/9346 , G01S2013/9364 , G01S2013/9367 , G05D1/0083 , G05D1/0202 , G05D1/0231 , G05D1/0255 , G05D1/0259 , G08G5/0021 , G08G5/065 , H04N7/181
Abstract: Systems and aircraft for avoiding a collision between an obstacle an aircraft on a ground surface are provided. In some embodiments, the aircraft includes a wing and a stabilizer and a collision avoidance system includes proximity sensors, video imagers, and a display. Proximity sensors are disposed on the wing and the stabilizer. The respective proximity sensors are configured to transmit first and second obstacle detection signals. A first video imager is disposed on the wing and a second video imager is disposed on a rear portion of the aircraft. The respective video imagers are configured to generate video signals associated with the wing and with the stabilizer. The display is configured to generate video images of the regions in response to detection of objects in the regions.
Abstract translation: 提供了用于避免在地面上的飞机的障碍物之间的碰撞的系统和飞机。 在一些实施例中，飞机包括机翼和稳定器，并且防撞系统包括接近传感器，视频成像器和显示器。 接近传感器设置在机翼和稳定器上。 相应的接近传感器被配置为发送第一和第二障碍物检测信号。 第一视频成像器设置在机翼上，第二视频成像器设置在飞机的后部。 相应的视频成像器被配置为产生与机翼和稳定器相关联的视频信号。 显示器被配置为响应于区域中的对象的检测而生成区域的视频图像。
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公开(公告)号：US20240263563A1
公开(公告)日：2024-08-08
申请号：US17248020
申请日：2021-01-05
Applicant: Gulfstream Aerospace Corporation
Inventor： Jeffrey Hausmann , Michael Knight
CPC classification number: F01D21/14 , F01D17/02 , B64D2045/0085 , B64F1/005 , F05D2260/85 , F05D2270/80
Abstract: The disclosed embodiments describe cover detection systems, controllers, and aircraft. The aircraft includes the controller and parts of the cover detection systems. A cover detection system includes an engine, a first sensor, a second sensor, an engine cover, and a controller. The engine has moving parts and defines a fluid opening. The fluid opening exposes the moving parts to an ambient environment. The first sensor component is located proximate to the engine and the second sensor component is configured to interact with the first sensor component. The engine cover assembly includes an engine cover and a second sensor. The engine cover is configured to cover the fluid opening. The controller is configured to determine whether the engine cover is installed on the engine based on an interaction between the first sensor component and the second sensor component.
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公开(公告)号：US20230399117A1
公开(公告)日：2023-12-14
申请号：US17806027
申请日：2022-06-08
Applicant: Gulfstream Aerospace Corporation
Inventor： Jeffrey Hausmann , Gary Freeman , Michael Knight , Ozan Ates , Kristin Medin , Jim Jordan , Scott Bohanan
Abstract: A throttle quadrant system for an aircraft includes: a first throttle handle to control a first engine of the aircraft, the first throttle handle having a first activatable visual indicator integrated therein; a second throttle handle to control a second engine of the aircraft, the second throttle handle comprising a second activatable visual indicator integrated therein; and at least one controller to control activation and operation of the first activatable visual indicator and the second activatable visual indicator. The at least one controller responds to first engine data related to operating status of the first engine to selectively activate the first activatable visual indicator. The at least one controller also responds to second engine data related to operating status of the second engine to selectively activate the second activatable visual indicator.
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Patent Agency Ranking
26.发明申请公开(公告)号：US20200156795A1
公开(公告)日：2020-05-21
申请号：US16195419
申请日：2018-11-19
Applicant: Gulfstream Aerospace Corporation
Inventor： Michael Knight
IPC: B64D11/06
Abstract: An aircraft seat assembly for supporting a seat occupant, and a method for fabricating an aircraft seat assembly for supporting a seat occupant are provided. In one non-limiting example, the aircraft seat assembly includes a seat structure and a seat cushion that is supported by the seat structure. A vibration mitigating apparatus is operatively coupled to the seat structure to prevent or reduce vibrations from transferring to the seat occupant.
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27.发明申请公开(公告)号：US20200155792A1
公开(公告)日：2020-05-21
申请号：US16197847
申请日：2018-11-21
Applicant: Gulfstream Aerospace Corporation
Inventor： Michael Knight
Abstract: An aircraft seat assembly for supporting a seat occupant, and a method for fabricating an aircraft seat assembly for supporting a seat occupant are provided. In one non-limiting example, the aircraft seat assembly includes a seat cushion supported by the seat structure. A vibration producing apparatus configured to produce vibrations conducive for inducing drowsiness. The vibration producing apparatus is disposed adjacent to or within the seat structure for transferring the vibrations to the seat occupant.
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公开(公告)号：US20190193838A1
公开(公告)日：2019-06-27
申请号：US16291527
申请日：2019-03-04
Applicant: Gulfstream Aerospace Corporation
Inventor： Michael Knight , James Grieco
Abstract: An aircraft, a control surface arrangement, and a method of assembling an aircraft are disclosed herein. In an exemplary embodiment, the aircraft includes, but is not limited to, an airframe, a control surface, and a rotary actuator. The rotary actuator rotatably mounts the control surface to the airframe. The rotary actuator supports the control surface on the airframe and is configured to rotate the control surface with respect to the airframe when the rotary actuator is actuated. The rotary actuator is further configured to deliver torque to the control surface from a longitudinally intermediate portion of the rotary actuator.
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公开(公告)号：US20180141678A1
公开(公告)日：2018-05-24
申请号：US15359987
申请日：2016-11-23
Applicant: Gulfstream Aerospace Corporation
Inventor： Charles Michaels , Michael Knight , Douglas Klutzke
CPC classification number: B64D47/08 , B64C1/14 , B64C25/10 , B64D11/0689 , B64D43/00 , H04N5/2252 , H04N5/2253 , H04N5/23203 , H04N5/23293 , H04N7/183
Abstract: Aircraft, vision sensor systems, and methods of operating deployable vision systems are provided. An aircraft includes a fuselage and a vision sensor system. The fuselage defines an outer mold line and the vision sensor system includes a housing and a vision sensor package. The housing is selectively deployable between a retracted position and a deployed position and is disposed within the outer mold line in the retracted position and outside of the outer mold line in the deployed position. The vision sensor package is associated with the housing and is positioned to collect imaging information when the housing is in the deployed position.
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公开(公告)号：US09878778B2
公开(公告)日：2018-01-30
申请号：US14459488
申请日：2014-08-14
Applicant: Gulfstream Aerospace Corporation
Inventor： Timothy Conners , Michael Knight , Robert Cowart
IPC: B64C13/16 , B64C9/04 , B64C23/04 , B64D31/06 , B64D33/02 , F02C9/28 , B64C30/00 , G01L19/00 , G01L19/14
CPC classification number: B64C23/04 , B64C13/16 , B64C30/00 , B64D31/06 , B64D33/02 , F02C9/28 , G01L19/0084 , G01L19/14
Abstract: A system for controlling a pressure field around an aircraft in flight is disclosed herein. In a non-limiting embodiment, the system includes, but is not limited to, a plurality of pressure sensors that are arranged on the aircraft to measure the pressure field. The system further includes, but is not limited to, a controller that is communicatively coupled with the plurality of pressure sensors. The controller is configured to receive information that is indicative of the pressure field from the plurality of pressure sensors. The controller is also configured to determine when the pressure field deviates from a desired pressure field based on the information. The controller is also configured to transmit an instruction to a movable component onboard the aircraft that will cause the movable component to move in a manner that reduces the deviation.
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