-
公开(公告)号：US20130168493A1
公开(公告)日：2013-07-04
申请号：US13532699
申请日：2012-06-25
申请人： Matthew Todd Keennon , Karl Robert Klingebiel , Alexander Andryukov , Bart Dean Hibbs , John Peter Zwaan
发明人： Matthew Todd Keennon , Karl Robert Klingebiel , Alexander Andryukov , Bart Dean Hibbs , John Peter Zwaan
IPC分类号： B64C33/02
CPC分类号： B64C33/025 , B64C19/00 , B64C33/02 , B64C2201/025 , B64C2201/10 , B64C2201/146
摘要： Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.
-
公开(公告)号：US08205823B2
公开(公告)日：2012-06-26
申请号：US12795539
申请日：2010-06-07
申请人： Matthew Todd Keennon , Karl Robert Klingebiel , Alexander Andryukov , Bart Dean Hibbs , John Peter Zwaan
发明人： Matthew Todd Keennon , Karl Robert Klingebiel , Alexander Andryukov , Bart Dean Hibbs , John Peter Zwaan
IPC分类号： B64C33/00
CPC分类号： B64C33/025 , B64C19/00 , B64C33/02 , B64C2201/025 , B64C2201/10 , B64C2201/146
摘要： Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.
摘要翻译： 比空中飞行器，具有扑翼的飞机，例如鸟巢飞机，其中角度定向控制是通过在扫掠角度行程和/或控制可变翼膜张力的过程中可展开的翼的偏转的可变差分扫掠角来实现的 。
-
公开(公告)号：US20100308160A1
公开(公告)日：2010-12-09
申请号：US12795539
申请日：2010-06-07
申请人： Matthew Todd Keennon , Karl Robert Klingebiel , Alexander Andryukov , Bart Dean Hibbs , John Peter Zwaan
发明人： Matthew Todd Keennon , Karl Robert Klingebiel , Alexander Andryukov , Bart Dean Hibbs , John Peter Zwaan
CPC分类号： B64C33/025 , B64C19/00 , B64C33/02 , B64C2201/025 , B64C2201/10 , B64C2201/146
摘要： Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.
摘要翻译： 比空中飞行器，具有扑翼的飞机，例如鸟巢飞机，其中角度定向控制是通过在扫掠角度行程和/或控制可变翼膜张力的过程中可展开的翼的偏转的可变差分扫掠角来实现的 。
-
公开(公告)号：US20120048994A1
公开(公告)日：2012-03-01
申请号：US13023772
申请日：2011-02-09
CPC分类号： B64C33/025 , B64C19/00 , B64C33/02 , B64C2201/025 , B64C2201/10 , B64C2201/146
摘要： Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.
摘要翻译： 比空中飞行器，具有扑翼的飞机，例如鸟巢飞机，其中角度定向控制是通过在扫掠角度行程和/或控制可变翼膜张力的过程中可展开的翼的偏转的可变差分扫掠角来实现的 。
-
公开(公告)号：US08210471B2
公开(公告)日：2012-07-03
申请号：US13023772
申请日：2011-02-09
IPC分类号： B64C33/00
CPC分类号： B64C33/025 , B64C19/00 , B64C33/02 , B64C2201/025 , B64C2201/10 , B64C2201/146
摘要： Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.
-
公开(公告)号：US20100194218A1
公开(公告)日：2010-08-05
申请号：US12565710
申请日：2009-09-23
IPC分类号： H02K9/00
CPC分类号： H02K3/14 , H02K3/30 , H02K3/32 , H02K3/47 , H02K7/14 , H02K9/02 , H02K9/06 , H02K9/14 , H02K9/22 , H02K16/02 , H02K21/12 , Y02E10/725 , Y10T29/49009
摘要： In one possible implementation, a motor is provided including a rotor and a stator. Front cooling fins are thermally coupled to a front of the stator, and rear cooling fins are thermally coupled to a rear portion of the stator. The winding is between the front and rear cooling fins.
摘要翻译： 在一个可能的实施方式中，提供了包括转子和定子的电动机。 前冷却翅片热耦合到定子的前部，并且后冷却片热耦合到定子的后部。 绕组在前后冷却片之间。
-
公开(公告)号：US20100187237A1
公开(公告)日：2010-07-29
申请号：US12586544
申请日：2009-09-23
CPC分类号： F17C1/12 , F17C2201/0128 , F17C2203/0325 , F17C2203/0329 , F17C2203/0358 , F17C2203/0391 , F17C2203/0395 , F17C2203/0604 , F17C2203/0629 , F17C2203/0643 , F17C2203/0646 , F17C2203/0673 , F17C2205/0314 , F17C2205/0332 , F17C2205/0352 , F17C2209/22 , F17C2209/221 , F17C2209/227 , F17C2209/238 , F17C2221/012 , F17C2223/0161 , F17C2223/033 , F17C2223/047 , F17C2227/0304 , F17C2227/0306 , F17C2227/0381 , F17C2250/0408 , F17C2250/043 , F17C2250/0636 , F17C2260/012 , F17C2260/033 , F17C2265/034 , F17C2270/0189 , Y02E60/321 , Y10T29/49 , Y10T29/49826 , Y10T137/0318
摘要： A hydrogen storage tank for a hydrogen fueled aircraft. The tank has a wall made of layers of aerogel sections around a hard shell layer, sealed within a flexible outer layer, and having the air removed to form a vacuum. The periphery of each layer section abuts other sections of that layer, but only overlies the periphery of the sections of other layers at individual points. The wall is characterized by a thermal conductivity that is lower near its gravitational top than its gravitational bottom. The tank has two exit passageways, one being direct, and the other passing through a vapor shield that extends through the wall between two layers of aerogel. A control system controls the relative flow through the two passages to regulate the boil-off rate of the tank.
摘要翻译： 用于氢燃料飞机的储氢罐。 罐具有由围绕硬壳层的气凝胶部分的层制成的壁，密封在柔性外层内，并且除去空气以形成真空。 每个层部分的周边邻接该层的其他部分，但仅在各个点处覆盖其它层的部分的周边。 该壁的特征在于导热系数在其重力顶部附近比其引力底部更低。 该罐具有两个出口通道，一个是直接通道，另一个通过蒸气屏蔽，其在两层气凝胶之间延伸穿过壁。 控制系统控制通过两个通道的相对流量来调节罐的沸腾速率。
-
公开(公告)号：US08604652B2
公开(公告)日：2013-12-10
申请号：US12565715
申请日：2009-09-23
CPC分类号： H02K3/14 , H02K3/30 , H02K3/32 , H02K3/47 , H02K7/14 , H02K9/02 , H02K9/06 , H02K9/14 , H02K9/22 , H02K16/02 , H02K21/12 , Y02E10/725 , Y10T29/49009
摘要： In one possible embodiment, an aircraft electric motor cooling system is provided having an airflow path through a spinner which includes a first airflow path between an inner rotor and a stator, a second airflow path between an outer rotor the stator and a third airflow path along an outer surface of the outer rotor.
摘要翻译： 在一个可能的实施例中，提供了一种飞行器电动机冷却系统，其具有通过旋转器的气流路径，该旋转器包括内转子和定子之间的第一气流路径，位于外转子与定子之间的第二气流路径和沿着 外转子的外表面。
-
公开(公告)号：US20130047435A1
公开(公告)日：2013-02-28
申请号：US13220343
申请日：2011-08-29
IPC分类号： B21D53/02
CPC分类号： B23P15/26 , B32B5/18 , B32B9/005 , B32B9/007 , B32B33/00 , B32B37/142 , B32B2307/302 , B32B2605/18 , B64D13/006 , B64D2013/0614 , F28D9/0025 , F28D9/0081 , F28F3/005 , F28F3/027 , F28F21/02 , F28F2245/04 , H01L23/34 , H01L23/467 , H01L2924/0002 , H05K7/20509 , Y10T29/4935 , H01L2924/00
摘要： A method of manufacturing a heat transfer system is provided that includes, in one form, preparing a heat conducting array by perforating at least a portion of the heat conducting array, wrapping the heat conducting array around foam elements, placing a heat conducting spreader along one surface area of the foam elements, placing a lower skin over the heat conducting spreader, placing an upper skin over an opposite surface area of the foam elements to create a structural assembly, and curing the structural assembly. A material of the foam elements flows through the perforated portion of the heat conducting array during the curing step.
摘要翻译： 提供一种制造传热系统的方法，其一种形式包括通过穿透至少一部分导热阵列来制备导热阵列，将热传导阵列围绕泡沫元件缠绕，沿着一个放置导热散热器 泡沫元件的表面积，将较低的皮肤放置在导热吊具上方，将上部皮肤放置在泡沫元件的相对表面区域上以形成结构组件，并固化该结构组件。 在固化步骤期间，泡沫元件的材料流过导热阵列的穿孔部分。
-
公开(公告)号：US20100192890A1
公开(公告)日：2010-08-05
申请号：US12586631
申请日：2009-09-23
CPC分类号： F02B43/00 , F01P2050/20 , F01P2060/02 , F01P2060/10 , F02B29/0412 , F02B29/0493 , F02C6/12 , F02C7/143 , F02C7/16 , F02C7/224 , F02M31/02 , F02M31/16 , F02M31/20 , F05D2260/205 , Y02T10/126 , Y02T10/146 , Y02T50/675
摘要： A high-altitude aircraft powerplant including an engine, a two-stage turbocharger having an intercooler and an aftercooler, a cryogenic hydrogen fuel source, and a cooling system including a hydrogen heat exchanger. Aided by a ram-air cooler that cools a coolant to a near-ambient temperature, the heat exchanger is configured to heat the hydrogen using the coolant, and to cool the coolant to a temperature well below the ambient temperature during high-altitude flight. The intercooler and aftercooler use the sub-ambient temperature coolant, as does a separate sensor. The ram-air cooler includes a front portion and a rear portion. The cooling system includes three cooling loops which respectively incorporate only the front portion, only the rear portion, and both portions of the ram-air cooler.
摘要翻译： 包括发动机的高空飞机动力装置，具有中间冷却器和后冷器的两级涡轮增压器，低温氢燃料源和包括氢热交换器的冷却系统。 在冷却剂冷却至接近环境温度的冲压空气冷却器的帮助下，热交换器被配置为使用冷却剂加热氢气，并且在高空飞行期间将冷却剂冷却至远低于环境温度的温度。 中间冷却器和后冷却器与单独的传感器一样使用次环境温度的冷却液。 冲压空气冷却器包括前部和后部。 冷却系统包括三个冷却回路，其仅分别仅包括前部，后部和压缩空气冷却器的两个部分。
-
-
-
-
-
-
-
-
-
搜索结果
25 条记录 (耗时 0.027 秒)
