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81. 发明申请

WO2014185998A3 PROPULSION SYSTEM USING VORTEX GENERATORS AND SUPERSONIC AIRCRAFT EQUIPPED WITH THE PROPULSION SYSTEM 审中-公开
公开(公告)号：WO2014185998A3
公开(公告)日：2014-11-20
申请号：PCT/US2014/014790
申请日：2014-02-05
申请人： GULFSTREAM AEROSPACE CORPORATION , RYBALKO, Michael , CONNORS, Timothy , WAYMAN, Tom
发明人： RYBALKO, Michael , CONNORS, Timothy , WAYMAN, Tom
IPC分类号： B64D33/02
摘要： A propulsion system for a supersonic aircraft includes an engine, a compression surface upstream of the engine, a shroud surrounding the engine configured to direct airflow passing over the compression surface towards the engine, and a plurality of vortex generators positioned upstream of the engine. The vortex generators have a height such that when the supersonic aircraft is flown at a predetermined speed, the plurality of vortex generators create a plurality of vortices that propagate partially outside of a boundary layer formed proximate a surface of a supersonic inlet. The vortices cause a high-velocity portion of the airflow to move towards a portion of the engine having a higher sensitivity to changes in stagnation pressure and a low-velocity portion of the airflow to move away from the portion of the engine having the higher sensitivity to changes in stagnation pressure prior to the airflow reaching a face of the engine.

82. 发明申请

WO2014138441A1 RUNWAY TAKEOFF MONITOR 审中-公开
标题翻译： RUNWAY TAKEOFF监视器
公开(公告)号：WO2014138441A1
公开(公告)日：2014-09-12
申请号：PCT/US2014/021326
申请日：2014-03-06
申请人： GULFSTREAM AEROSPACE CORPORATION , HORNE, Thomas , LANDERS, Thomas , MAYO, John
发明人： HORNE, Thomas , LANDERS, Thomas , MAYO, John
IPC分类号： G01C21/00
CPC分类号： G08G5/0065 , G01C23/005 , G08G5/0021 , G08G5/065
摘要： Disclosed is a runway alerting method and system for an aircraft during a take-off maneuver. The method includes determining stopping positions for the aircraft along the runway using aircraft energy state, deceleration and braking information and displaying the stopping positions on a display. When performing a takeoff maneuver in an aircraft, it is sometimes necessary to abort the takeoff and stop the aircraft on the remaining available runway. Engine failure, system failure, or contaminated runway effects are some causes for a pilot to abort a takeoff attempt.
摘要翻译：公开了一种在起飞操纵期间飞机的跑道报警方法和系统。该方法包括使用飞机能量状态，减速度和制动信息确定飞机沿着跑道的停止位置，并在显示器上显示停止位置。在飞机上进行起飞时，有时需要中止起飞，并在剩余的可用跑道上停止飞机。发动机故障，系统故障或污染的跑道效应是飞行员中止起飞尝试的一些原因。

83. 发明申请

WO2014126860A1 SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM 审中-公开
标题翻译：用于控制SONIC BOOM磁头的系统和方法
公开(公告)号：WO2014126860A1
公开(公告)日：2014-08-21
申请号：PCT/US2014/015600
申请日：2014-02-10
申请人： GULFSTREAM AEROSPACE CORPORATION , FREUND, Donald
发明人： FREUND, Donald
IPC分类号： B64C30/00
CPC分类号： B64C23/00 , B64C3/185 , B64C3/20 , B64C3/38 , B64C3/42 , B64C9/00 , B64C17/10 , B64C30/00 , B64D37/00 , Y02T50/14 , Y02T50/44
摘要： A system for controlling a magnitude of a sonic boom caused by off-design operation of a supersonic aircraft includes a sensor configured to detect a condition of the supersonic aircraft. The system further includes a control surface that is mounted to a wing of the supersonic aircraft. The system still further includes a processor communicatively coupled to the sensor and operatively coupled with the control surface. The processor is configured to (1) receive information from the sensor indicative of the condition of the supersonic aircraft, (2) determine that there is a deviation between a lift distribution and a design-condition lift distribution based on the information, and (3) control the control surface to move in a manner that reduces the deviation. The magnitude of the sonic boom is reduced when the deviation is reduced.
摘要翻译：用于控制由超音速飞行器的脱离设计操作引起的声音吊杆的大小的系统包括被配置为检测超音速飞行器的状况的传感器。该系统还包括安装在超音速飞行器的机翼上的控制表面。系统还包括通信地耦合到传感器并且与控制表面可操作地耦合的处理器。处理器被配置为（1）从传感器接收指示超音速飞行器的状况的信息，（2）基于该信息确定升力分布与设计状况提升分布之间存在偏差，并且（3 ）控制控制面以减少偏差的方式移动。当偏差减小时，声音臂的大小减小。

84. 发明申请

WO2014126858A1 SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM 审中-公开
标题翻译：用于控制SONIC BOOM磁头的系统和方法
公开(公告)号：WO2014126858A1
公开(公告)日：2014-08-21
申请号：PCT/US2014/015591
申请日：2014-02-10
申请人： GULFSTREAM AEROSPACE CORPORATION , FREUND, Donald
发明人： FREUND, Donald
IPC分类号： B64C30/00
CPC分类号： B64C23/00 , B64C3/185 , B64C3/20 , B64C3/38 , B64C3/42 , B64C9/00 , B64C17/10 , B64C30/00 , B64D37/00 , Y02T50/14 , Y02T50/44
摘要： Methods and systems for controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds are disclosed herein. The method includes, but is not limited to, monitoring, with a processor, a weight of the supersonic aircraft and a distribution of fuel onboard the supersonic aircraft. The method further includes, but is not limited to, determining, with the processor, that there is a deviation of the weight of the supersonic aircraft from a design-condition weight. The method still further includes, but is not limited to, controlling, with the processor, a redistribution of the fuel onboard the supersonic aircraft to adjust an amount of fuel stored within a wing to minimize a twist in the wing caused by the deviation. Such redistribution will reduce the magnitude of the sonic boom caused by the deviation.
摘要翻译：本文公开了用于控制由超音速飞行器超超速度的偏离设计条件操作引起的声波起重量的方法和系统。该方法包括但不限于用处理器监测超音速飞机的重量和超音速飞机上的燃料分配。该方法还包括但不限于与处理器确定超音速飞机的重量与设计条件权重的偏差。该方法还包括但不限于与处理器一起控制超音速飞机上的燃料的重新分配，以调节存储在机翼内的燃料量，以最小化由偏差引起的机翼扭转。这种重新分配将减少由偏差引起的声波爆震的大小。

85. 发明申请

WO2013134028A1 METHOD AND SYSTEM FOR DISPLAYING INFORMATION 审中-公开
标题翻译：用于显示信息的方法和系统
公开(公告)号：WO2013134028A1
公开(公告)日：2013-09-12
申请号：PCT/US2013/028138
申请日：2013-02-28
申请人： MARTIN, Scott , GULFSTREAM AEROSPACE CORPORATION
发明人： MARTIN, Scott
IPC分类号： G01C21/30 , G01S13/89 , G06T17/05
CPC分类号： G01C23/005
摘要： A display system for an aircraft includes a controller in communication with a display. The controller receives a category associated with a phase of flight of the aircraft. Information related to operation of the aircraft and associated with the received category is displayed on the display.
摘要翻译：用于飞行器的显示系统包括与显示器通信的控制器。控制器接收与飞行器的飞行阶段相关联的类别。与显示器上显示有关飞机操作和与接收类别相关的信息。

86. 发明申请

WO2013116448A1 METHODS AND SYSTEMS FOR DETERMINING AIRSPEED OF AN AIRCRAFT 审中-公开
标题翻译：用于确定飞机飞行的方法和系统
公开(公告)号：WO2013116448A1
公开(公告)日：2013-08-08
申请号：PCT/US2013/024028
申请日：2013-01-31
申请人： THOMAS, Jason , GULFSTREAM AEROSPACE CORPORATION
发明人： THOMAS, Jason
IPC分类号： G01P13/02 , G01P5/14 , G01C21/00
CPC分类号： G01P5/06 , G01P21/025
摘要： The disclosed embodiments relate to methods and systems for determining airspeed of an aircraft.
摘要翻译：所公开的实施例涉及用于确定飞机空速的方法和系统。

87. 发明申请

WO2013109565A1 VIRTUAL KEYBOARD ARRANGEMENT 审中-公开
标题翻译：虚拟键盘布置
公开(公告)号：WO2013109565A1
公开(公告)日：2013-07-25
申请号：PCT/US2013/021631
申请日：2013-01-16
申请人： MARTIN, Scott , MEDIN, Kristin , GULFSTREAM AEROSPACE CORPORATION
发明人： MARTIN, Scott , MEDIN, Kristin
IPC分类号： G06F3/048
CPC分类号： G06F3/0482 , G06F3/04817 , G06F3/04886
摘要： A display assembly includes display having a bottom edge. An input device is integrated with the display for receiving input from a user. A plurality of icons are arranged as a row and displayed on the display. Each of the icons is selectable by the user. The row of icons is displayed non-parallel to the bottom edge of the display.
摘要翻译：显示组件包括具有底边的显示器。输入设备与显示器集成，用于接收来自用户的输入。多个图标被排列成行并显示在显示器上。每个图标可由用户选择。图标行显示为不平行于显示器的底部边缘。

88. 发明申请

WO2013106500A1 MOUNTING ASSEMBLY AND METHOD FOR MOUNTING A SOUND-DEADENING BODY TO A FUSELAGE OF AN AIRCRAFT 审中-公开
标题翻译：安装组件和将声音消失体安装到飞机的装置上的方法
公开(公告)号：WO2013106500A1
公开(公告)日：2013-07-18
申请号：PCT/US2013/020928
申请日：2013-01-10
申请人： LUCAS, Michael Eugene , YOVICH, Nicholas W. , GULFSTREAM AEROSPACE CORPORATION
发明人： LUCAS, Michael Eugene , YOVICH, Nicholas W.
IPC分类号： B64C1/40
CPC分类号： B64C1/403 , B64C1/40 , Y10T29/4978
摘要： A mounting assembly for mounting a sound-deadening body to a fuselage of an aircraft and a method for attaching a sound-deadening body to a fuselage of an aircraft using the mounting assembly is disclosed herein. In a non-limiting embodiment, the mounting assembly includes, but is not limited to, a retaining member that is configured to engage the sound-deadening body. The mounting assembly further includes an isolating member that is engaged with the retaining member. The isolating member is configured for connection to the fuselage and is further configured to diminish transmission of vibration from the fuselage to and through the retaining member, and therefore to reduce the transmission of sound into the cabin.
摘要翻译：本文公开了一种用于将消音体安装到飞行器的机身上的安装组件以及使用安装组件将防声体附接到飞行器的机身的方法。在非限制性实施例中，安装组件包括但不限于构造成接合防声体的保持构件。安装组件还包括与保持构件接合的隔离构件。隔离构件被构造成用于连接到机身，并且还被配置为减小从机身到和通过保持构件的振动的传递，并且因此减少声音进入舱室的传播。

89. 发明申请

WO2013086155A1 IMPROVED THERMAL-ACOUSTIC SECTIONS FOR AN AIRCRAFT 审中-公开
标题翻译：改进航空器的热声部分
公开(公告)号：WO2013086155A1
公开(公告)日：2013-06-13
申请号：PCT/US2012/068195
申请日：2012-12-06
申请人： WANG, Tongan , MAXON, John, Willett , FOOSE, Andrew , HORNICK, David, Charles , FILA, Josef , GULFSTREAM AEROSPACE CORPORATION
发明人： WANG, Tongan , MAXON, John, Willett , FOOSE, Andrew , HORNICK, David, Charles , FILA, Josef
IPC分类号： E04B1/82
CPC分类号： B64C1/40 , B29C65/00 , B29C66/11 , B29C66/1122 , B29C66/1142 , B29C66/43 , B29K2105/04 , B32B3/12 , B32B5/26 , B32B5/32 , B32B7/02 , B32B2250/02 , B32B2250/03 , B32B2250/04 , B32B2250/05 , B32B2250/20 , B32B2250/22 , B32B2266/0257 , B32B2266/0285 , B32B2266/06 , B32B2307/102 , B32B2307/718 , B32B2605/18 , B64C1/00 , E04B1/82 , E04B1/84 , G10K11/00 , G10K11/02 , Y02T50/46 , Y10T428/24149
摘要： Embodiments of thermal-acoustic sections for an aircraft for reducing noise along an acoustic path produced from an acoustic source are provided herein. The thermal-acoustic section comprises a first porous layer having a first characteristic acoustic impedance. A second porous layer is disposed adjacent to the first porous layer and has a second characteristic acoustic impedance that is greater than the first characteristic acoustic impedance. The thermal-acoustic section is configured to be positioned along the acoustic path such that at least a portion of the noise from the acoustic source is directed through the first porous layer to the second porous layer to promote absorption of the noise.
摘要翻译：本文提供了用于从声源产生的用于降低沿着声学路径的噪声的用于飞行器的热声部分的实施例。热声部分包括具有第一特征声阻抗的第一多孔层。第二多孔层设置成与第一多孔层相邻并且具有大于第一特征声阻抗的第二特征声阻抗。热声部分被配置成沿着声学路径定位，使得来自声源的噪声的至少一部分被引导通过第一多孔层到第二多孔层以促进噪声的吸收。

90. 发明申请

WO2013063392A1 METHODS AND SYSTEMS FOR AVOIDING A COLLISION BETWEEN AN AIRCRAFT ON A GROUND SURFACE AND AN OBSTACLE 审中-公开
标题翻译：用于避免地面和飞机之间的飞机碰撞的方法和系统
公开(公告)号：WO2013063392A1
公开(公告)日：2013-05-02
申请号：PCT/US2012/062120
申请日：2012-10-26
申请人： KNIGHT, Michael , GULFSTREAM AEROSPACE CORPORATION
发明人： KNIGHT, Michael
IPC分类号： G08B21/00
CPC分类号： 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
摘要： The disclosed embodiments relate to methods and systems for avoiding a collision between an obstacle and a vehicle, such as an aircraft, on a ground surface. A processor receives a detection signal from one of a plurality of proximity sensors. The detection signal indicates that the obstacle has been detected. In response to receiving the detection signal, a video image signal is transmitted from the processor to a display in the cockpit of the aircraft. The video image signal corresponds to a particular video imager that is associated with the particular proximity sensor that detected the obstacle. A video image, of a particular region around the aircraft that includes the obstacle is displayed on a display. In response to receiving the detection signal, the processor can also transmit an alert signal, and a brake activation signal to activate a braking system to prevent the aircraft from colliding with the obstacle.
摘要翻译：所公开的实施例涉及用于避免障碍物和诸如飞机的车辆在地面上的碰撞的方法和系统。处理器从多个接近传感器之一接收检测信号。检测信号表示已经检测到障碍物。响应于接收到检测信号，视频图像信号从处理器发送到飞行器驾驶舱中的显示器。视频图像信号对应于与检测到障碍物的特定接近传感器相关联的特定视频成像器。在显示器上显示包括障碍物在内的飞机周围的特定区域的视频图像。响应于接收到检测信号，处理器还可以发送报警信号和制动启动信号以启动制动系统以防止飞机与障碍物碰撞。

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