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1. 发明申请

WO2017187073A1 SYSTÈME DE PROPULSION D'UN AÉRONEF COMPRENANT UN ORGANE RECOUVERT D'UNE STRUCTURE RAINURÉE 审中-公开
标题翻译：用于推进包含覆盖有沟槽结构的器官的飞机的系统
公开(公告)号：WO2017187073A1
公开(公告)日：2017-11-02
申请号：PCT/FR2017/050967
申请日：2017-04-24
申请人： SAFRAN
发明人： GONCALVES, Emilie , LANFANT, Nicolas Pierre , MANDEL, Robin
IPC分类号： B64D15/00 , B64D15/16 , B64D15/20 , B64D15/22 , F01D25/02
CPC分类号： B64C23/005 , B64D15/00 , B64D15/12 , B64D15/16 , B64D15/163 , B64D15/20 , B64D15/22 , F01D5/141 , F01D5/143 , F01D9/02 , F01D25/02 , F02C7/047 , F02K3/06 , F05D2220/323 , F05D2250/61 , F05D2260/407 , Y02T50/673
摘要： L'invention concerne un système de propulsion d'un aéronef comportant au moins un organe (1, 3, 4, 8) en contact avec un écoulement turbulent d'un flux (F), caractérisée en ce que ledit organe est recouvert, au moins partiellement d'une structure (S) piézoélectrique telle qu'un film piézoélectrique, ladite structure (S) comprenant une structure (5, 6, 7,9) rainurées comprenant une succession de rainures, en contact avec l'écoulement du flux, les rainures s'étendant dans le sens d'écoulement du flux, la structure rainurée comprenant un moins un paramètre géométrique (h, s, w) configuré pour s'adapter en fonction d'au moins un paramètre de l'écoulement de flux et/ou d'un point de fonctionnement du système de propulsion et/ou un régime moteur du système de propulsion.
摘要翻译：
本发明涉及一种系统和egrave;我推进一个具有é包括ronef至少一个构件（1，3，4，8）与écoulement紊流接触（F），其特征在于éRISéE在所述构件与结构（S）PIéZOé电覆盖至少部分，例如膜PIéZOé电，所述结构（S），其包括结构（5,6，7,9）包括与所述écoulement流动接触槽的连续槽的éES，凹槽S'é在DE coulement流动方向趋向，结构包括配置的一个减去一个几何参数（h，s，w）的凹槽; 以适合的至少一个参数＆egrave的函数;是系统＆egrave的écoulement流量和/或操作点;我推进和/或系统和egrave的řé发动机速度;我推进力。

2. 发明申请

WO2015095019A1 NONWOVEN FABRIC WITH LOW ICE ADHESION 审中-公开
标题翻译：非织造布与低冰粘合剂
公开(公告)号：WO2015095019A1
公开(公告)日：2015-06-25
申请号：PCT/US2014/070289
申请日：2014-12-15
申请人： E. I. DU PONT DE NEMOURS AND COMPANY
发明人： BHASKAR, Srijanani , HARMER, Mark Andrew , MASSOUDA, Debora Flanagan
IPC分类号： B64D15/16
CPC分类号： B64D15/16 , Y02B10/30
摘要： The present disclosure provides a method to remove ice from a substrate with very low amounts of force needed to remove the ice. It has been found that certain nonwoven fabrics provide a relatively ice-phobic surface. The application of the nonwoven fabric to a substrate can provide a substrate wherein any accumulated ice is easily removed.
摘要翻译：本公开提供了一种用于以非常少量的除去冰所需的力从基材除去冰的方法。已经发现，某些非织造织物提供了相对较为恐怖的表面。将无纺布应用于基底可以提供其中容易除去任何积聚的冰的基底。

3. 发明申请

WO01062593A1 DEVICE FOR AN AEROPLANE 审中-公开
标题翻译：机场设备
公开(公告)号：WO01062593A1
公开(公告)日：2001-08-30
申请号：PCT/SE2001/000364
申请日：2001-02-20
IPC分类号： B64D15/00 , B64D15/16 , B64D15/18
CPC分类号： B64D15/16 , B64D15/00
摘要： The present invention relates to an arrangement for an aircraft (2) to reduce icing on the wings (3), horizontal stabilizer (4) and vertical stabilizer (5). The arrangement consists of a thermally insulating, water-repellent and non-stick covering (1) intended for application to those parts of the aircraft where icing otherwise causes problems. The icing-preventing covering (1) essentially consists of 1-2 mm thick layer of a thermally insulating material, for example chloroprene cellular rubber, which has been impregnated with silicon to make the cellular rubber water-repellent and to give the surface "non-stick" properties.
摘要翻译：本发明涉及一种用于飞机（2）减少机翼（3），水平稳定器（4）和垂直稳定器（5）上的结冰的装置。该装置包括隔热，防水和不粘的覆盖物（1），用于应用于飞机的那些部分，否则会导致问题。防冰覆盖物（1）基本上由1-2mm厚的绝热材料层（例如氯丁二烯泡沫橡胶）组成，其已经用硅浸渍以使多孔橡胶防水并且赋予表面“非” 贴“属性。

4. 发明申请

WO1998000274A1 HEATING OF COMPONENTS 审中-公开
标题翻译：加热组件
公开(公告)号：WO1998000274A1
公开(公告)日：1998-01-08
申请号：PCT/AU1997000416
申请日：1997-07-01
申请人： AYRES, Patrick, Michael, William
IPC分类号： B29C33/02
CPC分类号： B29C33/06 , B29C35/08 , B29C70/04 , B29C2035/0211 , B29C2035/0811 , B29K2307/00 , B29K2707/04 , B64D15/16 , H05B6/105
摘要： The present invention provides a method of and apparatus for heating an article by using magnetic induction heating and/or resistive heating. The method/apparatus allow for heating of articles having a matrix of fibres and resin and the article is formed by curing the resin through the magnetic induction heating and/or resistive heating. The articles include an electrically conductive constituent which is heated by magnetic induction heating. The electrically conductive constituent includes carbon fibres. The natural conductivity of the fibres themselves will preferably be used as the medium for generation of the induction heating currents.
摘要翻译：本发明提供一种通过使用磁感应加热和/或电阻加热来加热制品的方法和设备。该方法/装置允许加热具有纤维和树脂基质的制品，并且通过磁感应加热和/或电阻加热固化树脂形成制品。物品包括通过磁感应加热加热的导电成分。导电成分包括碳纤维。纤维本身的天然导电性优选用作产生感应加热电流的介质。

5. 发明申请

WO2015054334A1 ACOUSTIC CONTROLLED ICE DEFLECTING AUXILIARY POWER UNIT INLET SYSTEM 审中-公开
标题翻译：控制冰控制辅助电源单元进线系统
公开(公告)号：WO2015054334A1
公开(公告)日：2015-04-16
申请号：PCT/US2014/059602
申请日：2014-10-08
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： BELL, Melissa A. , ROLLINS, Michael J. , HAGSHENAS, Behzad , VITALE, Jack V.
IPC分类号： B65D41/00 , B65D33/00
CPC分类号： B64D33/02 , B64D15/16 , B64D41/00 , B64D2033/0206 , B64D2033/0213 , B64D2033/0233 , F02C7/045 , F02C7/05 , F02C7/057
摘要： An auxiliary power unit for an aircraft includes a turbine engine. An inlet includes an opening and a passageway between the opening and the turbine engine. An acoustic splitter is supported within the passageway for attenuating noise within the inlet. An inlet door is movable between a closed position and a fully open position. A portion of the inlet door aligns with a part of the passageway in at least a first position and divides the passageway to deflect ice and noise in at least a second position. An air inlet and a method are also disclosed.
摘要翻译：用于飞行器的辅助动力单元包括涡轮发动机。入口包括开口和在开口和涡轮发动机之间的通道。通道内支持声分离器，用于衰减入口内的噪音。入口门可在关闭位置和完全打开位置之间移动。入口门的一部分在至少第一位置与通道的一部分对准，并且在至少第二位置中划分通道以使冰和噪声偏转。还公开了一种进气口和方法。

6. 发明申请

WO2013022767A3 METHOD AND APPARATUS FOR INHIBITING FORMATION OF AND/OR REMOVING ICE FROM AIRCRAFT COMPONENTS 审中-公开
标题翻译：用于禁止从飞机组件形成和/或移除冰的方法和装置
公开(公告)号：WO2013022767A3
公开(公告)日：2013-05-10
申请号：PCT/US2012049560
申请日：2012-08-03
申请人： GEN ATOMICS , GILES ALAN M , MACHIN JAMES T , GERIGUIS JOHN A
发明人： GILES ALAN M , MACHIN JAMES T , GERIGUIS JOHN A
IPC分类号： H02N2/06 , H01L41/02
CPC分类号： B64D15/20 , B64C3/00 , B64C9/00 , B64C11/16 , B64D15/16 , B64D15/163 , B64D15/22
摘要： Methods and systems are generally described that inhibit debris (such as ice) accretions and/or remove debris (such as ice) accretions from the exterior surface of an aircraft. In some embodiments, the invention is a system (100) for an aircraft comprising: a component (120) of the aircraft having a surface; a plurality of piezo-kinetic actuators (114, 116, 118) each positioned proximate to a portion of the surface; and a control unit (102) coupled to the plurality of actuators, the control unit configured to actuate one or more of the actuators at one or more frequencies between about 1 Hz and about 1 kHz; wherein the actuators are each configured to introduce a displacement of the surface in three dimensions to inhibit a formation of ice on at least the portion of the surface and to break up existing ice formations on at least the portion of the surface.
摘要翻译：通常描述的方法和系统是抑制来自飞行器外表面的碎片（例如冰）的积聚和/或去除碎片（例如冰）的积累。在一些实施例中，本发明是用于飞行器的系统（100），包括：具有表面的飞机的部件（120）; 多个压电动力学致动器（114,116,118），各自定位成接近所述表面的一部分; 以及耦合到所述多个致动器的控制单元（102），所述控制单元被配置为以大约1Hz和大约1kHz之间的一个或多个频率致动所述致动器中的一个或多个; 其中所述致动器各自被构造成在三维空间中引入所述表面的位移，以阻止在所述表面的至少所述部分上形成冰并在所述表面的至少一部分上分解现有的冰层。

7. 发明申请

WO2009019696A3 MECHANICAL VIBRATION DEICING SYSTEM 审中-公开
标题翻译：机械振动检测系统
公开(公告)号：WO2009019696A3
公开(公告)日：2010-03-04
申请号：PCT/IL2008001086
申请日：2008-08-07
申请人： GORNIK AMICHAI
发明人： GORNIK AMICHAI
IPC分类号： B64D15/18
CPC分类号： B64D15/16 , B64D15/20
摘要： An aircraft deicing system including at least one motor operative to drive at least one eccentric mass in rotational motion and at least one displacer coupled to at least one location on at least one aircraft surface and coupled to the at least one eccentric mass such that forces produced by the rotational motion of the eccentric mass are applied to the at least one displacer, causing the at least one displacer to displace the at least one aircraft surface in a plurality of directions at each of the at least one location, thereby causing disengagement of ice from the at least one aircraft surface.
摘要翻译：一种飞机除冰系统，包括至少一个电动机，其用于驱动旋转运动中的至少一个偏心质量块，以及耦合到至少一个飞行器表面上的至少一个位置的至少一个置换器，并联接到所述至少一个偏心质量块，通过所述偏心质量块的旋转运动被施加到所述至少一个置换器，使得所述至少一个置换器在所述至少一个位置中的每一个处沿着多个方向移位所述至少一个飞行器表面，从而导致冰的分离从至少一个飞行器表面。

8. 发明申请

WO02016200A2 DEICER FOR AIRCRAFT 审中-公开
标题翻译：飞机审判员
公开(公告)号：WO02016200A2
公开(公告)日：2002-02-28
申请号：PCT/US2001/025873
申请日：2001-08-17
IPC分类号： B64D15/16
CPC分类号： B64D15/16
摘要： A deicer (10) is provided for breaking up and removing accumulated ice on an airfoil surface (14). The deicer (10) includes a bonside surface (22) that is bonded to the airfoil surface (14), a breezeside surface (24) on which the ice will accumulate, and passage-defining surfaces therebetween. The passage-defining surfaces define a plurality of expansible and contractible inflation passages (30) and include a moisture-impervious coating whereby moisture within the inflation passages (30) will not be absorbed by the surfaces (26, 28). The bondside, breezeside (24) and passage-defining surfaces (26, 28) may be contained on a deicer panel (10) and means may be provided for introducing inflation fluid to an evacuating inflation fluid from the passages (30) to expand and contract the inflation passages (30) to break up and remove the accumulated ice.
摘要翻译：提供一种除冰机（10），用于分解和除去翼面（14）上积聚的冰。除冰器（10）包括结合到翼型件表面（14）的边缘表面（22），冰块将积聚的微风表面（24）和其间的通道限定表面。通道限定表面限定多个可膨胀和可收缩的充气通道（30）并且包括不透湿的涂层，其中充气通道（30）内的水分不会被表面（26,28）吸收。可以在除冰板（10）上包含边缘（B），通风限定表面（26）和通道限定表面（26,28），并且可以提供装置用于将膨胀流体从通道（30）引入到抽空的充气流体中以膨胀和收紧通货膨胀通道（30）来打破和消除积冰。

9. 发明申请

WO1990008064A1 SMART SKIN ICE DETECTION AND DE-ICING SYSTEM 审中-公开
标题翻译：智能皮肤冰检测和去皮系统
公开(公告)号：WO1990008064A1
公开(公告)日：1990-07-26
申请号：PCT/US1990000180
申请日：1990-01-09
申请人： GERARDI, Joseph, J. , DAHL, Philip, R. , HICKMAN, Gail, A.
IPC分类号： B64D15/16
CPC分类号： G01M5/0066 , B64D15/16 , B64D15/20 , G01M5/0016 , G01M5/0083 , G08B19/02
摘要： The de-icing system of the present invention comprises a piezoelectric sensor means (IAS) and a processor means (CPU). A piezoelectric film is the preferred sensor means and a microprocessor is the preferred processor means. In a preferred embodiment, a strip of piezoelectric film (IAS) placed at a point of model kinetic energy such as the boundary layer transition point or the vortex generator of the aircraft. Such placement of the strip provides adequate airflow to excite the piezoelectric film (IAS) without using a power source, thus providing a passive system. The sensor (IAS) allows measurement of distributed strain and vibrational modes indicative of structural icing. The microprocessor (CPU), which controls the system, processes signals from the sensors (IAS), determines whether ice is present, and indicates (DSP) the presence of ice when appropriate. The film (IAS) may be used in a single piece, which may be as large as the area for which ice detection is desired - for example, the entire leading edge of an aircraft wing - or in multiple pieces, and may be embedded in or attached to a surface. This provides a passive, autonomous system for distributed ice detection over a single sensor or between multiple sensors.

10. 发明申请

WO2014040819A1 DE-ICING SYSTEM AND METHOD 审中-公开
标题翻译： DE-ICING系统和方法
公开(公告)号：WO2014040819A1
公开(公告)日：2014-03-20
申请号：PCT/EP2013/067084
申请日：2013-08-15
申请人： SELEX ES LTD
发明人： MACLEAN, John Ronald , MAGUIRE, Stuart Douglas , PATERSON, Jack , LAWSON, Steven
IPC分类号： B64D15/16
CPC分类号： B64D15/16 , B64D15/163
摘要： A de-icing system for a hemispherical protective housing 1 mounted on an aircraft structure is described. The system comprises a series of piezo-electric devices mounted at the boundary 2 of the housing 1. The piezo-electric devices generate ultrasonic frequencies and resonance of the protective housing is induced. One of the piezo-electric devices senses the frequency generated in the protective housing and acts as part of a feedback loop to maintain structural resonance of the protective housing 1. The structural resonance of the protective housing 1 prevents the build-up of ice. Additionally, higher power resonances can be generated to remove ice already built up on the protective housing 1. The system also enables detection of ice build-up on the protective housing 1 by monitoring any change in the frequency required to maintain structural resonance of the protective housing 1.
摘要翻译：描述了安装在飞行器结构上的半球形保护壳体1的除冰系统。该系统包括安装在壳体1的边界2处的一系列压电装置。压电装置产生超声频率并且引起保护壳体的共振。压电装置中的一个感测在保护壳体中产生的频率，并且作为反馈回路的一部分，以保持保护壳体1的结构共振。保护壳体1的结构共振防止了冰的积聚。此外，可以产生更高功率的共振，以去除已经建立在保护壳体1上的冰。该系统还能够通过监视维持保护性结构共振所需的频率的任何变化来检测保护壳体1上的积冰房屋1。

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