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31. 发明申请

WO2014179086A2 VACUUM BAG MOLDING ASSEMBLY AND METHODS 审中-公开
标题翻译：真空袋模具组件和方法
公开(公告)号：WO2014179086A2
公开(公告)日：2014-11-06
申请号：PCT/US2014/034539
申请日：2014-04-17
申请人： GULFSTREAM AEROSPACE CORPORATION , BALLOW, Paul J.
发明人： BALLOW, Paul J.
IPC分类号： B29C43/12 , B29C33/10
CPC分类号： B29C43/12 , B29C33/68 , B29C70/44
摘要： An assembly for vacuum bag molding includes a mold for receiving a workpiece. An edge breather comprising a plurality of braided polymer threads is disposed about a periphery of the workpiece. A vacuum bag film is disposed over the workpiece and the edge breather. A seal seals the vacuum bag film to the mold and a passageway in fluidic communication with the edge breather.
摘要翻译：用于真空袋成型的组件包括用于接收工件的模具。包括多个编织聚合物线的边缘通气器围绕工件的周边设置。真空袋膜设置在工件和边缘通气器上。密封件将真空袋膜密封到模具和与边缘通气器流体连通的通道。

32. 发明申请

WO2014172126A1 DISPLAY SYSTEM AND METHOD FOR DISPLAYING INFORMATION 审中-公开
标题翻译：用于显示信息的显示系统和方法
公开(公告)号：WO2014172126A1
公开(公告)日：2014-10-23
申请号：PCT/US2014/033121
申请日：2014-04-07
申请人： GULFSTREAM AEROSPACE CORPORATION , MANOCHIO, Frank
发明人： MANOCHIO, Frank
IPC分类号： G01C23/00
CPC分类号： B64D43/00 , G09G3/002
摘要： A display system is disclosed herein. The display system includes, but is not limited to, a rear projection screen. The display system further includes, but is not limited to, a first projector arranged to project a first image on the rear projection screen. The display system further includes a second projector arranged to project a second image on the rear projection screen. The display system still further includes a processor that is operatively coupled with the first projector and the second projector. The processor is configured to control the first projector to project the first image and to control the second projector to project the second image, and is further configured to align the second image with the first image in an overlaying manner so as to create the appearance of a single image, a portion of the second image being substantially identical to a portion of the first image.
摘要翻译：本文公开了显示系统。显示系统包括但不限于背投屏幕。显示系统还包括但不限于布置成将第一图像投影在后投影屏幕上的第一投影仪。显示系统还包括第二投影仪，其布置成将第二图像投影在后投影屏幕上。显示系统还包括可操作地与第一投影仪和第二投影仪耦合的处理器。处理器被配置为控制第一投影仪投射第一图像并且控制第二投影仪投影第二图像，并且还被配置为以叠加方式将第二图像与第一图像对准，以便产生外观单个图像，第二图像的一部分基本上与第一图像的一部分相同。

33. 发明申请

WO2013106125A2 FLAP ROLLER ARRANGEMENT, FLAP ASSEMBLY, AND METHOD FOR REMOVING A ROLLER ASSEMBLY FROM A FLAP FITTING 审中-公开
标题翻译：襟翼滚子装置，襟翼装配和从襟翼接合部移除滚子总成的方法
公开(公告)号：WO2013106125A2
公开(公告)日：2013-07-18
申请号：PCT/US2012/061328
申请日：2012-10-22
申请人： GULFSTREAM AEROSPACE CORPORATION , GRIECO, James R. , PAKHLEVANYAN, Gary
发明人： GRIECO, James R. , PAKHLEVANYAN, Gary
IPC分类号： B64C3/58 , B23P19/00
CPC分类号： B64C9/02 , B64C9/16 , Y02T50/32 , Y02T50/44 , Y10T29/49815
摘要： A flap roller arrangement for supporting a flap on a wing of an aircraft is disclosed herein. The flap roller arrangement includes, but is not limited to, a roller assembly that is configured for rolling engagement with a flap track of the wing and for engagement with a flap fitting. The flap roller arrangement further includes a retaining member that is removably coupled to the roller assembly. The roller assembly is configured to egress through an opening in the flap fitting in a direction away from the flap track. The retaining member is configured to obstruct egress of the roller assembly through the opening when the retaining member is coupled to the roller assembly. The roller assembly is enabled to egress through the opening when the retaining member is removed from the roller assembly.
摘要翻译：本文公开了一种用于在飞行器的机翼上支撑翼片的翼片滚子装置。挡板辊布置包括但不限于：辊组件，其被配置为与翼的翼片轨道滚动接合并用于与翼片配件接合。挡板辊布置还包括可移除地联接到辊组件的保持构件。辊组件被构造成沿着远离翼片轨迹的方向排出翼片配件中的开口。保持构件被构造成当保持构件联接到辊组件时阻止辊组件通过开口的出口。当保持构件从辊组件移除时，辊组件能够通过开口排出。

34. 发明申请

WO2013028557A1 AIR INLET ARRANGEMENT AND METHOD OF MAKING THE SAME 审中-公开
标题翻译：空气入口装置及其制造方法
公开(公告)号：WO2013028557A1
公开(公告)日：2013-02-28
申请号：PCT/US2012/051455
申请日：2012-08-17
申请人： GULFSTREAM AEROSPACE CORPORATION , CONNERS, Timothy R. , HENNE, Preston A. , HOWE, Donald C.
发明人： CONNERS, Timothy R. , HENNE, Preston A. , HOWE, Donald C.
IPC分类号： F02C7/04
CPC分类号： F02K1/46 , B64D33/02 , B64D2033/026 , B64D2033/0273 , B64D2033/0286 , F02C7/00 , F02C7/04 , F02C7/045 , F02K1/04 , F02K1/34 , F02K3/02 , F02K7/00 , F02K7/10 , F02K7/16 , F02K7/20 , F05D2210/12 , F05D2220/323 , F05D2220/80 , F05D2230/60 , F05D2250/70 , F05D2260/96 , Y10T29/49346 , Y10T137/0536
摘要： An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.
摘要翻译：本文公开了一种与超音速喷气发动机一起使用的入口装置，其构造成当超音速喷气发动机以预定的功率设定运行并以预定的马赫速度运动时以预定的质量流量消耗空气。空气入口装置包括但不限于具有整流罩和与整流罩同轴对准的中心体的整流罩。中心体的突出部分在前罩的上游延伸的长度大于传统的尖钉长度。突出部分构造成将在突出部分上流动的空气从入口的路径转移到超音速喷气发动机，使得接近并进入入口的剩余气流匹配预定的质量流量。

35. 发明申请

WO2007084679A2 APPARATUS AND METHOD FOR BACKUP CONTROL IN A DISTRIBUTED FLIGHT CONTROL SYSTEM 审中-公开
标题翻译：分布式飞行控制系统中的备份控制的装置和方法
公开(公告)号：WO2007084679A2
公开(公告)日：2007-07-26
申请号：PCT/US2007/001462
申请日：2007-01-17
申请人： GULFSTREAM AEROSPACE CORPORATION , HIRVONEN, Jukka, Matti
发明人： HIRVONEN, Jukka, Matti
IPC分类号： G05D1/00
CPC分类号： G05D1/0077 , B64C13/42 , Y02T50/44
摘要： Embodiments of the invention relate to a flight control system for controlling an aircraft during flight. The flight control system may include a primary controller configured to receive an input from a pilot and to output a primary control signal and a primary transmission path connected to the primary controller and configured to relay the primary control signal. The flight control system may also include a backup controller configured to receive the input from the pilot and to output a backup control signal and a backup transmission path connected to the backup controller and configured to relay the backup control signal. Additionally, the flight control system may include an actuator having a remote electronics unit configured to receive the primary control signal and the backup control signal and to determine if the primary control signal is available and valid. The remote electronics unit may be configured to output an actuator command based on the primary control signal if the primary control signal is available and valid and to output the actuator command based on the backup control signal if the primary control signal is unavailable or invalid.
摘要翻译：本发明的实施例涉及一种用于在飞行中控制飞行器的飞行控制系统。飞行控制系统可以包括主控制器，其被配置为从导频接收输入并输出连接到主控制器并且被配置为中继主控制信号的主控制信号和主传输路径。飞行控制系统还可以包括备用控制器，其被配置为从飞行员接收输入并输出备用控制信号和连接到备用控制器并被配置为中继备用控制信号的备用传输路径。此外，飞行控制系统可以包括具有远程电子单元的致动器，该远程电子单元被配置为接收主控制信号和备用控制信号，并且确定主控制信号是否可用且有效。如果主控制信号可用且有效，则远程电子单元可以被配置为基于主控制信号来输出致动器命令，并且如果主控制信号不可用或无效，则基于备用控制信号输出致动器命令。

36. 发明申请

WO2005068782A1 LAMINOR/TURBULENT TRANSITION ZONE STABILIZATION ON A TURBINE VANE 审中-公开
标题翻译：涡轮风扇层流板/涡轮转换区域稳定
公开(公告)号：WO2005068782A1
公开(公告)日：2005-07-28
申请号：PCT/US2004/009897
申请日：2004-03-26
申请人： GULFSTREAM AEROSPACE CORPORATION , HENNE, Preston , MILLS, Robert
发明人： HENNE, Preston , MILLS, Robert
IPC分类号： F01D5/14
CPC分类号： F04D29/681 , F01D5/145 , F04D29/384 , F05D2240/31 , Y02T50/673
摘要： A turbine fan blade (40) adapted to trip and control a boundary layer transition at a side surface of the blade (40) during operation as a component in a turbine fan assembly (35). The turbine fan blade (40) includes a leading edge (55), a trailing edge (58), and two side surfaces including a high-pressure side surface (49) and a low-pressure side surface (52). At least one of the two side surfaces has an essentially smooth surface portion (61) located between the leading and trailing edges, and the essentially smooth surface portion is interrupted by a surface deviation (64). The surface deviation is configured to trip a positionally stabilized boundary layer transition (24) at a location toward the trailing edge from the surface deviation during operation of the turbine fan blade in the turbine fan assembly. In this manner, fatigue inducing aerodynamic forces experienced upon the blade during operation are controlled.
摘要翻译：一种涡轮机风扇叶片（40），其适于在作为涡轮机风扇组件（35）中的部件操作期间跳闸和控制在叶片（40）的侧表面处的边界层过渡。涡轮风扇叶片（40）包括前缘（55），后缘（58）和包括高压侧表面（49）和低压侧表面（52）的两个侧表面。两个侧表面中的至少一个具有位于前缘和后缘之间的基本平滑的表面部分（61），并且基本上平滑的表面部分被表面偏差（64）中断。表面偏差被配置为在涡轮机风扇组件中的涡轮风扇叶片的操作期间，从位于朝向后缘的位置处的位置稳定的边界层过渡（24）脱离表面偏离。以这种方式，控制在操作期间在叶片上经历的疲劳引起的空气动力。

37. 发明申请

WO2021146743A1 TERRAIN DATABASE CARVING AROUND RUNWAYS 审中-公开
公开(公告)号：WO2021146743A1
公开(公告)日：2021-07-22
申请号：PCT/US2021/070003
申请日：2021-01-06
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： FERREIRA, Sergio , MORAN, Brendan
IPC分类号： B64D45/04 , G08G5/00 , G08G5/04 , G01C5/00 , G01C5/005 , G08G5/0013 , G08G5/0021 , G08G5/0086 , G08G5/025 , G08G5/045
摘要： Vertical resolution and/or vertical accuracy of terrain elevation data near an aircraft runway is adjusted by obtaining local terrain data, yielding a first elevation value for a query location. A processor receptive of the first elevation value computes plane equations based on a predetermined standard model adapted to geometrically conform to the aircraft runway, yielding a second elevation value for the query location. The processor selectively uses the first and second elevation values to generate an adjusted elevation value that is supplied to a terrain avoidance and warning system.

38. 发明申请

WO2020046984A1 PIECEWISE RECOVERY SYSTEM 审中-公开
公开(公告)号：WO2020046984A1
公开(公告)日：2020-03-05
申请号：PCT/US2019/048399
申请日：2019-08-27
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： PROSSER, Kevin , LANDERS, Thomas , VAIDYA, Abhishek , FINLAYSON, Blake , SAKHAEI, Alborz
IPC分类号： G05D1/10 , G08G5/00
摘要： A projected recovery trajectory (60) for an aircraft autopilot system is precomputed by providing a stored set of predefined recovery mode segments, including: a mode 1 segment that models the aircraft coasting; a mode 2 segment that models the aircraft executing a nose high recovery; a mode 3 segment that models the aircraft executing a nose low recovery; a mode 4 segment that models the aircraft executing a throttle only recovery; and a mode 5 segment that models the aircraft executing a terrain avoidance recovery. A processor generates at least one projected recovery trajectory (60) based on a current state of the aircraft, where the processor selectively concatenates selected ones of the predefined recovery mode segments (100) into a sequence and uses that sequence to generate the projected trajectory (60).

39. 发明申请

WO2019222525A1 TACTILE RESPONSIVE SURFACE FOR VIRTUAL REALITY TRAINING DEVICE 审中-公开
公开(公告)号：WO2019222525A1
公开(公告)日：2019-11-21
申请号：PCT/US2019/032703
申请日：2019-05-16
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： NUSBAUM, Chris , TOLER, Brian , TOLBERT, Casey
IPC分类号： G09B9/30 , G09B9/16
摘要： An input device for providing user input to a computing device includes a seat portion allowing a user to sit on the device. The input device further includes several human interface devices having positional sensors that detect changes in rotation or translation of a movable tactile surface with respect to a fixed tactile surface and provide a signal indicative thereof. These signals are used are used by a computer to change an image of virtual fixed and movable surfaces within a head mounted display.

40. 发明申请

WO2019099545A1 POTENTIAL AIRCRAFT TRAJECTORY WIND EFFECT COMPUTATION 审中-公开
公开(公告)号：WO2019099545A1
公开(公告)日：2019-05-23
申请号：PCT/US2018/061090
申请日：2018-11-14
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： PROSSER, Kevin
IPC分类号： G05D1/00 , G06F19/00
摘要： Systems, aircraft, and non-transitory media are provided. An avionics system for an aircraft includes a storage device and one or more data processors. The storage device stores instructions for monitoring an actual performance of the aircraft. The one or more data processors are configured to execute the instructions to: generate a lateral component and a longitudinal component of a measured moving air mass relative to the aircraft; generate a plurality of wind independent positions of the aircraft along a potential aircraft trajectory based on a prediction model; and generate a plurality of wind corrected positions of the aircraft based on the plurality of wind independent positions, on the lateral component, and on the longitudinal component.

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