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    Supersonic aircraft with spike for controlling and reducing sonic boom
    91.
    发明授权
    Supersonic aircraft with spike for controlling and reducing sonic boom 有权

    公开(公告)号：US09714084B2

    公开(公告)日：2017-07-25

    申请号：US14074913

    申请日：2013-11-08

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Preston A. Henne ,  Donald C. Howe

    IPC: B64C30/00 ,  B64C23/04

    CPC classification number: B64C23/04 ,  B64C30/00

    Abstract: Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when the vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region there between and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle.

    INTEGRATED POWER DISTRIBUTION, DATA NETWORK, AND CONTROL ARCHITECTURES FOR A VEHICLE
    94.
    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.

    AIRCRAFT AND EXTERIOR SPEAKER SYSTEMS FOR AIRCRAFT
    96.
    发明申请
    AIRCRAFT AND EXTERIOR SPEAKER SYSTEMS FOR AIRCRAFT 有权
    用于飞机的飞机和外部扬声器系统

    公开(公告)号：US20160318627A1

    公开(公告)日：2016-11-03

    申请号：US14697895

    申请日：2015-04-28

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Michael Lucas ,  Michael Brinley ,  Kristopher Lynch

    IPC: B64D47/02 ,  B64D45/00 ,  B64C1/12

    CPC classification number: B64D47/02 ,  B64D45/00 ,  B64D2045/0095 ,  G10K9/20 ,  G10K2210/1281 ,  H04R7/045

    Abstract: Aircraft, aircraft exterior speaker systems, and methods of projecting sound waves from an exterior of an aircraft are provided. An aircraft includes an outer skin membrane, a vibration actuator, and a controller. The outer skin membrane has an exterior surface that defines an exterior boundary of the aircraft. The vibration actuator is coupled for common vibration with the outer skin membrane. The controller is operatively coupled with the vibration actuator and is configured to generate a command for the vibration actuator based on audible content to be projected from the exterior surface. The controller is further configured to transmit the command to the vibration actuator. The vibration actuator is configured to vibrate in response to receiving the command.

    Abstract translation: 提供飞机，飞机外部扬声器系统以及从飞机外部投射声波的方法。 飞机包括外皮膜，振动致动器和控制器。 外皮膜具有限定飞机外部边界的外表面。 振动致动器与外皮膜共同振动。 控制器可操作地与振动致动器耦合，并且被配置为基于从外表面突出的可听内容产生用于振动致动器的命令。 控制器还被配置为将该命令发送到振动致动器。 振动致动器被配置为响应于接收到该命令而振动。

    X-BAND AVIAN RADAR DETECTION AND WARNING SYSTEM
    98.
    发明申请
    X-BAND AVIAN RADAR DETECTION AND WARNING SYSTEM 审中-公开
    X-BAND AVIAN雷达探测和警告系统

    公开(公告)号：US20160282131A1

    公开(公告)日：2016-09-29

    申请号：US14665418

    申请日：2015-03-23

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Gary Palfreyman

    IPC: G01C21/34 ,  G01S13/42 ,  G01S7/41 ,  G01S13/93

    CPC classification number: G01S7/415 ,  G01S13/426 ,  G01S13/5242 ,  G01S13/66 ,  G01S13/9303 ,  G08G5/0021 ,  G08G5/0052 ,  G08G5/045

    Abstract: The disclosed embodiments relate to an aircraft having an X-band avian radar detection and warning system. The system can include an X-band radar system and a processor. The processor can include a target processor module that can process the reflected X-band radar signals to: detect targets in a projected flight path of the aircraft; identify one or more targets that are determined to correspond to one or more birds; and generate a bird detection signal. In response to receiving the bird detection signal, the warning generator module can generate and transmit a warning generator signal to at least one cockpit output device in the cockpit of the aircraft to cause it to generate a warning signal that is perceptible in the cabin of the aircraft to warn pilots and crew of a potential collision with the birds so that the pilot can take evasive action.

    Abstract translation: 所公开的实施例涉及具有X波段禽雷达检测和警告系统的飞行器。 该系统可以包括X波段雷达系统和处理器。 处理器可以包括目标处理器模块，该目标处理器模块可以处理反射的X波段雷达信号，以便：检测飞行器的投影飞行路径中的目标; 识别确定为对应于一只或多只鸟的一个或多个目标; 并产生鸟检测信号。 响应于接收到鸟类检测信号，警报发生器模块可以生成并向飞行器的驾驶舱中的至少一个驾驶舱输出设备发送警告发生器信号，以使其产生在驾驶舱内可感知的警告信号 飞机警告飞行员和机组人员与鸟类发生潜在的碰撞，以便飞行员可以采取回避行动。

    SYSTEM AND METHOD FOR CONTROLLING A PRESSURE FIELD AROUND AN AIRCRAFT IN FLIGHT
    100.
    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。

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