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1. 发明申请

WO2020112200A3 A PROPULSION SYSTEM FOR AN AIRCRAFT, A NOZZLE FOR USE WITH THE PROPULSION SYSTEM, AND A METHOD OF MANUFACTURING A PROPULSION SYSTEM FOR AN AIRCRAFT 审中-公开
公开(公告)号：WO2020112200A3
公开(公告)日：2020-06-04
申请号：PCT/US2019/049811
申请日：2019-09-05
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： CONNERS, Timothy R.
IPC分类号： F02K1/34 , F02K1/06
摘要： A propulsion system for an aircraft includes: (1) an engine configured to generate a mass flow, (2) a nozzle having a pathway having a throat and a trailing edge, the throat or the trailing edge being configured to enlarge and contract, (3) a deployable obstructer disposed in the nozzle, (4) a first pressure sensor to sense the static pressure of the mass flow at the nozzle exit, (5) a second pressure sensor to sense the ambient pressure proximate the aircraft, and a (6) controller. The controller is coupled with the first and second pressure sensors, the deployable obstructer, and the throat or the trailing edge (whichever is configured to enlarge and contract). The controller receives the static and ambient pressures and when there is a disparity, the controller controls at least one of the deployable obstructer, the throat, and the trailing edge in a manner that reduces the disparity.

2. 发明申请

WO2020112200A2 A PROPULSION SYSTEM FOR AN AIRCRAFT, A NOZZLE FOR USE WITH THE PROPULSION SYSTEM, AND A METHOD OF MANUFACTURING A PROPULSION SYSTEM FOR AN AIRCRAFT 审中-公开
公开(公告)号：WO2020112200A2
公开(公告)日：2020-06-04
申请号：PCT/US2019/049811
申请日：2019-09-05
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： CONNERS, Timothy R.
IPC分类号： F02K1/15 , F02K1/12
摘要： A propulsion system for an aircraft includes: (1) an engine configured to generate a mass flow, (2) a nozzle having a pathway having a throat and a trailing edge, the throat or the trailing edge being configured to enlarge and contract, (3) a deployable obstructer disposed in the nozzle, (4) a first pressure sensor to sense the static pressure of the mass flow at the nozzle exit, (5) a second pressure sensor to sense the ambient pressure proximate the aircraft, and a (6) controller. The controller is coupled with the first and second pressure sensors, the deployable obstructer, and the throat or the trailing edge (whichever is configured to enlarge and contract). The controller receives the static and ambient pressures and when there is a disparity, the controller controls at least one of the deployable obstructer, the throat, and the trailing edge in a manner that reduces the disparity.

3. 发明申请

WO2017127504A1 AIRCRAFT AIR STAIR SUPPORT 审中-公开
公开(公告)号：WO2017127504A1
公开(公告)日：2017-07-27
申请号：PCT/US2017/014071
申请日：2017-01-19
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： HARP, Michael , MIKEAL, Quent
IPC分类号： B64C1/14 , B64C1/24 , B64D9/00 , B63B27/14
CPC分类号： B64C1/1423 , B63B27/14 , B64C1/1407 , B64C1/24 , B64D9/00
摘要： Air stair support systems, stair support cable assemblies, and hooks are disclosed herein. A stair support system includes, but is not limited to, an aircraft fuselage, a door seal, a stair door, and a stair support cable assembly. The aircraft fuselage defines a door frame and a stair hook receptacle. The stair door has a retracted position within the door frame and an extended position that forms an entry/exit stairway. The stair support cable assembly includes a cable and two hooks. The first hook includes a curved end portion configured to hook onto the stair hook receptacle, a cable end portion secured to the cable, and an intermediate portion having first and second intermediate legs that extend the intermediate portion away from the door seal when installed on the door frame and the stair door. The second hook is configured to hook on the stair door.
摘要翻译：这里公开了空气楼梯支撑系统，楼梯支撑电缆组件和钩子。楼梯支撑系统包括但不限于飞机机身，门密封件，楼梯门和楼梯支撑电缆组件。飞机机身定义了一个门框和一个楼梯吊钩插座。楼梯门在门框内具有缩回位置，并且形成入口/出口楼梯的延伸位置。楼梯支撑电缆组件包括一根电缆和两个钩子。第一钩包括弯曲的端部部分，该弯曲的端部部分构造成钩在楼梯吊钩容纳部上，电缆端部固定到电缆，以及中间部分，具有第一中间腿和第二中间腿，当安装在第一中间腿上时，门框和楼梯门。第二个挂钩配置为钩在楼梯门上。

4. 发明申请

WO2017027087A1 TRAILING EDGE COMPONENTS, AIRCRAFT STRUCTURES INCLUDING TRAILING EDGE COMPONENTS AND METHODS FOR MANUFACTURING TRAILING EDGE COMPONENTS 审中-公开
标题翻译：跟踪边缘部件，包括拖车边缘部件的飞机结构和制造牵引部件的方法
公开(公告)号：WO2017027087A1
公开(公告)日：2017-02-16
申请号：PCT/US2016/035431
申请日：2016-06-02
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： AUTRY, Brenden , WILLIAMS, Bryan , COPE, Travis , DAGGETT, Susan , MCKEE, Mike , RUSSO, Francis , AITKEN, Charles
IPC分类号： B64C3/26 , B32B3/26 , B64C3/20
CPC分类号： B64C3/28 , B32B1/00 , B32B3/263 , B32B5/024 , B32B5/06 , B32B5/26 , B32B7/12 , B32B2250/44 , B32B2260/021 , B32B2260/023 , B32B2260/046 , B32B2262/101 , B32B2262/106 , B32B2605/18 , B64C3/00 , B64C3/20 , B64C3/26 , B64C9/00 , B64C23/069 , Y02T50/164
摘要： Trailing edge components (23), aircraft structures comprising such trailing edge components, and methods of manufacturing such trailing edge components are provided. A trailing edge component (23) includes a first skin (24) comprising a first plurality of plies (35) of carbon fiber reinforced polymer material and having a first mating region (38). The first plurality of plies includes a first ply (44) with a first drop-off edge (37) in the first mating region. A second skin (26) includes a second plurality of plies (35) of carbon fiber reinforced polymer material and having a second mating region (38) affixed to the first mating region.
摘要翻译：提供后缘部件（23），包括这种后缘部件的飞行器结构以及制造这种后缘部件的方法。后缘部件（23）包括第一皮肤（24），其包括碳纤维增强聚合物材料的第一多个层（35）并具有第一配合区域（38）。第一多个层包括在第一配合区域中具有第一下落边缘（37）的第一层（44）。第二皮肤（26）包括碳纤维增强聚合物材料的第二多个层（35），并且具有固定到第一配合区域的第二配合区域（38）。

5. 发明申请

WO2016111871A1 SYSTEM ENABLING A PERSON TO SPEAK PRIVATELY IN A CONFINED SPACE 审中-公开
标题翻译：系统启动一个个人在一个确定的空间私人发言
公开(公告)号：WO2016111871A1
公开(公告)日：2016-07-14
申请号：PCT/US2015/067689
申请日：2015-12-28
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： MAXON, John W. , NEELY III, John J.
IPC分类号： G10K11/175
CPC分类号： G10L21/00 , G10K11/175
摘要： A system for enabling a person to speak privately in a confined space having a plurality of listening zones includes a sound-generating unit, a person-detecting unit configured to detect a first location of the person within the confined space and to generate a first signal containing information indicative of the first location, and a processor operatively coupled with the sound-generating unit and communicatively coupled with the person-detecting unit. The processor is configured to obtain the first signal from the person-detecting unit, to identify a first listening zone of the plurality of listening zones where the person is located based on the first signal, and to control the sound-generating unit to emit the sound into a second listening zone of the plurality of listening zones. The sound is configured to render a conversation had by the person in the first listening zone substantially inaudible from the second listening zone.
摘要翻译：一种用于使人能够在具有多个收听区域的有限空间中私下发言的系统包括：声音产生单元，人物检测单元，被配置为检测所述人在受限空间内的第一位置，并产生第一信号包含指示第一位置的信息，以及与声音产生单元可操作地耦合并与人物检测单元通信耦合的处理器。处理器被配置为从人物检测单元获得第一信号，以基于第一信号识别人所在的多个收听区域的第一收听区域，并且控制声音发生单元发出声音进入多个收听区域的第二监听区域。所述声音被配置为使得所述第一聆听区域中的人几乎不能从所述第二监听区域听到的对话。

6. 发明申请

WO2016076939A1 AIRCRAFT AND INSTRUMENTATION SYSTEM FOR VOICE TRANSCRIPTION OF RADIO COMMUNICATIONS 审中-公开
标题翻译：用于无线电通信语音转换的飞机和仪器系统
公开(公告)号：WO2016076939A1
公开(公告)日：2016-05-19
申请号：PCT/US2015/047217
申请日：2015-08-27
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： GASTON, Randy , WARD, James
IPC分类号： G10L15/26 , G08G5/00
CPC分类号： G10L15/26 , G08G5/0013 , G08G5/0021 , G10L25/48
摘要： Aircraft instrumentation systems, aircraft, and controllers are provided for transcribing radio communications. An aircraft instrumentation system and an aircraft include a radio device, a display device, and a controller. The controller is communicatively coupled with the radio device and the display device. The controller is configured to monitor the radio device and recognize a voice communication received over the radio device. The controller is further configured to generate an electronic transcript of the voice communication and control the display device to display a transcript of the voice communication.
摘要翻译：提供飞机仪表系统，飞机和控制器用于转录无线电通信。飞机仪表系统和飞机包括无线电设备，显示设备和控制器。控制器与无线电设备和显示设备通信地耦合。控制器被配置为监视无线电设备并识别通过无线电设备接收的语音通信。控制器还被配置为生成语音通信的电子录音，并且控制显示设备以显示语音通信的抄本。

7. 发明申请

WO2014126855A1 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：WO2014126855A1
公开(公告)日：2014-08-21
申请号：PCT/US2014/015585
申请日：2014-02-10
申请人： GULFSTREAM AEROSPACE CORPORATION , FREUND, Donald
发明人： FREUND, Donald
IPC分类号： B64C3/20
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 method of controlling a magnitude of a sonic boom caused by off-design condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist.
摘要翻译：控制由超音速飞行器在超音速下的非设计状态操作引起的声波爆震震级的方法包括但不限于在超音速和非设计状态下操作超音速飞行器的步骤。超音速飞机具有一对扫掠翼，其具有多个以一定角度定向的复合层，使得最大刚度的轴相对于该对扫掠翼的每个翼的后翼片不平行。该方法还包括但不限于在复合帘布层的脱离设计条件下以超音速速度降低由超音速飞行器操作引起的机翼扭转的步骤。该方法还包括但不限于通过减少机翼扭曲来最小化声音吊杆的大小。

8. 发明申请

WO2013122811A1 METHOD FOR ATTACHING A COMPONENT TO AN INTERNAL PORTION OF AN AIRCRAFT FUSELAGE 审中-公开
标题翻译：将组件连接到飞行器熔接件的内部部分的方法
公开(公告)号：WO2013122811A1
公开(公告)日：2013-08-22
申请号：PCT/US2013/025152
申请日：2013-02-07
申请人： LUCAS, Michael Eugene , GULFSTREAM AEROSPACE CORPORATION
发明人： LUCAS, Michael Eugene
IPC分类号： F16F13/24
CPC分类号： B64C1/403 , B23P19/10 , B23P2700/01 , F16B5/0692 , Y10T29/49826 , Y10T29/49895
摘要： A method for attaching a component to an internal portion of an aircraft fuselage is disclosed herein. The method includes, but is not limited to, mounting a vibration isolator assembly to the internal portion of the aircraft fuselage. The vibration isolator assembly has a protruding engagement portion having a flange. The method further includes, but is not limited to defining an opening in a vibration-deadening body. The method further includes, but is not limited to positioning the vibration-deadening body over the vibration isolator such that the protruding engagement portion is received within the opening. The method further includes, but is not limited to pressing a retaining member onto the protruding engagement portion such that the retaining member engages the flange.
摘要翻译：本文公开了将部件附接到飞行器机身的内部的方法。该方法包括但不限于将防振器组件安装到飞行器机身的内部。隔振器组件具有突出的接合部分，其具有凸缘。该方法还包括但不限于在防振体中限定开口。该方法还包括但不限于将防振体定位在隔振器上方，使得突出接合部分被容纳在开口内。该方法还包括但不限于将保持构件按压到突出接合部分上，使得保持构件接合凸缘。

9. 发明申请

WO2013116447A1 METHODS AND SYSTEMS FOR REQUESTING AND RETRIEVING AIRCRAFT DATA DURING FLIGHT OF AN AIRCRAFT 审中-公开
标题翻译：在飞机飞行期间要求和检索航空数据的方法和系统
公开(公告)号：WO2013116447A1
公开(公告)日：2013-08-08
申请号：PCT/US2013/024025
申请日：2013-01-31
申请人： O'DELL, Robert , GALLAGHER, Jim , CONZACHI, Keith , BRITT, Noëlle , KEREKESH, William , GEARY, Robert J. , GULFSTREAM AEROSPACE CORPORATION
发明人： O'DELL, Robert , GALLAGHER, Jim , CONZACHI, Keith , BRITT, Noëlle , KEREKESH, William , GEARY, Robert J.
IPC分类号： G06F7/70
CPC分类号： B64D45/00 , B64D2045/0085 , B64F5/60 , G08G5/0013 , H04B7/18508 , H04L67/125
摘要： The disclosed embodiments relate to methods and systems for requesting and retrieving aircraft data during flight of an aircraft. This aircraft data can be used to perform additional monitoring of aircraft sub-systems to detect an abnormal condition, and/or to identify one or more sources that are causing the abnormal condition. In one embodiment, aircraft data for one or more relevant parameters can be requested from the ground, measured on-board the aircraft, and stored in a data file that is then communicated back to personnel on the ground. The real-time aircraft data for one or more relevant parameters can then be analyzed to identify the one or more sources that are causing the abnormal condition.
摘要翻译：所公开的实施例涉及用于在飞行器飞行期间请求和检索飞行器数据的方法和系统。该飞行器数据可以用于对飞行器子系统执行附加监视以检测异常状况，和/或识别导致异常状况的一个或多个源。在一个实施例中，用于一个或多个相关参数的飞行器数据可以从飞机上的地面请求，并存储在数据文件中，然后将数据文件传回给地面上的人员。然后可以分析用于一个或多个相关参数的实时飞行器数据，以识别导致异常状况的一个或多个源。

10. 发明申请

WO2013116139A1 METHODS AND SYSTEMS FOR AIRCRAFT HEALTH AND TREND MONITORING 审中-公开
标题翻译：用于航空卫生和趋势监测的方法和系统
公开(公告)号：WO2013116139A1
公开(公告)日：2013-08-08
申请号：PCT/US2013/023396
申请日：2013-01-28
申请人： Gallagher, James , O'Dell, Robert , GULFSTREAM AEROSPACE CORPORATION
发明人： Gallagher, James , O'Dell, Robert
IPC分类号： G06F17/00
CPC分类号： B64F5/60 , B64D2045/0085
摘要： The disclosed embodiments relate to methods and systems for monitoring sub-systems of an aircraft to detect an abnormal condition, and for identifying one or more sources that are causing the abnormal condition. In response to detecting a trigger event during flight of the aircraft, data for a plurality of relevant parameters is measured and stored in a parameter file. The parameter file is transmitted from the aircraft over a wireless communication link, and relayed to a ground support network. At the ground support network, the measured data for the plurality of the relevant parameters is then used to identify the one or more sources that are causing the abnormal condition.
摘要翻译：所公开的实施例涉及用于监视飞机的子系统以检测异常状况以及用于识别导致异常状况的一个或多个源的方法和系统。响应于在飞行器飞行期间检测到触发事件，测量多个相关参数的数据并将其存储在参数文件中。参数文件通过无线通信链路从飞机发送，并转发到地面支持网络。在地面支持网络中，然后使用多个相关参数的测量数据来识别引起异常状况的一个或多个源。

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