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91. 发明申请

US20160318627A1 AIRCRAFT AND EXTERIOR SPEAKER SYSTEMS FOR AIRCRAFT 有权
标题翻译：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
申请人： Gulfstream Aerospace Corporation
发明人： Michael Lucas , Michael Brinley , Kristopher Lynch
IPC分类号： B64D47/02 , B64D45/00 , B64C1/12
CPC分类号： B64D47/02 , B64D45/00 , B64D2045/0095 , G10K9/20 , G10K2210/1281 , H04R7/045
摘要： 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.
摘要翻译：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。

92. 发明授权

US09482155B2 Isentropic compression inlet for supersonic aircraft 有权
标题翻译：超音速飞机的等熵压缩入口
公开(公告)号：US09482155B2
公开(公告)日：2016-11-01
申请号：US13629181
申请日：2012-09-27
申请人： Gulfstream Aerospace Corporation
发明人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
IPC分类号： F02C7/04 , B64D33/02 , B64C30/00 , F02K7/10
CPC分类号： F02C7/04 , B64C30/00 , B64D27/16 , B64D29/00 , B64D33/02 , B64D2033/026 , F02C7/042 , F02K7/10 , F05D2210/33 , F05D2220/80 , F05D2250/70 , Y10T29/49323 , Y10T137/0318 , Y10T137/0536
摘要： A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining overall engine performance.
摘要翻译：超音速入口包括松弛的等熵压缩表面，以通过使入口的压缩表面成形来改善净推进力，以将所得的冲击离开整流罩。入口压缩表面的松弛等熵压缩成形功能可减少罩面表面角度，从而改善入口阻力特性和干涉阻力特性。根据本发明的超音速进气口还显示了在保持总体发动机性能的同时降低了峰值声波悬臂超压。

93. 发明申请

US20160282131A1 X-BAND AVIAN RADAR DETECTION AND WARNING SYSTEM 审中-公开
标题翻译： 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
申请人： Gulfstream Aerospace Corporation
发明人： Gary Palfreyman
IPC分类号： G01C21/34 , G01S13/42 , G01S7/41 , G01S13/93
CPC分类号： G01S7/415 , G01S13/426 , G01S13/5242 , G01S13/66 , G01S13/9303 , G08G5/0021 , G08G5/0052 , G08G5/045
摘要： 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.
摘要翻译：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。

94. 外观设计

USD766790S1 Aircraft crew rest 有权
标题翻译：飞机机组休息
公开(公告)号：USD766790S1
公开(公告)日：2016-09-20
申请号：US29506200
申请日：2014-10-14
申请人： Gulfstream Aerospace Corporation
设计人： Kevin Sethapun , Aram Kasparian

95. 发明申请

US20160257397A1 SYSTEM AND METHOD FOR CONTROLLING A PRESSURE FIELD AROUND AN AIRCRAFT IN FLIGHT 有权
标题翻译：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
申请人： Gulfstream Aerospace Corporation
发明人： Timothy Conners , Michael Knight , Robert Cowart
IPC分类号： B64C23/04 , G01L19/14 , G01L19/00 , B64C30/00 , B64C13/16
CPC分类号： B64C23/04 , B64C13/16 , B64C30/00 , B64D31/06 , B64D33/02 , F02C9/28 , G01L19/0084 , G01L19/14
摘要： 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.
摘要翻译：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。

96. 外观设计

USD761189S1 Latch for interiors of aircraft 有权
标题翻译：飞机内部锁定
公开(公告)号：USD761189S1
公开(公告)日：2016-07-12
申请号：US29506224
申请日：2014-10-14
申请人： Gulfstream Aerospace Corporation
设计人： Andrew Fulford , Aram Kasparian

97. 外观设计

USD759569S1 Nose wheel tiller for aircraft 有权
标题翻译：用于飞机的鼻轮分蘖
公开(公告)号：USD759569S1
公开(公告)日：2016-06-21
申请号：US29506136
申请日：2014-10-13
申请人： Gulfstream Aerospace Corporation
设计人： Aram Kasparian , Andrew Fulford

98. 发明申请

US20160152323A1 AIRCRAFT, SYSTEMS, AND METHODS FOR TRIM CONTROL IN FLY-BY-WIRE AIRCRAFT SYSTEMS 审中-公开
标题翻译：飞行器飞行器系统的飞行器，系统和方法
公开(公告)号：US20160152323A1
公开(公告)日：2016-06-02
申请号：US14513125
申请日：2014-10-13
申请人： Gulfstream Aerospace Corporation
发明人： Kevin Claffy , Jong-Yeob Shin
IPC分类号： B64C13/50 , G05D1/08 , G05D1/00
CPC分类号： B64C13/506 , B64C13/0421 , B64C13/0427 , B64C13/503
摘要： Aircraft, fly-by-wire systems, and controllers are provided. An aircraft includes a trim control system and a fly-by-wire system. The trim control system is configured for controlling surfaces of the aircraft. The fly-by-wire system is communicatively coupled with the trim control system and includes an input device and a controller. The input device is configured to receive a re-trim input from a user. The controller is communicatively coupled with the input device and is configured to control the trim control system, to obtain the re-trim input from the user, and to set a pitch trim of the aircraft based on a stable flight condition at a present airspeed of the aircraft in response to the re-trim input from the input device.
摘要翻译：提供飞机，线控系统和控制器。一架飞机包括一个修剪控制系统和一个线控飞行系统。修剪控制系统被配置为控制飞行器的表面。线控线系统与调整控制系统通信耦合，并包括输入设备和控制器。输入设备被配置为从用户接收修剪输入。控制器与输入设备通信耦合，并且被配置为控制修剪控制系统，以获得来自用户的修剪输入，以及基于当前空速的稳定飞行条件来设置飞行器的俯仰微调飞机响应于从输入设备的重新修剪输入。

99. 发明申请

US20160101865A1 CONSOLE ASSEMBLY INCLUDING STOWABLE SUPPORT SURFACE 有权
标题翻译：控制台总成包括可支持的支持表面
公开(公告)号：US20160101865A1
公开(公告)日：2016-04-14
申请号：US14866164
申请日：2015-09-25
申请人： Gulfstream Aerospace Corporation
发明人： Tristan Flynn , Todd Loar
IPC分类号： B64D11/00 , B64D43/00
CPC分类号： B64D43/00
摘要： A console assembly for use on a flight deck of an aircraft includes, but is not limited to, a console having a recess. The recess has an opening. The console assembly further includes a mounting assembly mounted within the recess. The console assembly further includes a support surface mounted to the mounting assembly. The console assembly further includes a closeout panel that is mounted to the support surface. The support surface fits within the recess. The mounting assembly facilitates movement of the support surface between a retracted and a deployed position. The support surface is disposed within the recess while in the retracted position and outside of the recess while in the deployed position. The closeout panel is disposed at a location on the support surface that causes the closeout panel to close the opening of the recess when the support surface is in the retracted position.
摘要翻译：在飞行器的驾驶舱上使用的控制台组件包括但不限于具有凹部的控制台。凹槽有一个开口。控制台组件还包括安装在凹部内的安装组件。控制台组件还包括安装到安装组件的支撑表面。控制台组件还包括安装到支撑表面的闭合面板。支撑表面装配在凹槽内。安装组件有助于支撑表面在缩回和展开位置之间的移动。支撑表面在处于展开位置的同时处于缩回位置和凹部外部时设置在凹部内。闭合面板设置在支撑表面上的位置处，当支撑表面处于缩回位置时，导致闭合面板闭合凹部的开口。

100. 发明申请

US20160101845A1 AIRCRAFT AND AIR EXCHANGE SYSTEMS FOR VENTILATED CAVITIES OF AIRCRAFT 有权
标题翻译：飞机通风航空器和飞机交换系统
公开(公告)号：US20160101845A1
公开(公告)日：2016-04-14
申请号：US14513172
申请日：2014-10-13
申请人： Gulfstream Aerospace Corporation
发明人： Tongan Wang , Michael Eugene Lucas , Kristopher P. Lynch , Tyler Relf , John Willett Maxon, JR.
IPC分类号： B64C1/40 , B64D37/32 , B64C7/00
CPC分类号： B64C1/40 , B64C7/00 , B64D37/32
摘要： Aircraft, wing-to-body fairing assemblies, and air exchange systems are provided. An aircraft includes a fuselage, a wing secured to the fuselage, an outer skin panel, and an air exchange system. The outer skin panel is secured to the wing and/or the fuselage and at least partially defines a cavity. The air exchange system is secured to the outer skin panel and exchanges air between the cavity and an external environment. The air exchange system includes an air inlet, a diffuser, and a silencer. The air inlet is disposed in the outer skin panel and accommodates an air flow between the cavity and the external environment. The diffuser is attached to the air inlet and has a varying cross sectional area to change the speed of the air flow. The silencer is attached to the diffuser and communicates the air flow between the diffuser and the cavity and reduces noise.
摘要翻译：提供飞机，翼对整流罩组件和空气交换系统。一架飞机包括一个机身，一个固定在机身上的机翼，一个外壳和一个空气交换系统。外部皮肤面板固定到机翼和/或机身上，并且至少部分地限定空腔。空气交换系统固定在外皮面板上，并在空腔和外部环境之间交换空气。空气交换系统包括进气口，扩散器和消音器。空气入口设置在外表面板中并且容纳在空腔和外部环境之间的空气流。扩散器连接到空气入口并且具有变化的横截面积以改变空气流的速度。消声器连接到扩散器，并使扩散器和空腔之间的空气流通过并减少噪音。

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