专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

81. 发明申请

US20160130010A1 INVERTIBLE AIRCRAFT 有权
标题翻译：可反转的飞机
公开(公告)号：US20160130010A1
公开(公告)日：2016-05-12
申请号：US14885972
申请日：2015-10-16
申请人： AeroVironment Inc.
发明人： Matthew Todd Keennon , Karl Robert Klingebiel
IPC分类号： B64D31/00 , B64C27/08 , B64C39/02 , B64C27/473
CPC分类号： B64D31/06 , B64C11/20 , B64C11/32 , B64C27/04 , B64C27/06 , B64C27/08 , B64C27/12 , B64C27/473 , B64C27/59 , B64C29/0033 , B64C39/02 , B64C39/024 , B64C39/028 , B64C2027/4733 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/126 , B64C2201/127 , B64D31/00 , G05D1/0038 , G05D1/005
摘要： A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.
摘要翻译：旋翼航空器包括机身，一个或多个用于垂直飞行的电动驱动转子和控制系统。电动机在两个旋转方向中驱动一个或多个转子，以提供垂直或反向的飞行。使用方向传感器来控制推力的主要方向，并且基于机身相对于重力的取向来自动地调整操作指令和收集的信息。转子配置有转向符合旋转方向的叶片。

82. 发明申请

US20160083085A1 ELECTRIFIED ROTORCRAFT 审中-公开
标题翻译：电动转子
公开(公告)号：US20160083085A1
公开(公告)日：2016-03-24
申请号：US14811186
申请日：2015-07-28
申请人： Sikorsky Aircraft Corporation
发明人： Michael Peter Strauss , Mark Denton Bystry, JR. , Michael Joseph DeVita
IPC分类号： B64C27/12 , B64D35/00 , B64D31/00
CPC分类号： B64C27/12 , B64C27/14 , B64D31/00 , B64D35/00 , B64D2027/026
摘要： An electrified propulsion system for a rotary wing aircraft includes a flight control computer that receives a signal indicative of a power demand on an engine; an engine control system that is in communication with the engine and is configured to control operation of the engine at a selected operating point; a generator that is in mechanical communication with the engine and is configured to receive mechanical power from the engine and convert the mechanical power to electrical power; an electric motor that is in electrical communication with the generator and is configured to receive the electric power; and a rotor that is in mechanical communication with the electric motor; wherein the electric motor is configured to control rotation and provide the mechanical power demand of the rotor at the selected operating point in response to the received signal.
摘要翻译：用于旋翼机的电气化推进系统包括飞行控制计算机，其接收指示发动机的功率需求的信号; 发动机控制系统，其与所述发动机通信并被配置为在所选择的操作点处控制所述发动机的操作; 与发动机机械连通的发电机，其被构造成从发动机接收机械动力并将机械动力转换成电力; 电动机，其与发电机电连通并被配置为接收电力; 以及与所述电动机机械连通的转子; 其中所述电动机被配置为响应于所述接收到的信号来控制旋转并且在所选择的操作点提供所述转子的机械功率需求。

83. 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.

84. 发明授权

US09242738B2 Personal aircraft 有权
公开(公告)号：US09242738B2
公开(公告)日：2016-01-26
申请号：US13931954
申请日：2013-06-30
申请人： Zee.Aero Inc.
发明人： Ilan Kroo
IPC分类号： B64C27/22 , B64D31/00 , B64C3/16 , B64C29/00 , B64C39/12
CPC分类号： B64D31/00 , B64C3/16 , B64C29/00 , B64C29/0025 , B64C39/12 , Y02T50/12
摘要： A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.

85. 发明授权

US09193453B2 Method of driving rotation of a rotorcraft rotor by anticipating torque needs between two rotary speed setpoints of the rotor 有权
标题翻译：通过预期转子的两个转速设定值之间的扭矩需求来驱动旋翼航空器转子的旋转的方法
公开(公告)号：US09193453B2
公开(公告)日：2015-11-24
申请号：US14140647
申请日：2013-12-26
申请人： AIRBUS HELICOPTERS
发明人： Jean-Baptiste Vallart , Hilario Vieira
IPC分类号： B64C19/00 , B64C27/32 , B64C27/57 , B64C27/12 , B64D31/00 , B64D31/06 , F02C9/00 , B64C27/04
CPC分类号： B64D31/06 , B64C27/04 , B64C27/12 , B64C27/57 , B64D31/00 , F02C9/00 , F05D2220/329 , F05D2270/335 , F05D2270/44 , Y02T50/671
摘要： A method of driving a rotorcraft rotor (1, 2) at variable controlled speeds. Starting from a required speed (Nr), a setpoint for total power (Pt) is calculated while taking account of an anticipated power (Pf) to be delivered by the power plant (3) for driving the main rotor (1) at the required speed (Nr), and while taking account of a power surplus (S) relating to progressive power needs to be delivered from a current power (Pc) for driving the main rotor (1) at a current speed (V) of rotation to an anticipated power (Pf) for driving the main rotor (1) at the required speed (Nr). By way of example, account may be taken at least of the acceleration or conversely of the deceleration of the main rotor (1) between the current speed (V) and the required speed (Nr), or indeed account may be taken of the flight circumstance of the rotorcraft determining the calculated required speed (Nr).
摘要翻译：以可变的受控速度驱动旋翼航空器转子（1,2）的方法。从所需速度（Nr）开始，计算用于总功率（Pt）的设定点，同时考虑由用于驱动主转子（1）的所需发电厂（3）提供的预期功率（Pf）速度（Nr），并且考虑到与逐行动力有关的功率剩余（S）需要从用于驱动主转子（1）的当前功率（Pc）以当前旋转速度（V）传递到用于以所需速度（Nr）驱动主转子（1）的预期功率（Pf）。作为示例，可以至少考虑到当前速度（V）和所需速度（Nr）之间的主转子（1）的减速度的加速度或相反，或者实际上可以考虑飞行旋翼航空器确定计算所需速度（Nr）的情况。

86. 发明授权

US09169027B2 Electrified rotorcraft 有权
标题翻译：电动旋翼飞机
公开(公告)号：US09169027B2
公开(公告)日：2015-10-27
申请号：US14046377
申请日：2013-10-04
申请人： Michael Peter Strauss , Mark Denton Bystry, Jr. , Michael Joseph DeVita
发明人： Michael Peter Strauss , Mark Denton Bystry, Jr. , Michael Joseph DeVita
IPC分类号： G01C23/00 , B64D31/00 , B64D35/00 , B64C27/14 , B64D27/02
CPC分类号： B64C27/12 , B64C27/14 , B64D31/00 , B64D35/00 , B64D2027/026
摘要： An electrified propulsion system for a rotary wing aircraft includes a flight control computer that receives a signal indicative of a power demand on an engine; an engine control system that is in communication with the engine and is configured to control operation of the engine at a selected operating point; a generator that is in mechanical communication with the engine and is configured to receive mechanical power from the engine and convert the mechanical power to electrical power; an electric motor that is in electrical communication with the generator and is configured to receive the electric power; and a rotor that is in mechanical communication with the electric motor; wherein the electric motor is configured to control rotation and provide the mechanical power demand of the rotor at the selected operating point in response to the received signal.
摘要翻译：用于旋翼机的电气化推进系统包括飞行控制计算机，其接收指示发动机的功率需求的信号; 发动机控制系统，其与所述发动机通信并被配置为在所选择的操作点处控制所述发动机的操作; 与发动机机械连通的发电机，其被构造成从发动机接收机械动力并将机械动力转换成电力; 电动机，其与发电机电连通并被配置为接收电力; 以及与所述电动机机械连通的转子; 其中所述电动机被配置为响应于所述接收到的信号来控制旋转并且在所选择的操作点提供所述转子的机械功率需求。

87. 发明申请

US20150115706A1 METALLISATION OF AN ELECTRICALLY INSULATING HOUSING OF AN AERONAUTIC ENGINE 有权
标题翻译：航空发动机电气绝缘外壳的金属化
公开(公告)号：US20150115706A1
公开(公告)日：2015-04-30
申请号：US14528467
申请日：2014-10-30
申请人： SNECMA
发明人： Julien SAYN-URPAR , Jeremy Edmond FERT , Thierry KOHN , Julien PAVILLET
IPC分类号： B64D31/00
CPC分类号： B64D31/00 , F01D25/28 , F02C7/32 , H01R4/64 , Y02T50/672
摘要： The invention relates to an aeronautic engine (1), comprising: a housing (10), made of electrically insulating material, said housing (10) comprising at least one metallic piece (16a, 16b, 17, 18), a structural piece (2) of the engine (1), comprising metallic material (2, 3) and connected to the housing (10), and an equipment (30), fixed to the housing (10), the aeronautic engine (1) being characterized in that the equipment is connected to the structural piece (2) by means of the metallic piece (16a, 16b, 17, 18) by means of an electrically conductive connecting path (20, 22).
摘要翻译：本发明涉及一种航空发动机（1），包括：由电绝缘材料制成的壳体（10），所述壳体（10）包括至少一个金属片（16a，16b，17,18），结构件包括金属材料（2,3）并连接到壳体（10）的发动机（1）的外壳（2）和固定到壳体（10）的设备（30），其特征在于：设备通过导电连接路径（20,22）通过金属片（16a，16b，17,18）连接到结构件（2）。

88. 发明申请

US20150076279A1 EXTENDED ENDURANCE AIR VEHICLE 审中-公开
标题翻译：延伸耐用空气车辆
公开(公告)号：US20150076279A1
公开(公告)日：2015-03-19
申请号：US14485685
申请日：2014-09-13
申请人： William Edmund Nelson
发明人： William Edmund Nelson
IPC分类号： B64B1/02 , B64D33/00 , B64D31/00
CPC分类号： B64B1/02 , B64B1/10 , B64B1/12 , B64B1/20 , B64B1/22 , B64B1/28 , B64B1/32 , B64B1/34 , B64B1/58 , B64B2201/00 , B64D27/24 , B64D2211/00 , G05D1/0011
摘要： An air vehicle comprises a vehicle body and a propulsion assembly. The vehicle body has the shape of a wing airfoil so that the vehicle body generates lift when air flows over the vehicle body. The vehicle body has a body longitudinal axis, and includes a first hull and a second hull that are secured together side-by-side, the hulls having longitudinal axes that are substantially parallel to the body longitudinal axis. Each hull defines a separate fluid chamber that is filled with a fluid that is at least partially buoyant. The propulsion assembly is secured to the vehicle body. The propulsion assembly generates thrust and includes a port front engine, a port rear engine, a starboard front engine, and a starboard rear engine, wherein at least two of the engines have independently controlled thrust vectors.
摘要翻译：一种机动车辆包括车体和推进组件。车身具有翼型件的形状，使得当空气流过车体时车身产生升力。车体具有主体纵向轴线，并且包括并排固定在一起的第一船体和第二船体，所述船体具有基本上平行于主体纵向轴线的纵向轴线。每个船体限定了一个单独的流体室，其中填充有至少部分浮力的流体。推进组件固定在车体上。推进组件产生推力并且包括端口前置发动机，端口后部发动机，右舷前置发动机和右舷后部发动机，其中至少两个发动机具有独立控制的推力矢量。

89. 发明申请

US20140365039A1 SYSTEM AND METHOD FOR MAXIMIZING AIRCRAFT SAFE LANDING CAPABILITY DURING ONE ENGINE INOPERATIVE OPERATION 审中-公开
标题翻译：在一个发动机无效操作期间最大化飞机安全着陆能力的系统和方法
公开(公告)号：US20140365039A1
公开(公告)日：2014-12-11
申请号：US14297159
申请日：2014-06-05
申请人： BELL HELICOPTER TEXTRON INC.
发明人： Joseph M. Schaeffer , Jignesh Patel , Eric O'Neill
IPC分类号： B64D31/00 , B64C27/54 , B64C19/00
CPC分类号： B64D31/00 , B64C19/00 , B64C27/54 , B64C27/57 , G05D1/0072
摘要： A method of preserving rotor speed during a one engine inoperative operation of an rotorcraft, the method can include: detecting a failure of a first engine; monitoring an engine parameter associated with a second engine; using a computer processor to compare the engine parameter to an engine limit; and commanding a decrease collective pitch command when the engine parameter is within a predefined range of the engine limit.
摘要翻译：一种在旋转飞机的一个发动机不工作的操作期间保持转子速度的方法，所述方法可以包括：检测第一发动机的故障; 监测与第二发动机相关联的发动机参数; 使用计算机处理器将发动机参数与发动机限制进行比较; 并且当所述发动机参数在所述发动机限制的预定义范围内时，命令减小集体俯仰命令。

90. 发明授权

US08903622B2 Vehicle power generation system and method thereof 有权
标题翻译：车辆发电系统及其方法
公开(公告)号：US08903622B2
公开(公告)日：2014-12-02
申请号：US13548413
申请日：2012-07-13
申请人： Chien-Ping Tseng
发明人： Chien-Ping Tseng
IPC分类号： B64D31/00 , B60W30/188 , B60L11/12 , B60W10/02 , B60R16/02 , B60W10/30 , B60W10/06 , B60L3/00
CPC分类号： B60W30/1886 , B60L3/0069 , B60L11/12 , B60R16/02 , B60W10/02 , B60W10/06 , B60W10/30 , Y02T10/70 , Y02T10/7077 , Y02T10/7258
摘要： The vehicle power generation system includes: a power generation unit, a power supply unit, a clutch mechanism, and a control unit. The power generation unit includes generator, power input shaft, and a power output unit. The clutch mechanism includes a speed increasing unit and a motor controller for attaching the speed increasing unit to the crankshaft or detaching the speed increasing unit from the crankshaft. The control unit is electrically connected to the motor controller, and includes a power generation condition determining unit.
摘要翻译：车辆发电系统包括：发电单元，电源单元，离合器机构和控制单元。发电单元包括发电机，动力输入轴和动力输出单元。离合器机构包括增速单元和用于将增速单元附接到曲轴或将增速单元从曲轴分离的马达控制器。控制单元电连接到电动机控制器，并且包括发电条件确定单元。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式