公开(公告)号：US12115881B2

公开(公告)日：2024-10-15

申请号：US17172384

申请日：2021-02-10

申请人： Bell Textron Inc.

发明人： William A Amante

IPC分类号： B60L50/60 ,  B60L53/50 ,  B60L58/26 ,  B64C1/38 ,  B64D27/24 ,  H01M10/613 ,  H01M10/625 ,  H01M10/6556

CPC分类号： B60L58/26 ,  B60L50/60 ,  B60L53/50 ,  B64C1/38 ,  B64D27/24 ,  H01M10/613 ,  H01M10/625 ,  H01M10/6556 ,  B60L2200/10 ,  H01M2220/20

摘要： A nonintegral cold plate is described for providing cooling of battery charging. The nonintegrated cold plate can receive and circulate coolant against a surface of a battery or of a vehicle. After charging the nonintegrated cold plate can be removed to save weight on the vehicle's payload.

公开(公告)号：US20240262517A1

公开(公告)日：2024-08-08

申请号：US18586428

申请日：2024-02-24

申请人： Joby Aero, Inc.

发明人： JoeBen Bevirt ,  Gregor Veble Mikic ,  Joey Milia ,  Rob Thodal ,  Vishnu Vithala

IPC分类号： B64D27/24 ,  B64C1/38 ,  B64C21/08 ,  B64C23/00 ,  B64C27/32

CPC分类号： B64D27/24 ,  B64C1/38 ,  B64C23/005 ,  B64C21/08 ,  B64C27/32 ,  B64C2230/04

摘要： An aircraft propulsion system with an internally cooled electric motor adapted for use in an aerial vehicle. The motor may have its stator towards the center and have an external rotor. The rotor structure may be air cooled and may be a complex structure with an internal lattice adapted for airflow. The stator structure may be liquid cooled and may be a complex structure with an internal lattice adapted for liquid to flow through. A fluid pump may pump a liquid coolant through non-rotating portions of the motor stator and then through heat exchangers cooled in part by air which has flowed through the rotating portions of the motor rotor. The drag reduction portion and the cooled electric motor portion may share the same inlet.

公开(公告)号：US11873073B2

公开(公告)日：2024-01-16

申请号：US17186519

申请日：2021-02-26

申请人： Hamilton Sundstrand Corporation

发明人： William E. Rhoden ,  Anders Walker ,  David Cripe ,  Ross Keith Wilcoxon ,  Jeremiah Wolf

IPC分类号： B64C1/38 ,  F28D1/02

CPC分类号： B64C1/38 ,  F28D1/0233 ,  F28F2280/00

摘要： Phased array antennas, such as a multi-function aperture, are limited in performance and reliability by traditional air-cooled thermal management systems. A fuel-cooled multi-function aperture passes engine fuel through heat exchangers that surround the multi-function aperture to provide better heat transfer than can be achieved through air cooling systems. The increased heat transfer and thermal management results in a multi-function aperture with improved performance and reliability.

公开(公告)号：US20180257756A1

公开(公告)日：2018-09-13

申请号：US15977174

申请日：2018-05-11

申请人： ROHR, INC.

发明人： Teresa M. Kruckenberg ,  Vijay V. Pujar ,  Robert L. Braden

IPC分类号： B64C1/38 ,  B64C21/00 ,  B64C23/00

CPC分类号： B64C1/38 ,  B64C21/00 ,  B64C23/005 ,  B64C2220/00 ,  B64C2230/02 ,  Y02T50/166

摘要： A method of generating a pressure wave proximate an airflow surface and altering airflow to promote a localized lowering of skin friction over the airflow surface is described herein. A series of pressure waves may be configured to create a virtual riblet to control turbulent vortices in a boundary layer adjacent to the airflow surface creating a virtual riblet. The pressure waves may be configured to prevent disruption of the flow of air relative to at least one of a step or a gap associated with the airflow surface. The pressure wave generating system may be comprised of at least one of a thermoacoustic material, a piezoelectric material and a semiconductor material, and a microelectric circuit.

公开(公告)号：US20180186478A1

公开(公告)日：2018-07-05

申请号：US15813343

申请日：2017-11-15

申请人： NATIONAL CHUNG SHAN INSTITUTE OF SCIENCE AND TECHNOLOGY

发明人： MAU-YI HUANG ,  REN-SO DENG ,  GENG-WEN CHANG ,  DAR-PING JUANG ,  CHENG-HUAN WANG

IPC分类号： B64G1/58 ,  B64C1/38 ,  B29C70/08

CPC分类号： B64G1/58 ,  B29C65/02 ,  B29C66/1282 ,  B29C66/1284 ,  B29C66/1286 ,  B29C66/543 ,  B29C66/7212 ,  B29C66/73754 ,  B29C70/081 ,  B32B2307/304 ,  B32B2307/3065 ,  B32B2605/18 ,  B64C1/38 ,  B64C30/00

摘要： An integrated heat shield which encloses a frame structure comprises a leading edge component, a left side component, a right side component, an optionally top component, an optional bottom component and an optional trailing edge subassembly, wherein the leading edge component and the left and right side components are directly, integrally co-cured on the frame structure while in a B-stage. The leading edge component and the left and right side components are shingle laminated to form ply angles to air flow. The leading edge component and the side components are scarf-jointed or step-jointed. The side components and trailing edge subassembly are also scarf jointed or step-jointed. The co-curing as well as the scarf or step joints makes the heat shield an integrated assembly. A method of manufacturing the integrated heat shield is further introduced.

公开(公告)号：US20170113245A1

公开(公告)日：2017-04-27

申请号：US15206322

申请日：2016-07-11

申请人： The Boeing Company

发明人： Douglas H. Berry ,  Scott A. Davis

IPC分类号： B05D1/32 ,  B64C1/38 ,  B05D5/00 ,  B05D7/00 ,  B05D3/10

CPC分类号： B05D1/32 ,  B05D3/108 ,  B05D3/12 ,  B05D5/00 ,  B05D5/065 ,  B05D7/57 ,  B05D2202/00 ,  B64C1/38 ,  B64C3/36 ,  B64C5/02 ,  B64C7/02 ,  B64C23/065 ,  Y10T428/24628

摘要： An aero-contoured coating system is provided. The system has an aerodynamically functional coating having at least one or more color layers, one or more first clearcoat layers over the color layer(s) to obtain a pre-aero-contoured coating, the one or more first clearcoat layers configured for abrasion and aero-contouring to obtain an aero-contoured surface, and one or more additional clearcoat layers over the aero-contoured surface. The system further has a structure having a prepared and primed substrate surface with a primer layer. The system further has an aero-contouring device to abrade a plurality of flow surfaces on a pre-aero-contoured coated surface and to mechanically aero-contour a plurality of coating edges to reduce one or more coating edge peaks and coating edge angles of abutting coating edges between the one or more color layers. The system further has one or more masking elements for masking the one or more color layers.

公开(公告)号：US20160265133A1

公开(公告)日：2016-09-15

申请号：US15036010

申请日：2014-11-10

申请人： ALENIA AERMACCHI S.P.A.

发明人： Luca BOTTERO ,  Massimo GREGORI

IPC分类号： C25D5/54 ,  B64C1/38 ,  C25D3/12 ,  C25D3/56 ,  C25D7/00 ,  C25D21/12

CPC分类号： C25D5/54 ,  B64C1/38 ,  B64C3/36 ,  B64C2001/0072 ,  B64C2001/0081 ,  C25D3/12 ,  C25D3/562 ,  C25D7/00 ,  C25D21/12

摘要： A method includes providing an aircraft component including a substrate made of composite material and a polymeric matrix; and applying a protective coating made of metallic material to the substrate. The protective coating is applied to the polymeric matrix by an electrolytic deposition process.

摘要翻译： 一种方法包括提供包括由复合材料制成的基底和聚合物基体的飞行器部件; 并将由金属材料制成的保护涂层施加到基底上。 通过电解沉积工艺将保护涂层施加到聚合物基质上。

公开(公告)号：US20160194069A1

公开(公告)日：2016-07-07

申请号：US14881117

申请日：2015-10-12

申请人： Rapid Unmanned Aerial Systems, LLC

发明人： Alan TAYLOR

IPC分类号： B64C1/38 ,  B64C27/08 ,  B64F5/00 ,  B64C39/02

CPC分类号： B64C1/38 ,  B64C27/08 ,  B64C39/024 ,  B64C2001/0054 ,  B64C2001/0072 ,  B64C2201/027 ,  B64C2201/042 ,  B64F5/10 ,  Y02T50/43

摘要： An unmanned aerial vehicle includes a body and a heat source disposed in the body. The heat source includes at least one of an electronic controller system and a motor. The unmanned aerial vehicle further includes a plurality of rotor blades. At least a portion of the body is constructed of crystalline carbon fibers.

摘要翻译： 无人驾驶飞行器包括设置在车体中的主体和热源。 热源包括电子控制器系统和电动机中的至少一个。 无人飞行器还包括多个转子叶片。 身体的至少一部分由结晶碳纤维构成。

公开(公告)号：US09290261B2

公开(公告)日：2016-03-22

申请号：US13157284

申请日：2011-06-09

申请人： Wendell V. Twelves ,  Kathleen E. Sinnamon

发明人： Wendell V. Twelves ,  Kathleen E. Sinnamon

IPC分类号： F16B1/00 ,  B64C9/02 ,  F16B5/02

CPC分类号： F16B5/0241 ,  B64C1/06 ,  B64C1/38 ,  B64C9/02 ,  B64F5/00 ,  Y10T29/49826 ,  Y10T403/21 ,  Y10T403/217

摘要： An example adjustable linking member of a mounting assembly includes a first attachment portion and a second attachment portion. The first attachment portion connects a linking member to a first component. The second attachment portion connects the linking member to a second component. A variable portion of the adjustable linking member varies a distance between the first attachment portion and the second attachment portion in a first direction when heated. The variable portion varies the distance between the first attachment portion and the second attachment portion in a second direction when cooled. The first direction is opposite the second direction.

摘要翻译： 安装组件的示例性可调连接构件包括第一附接部分和第二附接部分。 第一附接部分将连接部件连接到第一部件。 第二附接部分将连接部件连接到第二部件。 可调连接构件的可变部分在加热时在第一方向上改变第一附接部分和第二附接部分之间的距离。 当冷却时，可变部分在第二方向上改变第一附接部分和第二附接部分之间的距离。 第一个方向与第二个方向相反。

公开(公告)号：US09193457B2

公开(公告)日：2015-11-24

申请号：US13969467

申请日：2013-08-16

申请人： Charl Emelio Janeke

发明人： Charl Emelio Janeke

IPC分类号： B64C30/00 ,  B64C1/00 ,  B64C1/38

CPC分类号： B64C1/38 ,  B64C1/0009 ,  B64C23/04 ,  B64C30/00 ,  B64C2001/0045 ,  B64D27/023

摘要： An apparatus and method for mitigating the shock front of an aerospace plane flying at hypersonic speeds. The invention employs supercooling driven by the cryogenic power of liquid hydrogen, regenerative evaporation of liquid hydrogen or liquid nitrogen and consequential isothermal compression, to usurp the shock front in totality at Mach 1.

摘要翻译： 一种减轻超音速飞行的航空航天飞机的冲击前沿的装置和方法。 本发明采用由液氢的低温动力驱动的过冷，液态氢或液氮的再生蒸发和随后的等温压缩，以Mach 1全面篡夺冲击前沿。