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1. 发明授权

US06293498B1 Hybrid deicing system and method of operation 失效
标题翻译：混合除冰系统及其操作方法
公开(公告)号：US06293498B1
公开(公告)日：2001-09-25
申请号：US09507404
申请日：2000-02-18
申请人： John Stanko , Lowell Pearson
发明人： John Stanko , Lowell Pearson
IPC分类号： B64D1500
CPC分类号： B64F5/23 , B64F5/20
摘要： This invention overcomes the disadvantage of the prior systems and produces a high velocity specially formed and constituted pressure aerodynamic stream system for efficiently and effectively removing ice from an aircraft. The specially formed stream system includes a stream within a stream, wherein a deicing fluid such a glycol is entrained within and encased by a surrounding jacket of entraining fluid such as air. This deicing is now known as coaxial stream/stream within a stream deicing. The special nozzle allows the stream to maintain fluid separation over its flight path so that aircraft contact is made by to be known as coaxial stream/stream within a stream deicing. The coaxial stream/stream within a stream deicing is further enhanced by pressurizing the stream to deliver the stream as a high pressure, high velocity stream to improve the aerodynamic sweeping action of the airstream.
摘要翻译：本发明克服了现有系统的缺点，并且产生高速特别形成和构成的压力空气动力流系统，用于有效地和有效地从飞机上去除冰。特殊形成的流系统包括流内的流，其中除冰流体如二醇被夹带在夹带流体例如空气的周围夹套内。这种除冰现在被称为流除冰中的同轴流/流。专用喷嘴允许流在其飞行路径上保持流体分离，使得飞行器接触通过在流除冰中被称为同轴流/流来制造。通过对流进行加压来进一步增强流除冰中的同轴流/流，以将流作为高压高速流输送以改善气流的气动扫荡动作。

2. 发明授权

US06209823B1 Apparatus and method for deicing aircraft 失效
标题翻译：飞机除冰装置及方法
公开(公告)号：US06209823B1
公开(公告)日：2001-04-03
申请号：US09392701
申请日：1999-09-09
申请人： Clifton L. Foster
发明人： Clifton L. Foster
IPC分类号： B64D1500
CPC分类号： B60S3/002 , B64F5/20 , B64F5/23
摘要： An apparatus for deicing includes a vehicle frame, such as part of a truck, and a boom having one end mounted on the vehicle frame and a free end. A compressor unit is supported by the boom and includes a compressor having an air outlet. A deicer air jet nozzle is located at the free end of the boom and operatively coupled to the air outlet of the compressor for receiving air and discharging the air for a deicer application.
摘要翻译：用于除冰的装置包括诸如卡车的一部分的车架和具有安装在车架上的一端和自由端的吊杆。压缩机单元由起重臂支撑并且包括具有出气口的压缩机。除冰机空气喷嘴位于起重臂的自由端处并且可操作地联接到压缩机的空气出口，用于接收空气并排出用于除冰机应用的空气。

3. 发明授权

US06196500B1 Hybrid ice protection system for use on roughness-sensitive airfoils 有权
标题翻译：用于粗糙度敏感翼型的混合防冰系统
公开(公告)号：US06196500B1
公开(公告)日：2001-03-06
申请号：US09330444
申请日：1999-06-11
申请人： Kamel M. Al-Khalil , Thomas F. W. Ferguson
发明人： Kamel M. Al-Khalil , Thomas F. W. Ferguson
IPC分类号： B64D1500
CPC分类号： B64D15/16 , B64D15/163
摘要： An electro-thermal or hot gas anti-icer of the “running-wet” type is mounted at the leading edge of an airfoil. Mechanical de-icers are mounted on the surfaces aft of the anti-icer. The mechanical de-icers throw off ice without creating runback water, thereby eliminating runback refreeze ridges caused by a known hybrid ice-protection system. Advantageously, the de-icers are of a type in which the airfoil has a semi-rigid skin that forms an aerodynamic surface of the airfoil, and in which there is at least one mechanical actuator for flexing the skin.
摘要翻译： “跑步湿式”类型的电热或热气体防冰器安装在翼型的前缘。机械除冰器安装在防冰板后面的表面上。机械除冰器在不产生回流水的情况下扔冰，从而消除由已知的混合防冰系统引起的回流重冰脊。有利地，除冰器是其中翼型件具有半刚性皮肤的类型，其形成翼型件的空气动力学表面，并且其中存在至少一个用于使皮肤弯曲的机械致动器。

4. 发明授权

US06832742B2 System and method for an electrical de-icing coating 有权
标题翻译：电除冰涂层的系统和方法
公开(公告)号：US06832742B2
公开(公告)日：2004-12-21
申请号：US10169533
申请日：2002-11-07
申请人： Victor Petrenko , Lev Deresh
发明人： Victor Petrenko , Lev Deresh
IPC分类号： B64D1500
CPC分类号： B63J99/00 , B64D15/12 , B64D15/163 , E01C11/265 , H05B3/347 , H05B2203/005 , H05B2203/007 , H05B2203/011 , H05B2203/013 , H05B2203/017 , H05B2214/02
摘要： A system for modifying ice adhesion strength of ice adhered to an object comprises a composite coating containing wire electrodes covering the surface to be protected. In one embodiment, a composite coating contains electrode wires and insulator fibers. The composite coating is applied to the surface of an object on which the ice adhesion strength is to be modified. The electrode wires are connected to a dc bias source, and they function as cathodes and anodes alternately. The source generates a DC bias to an interface between the ice and the surface when the ice completes the circuit between anode and cathode wires. In another embodiment, a wire mesh is disposed on an electrically conductive surface of the object an opposing DC biases are applied to the mesh and the surface. In another embodiment, the coating has anode and cathode wires woven by insulator fibers as a composite cloth applied to the surface to protect the surface from ice.
摘要翻译：用于改变粘附到物体上的冰的粘附强度的系统包括含有覆盖被保护表面的线电极的复合涂层。在一个实施例中，复合涂层包含电极线和绝缘体纤维。将复合涂层施加到将要修饰冰粘附强度的物体的表面上。电极线连接到直流偏置源，并且它们交替地用作阴极和阳极。当冰完成阳极和阴极电线之间的电路时，源会向冰和表面之间的界面产生直流偏压。在另一个实施例中，金属丝网设置在物体的导电表面上，相反的DC偏压被施加到网和表面。在另一个实施例中，涂层具有由绝缘体纤维编织的阳极和阴极丝，作为施加到表面的复合布，以保护表面免受冰。

5. 发明授权

US06644594B1 Flight refueling guide 失效
标题翻译：飞行加油指南
公开(公告)号：US06644594B1
公开(公告)日：2003-11-11
申请号：US10294771
申请日：2002-11-12
申请人： Bruce P. Hunn , James D. Francey
发明人： Bruce P. Hunn , James D. Francey
IPC分类号： B64D1500
CPC分类号： B64D39/06 , B64D39/00
摘要： In an in-flight refueling system of an aircraft having a recess therein containing a slipway leading to a fuel inlet port, an improvement is provided in the form of a guideway having a) a pair of lead-in lines on the surface of the aircraft which taper and converge towards the slipway and port and b) a plurality of dashes or bars on the surface, spaced longitudinally between the lead-in lines, a desired distance apart, to provide visual cues in aiding an operator in guiding a fuel boom and nozzle from a refueling aircraft to the slipway and port of a fuel receiving aircraft, to provide a visually more salient means to achieve a quick and effective refueling hook-up while avoiding or minimizing nozzle strikes that can damage the aircraft, the boom or its nozzle.
摘要翻译：在具有凹槽的飞行器的飞行中加油系统中，其中包含通向燃料入口的滑道，提供了具有a）在飞行器表面上的一对引入线的导轨的形式的改进其朝向滑道和端口逐渐收敛并且b）表面上的多个虚线或条，在引入线之间纵向间隔开期望的距离，以提供视觉提示以帮助操作者引导燃料臂和喷嘴从加油飞机到燃料接收飞机的滑道和港口，以提供视觉上更显着的手段来实现快速有效的加油连接，同时避免或最小化可能损坏飞行器，悬臂或其喷嘴的喷嘴冲击。

6. 发明授权

US06443395B1 Air inlet cowl for a jet engine equipped with de-icing means 有权
标题翻译：配有除冰装置的喷气发动机的进气罩
公开(公告)号：US06443395B1
公开(公告)日：2002-09-03
申请号：US09924460
申请日：2001-08-09
申请人： Alain Porte , Stéphane Viala , Olivier Barbara
发明人： Alain Porte , Stéphane Viala , Olivier Barbara
IPC分类号： B64D1500
CPC分类号： B64D15/04
摘要： Air inlet cowl for a jet engine equipped with deicing means. According to the invention, the hollow leading edge (16) of said cowl (9) comprises a mixer (19) for forming, at each moment, a mixture of the stream of hot air (20) being injected and some, previously injected, of the stream of air that is recirculating. This evens out the temperature inside said leading edge (16), eliminating hot spots and optimizing the de-icing.
摘要翻译：用于具有除冰装置的喷气发动机的进气罩。根据本发明，所述罩（9）的中空前缘（16）包括混合器（19），用于在每一时刻形成热流的混合物空气（20）被注入，并且预先注入了正在再循环的空气流。这可以使所述前缘（16）内的温度升高，消除热点并优化除冰。

7. 发明授权

US06237874B1 Zoned aircraft de-icing system and method 有权
标题翻译：分区飞机除冰系统及方法
公开(公告)号：US06237874B1
公开(公告)日：2001-05-29
申请号：US09419466
申请日：1999-10-15
申请人： Robert B. Rutherford , Richard L. Dudman
发明人： Robert B. Rutherford , Richard L. Dudman
IPC分类号： B64D1500
CPC分类号： B64D15/14
摘要： An electrothermal zoned de-icing system for an aircraft employs a heat-conducting tape bonded to the leading edge of an aircraft structure subject to an impinging airstream during flight. The heat-conducting tape has a spanwise parting strip area, and first and second ice accumulation and shedding zones. The tape comprises a non-metallic electrical and heat-conducting layer consisting of flexible expanded graphite foil laminated to an outer heat-conducting layer, in which the thickness of the flexible expanded graphite foil layer in the parting strip area is always greater than the thickness of the foil layer in either of the ice accumulation and shedding zones. Therefore, the parting strip area has a decreased electrical resistance, a greater flow of current, and becomes hotter than the zones in which the foil layer is thinner. Because the flexible expanded graphite foil is a monolithic structure that may be shaped, sculptured or layered to form different thicknesses in different areas, only a single control mechanism for a single set of electric terminals is necessary to produce temperature differentials in the parting strip and ice accumulation and shedding zones for a cycled zoned de-icing system.
摘要翻译：用于飞行器的电热分区除冰系统采用在飞行期间接合撞击气流的飞行器结构的前缘结合的导热带。导热带具有翼展分离带区域，第一和第二冰积聚区域。胶带包括非金属电导热层，其由柔性膨胀石墨箔层压到外部导热层上，其中分离带区域中的柔性膨胀石墨箔层的厚度总是大于厚度的任何一个冰块和脱落区的箔层。因此，剥离带区域的电阻降低，电流流动更大，并且比箔层薄的区域变得更热。因为柔性膨胀石墨箔是可以成形，雕刻或分层以在不同区域中形成不同厚度的整体结构，所以仅需要用于单组电端子的单个控制机构来产生分离带和冰中的温度差积蓄和分流区域为循环地带的除冰系统。

8. 发明授权

US06820841B2 Arrangements for the de-icing, anti-icing and decontamination of aircraft or other vehicles 失效
标题翻译：飞机或其他车辆的除冰，除冰和去污的安排
公开(公告)号：US06820841B2
公开(公告)日：2004-11-23
申请号：US10126454
申请日：2002-04-19
申请人： P. Nicholas Mittereder , John M. Goston
发明人： P. Nicholas Mittereder , John M. Goston
IPC分类号： B64D1500
CPC分类号： B64F5/23 , B64F5/20 , Y02P70/585
摘要： Systems in which anti-icing fluids may be automatically mixed with water, and by which de-icing fluids may be heated and mixed with water, to provide variable temperatures and ratios of de-icing fluid-to-water to local aircraft de-icing fluid application devices in an instantaneous manner. Also contemplated herein are systems that additionally are configured for applying decontamination fluid and/or corrosion control fluid to military aircraft or other vehicles.
摘要翻译：防冰流体可以与水自动混合的系统，以及除冰流体可以与水一起加热和混合，以提供可变的温度和除冰流体与水的比例到当地的飞机除冰流体应用设备。本文还考虑的是另外构造成将去污液和/或腐蚀控制流体施加到军用飞机或其他车辆的系统。

9. 发明授权

US06360992B1 Hybrid deicing system and method of operation 失效
标题翻译：混合除冰系统及其操作方法
公开(公告)号：US06360992B1
公开(公告)日：2002-03-26
申请号：US09546121
申请日：2000-04-10
申请人： John Stanko , Lowell Pearson
发明人： John Stanko , Lowell Pearson
IPC分类号： B64D1500
CPC分类号： B64F5/23 , B64F5/20
摘要： A hybrid deicing system for deicing ice or snow covered surfaces comprises a source of pressurized air and a source of pressurized deicing fluid. A nozzle assembly receives the pressurized air and the pressurized deicing fluid at a forward position, a middle position or a rearward position of the nozzle assembly. The nozzle assembly discharges the pressurized deicing fluid and pressurized air as a first independent stream within a second independent stream.
摘要翻译：用于除冰或覆盖冰雪的表面的混合除冰系统包括加压空气源和加压除冰流体源。喷嘴组件在喷嘴组件的前部位置，中间位置或后部位置处接收加压空气和加压除冰流体。喷嘴组件将加压的除冰流体和加压空气作为第二独立流中的第一独立流排出。

10. 发明授权

US06279856B1 Aircraft de-icing system 有权
标题翻译：飞机除冰系统
公开(公告)号：US06279856B1
公开(公告)日：2001-08-28
申请号：US09364804
申请日：1999-07-30
申请人： Robert B. Rutherford , Richard L. Dudman
发明人： Robert B. Rutherford , Richard L. Dudman
IPC分类号： B64D1500
CPC分类号： B64D15/14
摘要： An electrothermal zoned de-icing system for an aircraft employs a heat-conducting tape bonded to the leading edge of an aircraft structure. The heat-conducting tape has a spanwise parting strip area, and first and second ice accumulation and shedding zones. The tape comprises a non-metallic electrical and heat conducting layer consisting of flexible expanded graphite foil laminated to an outer heat-conducting layer, in which the thickness of the flexible expanded graphite foil layer in the parting strip area is always greater than the thickness of the foil layer in either of the ice accumulation and shedding zones. Therefore, the parting strip area has a decreased electrical resistance, a greater flow of current, and becomes hotter than the zones in which the foil layer is thinner. Because the flexible expanded graphite foil is a monolithic structure that may be shaped, sculptured or layered to form different thicknesses in different areas, only a single control mechanism for a single set of electric terminals is necessary to produce desired watt densities and temperatures in the parting strip and ice accumulation and shedding zones.
摘要翻译：用于飞机的电热分区除冰系统采用结合到飞行器结构的前缘的导热带。导热带具有翼展分离带区域，第一和第二冰积聚区域。胶带包括非金属电导热层，其由柔性膨胀石墨箔层压到外导热层上，其中分离条区域中的柔性膨胀石墨箔层的厚度总是大于任何冰块和脱落区域中的箔层。因此，剥离带区域的电阻降低，电流流动更大，并且比箔层薄的区域变得更热。因为柔性膨胀石墨箔是可以成形，雕刻或分层以在不同区域中形成不同厚度的整体结构，所以仅需要用于单组电端子的单个控制机构来产生分流中所需的瓦特密度和温度带和冰积聚和脱落带。

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