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1. 发明授权

US07543777B2 Air guiding flap of an aircraft comprising control of the pressure forces impinging thereon, process for adjusting the position of an air guiding flap and ram air system including such an air guiding flap 失效
标题翻译：飞行器的导风翼包括控制冲击其上的压力的过程，用于调节空气引导翼片和冲击空气系统的位置，包括这种导气翼
公开(公告)号：US07543777B2
公开(公告)日：2009-06-09
申请号：US10582567
申请日：2004-12-30
申请人： Rüdiger Schmidt , Alexander Solntsev
发明人： Rüdiger Schmidt , Alexander Solntsev
IPC分类号： B64D33/00 , F02C7/04
CPC分类号： F02C7/042 , B64D33/02 , B64D33/04 , F02C6/08 , F02C7/057
摘要： An air guiding flap of an aircraft wherein one surface thereof faces an air duct and is exposed to a prevailing pressure in the air duct and whose opposite surface is exposed to the pressure of the relative wind flowing past the aircraft. The air guiding flap comprises an actuator for automatically opening and closing the air guiding flap which actuator cooperates with a device for controlling the position of the air guiding flap. In order to keep the stress on the air guiding flap low a force detecting device is provided which detects the force impinging on the actuator base don a difference between the prevailing pressure in the air duct and the pressure of the relative wind flowing past the aircraft. The controlling device adjusts the position of the air guiding flap such that the force impinging on the actuator at any one time is at least essentially zero.
摘要翻译：飞机的导风翼，其一个表面面向空气管道，并且暴露在空气管道中的主要压力下，并且其相对表面暴露于流经飞机的相对风的压力。引导翼片包括用于自动打开和关闭空气引导翼片的致动器，该致动器致动器与用于控制导气翼片的位置的装置配合。为了使空气引导翼片上的应力保持较低，提供了一种力检测装置，其检测致动器基座上的力与空气管道中的主要压力和流过飞机的相对风力的压力之间的差异。控制装置调节空气引导翼片的位置，使得在任何一个时刻撞击致动器的力至少基本为零。

2. 发明授权

US08292222B2 Air-conditioning system with icing protection for an aircraft 有权
标题翻译：用于飞机防冰保护的空调系统
公开(公告)号：US08292222B2
公开(公告)日：2012-10-23
申请号：US12322999
申请日：2009-02-10
申请人： Alexander Solntsev , Johannes Eichholz , Holger Bammann
发明人： Alexander Solntsev , Johannes Eichholz , Holger Bammann
IPC分类号： B64D13/08
CPC分类号： B64D13/08 , B64D2013/0618 , B64D2013/0688 , Y02T50/56
摘要： Aircraft air-conditioning system (1) for an aircraft having a plurality of zones (2, 4), comprising a first line (6) for feeding cold air at an actual temperature T1act., a second line (14) which branches off a portion of the air from the first line (6) at a branching point (10) and feeds the air to a plurality of zones (2, 4) of an aircraft, wherein warm air is fed through a first trim valve (12) into the second line (14) so that the air in the second line (14) is heated to the actual temperature T2act., and a first zone feed line (24) feeding the air downstream of the first trim valve (12) to a first zone (2), wherein a second trim valve (26) is arranged in the first zone feed line (24), through which valve warm air is fed into the first zone feed line (24) so that the air in the first zone feed line (24) is heated to the actual temperature Tzf1act., and the first line (6) downstream and/or upstream of the branching point (1) feeds cold air at least to one further zone. A second feed line (18) feeds air downstream of the first adjustment (12) to a second zone (4). A heating device (20) can be arranged in the second feed line (18).
摘要翻译：一种用于具有多个区域（2,4）的飞行器的飞行器空调系统（1），包括用于以实际温度T1act进行冷空气的第一管线（6），第二管线（14），其分支在分支点（10）处来自第一管线（6）的空气的一部分，并将空气供给飞机的多个区域（2,4），其中暖空气通过第一调节阀（12）进入第二管线（14），使得第二管线（14）中的空气被加热到实际温度T2act;以及第一区域进料管线（24），其将第一调节阀（12）下游的空气供给到第一管区域（2），其中第二调节阀（26）布置在第一区域供给管线（24）中，阀暖空气通过该第二区域供给管线（24）进入第一区域供给管线（24），使得第一区域中的空气进给管线（24）被加热到实际温度Tzf1act，并且分支点（1）的下游和/或上游的第一管线（6）将冷空气供给至少一个另外的区域。第二进料管线（18）将第一调节件（12）下游的空气送入第二区域（4）。加热装置（20）可以布置在第二进料管线（18）中。

3. 发明申请

US20100096118A1 Ram Air Based Cooling And Ventilation System For An Aircraft 有权
标题翻译：基于Ram Air的冷却通风系统
公开(公告)号：US20100096118A1
公开(公告)日：2010-04-22
申请号：US12520240
申请日：2007-12-12
申请人： Thomas Scherer , Ruediger Schmidt , Alexander Solntsev
发明人： Thomas Scherer , Ruediger Schmidt , Alexander Solntsev
IPC分类号： F25B29/00 , B64D13/00 , B60H3/00 , B60H1/34 , F24F7/007
CPC分类号： B64D13/00 , Y02T50/56
摘要： The invention concerns a cooling system for an aircraft with an air inlet (4) through which air from the environment of the aircraft enters a ram air channel (2), and an air outlet (6) through which air emerges from the ram air channel (2). A heat exchanger (10) is arranged in the ram air channel (2). A ventilation device (8) is in fluid communication with the ram air channel (2). Also connected to the ram air channel (2) is a distribution line (12) to cool at least one heat-loaded component of the aircraft, in particular a cabin air conditioning system, and/or to ventilate an installation space of the at least one heat-loaded component.
摘要翻译：本发明涉及一种用于具有空气入口（4）的飞行器的冷却系统，来自飞行器环境的空气通过该进气口进入冲压空气通道（2）和空气出口（6），空气从冲压空气通道（2）。热交换器（10）设置在冲压空气通道（2）中。通风装置（8）与冲压空气通道（2）流体连通。还连接到冲压空气通道（2）的是分配线（12），用于冷却飞机的至少一个加热部件，特别是机舱空调系统，和/或至少使安装空间通风一个热负荷组件。

4. 发明申请

US20070125906A1 Ram air channel for the supply of ambient air in an aircraft 有权
标题翻译：用于在飞机上供应环境空气的Ram空气通道
公开(公告)号：US20070125906A1
公开(公告)日：2007-06-07
申请号：US10582572
申请日：2004-12-30
申请人： Thomas Scherer , Alexander Solntsev , Michael Heesch
发明人： Thomas Scherer , Alexander Solntsev , Michael Heesch
IPC分类号： B64D33/02
CPC分类号： F02C7/042 , B64D13/00 , F02C6/08 , Y02T50/56 , Y02T50/671 , Y10T137/0536 , Y10T137/0645
摘要： A ram air channel (10) for the supply of ambient air in an aircraft includes a first air inlet (12) and a main flow channel (16) which extends downstream of the first air inlet (12). In order to guarantee that the systems on board the aircraft are supplied, in a simple and reliable way, with the required ambient air in any operational state of the aircraft, ie. both during the flight and on the ground, the ram air channel (10) has a second air inlet (24) which is independent from the first air inlet (12).
摘要翻译：用于在飞行器中供应环境空气的冲压空气通道（10）包括在第一空气入口（12）的下游延伸的第一空气入口（12）和主流动通道（16）。为了保证飞机上的系统能够以简单可靠的方式提供飞机任何运行状态下所需的环境空气，即。在飞行中和在地面上，冲压空气通道（10）具有独立于第一空气入口（12）的第二进气口（24）。

5. 发明授权

US08807484B2 Gas exhaust diverter 有权
标题翻译：排气分流器
公开(公告)号：US08807484B2
公开(公告)日：2014-08-19
申请号：US13388144
申请日：2010-08-02
申请人： Hugo Alexandre Duart Mendes Raposeiro , Bruno Stefes , Holger Bammann , Thomas Selchert , James Brown , Heiko Rothe , Alexander Solntsev
发明人： Hugo Alexandre Duart Mendes Raposeiro , Bruno Stefes , Holger Bammann , Thomas Selchert , James Brown , Heiko Rothe , Alexander Solntsev
IPC分类号： B64D1/00
CPC分类号： B64D13/00 , B64C1/1453
摘要： An aircraft comprises an outer aerodynamic surface and an exhaust duct having an opening in the outer aerodynamic surface. The duct has a duct wall curved at the opening so as to blend with the aerodynamic surface downstream of the duct. At least one fixed flow diverter is provided for diverting high temperature exhaust gas exiting the duct away from the aerodynamic surface immediately downstream of the duct opening. The curved duct wall provides low aerodynamic drag in cruise. The flow diverter(s) give aircraft designers freedom in terms of where the duct opening can be positioned without compromising the structural integrity of the aircraft through excessive heating of the aerodynamic surface immediately downstream of the duct opening.
摘要翻译：飞行器包括外部空气动力学表面和在外部空气动力学表面中具有开口的排气管道。管道具有在开口处弯曲的管道壁，以便与管道下游的空气动力学表面混合。提供至少一个固定流量分流器，用于将离开管道的高温废气远离管道开口下游的空气动力学表面。弯曲的管道壁在巡航中提供低气动阻力。流量分配器使得飞机设计者在管道开口可以被定位的位置方面是自由的，而不会通过在管道开口的紧下游的空气动力学表面的过度加热来牺牲飞行器的结构完整性。

6. 发明申请

US20120126061A1 GAS EXHAUST DIVERTER 有权
标题翻译：气体排气口
公开(公告)号：US20120126061A1
公开(公告)日：2012-05-24
申请号：US13388144
申请日：2010-08-02
申请人： Hugo Alexandre Duart Mendes Raposeiro , Bruno Stefes , Holger Bammann , Thomas Selchert , James Brown , Heiko Rothe , Alexander Solntsev
发明人： Hugo Alexandre Duart Mendes Raposeiro , Bruno Stefes , Holger Bammann , Thomas Selchert , James Brown , Heiko Rothe , Alexander Solntsev
IPC分类号： B64D13/00
CPC分类号： B64D13/00 , B64C1/1453
摘要： An aircraft comprises an outer aerodynamic surface and an exhaust duct having an opening in the outer aerodynamic surface. The duct has a duct wall curved at the opening so as to blend with the aerodynamic surface downstream of the duct. At least one fixed flow diverter is provided for diverting high temperature exhaust gas exiting the duct away from the aerodynamic surface immediately downstream of the duct opening. The curved duct wall provides low aerodynamic drag in cruise. The flow diverter(s) give aircraft designers freedom in terms of where the duct opening can be positioned without compromising the structural integrity of the aircraft through excessive heating of the aerodynamic surface immediately downstream of the duct opening.
摘要翻译：飞行器包括外部空气动力学表面和在外部空气动力学表面中具有开口的排气管道。管道具有在开口处弯曲的管道壁，以便与管道下游的空气动力学表面混合。提供至少一个固定流量分流器，用于将离开管道的高温废气远离管道开口下游的空气动力学表面。弯曲的管道壁在巡航中提供低气动阻力。流量分配器使得飞机设计者在管道开口可以被定位的位置方面是自由的，而不会通过在管道开口的紧下游的空气动力学表面的过度加热来牺牲飞行器的结构完整性。

7. 发明申请

US20070117501A1 Cooling air supply for the cooling of different systems requiring cooling air in an aircraft 有权
标题翻译：用于冷却需要在飞机上冷却空气的不同系统的冷却空气
公开(公告)号：US20070117501A1
公开(公告)日：2007-05-24
申请号：US10582151
申请日：2004-12-30
申请人： Alexander Solntsev , Holger Bammann
发明人： Alexander Solntsev , Holger Bammann
IPC分类号： B64D13/00
CPC分类号： B64D13/00 , Y02T50/44 , Y02T50/56
摘要： A cooling air supply system (10) for an aircraft in order to supply cooling air from the aircraft surrounds to at least two devices requiring cooling air (38, 44, 56) within the aircraft, is designed with an air inlet (12), an air channel (16) communicating with the air inlet (12) and with an air distribution device (30, 32, 34) for the distribution of air to at least two devices requiring cooling air (38, 44, 56), whereby the air inlet (12) is proportioned in such a way that it covers the maximum cooling air requirement of at least two devices requiring cooling air (38, 44, 56).
摘要翻译：用于飞行器的用于从飞行器供应冷却空气的冷却空气供应系统（10）围绕到需要飞行器内的冷却空气（38,44,56）的至少两个设备，设计有进气口（12），与空气入口（12）连通的空气通道（16）和用于将空气分配到至少两个需要冷却空气的装置（38,44,56）的空气分配装置（30,32,34），由此，空气入口（12）的比例成正比，以覆盖需要冷却空气（38,44,56）的至少两个装置的最大冷却空气需求。

8. 发明授权

US06628867B1 Fiber optic real time display system 失效
标题翻译：光纤实时显示系统
公开(公告)号：US06628867B1
公开(公告)日：2003-09-30
申请号：US09665566
申请日：2000-09-19
申请人： Alexander Solntsev
发明人： Alexander Solntsev
IPC分类号： G02B606
CPC分类号： G02B6/06 , G02B6/3668 , G02B6/3672 , G02B6/368 , G02B6/4298
摘要： In a fiber optic display system an array of pixels form a continuous viewable surface. Each pixel is formed by a bundle of one or more optical fibers which vector light to the pixels from one or more light sources. High density of pixels at the viewable surface is achieved by bundling small diameter optical fibers adapted for vectoring light from a low density light sources. The two-dimensional geometry of the viewable surface is de-coupled from the light source which is arranged in a three dimensional space.
摘要翻译：在光纤显示系统中，像素阵列形成连续可见的表面。每个像素由一束或多根光纤形成，该光束将光从一个或多个光源向像素传播。可见表面的高密度像素是通过将适合于对来自低密度光源的光进行矢量化的小直径光纤进行捆扎来实现的。可视表面的二维几何形状从布置在三维空间中的光源脱耦合。

9. 发明申请

US20110151763A1 DEVICE AND METHOD FOR COOLING EXHAUST AIR OF AIRCRAFT AIR-CONDITIONING SYSTEMS 有权
标题翻译：用于冷却空气调节系统排气的装置和方法
公开(公告)号：US20110151763A1
公开(公告)日：2011-06-23
申请号：US12952809
申请日：2010-11-23
申请人： Thomas Selchert , Alexander Solntsev
发明人： Thomas Selchert , Alexander Solntsev
IPC分类号： B64D13/00
CPC分类号： B64D13/00
摘要： Device for exhaust air cooling of aircraft air-conditioning systems comprising a bypass channel that bypasses an aircraft air-conditioning system arranged downstream of a ram air channel with a ram air inlet channel portion, and merges into an outlet channel, arranged downstream of the aircraft air-conditioning system, before a discharge opening for exhaust air, a common inlet being provided for the ram air channel and the bypass channel.
摘要翻译：包括飞行器空调系统的排气冷却装置，其包括旁路通道，旁路通道布置在具有冲压空气入口通道部分的冲压空气通道下游的飞行器空调系统，并且汇合到布置在飞行器下游的出口通道空调系统，在排气口的排气口之前，为冲压空气通道和旁路通道设置公共入口。

10. 发明申请

US20110136425A1 FRESH AIR INLET FOR AN AIRCRAFT 有权
标题翻译：新鲜空气入口飞机
公开(公告)号：US20110136425A1
公开(公告)日：2011-06-09
申请号：US12994911
申请日：2009-05-27
申请人： Johannes Eichholz , Jens Beier , Alexander Solntsev , Ruediger Schmidt
发明人： Johannes Eichholz , Jens Beier , Alexander Solntsev , Ruediger Schmidt
IPC分类号： B64D13/00
CPC分类号： B64D33/02 , B64C7/00 , B64D13/00 , B64D2033/022 , B64D2241/00 , Y02T50/44 , Y02T50/56
摘要： The invention relates to a fresh air inlet for an aircraft that features at least one ram air inlet with at least one ram air inlet opening, at least one secondary air inlet opening that is spaced apart from the ram air inlet and at least one movably mounted flap, wherein the flap can be moved into a first position and into a second position, and wherein the flap essentially covers the secondary air inlet opening in the first position and at least partially opens the secondary air inlet opening and at least in certain areas extends into the air flow directed toward the ram air inlet opening in order to shield the ram air inlet opening from foreign matter in the second position. The air inlet according to the invention makes it possible to reduce the pressure loss of the air inlet on the ground or during flight phases with relatively slow speed due to the enlarged cross-sectional surface. This results in that the actual ram air inlet can be optimized for cruising phases, and that the energy expenditure for any downstream compressors and flow-induced noises can be considerably reduced.
摘要翻译：本发明涉及一种用于飞机的新鲜空气入口，其具有至少一个冲压空气入口，其具有至少一个冲压空气入口，至少一个与冲压空气入口间隔开的二次空气入口，以及至少一个可移动地安装翼片，其中所述翼片可以移动到第一位置并进入第二位置，并且其中所述翼片在所述第一位置基本上覆盖所述次级空气入口开口并且至少部分地打开所述次级空气入口开口，并且至少在某些区域延伸进入朝向冲压空气入口开口的空气流中，以便将冲压空气入口与第二位置的异物屏蔽。根据本发明的空气入口使得可以由于横截面增大而以相对较慢的速度减小地面上空气入口或飞行阶段的压力损失。这导致实际的冲压进气口可以针对巡航阶段进行优化，并且可以大大减少任何下游压缩机和流动引起的噪声的能量消耗。

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