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1. 发明授权

US09731832B2 Torque converter for rotorcraft 有权
公开(公告)号：US09731832B2
公开(公告)日：2017-08-15
申请号：US13922356
申请日：2013-06-20
申请人： Michael Joseph DeVita , Mark Denton Bystry, Jr. , Timothy Fred Lauder
发明人： Michael Joseph DeVita , Mark Denton Bystry, Jr. , Timothy Fred Lauder
IPC分类号： B64D35/00 , B64D27/04 , B64D35/02 , F16H45/02
CPC分类号： B64D35/00 , B64D27/04 , B64D35/02 , F16H45/02
摘要： A torque converter for converting torque between an input shaft and an output shaft includes an impeller operably connected to the input shaft and rotatable therewith. The torque converter further includes a turbine operably connected to the output shaft and rotatable therewith. A fluid flow system directs a flow of motive fluid through the impeller and through the turbine to drive rotation of the output shaft relative to the input shaft. A lockup mechanism is engageable to urge rotation of the output shaft at an output shaft rotational speed identical to an input shaft rotational speed. A switching module controls an actuation system to urge engagement of the lockup mechanism.

2. 发明申请

US20170066531A1 UAV CONFIGURATIONS AND BATTERY AUGMENTATION FOR UAV INTERNAL COMBUSTION ENGINES, AND ASSOCIATED SYSTEMS AND METHODS 审中-公开
标题翻译：无人机配置和无人机内燃机的电池补充及相关系统和方法
公开(公告)号：US20170066531A1
公开(公告)日：2017-03-09
申请号：US15261780
申请日：2016-09-09
申请人： Endurant Systems, LLC
发明人： Gregory Leonard McAdoo
IPC分类号： B64C39/02 , H02K7/18 , B64D27/24 , B64D45/00 , B64C29/00 , B64D27/04
CPC分类号： B64C39/024 , B64C27/08 , B64C27/26 , B64C29/0033 , B64C39/04 , B64C2201/021 , B64C2201/027 , B64C2201/042 , B64C2201/044 , B64C2201/141 , B64D27/04 , B64D27/24 , B64D45/00 , B64D2027/026 , B64D2045/0085 , B64D2221/00 , H02J7/14 , H02J7/34 , H02K7/1815 , Y02T50/64
摘要： UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.
摘要翻译：公开了UAV内燃机的UAV配置和电池增加以及相关的系统和方法。代表性的配置包括机身，相对于机身联接并可枢转的第一和第二翼，以及由机身承载的多个提升转子。代表性的电池增加装置包括直流动力马达，电子速度控制器和耦合到电子速度控制器的发电机组子系统。发电机组子系统可以包括电池组，交流发电机和电动机控制器，其具有相位控制电路，该相位控制电路可配置为整流来自交流发电机的多相交流输出，以产生经直流供电的电动机的整流直流馈电。电机控制器可配置为从电池组中抽取直流电源，以产生整流的直流电源。

3. 发明申请

US20160243910A1 Amphibious Flying Car 审中-公开
标题翻译：两栖飞行车
公开(公告)号：US20160243910A1
公开(公告)日：2016-08-25
申请号：US15026103
申请日：2014-08-04
申请人： Xinru HU
发明人： Xinru HU
IPC分类号： B60F5/02 , B63B5/24 , B63H5/07 , B64D41/00 , B64C27/26 , B64C27/52 , B64C3/56 , B64D27/04 , B60F3/00 , B64C37/00
CPC分类号： B60F5/02 , B60F3/003 , B63B5/24 , B63B2005/245 , B63H5/07 , B64C3/56 , B64C27/26 , B64C27/52 , B64C37/00 , B64D27/04 , B64D41/00
摘要： The present invention provides an amphibious flying car, comprising: a casing, a chassis, a ship bottom body, a vehicle wheel, a drive system and an operating system; an upper airfoil and a rotor wing which are arranged on the top of the casing, are fixed on a bearing carrier located at the orthocenter of the fuselage; a strake wing is provided at the position where the casing, the chassis and the ship bottom body are combined; the horizontal wing comprises a stabilizing plane and an elevator, which are respectively located at the front end and the rear end of the fuselage; the vertical twin fins are arranged at both sides of the rear end of the fuselage, and its root segments are fixedly connected to the strake wing.
摘要翻译：本发明提供一种两栖飞行车，其特征在于，包括：壳体，底盘，船底本体，车轮，驱动系统和操作系统; 设置在壳体顶部的上部翼型件和转子翼片固定在位于机身中心的轴承架上; 在壳体，底盘和船体底部组合的位置设置有翼翼，水平翼包括分别位于机身的前端和后端的稳定平面和升降机; 垂直双翅片布置在机身后端的两侧，其根部分固定连接到机翼上。

4. 发明申请

US20160025075A1 STIRLING ENGINE FOR AN EMISSION-FREE AIRCRAFT 有权
公开(公告)号：US20160025075A1
公开(公告)日：2016-01-28
申请号：US14877102
申请日：2015-10-07
申请人： EADS DEUTSCHLAND GMBH
发明人： Jost SEIFERT
IPC分类号： F03G6/06 , F03G7/06 , F02G1/055
CPC分类号： F03G6/068 , B64C1/16 , B64C3/32 , B64D13/006 , B64D27/02 , B64D27/04 , B64D27/06 , B64D27/08 , B64D27/24 , B64D2027/026 , F01B29/10 , F02G1/04 , F02G1/043 , F02G1/0435 , F02G1/044 , F02G1/053 , F02G1/0535 , F02G1/055 , F02G1/057 , F02G2243/02 , F02G2243/30 , F02G2244/50 , F02G2254/30 , F02G2280/10 , F03G7/06 , F25B9/14 , F25B2309/001 , F25B2309/003 , Y02E10/46 , Y02T50/62
摘要： Aircraft with an emission-free drive and method for emission-free driving of an aircraft. The aircraft includes a drive device structured and arranged to generate thrust, a lift device structured and arranged to generate lift, and a heat engine structured and arranged to convert thermal energy into kinetic energy to drive the drive device. The heat engine includes at least one flat-plate Stirling engine drivable by solar thermal radiation.

5. 发明申请

US20150114477A1 AIRCRAFT FUEL SUPPLY SYSTEMS 有权
标题翻译：飞机燃油供应系统
公开(公告)号：US20150114477A1
公开(公告)日：2015-04-30
申请号：US14395498
申请日：2013-04-18
申请人： EATON LIMITED
发明人： John Henry Wood
IPC分类号： F02M37/20 , B64D37/32 , F02M37/18
CPC分类号： F02M37/20 , B64C27/04 , B64D27/04 , B64D37/22 , B64D37/32 , F02C7/236 , F02C9/28 , F02M37/18 , F02M2037/085 , Y10T137/0379
摘要： A fuel supply system for an aircraft is provided for delivering in use fuel from a fuel tank to an aircraft powerplant. The in use fuel flows along a fuel flow passage from the fuel tank to the powerplant. A downstream pump is associated with the powerplant and configured to draw fluid along the fuel flow path so as to supply it to the powerplant in use. An upstream pump is disposed in or associated with the fuel tank and operable to pump fluid along the fuel flow passage. A pressure sensor is configured to monitor a pressure at an inlet to the downstream pump. A fuel system controller is responsive to the pressure sensor and configured to control the upstream pump so as to maintain the pressure at the inlet to the downstream pump at or above a predetermined threshold pressure.
摘要翻译：提供一种用于飞机的燃料供应系统，用于将燃料从燃料箱输送到飞行器动力装置。使用中的燃料沿着从燃料箱到动力装置的燃料流动通道流动。下游泵与动力装置相关联并且构造成沿着燃料流动路径抽取流体，以将其提供给使用中的动力装置。上游泵设置在燃料箱中或与燃料箱相关联并且可操作以沿着燃料流动通道泵送流体。压力传感器被配置为监测下游泵入口处的压力。燃料系统控制器响应于压力传感器并被配置为控制上游泵，以便将下游泵的入口处的压力保持在预定阈值压力以上。

6. 发明申请

US20130112158A1 AERODIESEL ENGINE 有权
标题翻译： AERODIESEL发动机
公开(公告)号：US20130112158A1
公开(公告)日：2013-05-09
申请号：US13650569
申请日：2012-10-12
申请人： Engineered Propulsion Systems, Inc.
发明人： Steven M. Weinzierl , Michael J. Fuchs
IPC分类号： F02B75/22 , B23P15/00
CPC分类号： F02B75/246 , B23P15/00 , B64D27/04 , F02B37/007 , F02B61/04 , F02B75/00 , F02B75/18 , F02B75/22 , F02B2075/1832 , F02D41/0082 , F02D41/0087 , Y02T50/44 , Y10T29/49231
摘要： The present invention is an aero engine that is provided with compression combustion and weighs less than 725 lbs. The present invention is further a method of forming the aero engine.
摘要翻译：本发明是一种具有压缩燃烧且重量小于725磅的航空发动机。本发明还涉及一种形成航空发动机的方法。

7. 发明授权

US07984684B2 Marine hulls and drives 失效
标题翻译：海洋船体和驱动器
公开(公告)号：US07984684B2
公开(公告)日：2011-07-26
申请号：US11545053
申请日：2006-10-06
申请人： Mitja Victor Hinderks
发明人： Mitja Victor Hinderks
IPC分类号： B63B1/24
CPC分类号： F02B77/13 , B63B1/28 , B63H5/125 , B63H21/14 , B63H21/20 , B63H2021/205 , B64D27/04 , B64D27/24 , B64D2027/026 , F01L1/0532 , F01L1/06 , F01L1/12 , F01L1/146 , F01L1/185 , F01L1/20 , F01L1/28 , F01L1/36 , F01L1/46 , F01L3/02 , F01L3/22 , F01L2001/0537 , F01L2101/00 , F01L2101/02 , F01L2105/00 , F02B59/00 , F02M26/00 , F02N11/04 , Y02T70/5209 , Y02T70/5218 , Y02T70/5236 , Y02T70/5281 , Y02T90/46 , Y10S903/905
摘要： The disclosure relates to marine craft which are capable of operating in the hydrofoil mode, many with extensible and retractable hydrofoil posts. Specific embodiments of large commercial hydrofoil craft are described, including those with structure which is the water during hydrofoil travel mode and which can be retracted to partly fit within recesses in the hull during other operating modes. Other craft, including those with hybrid electric drive, are disclosed having un-cooled reciprocating internal combustion engines. A number of arrangements for pistons and cylinders of unconventional configuration are described. These included are toroidal combustion or working chambers, some with fluid flow through the core of the toroid, pistons reciprocating between pairs of working chambers, tensile links between piston and crankshaft, energy absorbing piston-crank links, crankshafts supported on gas bearings. In some embodiments pistons mare rotate while reciprocating. High temperature exhaust emissions systems are described, including those containing filamentary material, as are procedures for reducing emissions during cold start by means of valves at reaction volume exit. Compound engines having the new engines as a reciprocating stage are described.
摘要翻译：本公开涉及能够以水翼模式操作的海洋工艺，许多具有可伸缩的水翼柱。描述了大型商用水翼工艺的具体实施例，包括在水翼行驶模式期间具有水的结构的那些，并且在其它操作模式期间可以缩回以部分地装配在船体的凹部内。公开了具有混合动力驱动装置的其它工艺，其具有未冷却的往复式内燃机。描述了用于非常规配置的活塞和气缸的多种布置。这些包括环形燃烧或工作室，一些流体流过环形磁芯，活塞在工作室对之间往复运动，活塞和曲轴之间的拉伸连接，能量吸收活塞 - 曲柄连杆，支撑在气体轴承上的曲轴。在一些实施例中，活塞在往复运动的同时旋转。描述了高温废气排放系统，包括含有丝状材料的系统，以及通过反应体积出口处的阀门减少冷启动期间的排放的程序。描述了具有新发动机作为往复运动台的复合发动机。

8. 发明申请

US20080297065A1 DUAL MODE SEARCHLIGHT DIMMING CONTROLLER SYSTEMS AND METHODS 有权
标题翻译：双模式搜索灯控制器系统和方法
公开(公告)号：US20080297065A1
公开(公告)日：2008-12-04
申请号：US11758499
申请日：2007-06-05
申请人： Saed M. Mubaslat , Craig E. Giffen , Richard P. Policy , Joseph L. Ferguson
发明人： Saed M. Mubaslat , Craig E. Giffen , Richard P. Policy , Joseph L. Ferguson
IPC分类号： H05B41/36
CPC分类号： H05B39/105 , B64D27/04 , B64D2203/00 , H05B33/0818 , H05B33/0851 , H05B37/036 , H05B39/047 , Y02B20/346 , Y02B20/48
摘要： A solid state microprocessor or digital signal processor (DSP) for dual mode illumination and dimming into modern aerospace searchlights. The system is a universal dimming platform with “smart functions” that include and are not limited to multiple light intensity linearization curves, analog and/or digital input dimming interface, built-in tests and health monitoring, synchronized dual mode light output with canopy position, light driver redundancy, lamp life reporting, and controlled switching with improved EMI. With real-time monitoring of the system parameters it monitors the lights proper operation and failures which can be a concern for flight-critical lighting.
摘要翻译：一种固态微处理器或数字信号处理器（DSP），用于双模照明和调光成现代航空航天探照灯。该系统是一个具有“智能功能”的通用调光平台，包括但不限于多个光强度线性化曲线，模拟和/或数字输入调光接口，内置测试和健康监测，具有冠层位置的同步双模光输出，光驱冗余，灯寿命报告，以及EMI改善的受控切换。通过实时监控系统参数，它可以监控灯具的正常运行和故障，这可能是飞行关键型照明的关键。

9. 发明申请

US20080027620A1 Piston Type Aircraft Engine 审中-公开
标题翻译：活塞式飞机发动机
公开(公告)号：US20080027620A1
公开(公告)日：2008-01-31
申请号：US11679130
申请日：2007-02-26
申请人： Josef Feuerlinger , Heinz Lippitsch , Johann Bayerl
发明人： Josef Feuerlinger , Heinz Lippitsch , Johann Bayerl
IPC分类号： B64D27/00
CPC分类号： F02B75/22 , B64D27/04 , F02B37/00 , F02B61/04 , F02B2075/027 , F02M63/0295 , F16F15/173 , Y02T10/144 , Y02T50/44 , Y10T74/2184
摘要： A propulsion assembly for propelling an aircraft is disclosed. The assembly includes a four stroke internal combustion engine, a propeller shaft that is operatively connected to the engine, and an electronic control unit that is connected to the engine and is configured to monitor and control at least one operating parameter of the engine. The engine includes two to twelve cylinders having a total displacement of less than 19.6 liters, and a crankshaft that is operatively connected to the cylinders. The crankshaft rotates at a speed of at least 3,000 rpm when the engine is operating under normal conditions. The engine also includes a closed loop liquid cooling system and a fuel injection system. The engine has a total power output of 140 to 600 hp, and a total wet installed weight of less than 1.1 kg/hp. The engine meets current RTCA DO-160d, RTCA DO-178b, and US FAA FAR33 guidelines.
摘要翻译：公开了一种用于推进飞行器的推进组件。组件包括四冲程内燃机，可操作地连接到发动机的螺旋桨轴和连接到发动机并被配置为监测和控制发动机的至少一个操作参数的电子控制单元。发动机包括总共位移小于19.6升的两至十二个气缸，以及可操作地连接到气缸的曲轴。当发动机在正常条件下运行时，曲轴以至少3,000rpm的速度旋转。发动机还包括闭环液体冷却系统和燃料喷射系统。发动机的总功率输出为140至600马力，总湿重小于1.1 kg / hp。发动机符合当前的RTCA DO-160d，RTCA DO-178b和美国FAA FAR33指南。

10. 发明授权

US06883752B2 Vibration damper for aircraft engine 失效
标题翻译：飞机发动机减振器
公开(公告)号：US06883752B2
公开(公告)日：2005-04-26
申请号：US10071233
申请日：2002-02-11
申请人： Thomas Koch , Johann Bayerl
发明人： Thomas Koch , Johann Bayerl
IPC分类号： B64D27/04 , F16F15/173 , B64D35/00
CPC分类号： F02B75/22 , B64D27/04 , F02B37/00 , F02B61/04 , F02B2075/027 , F02M63/0295 , F16F15/173 , Y02T10/144 , Y02T50/44 , Y10T74/2184
摘要： An internal combustion engine for an aircraft is described. The internal combustion engine includes a crankshaft defining first and second ends, a propeller, and a transmission disposed between the first end of the crankshaft and the propeller, operatively connecting the propeller to the crankshaft. A torsion bar is disposed between the first end of the crankshaft and the transmission, operatively connecting the crankshaft to the transmission. A torsional vibration damper is operatively connected at one of the first and the second ends of the crankshaft.
摘要翻译：描述了一种用于飞行器的内燃机。内燃机包括限定第一和第二端的曲轴，螺旋桨和布置在曲轴的第一端和螺旋桨之间的变速器，其将螺旋桨可操作地连接到曲轴。扭杆设置在曲轴的第一端和变速器之间，可操作地将曲轴连接到变速器。扭转振动阻尼器可操作地连接在曲轴的第一端和第二端中的一端。

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