公开(公告)号：US08549832B2

公开(公告)日：2013-10-08

申请号：US12649387

申请日：2009-12-30

申请人： Mahendra Maheshwari

发明人： Mahendra Maheshwari

IPC分类号： F02C7/047

CPC分类号： F02C7/047 ,  B64D15/12 ,  B64D2033/0233 ,  F05D2300/224 ,  F05D2300/5024 ,  Y02T50/672

摘要： An anti-icing system and method for an aircraft engine nacelle. The nacelle has an inlet lip that defines a leading edge of the nacelle and has a cross-sectional shape and oppositely-disposed exterior and interior surfaces. An anti-icing system contacts at least the inlet lip of the nacelle. The anti-icing system includes at least one heating element having a cross-sectional shape that conforms to the cross-sectional shape of the inlet lip and in which carbon nanotubes are oriented and arranged to conduct electrical current through the heating element. Passing an electrical current through the heating element causes Joule heating of the heating element and heating of the inlet lip by thermal conduction.

摘要翻译： 一种用于飞机发动机机舱的防冰系统和方法。 机舱具有限定机舱的前缘的入口唇缘，并且具有横截面形状并且相对设置的外表面和内表面。 防冰系统至少与机舱的入口唇缘相接触。 防冰系统包括至少一个加热元件，其具有符合入口唇缘的横截面形状的横截面形状，并且其中碳纳米管被定向和布置成传导电流通过加热元件。 使电流通过加热元件导致加热元件的焦耳加热并且通过热传导加热入口唇缘。

公开(公告)号：US08128775B2

公开(公告)日：2012-03-06

申请号：US12345701

申请日：2008-12-30

申请人： Mahendra Maheshwari ,  James J. Velten

发明人： Mahendra Maheshwari ,  James J. Velten

IPC分类号： B29C65/00 ,  B32B37/04 ,  B32B38/04

CPC分类号： B29C70/545 ,  B29C43/027 ,  B29C43/10 ,  B29C2043/3655 ,  B29K2995/0002 ,  B29L2031/3076 ,  B29L2031/737 ,  Y10S264/57 ,  Y10S264/70 ,  Y10S264/78 ,  Y10S425/037 ,  Y10T156/1028 ,  Y10T156/1056 ,  Y10T156/1057 ,  Y10T156/1062 ,  Y10T156/1304

摘要： A process and apparatus for producing perforated composite structures, such as acoustic skins suitable for aircraft engine nacelle and duct components. The process includes placing a mat member, a non-impregnated fabric member, and a resin film on a tool surface so that pins disposed on the mat member project through the fabric member and resin film to define holes therein. The fabric member is between the mat member and resin film, and the fabric member and resin film define a stack that conforms to the mat member and tool surface. A caul member is then placed on the stack so that apertures in the caul member are penetrated by the pins. The stack is heated to melt the resin film and cause molten resin to infuse the fabric member and yield a resin-infused fabric stack, after which the molten resin within the resin-infused fabric stack is at least partially cured.

摘要翻译： 用于生产穿孔复合结构的方法和设备，例如适用于飞机发动机机舱和管道部件的声学皮肤。 该方法包括将垫子，非浸渍的织物构件和树脂膜放置在工具表面上，使得设置在垫构件上的销突出穿过织物构件和树脂膜以在其中限定孔。 织物构件在垫材和树脂膜之间，织物和树脂膜限定了与垫材和工具表面一致的叠层。 然后将一个止动件放置在堆叠上，使得止动件中的孔被销钉穿透。 将该叠层加热熔化树脂膜，使熔融树脂注入织物，并产生树脂输入的织物叠层，此后树脂注入的织物叠层内的熔融树脂至少部分固化。

公开(公告)号：US20110167781A1

公开(公告)日：2011-07-14

申请号：US12649387

申请日：2009-12-30

申请人： Mahendra Maheshwari

发明人： Mahendra Maheshwari

IPC分类号： F02C7/047 ,  B82Y30/00

CPC分类号： F02C7/047 ,  B64D15/12 ,  B64D2033/0233 ,  F05D2300/224 ,  F05D2300/5024 ,  Y02T50/672

摘要： An anti-icing system and method for an aircraft engine nacelle. The nacelle has an inlet lip that defines a leading edge of the nacelle and has a cross-sectional shape and oppositely-disposed exterior and interior surfaces. An anti-icing system contacts at least the inlet lip of the nacelle. The anti-icing system includes at least one heating element having a cross-sectional shape that conforms to the cross-sectional shape of the inlet lip and in which carbon nanotubes are oriented and arranged to conduct electrical current through the heating element. Passing an electrical current through the heating element causes Joule heating of the heating element and heating of the inlet lip by thermal conduction.

摘要翻译： 一种用于飞机发动机机舱的防冰系统和方法。 机舱具有限定机舱的前缘的入口唇缘，并且具有横截面形状并且相对设置的外表面和内表面。 防冰系统至少与机舱的入口唇缘相接触。 防冰系统包括至少一个加热元件，其具有符合入口唇缘的横截面形状的横截面形状，并且其中碳纳米管被定向和布置成传导电流通过加热元件。 使电流通过加热元件导致加热元件的焦耳加热并且通过热传导加热入口唇缘。

公开(公告)号：US20100196654A1

公开(公告)日：2010-08-05

申请号：US12362515

申请日：2009-01-30

申请人： Mahendra Maheshwari

发明人： Mahendra Maheshwari

IPC分类号： B32B3/06 ,  B32B38/08 ,  B32B37/00 ,  B32B27/12

CPC分类号： B32B3/266 ,  B32B5/02 ,  B32B5/06 ,  B32B5/22 ,  B32B5/245 ,  B32B5/26 ,  B32B21/10 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2262/0269 ,  B32B2262/101 ,  B32B2262/105 ,  B32B2262/106 ,  B32B2266/0242 ,  B32B2266/08 ,  B32B2307/50 ,  B32B2307/542 ,  B32B2307/718 ,  B32B2605/18 ,  Y10T428/24033

摘要： A process for producing resin-impregnated laminate composite structures that comprise a closed-cell core between resin-impregnated fabric layers, and preliminary and composite structures formed by such a process. The process includes stitching a roving in a preliminary structure that includes the core so as to structurally reinforce the core. The roving passes through through-holes in the core and traverses opposite outer surfaces of the preliminary structure. The outer surfaces of the preliminary structure traversed by the roving may be defined by outer surfaces of the core, or the preliminary structure may further include two or more fabric layers on outer surfaces of the core such that the core is between the fabric layers, the roving passes through one or more fabric layers, and at least one of the outer surfaces of the preliminary structure and traversed by the roving is defined by a fabric layer.

摘要翻译： 一种树脂浸渍的层压复合结构的制造方法，其包括浸渍树脂的织物层之间的闭孔芯，以及通过这种工艺形成的预备和复合结构。 该方法包括在包括芯的初步结构中拼接粗纱，以便在结构上加强芯。 粗纱穿过芯中的通孔，穿过初级结构的相对的外表面。 由粗纱横穿的初步结构的外表面可以由芯的外表面限定，或者初步结构还可以在芯的外表面上包括两个或更多个织物层，使得芯在织物层之间， 粗纱通过一个或多个织物层，并且由织物层限定的初步结构的外表面和由粗纱穿过的至少一个外表面。

公开(公告)号：US20100080980A1

公开(公告)日：2010-04-01

申请号：US12241540

申请日：2008-09-30

申请人： Mahendra Maheshwari ,  James J. Velten ,  Steven Davies

发明人： Mahendra Maheshwari ,  James J. Velten ,  Steven Davies

IPC分类号： B32B3/26 ,  C09J5/00

CPC分类号： B29C70/088 ,  B29C70/086 ,  B29C70/443 ,  B29C70/547 ,  B29D99/0021 ,  B29L2031/3076 ,  Y10T428/249994

摘要： A process for producing composite structures having a core between resin-impregnated composite layers, and composite structures formed by such a process. The process uses non-impregnated fabric layers and a core layer placed on a mold such that the core layer is between at least two fabric layers, a first of which is disposed between the mold surface and a first surface of the core layer, and a second of which is disposed at a second surface of the core layer. The second fabric layer is then infused with a resin, which flows through holes in the core layer into the first fabric layer, such that the first and second fabric layers are uniformly impregnated with the resin and the core layer is not. The resin is then cured to cause the impregnated first and second fabric layers to bond to the core layer.

摘要翻译： 一种制备复合结构的方法，该复合结构具有浸渍树脂的复合层之间的芯，以及通过这种工艺形成的复合结构。 该方法使用非浸渍织物层和放置在模具上的芯层，使得芯层在至少两个织物层之间，第一织物层设置在模具表面和芯层的第一表面之间，并且 其中第二个设置在芯层的第二表面。 然后将第二织物层注入树脂，树脂通过芯层中的孔流入第一织物层，使得第一和第二织物层均匀地浸渍树脂，并且芯层不被浸渍。 然后将树脂固化以使浸渍的第一和第二织物层与芯层结合。

公开(公告)号：US07406909B2

公开(公告)日：2008-08-05

申请号：US11186650

申请日：2005-07-21

申请人： Tushar K. Shah ,  Mahendra Maheshwari ,  Greg W. Klein

发明人： Tushar K. Shah ,  Mahendra Maheshwari ,  Greg W. Klein

IPC分类号： F41H5/04 ,  B23K20/08

CPC分类号： F41H5/0442 ,  F41H5/04 ,  F42B39/14 ,  F42B39/16 ,  F42B39/24 ,  F42D5/045

摘要： An armor that is used, for example, in multi-cell missile launchers is disclosed. In some embodiments, the armor includes three layers. The inner-most layer undergoes explosive welding when exposed to a pressure wave from an explosion. An intermediate layer in-elastically deforms when exposed to the explosion. The third and outer-most layer includes a plurality of elongated, pressurized tubes that contain fire retardant, among other chemicals. Silicone gel is interposed between the tubes.

摘要翻译： 公开了用于例如多单元导弹发射器中的装甲。 在一些实施例中，装甲包括三层。 当暴露于爆炸的压力波时，最内层发生爆炸性焊接。 当暴露于爆炸时，中间层弹性变形。 第三和最外层包括多个细长的加压管，其包含阻燃剂以及其它化学品。 硅胶置于管之间。