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81. 发明授权

US07172157B2 Increasing the performance of aircraft on-board inert gas generating systems by turbocharging 有权
公开(公告)号：US07172157B2
公开(公告)日：2007-02-06
申请号：US11366872
申请日：2006-03-01
申请人： Philip E. Jones
发明人： Philip E. Jones
IPC分类号： B64D37/00
CPC分类号： B64D37/32 , A62B7/14 , Y10S261/02
摘要： A modular, on-board, inert gas generating system for aircraft is disclosed in which main components such as a heat exchanger, filter, air separation module, and turbocharger are provided in a modular unit sized to provide a variable flow of nitrogen-enriched air to the aircraft spaces to be inerted. For different inert gas requirements, for example in larger aircraft, multiple modular units may be provided without redesigning the basic system. A method for inerting fuel tanks, cargo holds and other void spaces using the modular approach and turbocharged engine bleed air is also disclosed.

82. 发明授权

US07137598B2 In-flight refueling system, sensor system and method for damping oscillations in in-flight refueling system components 有权
标题翻译：飞行中加油系统，传感器系统和用于阻尼飞行加油系统部件振荡的方法
公开(公告)号：US07137598B2
公开(公告)日：2006-11-21
申请号：US10927217
申请日：2004-08-26
申请人： German Von Thal
发明人： German Von Thal
IPC分类号： G01C3/00 , B64D37/00
CPC分类号： B64D39/02 , B64D39/00
摘要： An in-flight refueling system, sensor system and method are provided for detecting and damping changes in the disposition of an elongate hose extending from a tanker aircraft during an in-flight refueling operation. The various embodiments provide a compact, lightweight, and low-profile sensor device that may be fitted to the elongate hose so as to detect oscillations in the elongate hose and transmit a signal to a hose retracting device carried by the tanker aircraft such that the hose retracting device retracts the elongate hose in response to the signal so as to counteract the occurrence of oscillations within the elongate hose. Thus, these embodiments may minimize the effect of oscillations in the elongate hose by selectively retracting the elongate hose in response to oscillations detected therein as it extends from the tanker aircraft during an in-flight refueling operation.
摘要翻译：提供了一种飞行中加油系统，传感器系统和方法，用于在飞行中加油操作期间检测和阻止从油罐飞机延伸的细长软管的布置变化。各种实施例提供了紧凑，重量轻且薄型的传感器装置，其可以装配到细长软管，以便检测细长软管中的振荡并将信号传输到由油船飞行器承载的软管回缩装置，使得软管回缩装置响应于信号缩回细长软管，以抵消细长软管内的振荡的发生。因此，这些实施例可以通过在飞行中加油操作期间响应于其中检测到的振荡从油罐飞机延伸而选择性地缩回细长软管来最小化细长软管中的振荡的影响。

83. 发明授权

US06988693B2 Methods and apparatus for passive illumination of refueling hoses 有权
标题翻译：加油软管被动照明的方法和装置
公开(公告)号：US06988693B2
公开(公告)日：2006-01-24
申请号：US10627900
申请日：2003-07-25
申请人： Mark A. Shelly
发明人： Mark A. Shelly
IPC分类号： B64D37/00
CPC分类号： B63B27/24 , B63B49/00 , B64D39/04 , F16L2201/60 , G01R31/008
摘要： Methods and apparatus for illumination of aerial refueling hoses are disclosed. In one embodiment, a conduit for transferring a flowable material includes a wall member. A plurality of reflective members are at least one of formed within an outer layer of the wall member and disposed on an outer surface of the wall member. The reflective members are adapted to at least partially reflect light incident thereon. In one aspect, the reflective members include reflective glass beads. In a further aspect, a first portion of the wall member has a first concentration of reflective members, and a second portion has a second concentration of reflective members.
摘要翻译：公开了用于照明空中加油软管的方法和装置。在一个实施例中，用于传送可流动材料的导管包括壁构件。多个反射构件是至少一个形成在壁构件的外层内并且设置在壁构件的外表面上的反射构件。反射构件适于至少部分地反射入射在其上的光。在一个方面，反射构件包括反射玻璃珠。在另一方面，壁构件的第一部分具有第一浓度的反射构件，并且第二部分具有第二浓度的反射构件。

84. 发明申请

US20050166983A1 Flush mounted waste disposal service panel assembly 审中-公开
标题翻译：嵌入式废物处理服务面板组件
公开(公告)号：US20050166983A1
公开(公告)日：2005-08-04
申请号：US10772043
申请日：2004-02-03
申请人： James Shaw , Philip Jones
发明人： James Shaw , Philip Jones
IPC分类号： B64D37/00 , G05D7/00
CPC分类号： B64C1/1453 , B64D11/02 , Y02T50/46 , Y10T137/6906
摘要： The waste disposal service panel assembly includes a housing, waste drain valve, rinse/fill valve, handle assembly and service panel door. The housing has a tubular side wall and a base near one end of the side wall. The waste drain valve is at least partially mounted within the housing through the base. The waste drain valve includes an outlet positioned within the housing and an inlet configured to couple to a waste collection tank within a aircraft. The service panel door is pivotally coupled to the housing near an end of the side wall remote from the base. The service panel door has an outer surface configured to substantially match an outer contour of the aircraft's skin, and an outer cap coupled to an inner surface of the service panel door. The outer cap is configured and dimensioned to mate with the outlet to seal the outlet when the service panel door is closed.
摘要翻译：废物处理维修面板组件包括壳体，排泄阀，冲洗/填充阀，手柄组件和维修面板门。壳体具有管状侧壁和靠近侧壁一端的底座。废物排放阀至少部分地通过底座安装在壳体内。废物排放阀包括位于壳体内的出口和配置成耦合到飞行器内的废物收集箱的入口。维修面板门可靠近靠近底座的侧壁的端部连接到壳体。维修面板门具有被配置为基本上匹配飞行器的皮肤的外轮廓的外表面和联接到维修面板门的内表面的外盖。外盖的构造和尺寸设计为与出口配合，以在维修面板门关闭时密封出口。

85. 发明授权

US06913228B2 Aircraft with active center of gravity control 有权
标题翻译：具有主动重心控制的飞机
公开(公告)号：US06913228B2
公开(公告)日：2005-07-05
申请号：US10656501
申请日：2003-09-04
申请人： Howard Lee , John M. Morgenstern , Hossein Aminpour
发明人： Howard Lee , John M. Morgenstern , Hossein Aminpour
IPC分类号： B64C17/10 , B64C30/00 , B64D37/00
CPC分类号： B64C30/00 , B64C17/10
摘要： A supersonic aircraft comprises a wing, a fuselage, a plurality of fuel tanks contained within the wing and/or fuselage, and a fuel transfer system communicatively coupled to the plurality of fuel tanks and capable of transferring fuel among the plurality of fuel tanks. The aircraft further comprises at least one sensor capable of indicating a flight parameter and a controller. The controller is coupled to the one or more sensors and to the fuel transfer system. The controller can transfer fuel among the plurality of fuel tanks and adjust the aircraft center of gravity to reduce trim drag and increase aircraft range.
摘要翻译：超音速飞机包括机翼，机身，容纳在机翼和/或机身内的多个燃料箱，以及燃料传输系统，其通信地联接到多个燃料箱并且能够在多个燃料箱之间传送燃料。飞机还包括能够指示飞行参数的至少一个传感器和控制器。控制器耦合到一个或多个传感器和燃料传输系统。控制器可以在多个燃料箱之间传输燃料，并调整飞机重心以减少修剪阻力并增加飞机范围。

86. 发明申请

US20050139727A1 METHOD AND ARRANGEMENT FOR AIRCRAFT FUEL DISPERSION 有权
标题翻译：用于飞机燃料分配的方法和装置
公开(公告)号：US20050139727A1
公开(公告)日：2005-06-30
申请号：US10708818
申请日：2004-03-26
申请人： Gregg Wozniak , David Lamb , Dung Le
发明人： Gregg Wozniak , David Lamb , Dung Le
IPC分类号： B64C17/10 , B64D37/00
CPC分类号： B64C17/10 , B64D37/00
摘要： Method and arrangement for dispersing fuel 62 within a fuel containment system 60 of an aircraft 30 including utilizing a fuel containment system on an aircraft that is located at least partially within a wing 34 of the aircraft and defines a reservoir portion 42 and a remote portion 44. Fuel is pumped during at least aircraft flight operation from the reservoir portion to the remote portion at a pumped rate 80, while simultaneously fuel that is contained in the remote portion of the fuel containment system is permitted to drain to the reservoir portion at a drainage rate 82. The drainage rate is less than the pumped rate. A fuel mass 64 is accumulated in the remote portion of the fuel containment system because of a difference between the pumped rate and the drainage rate and as a result, a counteractive moment 49 is induced in the aircraft that is opposingly directed to a lift moment 46 caused by wing-lift 45 during aircraft flight.
摘要翻译：将燃料62分散在飞行器30的燃料容纳系统60内的方法和装置，包括在飞行器上至少部分地位于飞行器的翼部34内的燃料密封系统，并且限定了储存器部分42和远端部分44 。在至少飞行器飞行操作期间，以泵送速率80从储存器部分向远程部分泵送燃料，同时容纳在燃料容纳系统的远程部分中的燃料以排水速率排放到储存器部分 82。排水率小于抽水率。由于抽吸速率和排水速率之间的差异，燃料块64积聚在燃料容纳系统的远端部分，结果是在相对于提升力矩46的飞行器中引起了反作用力矩49 在飞机飞行期间由机翼45引起。

87. 发明授权

US06866228B2 Aerial refueling hose reel drive controlled by a variable displacement hydraulic motor and method for controlling aerial refueling hose reel 有权
标题翻译：由可变排量液压马达控制的空中加油软管卷盘驱动器和用于控制空中加油软管卷盘的方法
公开(公告)号：US06866228B2
公开(公告)日：2005-03-15
申请号：US10199134
申请日：2002-07-22
申请人： Asher Bartov
发明人： Asher Bartov
IPC分类号： B64D39/02 , B64D37/00
CPC分类号： B64D39/02
摘要： The invention is a variable displacement hydraulic motor-controlled hose reel drive system for aerial refueling of a receiver aircraft from a tanker aircraft. The system includes a variable displacement hydraulic motor, a tachometer/position sensor, a reaction torque sensor and a microprocessor which, depending upon data received from the system's position and reaction torque sensors, sends appropriate signals to the motor. The invention is also a method for deploying a hose and drogue so as to reduce the likelihood that the hose would go into oscillation after initial engagement of a receiver aircraft's probe with the drogue. In an embodiment of the invention, the hose is retracted prior to hook up of the probe and drogue, and the force required to retract the hose is recorded. After initial engagement of the probe with the drogue, the hose is retracted until the force required to retract the hose rises to about the same force previously recorded.
摘要翻译：本发明是用于从油船飞机对接收机飞行器进行空中加油的可变排量液压马达控制软管卷盘驱动系统。该系统包括可变排量液压马达，转速计/位置传感器，反作用转矩传感器和微处理器，根据从系统位置接收的数据和反作用转矩传感器，向马达发送合适的信号。本发明还是一种用于部署软管和锥套的方法，以便降低在接收器飞机的探头与锥套最初接合之后软管将进入振荡的可能性。在本发明的一个实施例中，软管在钩住探头和脱水之前缩回，并且记录缩回软管所需的力。在探头与锥套初始接合后，软管将缩回，直到缩回软管所需的力上升至与之前记录的大致相同的力。

88. 发明授权

US6076769A Hybrid fuel containment structure 失效
标题翻译：混合燃料遏制结构
公开(公告)号：US6076769A
公开(公告)日：2000-06-20
申请号：US264606
申请日：1999-03-08
申请人： David Paul Gallegos
发明人： David Paul Gallegos
IPC分类号： B60K15/00 , B64D37/06 , B64D37/00
CPC分类号： B64D37/06 , B60K15/00
摘要： A fuel containment area, and method of forming the same are disclosed herein. A fuel containment area is defined in part by a vehicle interior structure, such as an aircraft wing. Portions of the fuel containment area are provided with elastomeric partial bladders or appliques to bridge sections of the vehicle interior structure, to provide additional container integrity, and/or to segregate fuel from certain areas of the vehicle interior, e.g., about electrical components, mechanical leakages, or high temperature areas. The appliques are sealed to the vehicle interior by flexible transition joints to define a continuous, hybrid fuel container.
摘要翻译：燃料密封区域及其形成方法在此公开。燃料容纳区部分地由车辆内部结构（例如飞机机翼）限定。燃料容纳区域的部分设置有弹性部分气囊或贴布+ E，acu e + EE以桥接车辆内部结构的部分，以提供额外的容器完整性和/或将燃料与车辆内部的某些区域分离例如关于电气部件，机械泄漏或高温区域。贴片+ E，acu e + EE通过柔性过渡接头密封到车辆内部，以限定连续的混合燃料容器。

89. 发明授权

US5723870A Fluid gauging apparatus using magnetostrictive sensor and stick gauge 失效
标题翻译：使用磁致伸缩传感器和棒规的流体测量装置
公开(公告)号：US5723870A
公开(公告)日：1998-03-03
申请号：US647328
申请日：1996-05-06
申请人： David Henry Crowne , Lisa Brackenbury Maurice , Frederick Lloyd Lichtenfels, II , Kip Joseph Freeman
发明人： David Henry Crowne , Lisa Brackenbury Maurice , Frederick Lloyd Lichtenfels, II , Kip Joseph Freeman
IPC分类号： B64D37/00 , G01D5/48 , G01F23/00 , G01F23/04 , G01F23/296 , G01F23/72 , G01F23/74 , G01N15/06
CPC分类号： G01F23/0061 , B64D37/00 , G01D5/48 , G01F23/04 , G01F23/2963 , G01F23/72 , G01F23/74
摘要： 057238701 Apparatus for detecting fluid level in a container, comprises a housing adapted to be disposed in the container; a float with an associated magnetic element, the float position corresponding to fluid level in the container; a magnetostrictive sensor disposed inside the housing; and a stick gauge disposed inside the housing; the magnetostrictive sensor and the stick gauge each being operable to determine the float position.
摘要翻译：用于检测容器中的液位的装置包括适于设置在容器中的壳体; 具有相关联的磁性元件的浮子，浮动位置对应于容器中的液位; 设置在所述壳体内的磁致伸缩传感器; 和设置在所述壳体内的棒规; 磁致伸缩传感器和粘度计每个都可操作以确定浮子位置。

90. 发明授权

US5573208A Paper kite with frame 失效
标题翻译：纸风筝框架
公开(公告)号：US5573208A
公开(公告)日：1996-11-12
申请号：US278944
申请日：1994-07-22
申请人： Andre Cassagnes
发明人： Andre Cassagnes
IPC分类号： A63H27/08 , B64D37/00
CPC分类号： A63H27/08
摘要： A kite of the type that comprises a main frame with longitudinal rods (10, 12, 13) and transverse rods (11, 11'), has a secondary frame comprising rods known as "whiskers" (2). These rods (2) are extended to meet at a junction point (22) located in the median plane of symmetry. According to a first embodiment, straps (23, 24), either elastic or not elastic, stretch these rods (2). According to a second embodiment, an additional sail forms a keel, this sail being stretched between the median longitudinal rod (10) and the point of junction (22).
摘要翻译：包括具有纵向杆（10,12,13）和横杆（11,11'）的主框架的类型的风筝具有包括被称为“晶须”（2）的棒的辅助框架。这些杆（2）被延伸以在位于中间对称平面的接合点（22）处相遇。根据第一实施例，弹性或非弹性的带（23,24）拉伸这些杆（2）。根据第二实施例，附加的帆形成龙骨，该帆在中间纵向杆（10）和接合点（22）之间拉伸。

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