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71. 发明申请

WO2007005658A3 STANDBY DISPLAY AIRCRAFT MANAGEMENT SYSTEM 审中-公开
公开(公告)号：WO2007005658A3
公开(公告)日：2007-01-11
申请号：PCT/US2006/025679
申请日：2006-06-30
申请人： GULFSTREAM AEROSPACE CORPORATION , FIRRA, Steven
发明人： FIRRA, Steven
IPC分类号： G05D1/00
摘要： One embodiment of the present invention includes an aircraft instrumentation system for a cockpit instrument panel having a first device associated with a first pilot of an aircraft and positioned on the instrument panel substantially in front of the first pilot. The first device may include a first display and a first controller, which may have a set of controls for controlling the first display and aircraft systems. The instrumentation system may also include a second device associated with a second pilot of the aircraft and positioned on the instrument panel substantially in front of the second pilot. The second device may include a second display and a second controller, which may have a set of controls for controlling the second display and the aircraft systems. The instrumentation may be configured such that at least one of the first display and the second display presents attitude, altitude and airspeed at all times.

72. 发明申请

WO2005074469A2 MITIGATION OF UNSTEADY PEAK FAN BLADE AND DISC STRESSES IN TURBOFAN ENGINES THROUGH THE USE OF FLOW CONTROL DEVICES TO STABILIZE BOUNDARY LAYER CHARACTERISTICS 审中-公开
标题翻译：通过使用流量控制装置来稳定边界层特性，在涡轮发动机中减轻非球面风扇叶片和盘条应力
公开(公告)号：WO2005074469A2
公开(公告)日：2005-08-18
申请号：PCT/US2004/042885
申请日：2004-12-20
申请人： GULFSTREAM AEROSPACE CORPORATION , MILLS, Robert , HENNE, Preston
发明人： MILLS, Robert , HENNE, Preston
IPC分类号： F01D5/14 , F04D29/38 , F04D29/66 , F04D29/68 , F15D1/12
CPC分类号： F04D29/384 , F01D5/145 , F04D29/668 , F04D29/681 , F05D2240/31 , F15D1/12 , Y02T50/673
摘要： Method and apparatus for providing a turbofan blade (40) adapted to initiate and control a boundary layer transition at a side surface of the blade (40) during operation as a component in a turbofan assembly (35). The turbofan 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 fix a positionally unstable laminar to turbulent boundary layer transition (24) at a location toward the trailing edge from the surface deviation during operation of the turbofan blade in the turbofan assembly. In this manner, fatigue inducing and/or structurally damaging unsteady aerodynamic forces experienced upon the blade and/or fan disc during operation are controlled, and the resultant fluctuating fan blade and disc peak stresses are mitigated.
摘要翻译：一种用于提供涡轮风扇叶片（40）的方法和装置，适于在作为涡扇风扇组件（35）中的部件操作期间启动和控制在叶片（40）的侧表面处的边界层转变。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），并且基本上光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风扇组件中的涡扇风扇叶片的操作期间，将位置不稳定的层流固定在朝向后缘的位置处的湍流边界层过渡（24）。以这种方式，控制在操作期间在叶片和/或风扇盘上经历的疲劳诱导和/或结构损坏的不稳定空气动力，并且减轻所产生的波动的风扇叶片和盘峰值应力。

73. 发明申请

WO2003064254A3 FUSELAGE SHAPING AND INCLUSION OF SPIKE ON A SUPERSONIC AIRCRAFT FOR CONTROLLING AND REDUCING SONIC BOOM 审中-公开
公开(公告)号：WO2003064254A3
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： B64C23/04
摘要： Method and apparatus for configuring and operating an aircraft (120) for minimizing sonic boom effects (180) at ground level (GL) during supersonic flight including configuring the aircraft so that in flight, with landing gear retracted, a lower aircraft profile (160) is substantially linear or slightly concave downward. A nose portion (162) of the aircraft is arranged so that an apex (163) 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 (166). Weak pressure disturbances (168) 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 (170) simultaneously generated and radiated above the aircraft. The weak pressure disturbances generated below the aircraft are controlled to minimized ground level sonic boom effects.

74. 发明申请

WO2020149907A2 ENGINE MOUNTED AIRCRAFT GEARBOX DISPOSED IN PYLON 审中-公开
公开(公告)号：WO2020149907A2
公开(公告)日：2020-07-23
申请号：PCT/US2019/057242
申请日：2019-10-21
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： FREUND, Donald , KLUTZKE, Douglas , KNIGHT, Michael , MUZYCHKA, Derek
摘要： An aircraft includes a fuselage, an engine, a pylon, a nacelle cowling, and a gearbox assembly. The engine is spaced apart from the fuselage and the pylon is disposed between the fuselage and the engine. The accessory gearbox is fixed to the engine and is at least partially disposed in the pylon.

75. 发明申请

WO2020046988A1 PREDICTIVE AIRCRAFT FLIGHT ENVELOPE PROTECTION SYSTEM 审中-公开
公开(公告)号：WO2020046988A1
公开(公告)日：2020-03-05
申请号：PCT/US2019/048404
申请日：2019-08-27
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： PROSSER, Kevin , LANDERS, Thomas , VAIDYA, Abhishek , SAKHAEI, Alborz , FINLAYSON, Blake
IPC分类号： G08G5/00 , G05D1/10 , G08G5/04
摘要： The aircraft threat envelope protection system employs a threat envelope data structure in a computer-readable medium that stores at least one trigger condition for each of a plurality of different types of threats associated with the aircraft, and modeled using a common schema. A processor computes plural different projected trajectories representing different possible aircraft paths through spacetime. The processor associates at least some of the plurality of the threats to specific trigger points in spacetime along each of the projected trajectories. The processor will deprecate ones of the projected trajectories when they are deemed not viable to recover from a threat. The processor initiates an aircraft protective response when all projected trajectories but one have been deprecated and the aircraft is within a predetermined proximity to the closest trigger point in spacetime along the non-deprecated trajectory.

76. 发明申请

WO2019099538A1 PERFORMANCE CAPABILITY DETERMINATION FOR AIRCRAFT 审中-公开
公开(公告)号：WO2019099538A1
公开(公告)日：2019-05-23
申请号：PCT/US2018/061081
申请日：2018-11-14
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： PROSSER, Kevin
IPC分类号： B64C13/16 , B64D43/02
摘要： Systems and aircraft are provided. An avionics system 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: determine a first measured value of a flight characteristic of the aircraft at a first position of the aircraft; execute at least one flight maneuver between the first position and a second position of the aircraft; generate a predicted energy change between the first position and the second position based on the at least one flight maneuver and an energy state model; determine a second measured value of the flight characteristic of the aircraft at the second position; and generate an adjustment to the energy state model based on the first measured value, the second measured value, and the predicted energy change.

77. 发明申请

WO2016065234A1 AIRCRAFT DOOR WITH COMPRESSIBLE HEADER 审中-公开
标题翻译：具有可压缩头的飞机门
公开(公告)号：WO2016065234A1
公开(公告)日：2016-04-28
申请号：PCT/US2015/057070
申请日：2015-10-23
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： DREW, Dale , WHALEN JR., Patrick Thomas
IPC分类号： B64D11/06
CPC分类号： B64D11/0696 , B60N2/10 , B64D11/064
摘要： The disclosed embodiments relate to an aircraft having an in-flight leveling system for a seat onboard the aircraft that includes a swivel mechanism providing selective rotational movement of the a rear portion of the seat to compensate for an angle of inclination of the aircraft during flight. A locking mechanism is coupled to the swivel mechanism to retain the seat in a first position for use on the ground and a second position for use during flight. An actuator moves the locking mechanism between a locked condition and an unlocked condition permitting the seat to move between the first position to the second position enabling the seat to be substantially level when the aircraft is on the ground and during flight.
摘要翻译：所公开的实施例涉及具有用于飞机上的座椅的飞行间调平系统的飞行器，其包括旋转机构，该旋转机构提供座椅的后部的选择性旋转运动，以补偿飞行中的飞行器的倾斜角度。锁定机构联接到旋转机构以将座椅保持在用于地面的第一位置和在飞行期间使用的第二位置。执行器将锁定机构移动到锁定状态和解锁状态之间，从而允许座椅在第一位置与第二位置之间移动，使得当飞行器在地面上和在飞行中时座椅能够基本上水平。

78. 发明申请

WO2015134182A1 NOSE LANDING GEAR ARRANGEMENTS INCLUDING A FLEXIBLE SHEET AND METHODS FOR MAKING THE SAME 审中-公开
标题翻译：包括柔性片的SE ING ING ING AR ET ET ET AME AME AME AME AME AME AME AME AME
公开(公告)号：WO2015134182A1
公开(公告)日：2015-09-11
申请号：PCT/US2015/016188
申请日：2015-02-17
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： COOK, Brian , LOUIS, John , VAN DE VEN, Thomas , VIEITO, Robert, M.
IPC分类号： B64C25/16
CPC分类号： B64C25/14 , B64C25/001 , B64C25/34 , B64C2025/003
摘要： Nose landing gear arrangements for aircrafts, aircrafts including such nose landing gear arrangements, and methods for making such nose landing gear arrangements are provided. In one example, a nose landing gear arrangement includes a wheel assembly and a main strut. The main strut is operatively coupled to the wheel assembly and is configured to move between an extended position and a retracted position. The main strut in the extended position extends outside of the fuselage substantially along a generally vertical plane to position the wheel assembly for takeoff and/or landing of the aircraft. The main strut in the retracted position is disposed inside the fuselage. A flexible sheet is disposed adjacent to the main strut and is configured such that when the main strut is in the extended position the flexible sheet is positioned substantially around the main strut.
摘要翻译：提供了用于飞机的鼻子起落架装置，包括这种前起落架装置的飞机以及用于制造这种前起落架装置的方法。在一个示例中，前起落架布置包括车轮组件和主支柱。主支柱可操作地联接到车轮组件并且构造成在延伸位置和缩回位置之间移动。延伸位置的主支柱基本上沿着大致垂直的平面延伸到机身外部，以定位车轮组件以使飞行器起飞和/或降落。在缩回位置的主支柱设置在机身内部。柔性片被布置成与主支柱相邻，并且构造成使得当主支柱处于伸出位置时，柔性片基本上围绕主支柱定位。

79. 发明申请

WO2015109289A1 GROUND VEHICLE WARNING TO INDICATE PRESENCE OF AN OBSTACLE NEAR AN AIRCRAFT 审中-公开
标题翻译：地面车辆警告显示飞机附近的障碍物的存在
公开(公告)号：WO2015109289A1
公开(公告)日：2015-07-23
申请号：PCT/US2015/011943
申请日：2015-01-20
申请人： GULFSTREAM AEROSPACE CORPORATION
发明人： MARSDEN, Michael L. , MANOCHIO, Frank , WARD, James T. , KNIGHT, Michael D. , MEADE, Jason A. , GOOD, Jeff
IPC分类号： G08G1/16 , G08G5/04 , G08G5/06
CPC分类号： G08G5/045 , B64D45/00 , B64D47/02 , B64F1/225 , G08G5/025
摘要： The disclosed embodiments relate to avoiding a collision between an aircraft and an obstacle when the aircraft is being moved on a ground surface via a ground vehicle. Sensors can be mounted in and/or on the aircraft. The sensors can detect obstacles located in proximity to the aircraft and can communicate information to a processor on board the aircraft. When the processor determines that an obstacle is located in proximity to the aircraft, the processor generates a warning generator signal, which causes an apparatus to communicate a warning signal that is perceptible to an operator of the ground vehicle to warn the operator of the obstacle.
摘要翻译：所公开的实施例涉及当飞行器经由地面车辆在地面上移动时避免飞机和障碍物之间的碰撞。传感器可以安装在飞机上和/或飞机上。传感器可以检测位于飞机附近的障碍物，并可将信息传达给飞机上的处理器。当处理器确定障碍物位于飞行器附近时，处理器产生报警发生器信号，该信号使得设备传达对于地面车辆的操作者可以察觉到的警告信号，以警告操作者障碍物。

80. 发明申请

WO2015013057A1 METHODS AND SYSTEMS FOR DISPLAYING BACKUP AIRSPEED OF AN AIRCRAFT 审中-公开
标题翻译：显示飞机备用飞机的方法和系统
公开(公告)号：WO2015013057A1
公开(公告)日：2015-01-29
申请号：PCT/US2014/046599
申请日：2014-07-15
申请人： GULFSTREAM AEROSPACE CORPORATION , MENA, Mike , COLMENARES, Simon
发明人： MENA, Mike , COLMENARES, Simon
IPC分类号： G01S19/52
CPC分类号： G01P1/10
摘要： The disclosed embodiments relate to an aircraft that includes system for selecting an airspeed reference that is displayed within a cockpit of an aircraft. The system includes a processor and a display located in the cockpit. The processor is configured to determine whether primary airspeed is valid or invalid, and, to select a backup airspeed as the airspeed reference that is output to the display when it is determined that the primary airspeed is invalid. The display is configured to display the backup airspeed as the airspeed reference. The backup airspeed is generated based on Global Position System (GPS) information that is received by the aircraft.
摘要翻译：所公开的实施例涉及一种包括用于选择显示在飞行器的驾驶舱内的空速基准的系统的飞行器。该系统包括位于驾驶舱内的处理器和显示器。处理器被配置为确定主空速是有效还是无效，并且当确定主空速无效时，选择作为输出到显示器的空速基准的备用空速。显示器配置为将备用空速显示为空速参考。基于飞机接收的全球定位系统（GPS）信息产生备用空速。

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