公开(公告)号：EP3147207A1

公开(公告)日：2017-03-29

申请号：EP16175813.1

申请日：2016-06-22

申请人： The Boeing Company

发明人： NIKIC, Dejan

IPC分类号： B64C23/00

CPC分类号： B64C23/005 ,  B64C2211/00 ,  B64C2230/12 ,  B64F5/40 ,  Y02T50/166

摘要： An aircraft active flow control dielectric barrier discharge (DBD) device may include a machinable ceramic dielectric support 14 having an aerodynamic surface shaped to form an exposed flush part of an airfoil surface on an aircraft. The DBD device may include at least two electrodes 16, 18 configured to be oppositely charged and spaced apart from each other on the dielectric support.

摘要翻译： 飞行器主动流动控制电介质阻挡放电（DBD）装置可以包括具有空气动力学表面的可加工的陶瓷电介质支撑件14，其被成形为在飞行器上形成翼型件表面的暴露的齐平部分。 DBD器件可以包括至少两个电极16,18，其被构造为在电介质支撑件上彼此相对地充电并且彼此间隔开。

公开(公告)号：EP3229330A1

公开(公告)日：2017-10-11

申请号：EP17164803.3

申请日：2017-04-04

申请人： The Boeing Company

发明人： CLEMEN Jr, Mark Joseph ,  GROSSNICKLE, James A ,  NIKIC, Dejan

IPC分类号： H01S4/00 ,  H05H1/06 ,  H01S3/032 ,  H01S3/22

CPC分类号： H01S4/00 ,  H01S3/032 ,  H01S3/22 ,  H05H1/06

摘要： Laser amplification utilizing plasma confinement of a gas laser gain media is described. The gas laser gain media is compressed into plasma utilizing a self-reinforcing magnetic field referred to a plasma pinch (e.g., a flow stabilized z-pinch). In the pinch, the gas laser gain media is compressed to a high density, which improves the gain of the media. Coherent light is transmitted through the plasma pinch, which is amplified by the plasma pinch.

摘要翻译： 描述了利用气体激光增益介质的等离子体约束的激光放大。 气体激光增益介质利用被称为等离子体收缩的自增强磁场（例如，流动稳定的z收缩）被压缩成等离子体。 在捏合中，气体激光增益介质被压缩到高密度，这提高了介质的增益。 相干光透过等离子体夹点，由等离子体夹点放大。

公开(公告)号：EP3296092A1

公开(公告)日：2018-03-21

申请号：EP17185102.5

申请日：2017-08-07

申请人： The Boeing Company

发明人： MCIVER, Carl Roy ,  NIKIC, Dejan ,  DAY, Arthur C.

IPC分类号： B29C70/88

CPC分类号： B64D45/02 ,  B29C70/882

摘要： A method for placing electrical conductors interior to a composite structure prior to curing. A laminate stack is formed by assembling one or more composite layers, wherein the composite layers are pre-impregnated with a resin. One or more electrical conductors are placed on at least one of the composite layers prior to curing the laminate stack. One or more electrical insulators is optionally placed in proximity to one or more of the electrical conductors in at least one of the composite layers prior to curing the laminate stack. The laminate stack, including the composite layers, the electrical conductors, and the electrical insulators, is then cured to create the composite structure.

摘要翻译： 在固化之前将电导体放置在复合结构内的方法。 通过组装一个或多个复合层形成层压叠层，其中复合层用树脂预先浸渍。 在固化叠层之前，将一个或多个电导体置于至少一个复合层上。 一个或多个电绝缘体在固化叠层之前可选地放置在至少一个复合层中的一个或多个电导体附近。 然后将包括复合层，电导体和电绝缘体的层压叠层固化以形成复合结构。

公开(公告)号：EP3438437B1

公开(公告)日：2020-07-08

申请号：EP18173751.1

申请日：2018-05-23

申请人： The Boeing Company

发明人： HULL, John R. ,  GROSSNICKLE, James A. ,  NIKIC, Dejan ,  BOWCUTT, Kevin G.

IPC分类号： F02K7/14 ,  F23R7/00 ,  F23D11/32

公开(公告)号：EP3441774A1

公开(公告)日：2019-02-13

申请号：EP18187700.2

申请日：2018-08-07

申请人： The Boeing Company

发明人： NIKIC, Dejan

IPC分类号： G01R15/18 ,  G01R15/20 ,  G01R19/08

摘要： A plurality of magnetic field sensors (26), for example arranged in an array (30), is operative to measure changes in magnetic field strength proximate the surface(s) (18, 24) of a test structure (10). The test structure (10) may approximate the geometry of an airplane fuselage, wing, or the like. An electric current is applied to the test structure (10), and the magnetic field sensors (26) sense changes in a magnetic field caused by the current. A corresponding plurality of integrators (32) convert the sensor (26) outputs to magnetic field strength values. From the plurality of magnetic field strength values and corresponding sensor locations (27), a current density over the target surface (10) is inferred.

公开(公告)号：EP3438437A1

公开(公告)日：2019-02-06

申请号：EP18173751.1

申请日：2018-05-23

申请人： The Boeing Company

发明人： HULL, John R. ,  GROSSNICKLE, James A. ,  NIKIC, Dejan ,  BOWCUTT, Kevin G.

IPC分类号： F02K7/14 ,  F23R7/00 ,  F23D11/32

摘要： A scramjet (100) includes a converging inlet (110), a combustor (120) configured to introduce a fuel stream (132) into an air stream in a combustion chamber (130) and to combust the fuel air mixture stream (134) to create an exhaust stream, and a diverging exit nozzle configured to accelerate the exhaust stream (136). The combustor includes a fuel injection system (150) including at least one arcjet (160). A method (300) of creating thrust for an aircraft (10) includes compressing (310) a supersonic incoming air stream (112) in a converging inlet (110), injecting (320) a fuel stream (132) into the air stream in a combustion chamber (130) to create a fuel air mixture stream (134), igniting (330) the fuel air mixture stream to create an exhaust stream, and exhausting (350) the exhaust stream from a diverging exit nozzle (220). The injecting the fuel stream into the air stream includes injecting the fuel stream at a fuel speed sufficient to create shear between the fuel stream and the air stream.

公开(公告)号：EP3296365A1

公开(公告)日：2018-03-21

申请号：EP17187323.5

申请日：2017-08-22

申请人： The Boeing Company

发明人： DAY, Arthur C. ,  McIVER, Carl Roy ,  NIKIC, Dejan

IPC分类号： C09D5/24

CPC分类号： B32B7/14 ,  B32B27/20 ,  B32B2255/10 ,  B32B2262/106 ,  B32B2307/202 ,  B32B2605/18 ,  C09D5/24 ,  C09D11/52

摘要： A method for promoting electrical conduction between metallic components and composite materials. A composite body is coated with an adhering layer comprising a conductive material, and a metallic component is electrically connected to the conductive material of the adhering layer, when the metallic component is coupled to the composite body. The adhering layer is deposited inside a hole in the composite body, and/or along an edge of the hole, and/or on at least a portion of a surface of the composite body. The composite body is a structure of an aircraft or other vehicle comprised of composite materials formed from carbon fiber-reinforced polymers (CFRPs), the metallic component is a fastener or is positioned at an interface between the fastener and the composite body, and the electrical connection is made as part of a lightning protection system, an electromagnetic effects (EME) management system, or grounding system.

摘要翻译： 一种促进金属组分和复合材料之间导电的方法。 复合体涂覆有包含导电材料的粘合层，并且当金属部件连接至复合体时，金属部件电连接至粘合层的导电材料。 粘附层沉积在复合体中的孔内，和/或沿着孔的边缘，和/或复合体的至少一部分表面上。 复合体是由碳纤维增强聚合物（CFRP）形成的复合材料构成的飞行器或其他车辆的结构，金属部件是紧固件或位于紧固件和复合体之间的界面处，并且电气 连接作为雷电保护系统，电磁效应（EME）管理系统或接地系统的一部分。

公开(公告)号：EP3244706A1

公开(公告)日：2017-11-15

申请号：EP17156101.2

申请日：2017-02-14

申请人： The Boeing Company

发明人： NIKIC, Dejan

IPC分类号： H05H1/24

CPC分类号： H05H1/2406 ,  H05H1/24 ,  H05H2001/2412

摘要： A micro-hollow cathode discharge device (100). The device (100) includes a first electrode layer (102) comprising a first electrode. A hole (110) is disposed in the first electrode layer (102). The device (100) also includes a dielectric layer (104) having a first surface that is disposed on the first electrode layer (102). The hole (110) continues from the first electrode layer (102) through the dielectric layer (104). The device also includes a semi-conducting layer (106) disposed on a second surface of the dielectric layer (104) opposite the first surface. The semi-conducting layer (106) is a semiconductor material that spans across the hole (110) such that the hole (110) terminates at the semi-conducting layer (106). The device also includes a second electrode layer (108) disposed on the semi-conducting layer (106) opposite the dielectric layer (104).

摘要翻译： 一种微空心阴极放电装置（100）。 器件（100）包括包含第一电极的第一电极层（102）。 孔（110）设置在第一电极层（102）中。 器件（100）还包括具有布置在第一电极层（102）上的第一表面的电介质层（104）。 孔（110）从第一电极层（102）延续穿过介电层（104）。 该器件还包括设置在介电层（104）的与第一表面相对的第二表面上的半导体层（106）。 半导体层（106）是跨越孔（110）的半导体材料，使得孔（110）终止于半导体层（106）。 该器件还包括设置在与介电层（104）相对的半导体层（106）上的第二电极层（108）。