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91. 发明申请

WO2013062664A2 NOZZLE ARRANGEMENT AND METHOD OF MAKING THE SAME 审中-公开
标题翻译：喷嘴布置及其制造方法
公开(公告)号：WO2013062664A2
公开(公告)日：2013-05-02
申请号：PCT/US2012/051458
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： F02K1/46
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： A nozzle arrangement is disclosed herein for use with a supersonic jet engine that is configured to produce a plume of exhaust gases. The nozzle arrangement includes, but is not limited to, a nozzle having a trailing edge and a plug body partially positioned within the nozzle. The plug body has an expansion surface and a compression surface downstream of the expansion surface. A protruding portion of the plug body extends downstream of the trailing edge for a length greater than a conventional plug body length. The plug body is configured to shape the exhaust gases to flow substantially parallel to a free stream of air flowing off of the trailing edge of the nozzle and to cause the plume of exhaust gases to isentropically turn the free stream of air to move in a direction parallel to a longitudinal axis of the plug body.
摘要翻译：本文公开了一种与配置成产生一排废气的超音速喷气发动机一起使用的喷嘴装置。喷嘴装置包括但不限于具有后缘和部分地位于喷嘴内的塞体的喷嘴。塞体具有膨胀表面和膨胀表面下游的压缩表面。插塞体的突出部分延伸到后缘的下游一段长度比常规的塞体长度。塞体构造成使废气成形为基本上平行于从喷嘴的后缘流出的自由空气流流动，并使排气的羽流等熵地将空气流转向平行于插头主体的纵向轴线。

92. 发明申请

WO2011056795A2 LOW VISIBILITY LANDING SYSTEM AND METHOD 审中-公开
标题翻译：低能见度着陆系统和方法
公开(公告)号：WO2011056795A2
公开(公告)日：2011-05-12
申请号：PCT/US2010/055144
申请日：2010-11-02
申请人： GULFSTREAM AEROSPACE CORPORATION , TAKACS, Robert, S. , FREEMAN, Gary, M.
发明人： TAKACS, Robert, S. , FREEMAN, Gary, M.
IPC分类号： B64D45/04 , G08G5/02 , G01C21/00
CPC分类号： G05D1/0676 , G08G5/0021 , G08G5/025
摘要： Examples of the present invention may include a low visibility landing system for guiding aircraft on landing approaches. The low visibility landing system may aid a pilot during landing in low visibility conditions such that an aircraft may descend to lower altitudes without visual contact with the runway than is possible with other landing systems. The system may use various navigational systems to produce a hybrid signal that may be more stable than individual signals of those navigational systems. The hybrid signal is compared to a predetermined landing approach plan to determine the deviation of the aircraft from the landing approach plan and to provide guidance to the pilot to get the aircraft back onto the landing approach plan. The system may also use multiple navigational systems to perform checks on an operation of a primary navigational system to ensure that the primary navigational system is operating accurately.
摘要翻译：本发明的示例可以包括用于在着陆进近时引导飞机的低能见度着陆系统。低能见度着陆系统可以在低能见度条件着陆期间帮助飞行员，使得飞机可以降低到与降落跑道没有视觉接触的降低高度，而不是与其他着陆系统可能降低的高度。该系统可以使用各种导航系统来产生混合信号，该混合信号可能比那些导航系统的单个信号更稳定。将混合信号与预定的着陆进场计划进行比较，以确定飞机与着陆进场计划的偏差并为飞行员提供引导以使飞机返回到着陆进场计划。该系统还可以使用多个导航系统来对主导航系统的操作进行检查，以确保主导航系统正确地运行。

93. 发明申请

WO2009085380A2 LOW SHOCK STRENGTH INLET 审中-公开
标题翻译：低冲击强度入口
公开(公告)号：WO2009085380A2
公开(公告)日：2009-07-09
申请号：PCT/US2008/081055
申请日：2008-10-24
申请人： GULFSTREAM AEROSPACE CORPORATION , CONNERS, Timothy, R.
发明人： CONNERS, Timothy, R.
IPC分类号： F02C7/04
CPC分类号： B64D33/02 , B64D29/00 , B64D33/06 , B64D2033/026 , B64D2033/0273 , F02C7/042 , F02C7/045 , F02K3/025 , F02K7/16 , F05D2220/80 , Y02T50/672 , Y10T137/0368 , Y10T137/0536
摘要： Embodiments of the invention relate to a supersonic inlet having a cowl lip configured to capture the conic shock and exhibit a zero or substantially zero cowl angle. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft while allowing for an increase in engine pressure recovery and a subsequent improvement in generated thrust by the engine.
摘要翻译：本发明的实施例涉及一种超音速入口，其具有被配置为捕获圆锥冲击并且呈现零或基本零前导角的整流罩口。入口可以被配置为采用松弛的等熵压缩表面和内部旁路。机舱旁路可以防止由锥形冲击的捕获引入的流动变形到达涡轮机械，从而允许整流罩角度减小到零或基本为零。这样的前导角度可以减小入口对超音速飞行器的整体声波爆震特征的贡献，同时允许发动机压力恢复增加，并随后改善发动机产生的推力。

94. 发明申请

WO2009055041A3 LOW SHOCK STRENGTH PROPULSION SYSTEM 审中-公开
公开(公告)号：WO2009055041A3
公开(公告)日：2009-04-30
申请号：PCT/US2008/012129
申请日：2008-10-24
申请人： GULFSTREAM AEROSPACE CORPORATION , CONNERS, Timothy, R.
发明人： CONNERS, Timothy, R.
IPC分类号： B64D33/02
摘要： Embodiments of the invention relate to a supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine. By shaping the nacelle, embodiments of the invention may function to reduce sonic boom strength, cowl drag, and/or airframe interference drag. Embodiments of the invention may also function to improve total pressure recovery and/or total thrust of the primary flow path through the engine.

95. 发明申请

WO2008045108A2 ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT 审中-公开
标题翻译：超音速飞行器的等值压缩进口
公开(公告)号：WO2008045108A2
公开(公告)日：2008-04-17
申请号：PCT/US2006/047738
申请日：2006-12-15
申请人： GULFSTREAM AEROSPACE CORPORATION , HENNE, Preston, A. , CONNORS, Timothy, R. , HOWE, Donald, C.
发明人： HENNE, Preston, A. , CONNORS, Timothy, R. , HOWE, Donald, C.
IPC分类号： B64D33/02
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： Embodiments of the invention relate to a supersonic inlet employing relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Using supersonic inlets in accordance with the invention also demonstrated reductions in peak sonic boom overpressure while maintaining performance.
摘要翻译：本发明的实施例涉及采用松弛等熵压缩的超音速入口，以通过成形入口的压缩表面来改善净推进力。入口压缩表面的轻松等熵压缩成形用于减小罩边唇面角度，从而改善入口阻力特性和干扰阻力特性。根据本发明使用超音速进气口还证明了在保持性能的同时降低了峰值超音速超压。

96. 发明申请

WO2004074094A2 SYSTEM AND METHOD FOR AIRCRAFT CABIN ATMOSPHERIC COMPOSITION CONTROL 审中-公开
标题翻译：用于航空仓库大气成分控制的系统和方法
公开(公告)号：WO2004074094A2
公开(公告)日：2004-09-02
申请号：PCT/US2004/004582
申请日：2004-02-17
申请人： GULFSTREAM AEROSPACE CORPORATION , GEARY, Robert
发明人： GEARY, Robert
IPC分类号： B64D
CPC分类号： B64D13/06 , B64D2013/0681
摘要： Method and arrangement for adjusting nitrogen and oxygen concentrations within regions of an aircraft. The method includes separating nitrogen from ambient air onboard an aircraft thereby establishing a high-concentration nitrogen supply and then dispensing high-concentration nitrogen from the supply to a fire-susceptible, non-habitable region of the aircraft where the high-concentration nitrogen is reservoired thereby decreasing the capability for the atmosphere therein to support combustion. Oxygen is also separated from the ambient air thereby establishing a high-concentration oxygen supply that is dispensed to an occupant cabin of the aircraft thereby increasing the level of oxygen concentration within the cabin to a level greater than the naturally occurring concentration of oxygen at the experienced internal cabin pressure. When it is determined that reduced oxygen concentration is required in the occupant cabin, the reservoired high-concentration nitrogen is moved into the passenger cabin diluting the oxygen-elevated environment.
摘要翻译：调整飞机区域内氮和氧浓度的方法和装置。该方法包括从飞机上的环境空气中分离氮气，从而建立高浓度氮气供应，然后将高浓度氮气从供应部分分配到高浓度氮气储存的飞机的易燃，不可居住区域从而降低其中的气氛的能力以支持燃烧。氧气也与环境空气分离，从而建立高浓度氧气供应，其被分配到飞行器的乘员舱，从而将舱室内的氧浓度水平提高到大于经验的氧气的天然存在浓度内部舱内压力。当确定在乘员舱中需要降低的氧浓度时，将储存的高浓度氮气移动到乘客舱中，以稀释氧气升高的环境。

97. 发明申请

WO2003064254A2 FUSELAGE SHAPING AND INCLUSION OF SPIKE ON A SUPERSONIC AIRCRAFT FOR CONTROLLING AND REDUCING SONIC BOOM 审中-公开
标题翻译： FUSELAGE形状和包装在超音速飞机上控制和减少SONIC BOOM
公开(公告)号：WO2003064254A2
公开(公告)日：2003-08-07
申请号：PCT/US2003/002631
申请日：2003-01-30
申请人： GULFSTREAM AEROSPACE CORPORATION , HENNE, Preston , HOWE, Donald , WOLZ, Robert , HANCOCK, Jimmy, Jr.
发明人： HENNE, Preston , HOWE, Donald , WOLZ, Robert , HANCOCK, Jimmy, Jr.
IPC分类号： B64D
CPC分类号： B64C23/04 , B64C30/00
摘要： Method and apparatus for configuring and operating an aircraft for minimizing sonic boom effects at ground level during supersonic flight of the aircraft including configuring the aircraft so that in flight, with landing gear retracted, a lower profile of the aircraft is substantially linear or slightly concave downward. A nose portion of the aircraft is arranged so that an apex thereof is coincident with the lower profile of the aircraft. The aircraft is flown at supersonic speed and oriented during supersonic flight so that the substantially linear lower profile of the aircraft is oriented substantially parallel to onset airflow. Weak pressure disturbances are generated below the aircraft, and waves thereof are radiated below the aircraft toward the ground. These disturbances below the aircraft are of lesser magnitude than pressure disturbances simultaneously generated and radiated above the aircraft. The weak pressure disturbances generated below the aircraft are controlled so that differentials thereamong are sufficiently minimized that ground level sonic boom effects are minimized during supersonic flight. In a second aspect, a retractable spike is included at the nose or rear of the aircraft for minimizing sonic boom effects at ground level during supersonic flight.
摘要翻译：用于配置和操作飞行器的方法和装置，用于使飞机的超音速飞行期间在地平面处的声波起伏效应最小化，包括构造飞行器，使得在飞行中，随着起落架缩回，飞行器的下部轮廓基本上线性或略微向下凹。飞行器的鼻部被布置成使其顶点与飞行器的下轮廓重合。飞行器以超音速飞行并且在超音速飞行期间定向，使得飞行器的基本线性的下部轮廓基本上平行于起始气流取向。在飞机下面产生弱压力扰动，其波浪在飞机下方朝向地面辐射。飞机以下的这些干扰比同时产生和辐射在飞机上方的压力扰动小得多。控制飞机以下产生的弱压力扰动，使得它们之间的差异足够地最小化，使得在超音速飞行期间地面声级爆轰效应最小化。在第二方面，在飞行器的鼻子或后部包括可伸缩尖峰，以便在超音速飞行期间最小化在地平面处的声波起伏效应。

98. 发明授权

US11580864B2 Take-off performance prediction and alerting system 有权
公开(公告)号：US11580864B2
公开(公告)日：2023-02-14
申请号：US16947852
申请日：2020-08-20
申请人： Gulfstream Aerospace Corporation
发明人： Thomas C. Horne , Thomas F. Landers , Thomas P. Lavrisa , Suzanne Swaine
IPC分类号： G08G5/00 , B64D43/00 , B64D45/00
摘要： The aircraft take-off awareness system predicts and informs the pilot about where on the runway certain safety speeds will be achieved. A processor coupled to receive inertial data from the aircraft computes an aircraft weight estimate based at least in part upon the inertial data. The processor then computes a future acceleration prediction based on the computed aircraft weight estimate. Using the future acceleration prediction, the processor then computes the position of various warning reference distances corresponding to predicted positions on the runway at which said certain safety speeds will be achieved. The processor generates a display that it dynamically updates as the reference distances change as the aircraft proceeds down the runway during take-off or aborted take-off.

99. 发明授权

US11549295B2 Cabinet and method for making the same, and aircraft including a cabinet 有权
公开(公告)号：US11549295B2
公开(公告)日：2023-01-10
申请号：US16554178
申请日：2019-08-28
申请人： Gulfstream Aerospace Corporation
发明人： Timothy Allen Davis , Timothy O'Hara
IPC分类号： E05D15/56 , B64D11/00 , E05D13/00 , E05F3/22
摘要： Cabinets, methods for making cabinets, and aircraft including cabinets are provided. In one example, a cabinet includes a cabinet body that at least partially surrounds a cabinet space and that defines a cabinet opening that allows access to the cabinet space. A cabinet door at least partially covers the cabinet opening when in a closed position and extends upward from a lower edge portion to an upper edge portion. The cabinet door has an outer exposed surface facing generally in a first direction away from the cabinet space when in the closed position. The cabinet door is operatively coupled to the cabinet body for opening from the closed position to an open position including the lower edge portion moving generally upward and the upper edge portion moving generally upward and towards the first direction to expose the cabinet opening.

100. 发明授权

US11545126B2 Arrangements and methods for enhanced communication on aircraft 有权
公开(公告)号：US11545126B2
公开(公告)日：2023-01-03
申请号：US16355390
申请日：2019-03-15
申请人： Gulfstream Aerospace Corporation
发明人： Bethany Davis , Amy Mayo , Scott Bohanan , Jim Jordan , John Maxon , Paul Conti , Tongan Wang
IPC分类号： G10K11/178 , B64D47/00
摘要： Arrangements for communication and/or noise attenuation within an aircraft, and aircraft and methods for making aircraft including such arrangements are provided. In one example, an arrangement includes an array of first microphones cooperatively configured to be directed towards a first aircraft operator when disposed in a first cockpit seat to receive a first communication input from the first aircraft operator. An array of first speakers is cooperatively configured to be directed towards the first aircraft operator when disposed in the first cockpit seat to provide a first communication output to the first aircraft operator.

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