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41. 发明申请

US20170088283A1 AIRCRAFT PROPELLER DRIVE SYSTEM 有权
公开(公告)号：US20170088283A1
公开(公告)日：2017-03-30
申请号：US14870971
申请日：2015-09-30
申请人： BRP-POWERTRAIN GMBH & CO. KG
发明人： Harald MITTERMAIER , Johann BAYERL , Michael DOPONA , Thomas BAUMGARTNER
IPC分类号： B64D35/02 , B64D27/02
CPC分类号： B64D35/02 , B64D27/02 , B64D27/04 , F16D7/027 , F16F15/129
摘要： An aircraft propeller drive system has a gear to be driven by an engine and having a first plurality of teeth. A torsion bar has a first end driven by the gear and a second end rotatable relative to the first end about a torsion axis by a torsion angle. An output shaft is driven by the second end and is adapted for connection to a propeller. A clutch has a driven member rotationally fixed to the output shaft and a driving member having a second plurality of teeth. The first and second pluralities of teeth engage each other when a variation in the torsion angle from a mean torsion angle is greater than a predetermined angle. Torque is transferred between the gear and the output shaft via the clutch when the first and second pluralities of teeth engage each other.

42. 发明授权

US09556838B2 Aircraft fuel supply systems 有权
标题翻译：飞机燃油供应系统
公开(公告)号：US09556838B2
公开(公告)日：2017-01-31
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 , F02C7/236 , F02C9/28 , B64D37/22 , B64D37/32 , F02M37/18 , B64D27/04 , F02M37/08
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。

43. 发明申请

US20170008627A1 Hybrid Power Supply For Electric Multirotor Rotorcraft 审中-公开
标题翻译：电动多转子旋翼机的混合动力电源
公开(公告)号：US20170008627A1
公开(公告)日：2017-01-12
申请号：US15207436
申请日：2016-07-11
申请人： Joaquin de Soto , Jorge F. Miranda
发明人： Joaquin de Soto , Jorge F. Miranda
IPC分类号： B64C39/02 , H02K7/18 , B64C27/08 , B64D27/02 , G07C5/00 , B64D33/08
CPC分类号： B64C39/024 , B64C27/08 , B64C27/20 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/044 , B64C2201/108 , B64C2201/141 , B64C2201/146 , B64C2211/00 , B64D27/04 , B64D27/24 , B64D2027/026 , G07C5/008 , H02J7/1423 , H02K7/1815 , Y02T50/64
摘要： Embodiments are directed towards hybrid power supply that provides electric power to a multirotor rotorcraft to extend range or flying time. In one embodiment, an internal combustion engine and fuel tank are provided that interoperate with a battery provided by a commercial multirotor rotorcraft to substantially extend flying time or flying distance.
摘要翻译：实施例涉及向多转子旋翼飞机提供电力以延长范围或飞行时间的混合动力电源。在一个实施例中，提供内燃机和燃料箱，其与由商用多转子旋翼飞机提供的电池相互作用以大大延长飞行时间或飞行距离。

44. 发明申请

US20160340035A1 PERSONAL FLIGHT VEHICLE 审中-公开
标题翻译：个人飞行车
公开(公告)号：US20160340035A1
公开(公告)日：2016-11-24
申请号：US15110335
申请日：2015-01-06
申请人： 4525612 CANADA INC. DBA MAGINAIRE
发明人： Catalin Alexandru DURU
IPC分类号： B64C39/02 , B64D31/04 , B64D27/24 , B64D27/04 , B64C27/20 , B64C15/12
CPC分类号： B64C39/026 , B64C15/12 , B64C27/20 , B64D27/04 , B64D27/24 , B64D31/04 , B64D2027/026
摘要： A personal flight vehicle including a platform base assembly that provides a surface upon which the feet of an otherwise free-standing person are positionable, and including a plurality of axial flow propulsion systems positioned about a periphery of the platform base assembly. The propulsion systems generate a thrust flow in a direction substantially perpendicular to the surface of the platform base assembly, where the thrust flow is unobstructed by the platform base assembly. The thrust flow has a sufficient intensity to provide vertical takeoff and landing, flight, hovering and locomotion maneuvers. The vehicle allows the pilot to control the spatial orientation of the platform base assembly by the movement, preferably direct, of at least part of his or her body, and the spatial movement of the vehicle is thus controlled.
摘要翻译：一种个人飞行器，其包括平台基座组件，该平台基座组件提供一个表面，在该表面上，否则自由人的脚可定位在该表面上，并且包括围绕平台基座组件的周边定位的多个轴流推进系统。推进系统在基本上垂直于平台基座组件的表面的方向上产生推力流，其中推力流不受平台基座组件的阻碍。推力流量具有足够的强度提供垂直起飞和着陆，飞行，悬停和运动机动。车辆允许飞行员通过其身体的至少一部分的运动（优选直接）来控制平台基座组件的空间取向，并且因此控制车辆的空间运动。

45. 发明授权

US09261039B2 System and method for alerting and suppression of detonation and/or pre ignition phenomena in internal combustion engines by monitoring RPM fluctuation 有权
公开(公告)号：US09261039B2
公开(公告)日：2016-02-16
申请号：US14373753
申请日：2012-12-04
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Bernard Grumer , Nathan Levy
IPC分类号： G01M15/11 , G01M15/04 , F02D41/22 , F02P5/152 , F02D35/02 , F02D41/14 , F02D41/26 , F02D37/02 , F02D41/00 , B64D31/00 , F02P5/04
CPC分类号： F02D41/22 , B64D27/04 , B64D31/00 , B64D31/06 , F02D35/02 , F02D35/024 , F02D35/027 , F02D37/02 , F02D41/0007 , F02D41/0097 , F02D41/1497 , F02D41/263 , F02D41/266 , F02D2200/1012 , F02P5/045 , F02P5/152 , G01M15/046 , G01M15/11 , Y02T10/144
摘要： An engine system with advance detection of detonation and/or pre ignition, the system comprising an engine, operative for propulsion of a vehicle by generating rotational motion, whose rotational velocity over time is monitored; and a detonation and/or pre ignition detector operative to provide an alert for impending detonation and/or pre ignition of the engine, if the rotational velocity fluctuates over time to an extent which is predetermined to be unsafe.

46. 发明授权

US08882027B2 Aircraft power plant, an aircraft, and a method of using a piston engine in a power plant having a conventional gearbox 有权
标题翻译：飞机发电厂，飞机，以及在具有常规齿轮箱的发电厂中使用活塞发动机的方法
公开(公告)号：US08882027B2
公开(公告)日：2014-11-11
申请号：US13111177
申请日：2011-05-19
申请人： Jérôme Chemin , Thomas Manfredotti , Christian Mercier
发明人： Jérôme Chemin , Thomas Manfredotti , Christian Mercier
IPC分类号： B64D27/04 , B64D35/02 , B64D27/00 , B64C27/14
CPC分类号： B64D35/02 , B64C27/14 , B64D27/00 , B64D27/04
摘要： The present invention relates to a power plant (10) having a piston engine (30) driving a conventional gearbox (20) dimensioned for a turbine engine, said piston engine (30) comprising a first row (31) of pistons (33) presenting an angle (α) relative to a second row (32) of pistons (33). The power plant includes a flywheel (50) and a torsion shaft (40) set into motion by said pistons (33), said torsion shaft (40) being arranged between the first and second rows (31, 32) of pistons.
摘要翻译：本发明涉及一种具有活塞发动机（30）的动力装置（10），所述活塞发动机（30）驱动用于涡轮发动机的常规齿轮箱（20），所述活塞式发动机（30）包括活塞（33）的第一排（31）相对于活塞（33）的第二排（32）的角度（α）。发电厂包括飞轮（50）和由所述活塞（33）运动的扭转轴（40），所述扭转轴（40）布置在活塞的第一和第二排（31,32）之间。

47. 发明授权

US08870114B2 Hybrid drive for helicopters 有权
标题翻译：混合动力直升机
公开(公告)号：US08870114B2
公开(公告)日：2014-10-28
申请号：US13679209
申请日：2012-11-16
申请人： EADS Deutschland GmbH , Eurocopter Deutschland GmbH
发明人： Jean Botti , Johannes Stuhlberger , Peter Jänker , Valentin Klöppel , Georg Niesl
IPC分类号： B64D27/00 , B64D35/02 , B64D27/04 , B64D27/24 , B64C27/14 , B64D27/02 , B64C27/04
CPC分类号： B64D35/02 , B60L11/12 , B60L2200/10 , B64C27/04 , B64C27/14 , B64D27/04 , B64D27/24 , B64D2027/026 , Y02T10/646 , Y02T10/7077 , Y02T50/64 , Y10S903/903
摘要： The rotors of a helicopter are powered by electric motors. The electrical energy required for this purpose is produced by a motor-generator unit, which comprises one or more internal combustion engines. The motor-generator unit can be secured under the cabin floor. This yields a hybrid helicopter that can set the rotational frequency of the rotors within a large interval.
摘要翻译：直升机的转子由电动马达驱动。为此目的所需的电能由包括一个或多个内燃机的电动发电机组产生。电动发电机组可以固定在机舱底部。这产生了可以在大的间隔内设定转子的旋转频率的混合直升机。

48. 发明申请

US20110281679A1 HYBRID TRANSMISSION USING PLANETARY GEARSET FOR MULTIPLE SOURCES OF TORQUE FOR MARINE, OR TWO WHEELED LAND VEHICLES 审中-公开
标题翻译：用于海上或两轮车辆的多种扭矩源的运营商齿轮混合传动
公开(公告)号：US20110281679A1
公开(公告)日：2011-11-17
申请号：US12982109
申请日：2010-12-30
申请人： Daniel Larrabee , Thomas Northrop Wormer , Matt Rhode , Eric Serani , Josh Marshman , Cody Humbarger , Daniel Gaide , Derek Hillery , Alec Velazco , Eric Petersen , Jean Nicolas Koster
发明人： Daniel Larrabee , Thomas Northrop Wormer , Matt Rhode , Eric Serani , Josh Marshman , Cody Humbarger , Daniel Gaide , Derek Hillery , Alec Velazco , Eric Petersen , Jean Nicolas Koster
IPC分类号： F16H3/72 , F16H57/08
CPC分类号： B64D35/08 , B60K6/365 , B60K6/48 , B64C39/024 , B64C2201/042 , B64C2201/044 , B64C2201/165 , B64D27/04 , B64D27/24 , B64D2027/026 , F16H3/72 , Y02T10/6221 , Y02T50/44 , Y02T50/64
摘要： Provided are alternative hybrid transmission systems for marine, or two wheeled land vehicles, as well as propulsion systems and vehicles comprising such transmission systems, to improve various propulsion systems using a combination of at least two power sources with the option for simultaneous or alternating power input from two or more power sources, while providing desired characteristics or components. Such characteristics or components can include, but are not limited to: power, torque, acceleration, cruising speed or power, fuel efficiency, battery charging, endurance, power sizing, weight, capacity, efficiency, speed, mechanically and/or electrically added system requirements, design, fuel selection, functional design, structural design, lift to drag ratio, weight, and/or other desired characteristic or component.
摘要翻译：提供用于海洋或两轮陆地车辆的替代混合动力传动系统以及包括这种传动系统的推进系统和车辆，以改善使用至少两个动力源的组合的各种推进系统以及用于同时或交替动力输入的选项来自两个或更多个电源，同时提供期望的特性或部件。这些特征或组件可以包括但不限于：功率，扭矩，加速度，巡航速度或功率，燃料效率，电池充电，耐久性，功率尺寸，重量，容量，效率，速度，机械和/或电气附加系统要求，设计，燃料选择，功能设计，结构设计，提升阻力比，重量和/或其他所需特性或部件。

49. 发明申请

US20080006739A1 Vehicle power train including at least two power sources 审中-公开
标题翻译：车辆动力传动系包括至少两个动力源
公开(公告)号：US20080006739A1
公开(公告)日：2008-01-10
申请号：US11607854
申请日：2006-12-04
申请人： Kazuhiko Mochida , Curtis Longo , Garrick Talavera , Takao Tate , Michael Maxwell
发明人： Kazuhiko Mochida , Curtis Longo , Garrick Talavera , Takao Tate , Michael Maxwell
IPC分类号： B64D35/00 , F16F15/00 , F16H37/06
CPC分类号： B64D35/08 , B60L2200/10 , B60L2220/42 , B64C27/04 , B64D27/04 , B64D31/00 , F02B73/00 , H02K7/116 , H02K16/00 , H02K2213/06 , Y02T10/641 , Y02T10/646 , Y02T50/44 , Y10T74/19051 , Y10T477/60
摘要： A power train for a vehicle may include at least two power sources configured to supply power for propelling the vehicle. Each of the power sources may include a power source output shaft. The power train may further include a transmission including at least two transmission inputs operably coupled to the at least two power source output shafts, and a single transmission output shaft configured to supply power to a propulsion member. The power train may also include a controller configured to control operation of the at least two power sources, and the controller may include a full-authority digital electronic controller (FADEC).
摘要翻译：用于车辆的动力传动系可以包括被配置为提供用于推进车辆的动力的至少两个动力源。每个电源可以包括电源输出轴。动力传动系可以进一步包括传动装置，其包括可操作地联接到所述至少两个动力源输出轴的至少两个变速器输入，以及构造成向推进构件供给动力的单个变速器输出轴。动力传动系还可以包括被配置为控制至少两个电源的操作的控制器，并且控制器可以包括全权限的数字电子控制器（FADEC）。

50. 发明申请

US20040031267A1 CONTROL SYSTEM FOR A TURBO-CHARGED DIESEL AIRCRAFT ENGINE 失效
标题翻译：涡轮增压柴油机发动机的控制系统
公开(公告)号：US20040031267A1
公开(公告)日：2004-02-19
申请号：US10219494
申请日：2002-08-16
申请人： TOYOTA JIDOSHA KABUSHIKI KAISHA
发明人： Yukio Otake
IPC分类号： F02D023/00 , F04D029/26 , F04D029/18 , B64C011/30 , F01D007/00 , B63H003/10
CPC分类号： F02D1/065 , B64C11/303 , B64C11/305 , B64D27/04 , B64D31/14 , F02C9/48 , F02D23/02 , F02D31/001 , F02D41/0007 , F02D41/021 , F02D2250/38 , F05D2270/05 , Y02T10/144
摘要： In the control system for a turbo-charged diesel aircraft engine, the engine speed and the fuel injection amount are controlled by a single control lever in such a manner that the engine speed and the fuel injection amount maintain a predetermined fixed relationship in which the fuel injection amount is always smaller than a smoke limit amount. The control system further includes a boost compensator, that restricts the fuel injection amount to a value less than a boost pressure fuel limit determined by the boost pressure of the engine, and an altitude compensator that restricts the fuel injection amount to the value less than an altitude fuel limit.
摘要翻译：在用于涡轮增压柴油飞机发动机的控制系统中，发动机转速和燃料喷射量由单个控制杆控制，使得发动机转速和燃料喷射量保持预定的固定关系，其中燃料喷射量总是小于烟雾限制量。控制系统还包括升压补偿器，其将燃料喷射量限制为小于由发动机的增压压力确定的增压压力燃料极限的值;以及高度补偿器，其将燃料喷射量限制为小于高空燃油限制。

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