公开(公告)号：US08919494B2

公开(公告)日：2014-12-30

申请号：US13585533

申请日：2012-08-14

申请人： Brian Bobby Burkett ,  Galdemir Cezar Botura ,  Claude Marc Hubert ,  David Bert Sweet ,  Joseph Christopher Zecca ,  Timothy Robert Olson

发明人： Brian Bobby Burkett ,  Galdemir Cezar Botura ,  Claude Marc Hubert ,  David Bert Sweet ,  Joseph Christopher Zecca ,  Timothy Robert Olson

IPC分类号： E04B1/86

CPC分类号： H01C17/02 ,  B64D15/12 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0233 ,  Y10T29/49083

摘要： An electric heater (40) for integration into an acoustic panel (20) having sound-penetrating pores (30) communicating with a sound-canceling medium. The heater (40) includes an electrically conductive layer (53) with resistance-setting apertures (63) filled with sealant (73). Openings (83), which contribute to the sound-penetrating pores (30), extend through the sealant-filled apertures (63). The acoustic panel (20) can be assimilated into an aircraft component, such as a nacelle inlet lip, which requires both noise-reducing and ice-protecting features.

摘要翻译： 一种用于集成到具有与声音消除介质通信的声音穿透孔（30）的声学面板（20）的电加热器（40）。 加热器（40）包括具有填充有密封剂（73）的电阻设定孔（63）的导电层（53）。 有助于声音穿透孔（30）的开口（83）延伸穿过密封剂填充的孔（63）。 声学面板（20）可以被吸收到飞机部件中，例如机舱入口唇缘，其需要降噪和防冰特征。

公开(公告)号：US07837150B2

公开(公告)日：2010-11-23

申请号：US11963014

申请日：2007-12-21

申请人： Joseph Christopher Zecca ,  Galdemir Cezar Botura ,  Brian Bobby Burkett ,  Claude Marc Hubert ,  Michael John Layland ,  Timothy Robert Olson ,  James Michael Roman

发明人： Joseph Christopher Zecca ,  Galdemir Cezar Botura ,  Brian Bobby Burkett ,  Claude Marc Hubert ,  Michael John Layland ,  Timothy Robert Olson ,  James Michael Roman

IPC分类号： B64D15/12

CPC分类号： B64D15/12 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0233 ,  F02C7/045 ,  F02C7/047 ,  F05D2250/132 ,  H05B3/06 ,  Y02T50/672 ,  Y10T29/49826

摘要： An aircraft component includes a first segment having a first leading edge surface that extends to a first end of the first segment. The aircraft component also includes a second segment having a second leading edge surface that extends to a second end of the second segment. The second end is substantially adjacent to the first end of the first segment, and is connected to the first end. The first leading edge surface includes electrical resistance heating that extends to the first end of the first segment. In addition, the second leading edge surface includes electrical resistance heating that extends to the second end of the second segment. The electrical resistance heating is capable of providing ice protection heating immediately on either side of a juncture between the connected first and second ends.

摘要翻译： 飞行器部件包括具有延伸到第一段的第一端的第一前缘表面的第一段。 飞行器部件还包括具有延伸到第二段的第二端的第二前缘表面的第二段。 第二端基本上与第一段的第一端相邻，并且连接到第一端。 第一前缘表面包括延伸到第一段的第一端的电阻加热。 此外，第二前缘表面包括延伸到第二段的第二端的电阻加热。 电阻加热能够在连接的第一和第二端之间的接合部的任一侧立即提供加冰保护加热。

公开(公告)号：US20100038475A1

公开(公告)日：2010-02-18

申请号：US11963014

申请日：2007-12-21

申请人： Joseph Christopher Zecca ,  Galdemir Cezar Botura ,  Brian Bobby Burkett ,  Claude Marc Hubert ,  Michael John Layland ,  Timothy Robert Olson ,  James Michael Roman

发明人： Joseph Christopher Zecca ,  Galdemir Cezar Botura ,  Brian Bobby Burkett ,  Claude Marc Hubert ,  Michael John Layland ,  Timothy Robert Olson ,  James Michael Roman

IPC分类号： B64D15/12 ,  B64C1/40 ,  B23P11/00

CPC分类号： B64D15/12 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0233 ,  F02C7/045 ,  F02C7/047 ,  F05D2250/132 ,  H05B3/06 ,  Y02T50/672 ,  Y10T29/49826

摘要： An aircraft component includes a first segment having a first leading edge surface that extends to a first end of the first segment. The aircraft component also includes a second segment having a second leading edge surface that extends to a second end of the second segment. The second end is substantially adjacent to the first end of the first segment, and is connected to the first end. The first leading edge surface includes electrical resistance heating that extends to the first end of the first segment. In addition, the second leading edge surface includes electrical resistance heating that extends to the second end of the second segment. The electrical resistance heating is capable of providing ice protection heating immediately on either side of a juncture between the connected first and second ends.

摘要翻译： 飞行器部件包括具有延伸到第一段的第一端的第一前缘表面的第一段。 飞行器部件还包括具有延伸到第二段的第二端的第二前缘表面的第二段。 第二端基本上与第一段的第一端相邻，并且连接到第一端。 第一前缘表面包括延伸到第一段的第一端的电阻加热。 此外，第二前缘表面包括延伸到第二段的第二端的电阻加热。 电阻加热能够在连接的第一和第二端之间的接合部的任一侧立即提供加冰保护加热。

公开(公告)号：US20180084611A1

公开(公告)日：2018-03-22

申请号：US15270993

申请日：2016-09-20

申请人： Jin Hu ,  Galdemir Cezar Botura

发明人： Jin Hu ,  Galdemir Cezar Botura

IPC分类号： H05B3/14

CPC分类号： H05B3/145 ,  H05B3/06 ,  H05B3/20 ,  H05B2203/011 ,  H05B2203/017 ,  H05B2214/04

摘要： Disclosed is an attachment between a bus bar and a nano-carbon heater used for de-icing and/or anti-icing in an aircraft or other vehicle. The attachment between the bus bar and the heater is created through a coupling agent, a pre-preg glass fabric, and a conductive adhesive. This attachment allows for electrical connections to be made to the heater via the bus bar, and the attachment is strong enough to withstand stress from thermal cycles.