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公开(公告)号：US20230069974A1
公开(公告)日：2023-03-09
申请号：US17940101
申请日：2022-09-08
发明人： Stefan BENSMANN
摘要： A flow body for an aircraft is disclosed having a stiffening structure and a flow surface at least partially enclosing the stiffening structure, the flow surface having a leading edge and a trailing edge at a distance to each other in a chordwise direction, the flow body including a first heating device attached to or integrated into the flow surface in a first chordwise section, a second heating device attached to or integrated into the surface body in a second chordwise section. The first chordwise section and the second chordwise section are distanced from each other, the first chordwise section is closer to the leading edge than the second chordwise section, and at least the second heating device comprises an electric heater.
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公开(公告)号：US20190084682A1
公开(公告)日：2019-03-21
申请号：US15705966
申请日：2017-09-15
发明人： Roger J. Aubert , Jared M. Paulson
摘要： There is provided an ice protection system for a rotary aircraft, including a rotor blade susceptible to an ice buildup having an inboard portion and an outboard portion, the length of the inboard portion and the length of the outboard portion define a total length of the rotor blade; a first deicing system coupled to the inboard portion of the rotor blade, the first deicing system including a plurality of spanwise zones; and a second deicing system coupled to the outboard portion of the rotor blade, the second deicing system including a plurality of chordwise zones. In one aspect, there is provided a deicing system for a rotary aircraft. In another aspect, there is a method to de-ice a rotor blade of an aircraft.
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公开(公告)号：US09771158B2
公开(公告)日：2017-09-26
申请号：US11883102
申请日：2006-02-03
IPC分类号： B64D15/14
摘要： An electrothermal heater mat for anti-icing or de-icing of a helicopter rotor blade or other aerodynamic surface comprises a substrate, such as a flexible polyimide sheet, bearing tracks of a material of selected electrical resistivity, these tracks being formed by printing onto the substrate with a thermosetting ink loaded with electrically conductive (e.g. carbon) particles. Electrical bus bars/terminals for the supply of electrical energy to the resistive tracks may also be printed, using an ink loaded with particles of higher conductivity material such as copper or silver.
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公开(公告)号：US09499273B2
公开(公告)日：2016-11-22
申请号：US14163524
申请日：2014-01-24
申请人： ROLLS-ROYCE PLC
发明人： David Michael Beaven
摘要： A propeller assembly comprises two or more blade elements each comprising two or more blade element portions arranged sequentially radially along the blade element. Each of the two or more blade element portions that are radially equi-positioned along corresponding ones of the two or more blade elements together form a blade element portion array.Each of the two or more blade element portions comprise at least one heating element with each one of the at least one heating elements that is located in a correspondingly radially positioned blade element portion being connected to one another to form a heating element array.The two or more heating element arrays are adapted to sequentially heat respective ones of the two or more blade element portion arrays so as to de-ice the blade elements.
摘要翻译： 两个或更多个加热元件阵列适于顺序地加热两个或更多个刀片元件部分阵列中的相应的一个以使得刀片元件脱冰。
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公开(公告)号：US09457909B2
公开(公告)日：2016-10-04
申请号：US13870403
申请日：2013-04-25
摘要： Embodiments of the disclosure include a de-icing system for an aircraft. The de-icing system includes a plurality of resistive-inductive heating elements inserted adjacent to a flight control surface and a controller configured to provide a supply current to each of the plurality of resistive-inductive heating elements. Each of the plurality of resistive-inductive heating elements produces an electromagnetic field normal to the flight control surfaces and resistive heat in response to the supply current. The electromagnetic field induces an eddy current in the flight control surface.
摘要翻译： 本公开的实施例包括用于飞行器的除冰系统。 除冰系统包括与飞行控制表面相邻地插入的多个电阻感应加热元件和被配置为向多个电阻感应加热元件中的每一个提供电源电流的控制器。 多个电阻感应加热元件中的每一个响应于电源电流产生垂直于飞行控制表面的电磁场和电阻热。 电磁场在飞行控制表面中产生涡流。
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6.发明授权公开(公告)号：US09227732B2
公开(公告)日：2016-01-05
申请号：US14475451
申请日：2014-09-02
摘要： An electro-thermal ice protection system includes a controller for managing and controlling electrical power generated to heat and de-ice surfaces, such as aircraft wings. The system is comprised of a number of power control modules (PCMs) and at least one master control unit (MCU). These elements can be stacked together and mounted into rack systems in order to provide scalable organized power distribution for a de-icing and ice protection system. The electro-thermal system can be used with a load leveling system and method capable of controlling switches such that it appears to a generator that the load is constant. Switches can be scheduled such that, ideally, the power load seen by the power source has emissions of no more than one PWM load superpositioned with zero or more constant, non-modulated loads.
摘要翻译： 电热防冰系统包括用于管理和控制产生的加热和去冰表面的电力的控制器，例如飞机机翼。 该系统由多个功率控制模块（PCM）和至少一个主控单元（MCU）构成。 这些元件可以堆叠在一起并安装到机架系统中，以便为除冰和防冰系统提供可扩展的有组织的配电。 电热系统可以与负载均衡系统和方法一起使用，该系统和方法能够控制开关，使得它看起来是负载恒定的发电机。 可以安排开关，使得理想地，电源所看到的功率负载具有不超过一个PWM负载的发射，该负载与零个或多个恒定的未调制负载叠加。
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公开(公告)号：US20150329211A1
公开(公告)日：2015-11-19
申请号：US14812610
申请日：2015-07-29
发明人： David Patrick Calder , Julian Alexander Opificius , Erik Thomas Pederson , David Cenit Flosdorf
IPC分类号： B64D15/14
CPC分类号： B64D15/14 , B64D15/12 , Y10T156/10 , Y10T156/1052
摘要： A system and method for ice protection of a component, wherein the system is adapted to be adhesively bonded to a surface of the component. The system includes a heating element layer, at least one thermally conductive adhesive layer that adhesively bonds a first side of the heating element layer to the component, an insulation layer, at least one thermally insulating adhesive layer that adhesively bonds a second side of the heating element to the insulation layer, an electrical bus bar adapted to provide a connection between a power supply and the heating element layer, and at least one temperature sensor.
摘要翻译： 一种用于组件的防冰的系统和方法，其中所述系统适于粘合地结合到所述部件的表面。 该系统包括加热元件层，至少一个导热粘合剂层，其将加热元件层的第一侧粘合到部件上，绝缘层，至少一个热绝缘粘合剂层，其将加热的第二侧粘合 元件到绝缘层，适于提供电源和加热元件层之间的连接的电汇流条以及至少一个温度传感器。
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公开(公告)号：US20100123044A1
公开(公告)日：2010-05-20
申请号：US12620408
申请日：2009-11-17
申请人： Galdemir C. Botura
发明人： Galdemir C. Botura
CPC分类号： B64D15/14
摘要： An ice protection system (40) is provided for an aircraft surface having a plurality of ice-susceptible regions. The system (40) comprises an ice protector (51-55) for each ice-susceptible region, a controller (60) which independently controls each of the ice protectors (51-55), and input channels (71-79) which conveys data to the controller (60). The controller (60) uses the channel-conveyed data to determine optimum operation for each of the ice protectors and controls the supply electrical energy thereto in accordance with such optimization.
摘要翻译： 为具有多个易受冰的区域的飞机表面提供防冰系统（40）。 系统（40）包括用于每个易感冰雪区域的冰保护器（51-55），独立地控制每个冰保护器（51-55）的控制器（60）和输送通道 数据传送到控制器（60）。 控制器（60）使用通道传送的数据来确定每个冰保护器的最佳操作，并且根据这样的优化来控制供应电能。
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公开(公告)号：US5134380A
公开(公告)日：1992-07-28
申请号：US588488
申请日：1990-09-26
申请人： Otakar Jonas
发明人： Otakar Jonas
CPC分类号： B64D15/14 , B64D15/12 , G01N27/223 , G01R27/2635
摘要： A device and method for detecting the nature and condition of ice, water or air on a surface by producing output signals by measurement of dynamic dielectric constant and electrical conductivity of the material on the surface and decoding digital signals therefrom to display information as to the condition. More particularly, a sensing apparatus for producing output voltage signals in response to the formation of ice, water or air at a surface and processing a combination of voltage levels as digital signals to decoding circuitry to provide information which is independent of contamination and impurities and of the size and nature of sensor elements.
摘要翻译： 通过测量表面上的材料的动态介电常数和电导率来产生输出信号来检测表面上的冰，水或空气的性质和状况的装置和方法，并从其中解码数字信号以显示关于条件的信息 。 更具体地，涉及一种用于响应于在表面处形成冰，水或空气而产生输出电压信号的感测装置，并将电压电平的组合作为数字信号处理到解码电路以提供独立于污染和杂质的信息，以及 传感器元件的尺寸和性质。
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公开(公告)号：US4514619A
公开(公告)日：1985-04-30
申请号：US431951
申请日：1982-09-30
申请人： Michael M. Kugelman
发明人： Michael M. Kugelman
IPC分类号： G01R19/165 , B64D15/14 , G01R19/00 , G05D23/19 , H05B1/02
CPC分类号： H05B1/0236 , B64D15/14 , G05D23/19 , H05B2214/02 , Y10T307/469
摘要： Electrical circuitry for monitoring the current flow through resistance elements on the leading edge of an aircraft wing or horizontal stabilizer. The resistance elements are individually and sequentially activated for heating to thereby effect a de-icing or anti-icing function. The non-activated elements are sensed by the circuitry to determine inferentially if there is a predetermined current flow through the heating elements to achieve the intended de-icing or anti-icing function.
摘要翻译： 用于监测通过飞机机翼或水平稳定器前缘上的电阻元件的电流的电路。 电阻元件被单独且顺序地激活用于加热，从而实现除冰或防冰功能。 非激活元件由电路感测以确定是否存在通过加热元件的预定电流以实现预期的除冰或防冰功能。
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