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    Engine inlet cover detection system and method
    1.
    发明授权
    Engine inlet cover detection system and method 有权

    公开(公告)号：US12180851B2

    公开(公告)日：2024-12-31

    申请号：US17248020

    申请日：2021-01-05

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Jeffrey Hausmann ,  Michael Knight

    IPC: F01D21/14 ,  F01D17/02 ,  B64D45/00 ,  B64F1/00

    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.

    Aircraft, control surface arrangements, and methods of assembling an aircraft
    2.
    发明授权
    Aircraft, control surface arrangements, and methods of assembling an aircraft 有权

    公开(公告)号：US11077934B2

    公开(公告)日：2021-08-03

    申请号：US16291527

    申请日：2019-03-04

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Michael Knight ,  James Grieco

    IPC: B64C13/38 ,  B64C9/02 ,  B64C13/24

    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.

    INTEGRATED POWER DISTRIBUTION, DATA NETWORK, AND CONTROL ARCHITECTURES FOR A VEHICLE
    4.
    发明申请
    INTEGRATED POWER DISTRIBUTION, DATA NETWORK, AND CONTROL ARCHITECTURES FOR A VEHICLE 审中-公开

    公开(公告)号：US20170101067A1

    公开(公告)日：2017-04-13

    申请号：US14878904

    申请日：2015-10-08

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Pedro R. Carleial ,  Michael Knight

    IPC: B60R16/03 ,  B60R16/023

    CPC classification number: B60R16/03 ,  B60R16/023 ,  H02J3/00 ,  H02J4/00 ,  H02J13/00

    Abstract: An integrated power distribution, data network, and control architecture for a vehicle is provided that includes nodes distributed throughout the vehicle. Each node includes power distribution (PD) and data collection and distribution (DCD) components. The PD components receive electrical power from a source external to the node and distribute and control the electrical power supplied to active and passive electrical loads that are external to the node. The PD components include an electrical power input interface configured to receive an electrical power input from a source external to the node, and one or more power control modules. Each power control module can control the electrical power supplied to one or more electrical power output interfaces that supply power to the active and passive electrical loads. The DCD components receive data from data sources external to the node and transmit data to data consumers external to the node.

    SYSTEM AND METHOD FOR CONTROLLING A PRESSURE FIELD AROUND AN AIRCRAFT IN FLIGHT
    5.
    发明申请
    SYSTEM AND METHOD FOR CONTROLLING A PRESSURE FIELD AROUND AN AIRCRAFT IN FLIGHT 有权
    用于控制航空器中的压力场的系统和方法

    公开(公告)号：US20160257397A1

    公开(公告)日：2016-09-08

    申请号：US14459488

    申请日：2014-08-14

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Timothy Conners ,  Michael Knight ,  Robert Cowart

    IPC: B64C23/04 ,  G01L19/14 ,  G01L19/00 ,  B64C30/00 ,  B64C13/16

    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.

    Abstract translation: 本文公开了一种用于控制飞行中飞行器周围的压力场的系统。 在非限制性实施例中，系统包括但不限于布置在飞机上以测量压力场的多个压力传感器。 该系统还包括但不限于与多个压力传感器通信耦合的控制器。 控制器被配置为从多个压力传感器接收指示压力场的信息。 控制器还被配置为基于该信息来确定压力场何时偏离期望的压力场。 控制器还被配置为向飞行器上的可移动部件发送指令，该指令将使得可移动部件以减小偏差的方式移动。

    Aircraft, control surface arrangements, and methods of assembling an aircraft
    7.
    发明授权
    Aircraft, control surface arrangements, and methods of assembling an aircraft 有权

    公开(公告)号：US10220938B2

    公开(公告)日：2019-03-05

    申请号：US14567771

    申请日：2014-12-11

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Michael Knight ,  James Grieco

    IPC: B64C13/38 ,  B64C9/02 ,  B64C13/24 ,  B64C13/40

    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.

    Integrated power distribution, data network, and control architectures for a vehicle
    8.
    发明授权
    Integrated power distribution, data network, and control architectures for a vehicle 有权

    公开(公告)号：US10065583B2

    公开(公告)日：2018-09-04

    申请号：US14878904

    申请日：2015-10-08

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Pedro R. Carleial ,  Michael Knight

    IPC: B60L1/00 ,  B60L3/00 ,  H02G3/00 ,  B60R16/03 ,  B60R16/023

    Abstract: An integrated power distribution, data network, and control architecture for a vehicle is provided that includes nodes distributed throughout the vehicle. Each node includes power distribution (PD) and data collection and distribution (DCD) components. The PD components receive electrical power from a source external to the node and distribute and control the electrical power supplied to active and passive electrical loads that are external to the node. The PD components include an electrical power input interface configured to receive an electrical power input from a source external to the node, and one or more power control modules. Each power control module can control the electrical power supplied to one or more electrical power output interfaces that supply power to the active and passive electrical loads. The DCD components receive data from data sources external to the node and transmit data to data consumers external to the node.

    SYSTEM FOR CONTROLLING A WHEEL BRAKE OF AN AIRCRAFT
    9.
    发明申请
    SYSTEM FOR CONTROLLING A WHEEL BRAKE OF AN AIRCRAFT 审中-公开

    公开(公告)号：US20180215356A1

    公开(公告)日：2018-08-02

    申请号：US15419845

    申请日：2017-01-30

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Michael Knight ,  Timothy Burns

    IPC: B60T8/17 ,  B60T8/1761 ,  B60T8/34 ,  B60T8/50 ,  B64C25/46

    CPC classification number: B60T8/1703 ,  B60T8/1761 ,  B60T8/325 ,  B60T8/341 ,  B60T8/50 ,  B64C25/46

    Abstract: A system is provided having a normal operational mode and a modulated operational mode. The system includes an input device configured to generate a command signal. The system further includes a brake controller configured to generate a brake actuation signal in response to the command signal. The system further includes a fluid source configured to provide fluid in response to the brake actuation signal. The fluid has a first portion and a second portion. The system further includes a return valve in fluid communication with the fluid source, and configured to return the first portion of the fluid to the fluid source when the system is in the modulated operational mode. The system further includes a wheel brake in fluid communication with the fluid source and configured to engage a wheel of the aircraft in response to at least the second portion of the fluid.

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