公开(公告)号：US20180086470A1

公开(公告)日：2018-03-29

申请号：US15555216

申请日：2016-03-03

申请人： Sikorsky Aircraft Corporation

发明人： Wenping Zhao ,  Zaffir A. Chaudhry ,  Jinliang Wang ,  Dean Nguyen

IPC分类号： B64D15/12 ,  B64C27/473 ,  F01D5/28

CPC分类号： B64D15/12 ,  B64C27/473 ,  B64C2027/4736 ,  F01D5/282 ,  F05D2240/303 ,  F05D2300/603 ,  H05B3/145 ,  H05B3/36 ,  H05B2214/02 ,  H05B2214/04

摘要： A heater mat assembly for a blade using an electrical current is provided including a first heating element region configured to generate a first amount of heat using the electrical current and disposed at a first region of the heater mat assembly. A second heating element region extends form the first heating element region and is configured to generate a second amount of heat using the electrical current. The second amount of heat is different than the first amount of heat.

公开(公告)号：US09927480B2

公开(公告)日：2018-03-27

申请号：US14534756

申请日：2014-11-06

申请人： Rosemount Aerospace, Inc.

发明人： Michael Paul Nesnidal

IPC分类号： G01P5/165 ,  G01R31/02 ,  H02H5/04 ,  H05B3/34 ,  H05B1/02 ,  H05B3/56 ,  B64D15/12

CPC分类号： G01R31/021 ,  B64D15/12 ,  G01P5/165 ,  H02H5/043 ,  H05B1/0227 ,  H05B3/56 ,  H05B2203/014 ,  H05B2203/035 ,  H05B2214/02

摘要： A multi-function probe wire de-icing apparatus is described. The multi-function probe wire de-icing apparatus may include a multi-function probe wire, a main heater wire collocated with the multi-function probe wire, and a sacrificial wire deposed adjacent to the main heater wire. The sacrificial wire is configured to fail prior to the main heater wire failing.

公开(公告)号：US20180084613A1

公开(公告)日：2018-03-22

申请号：US15271003

申请日：2016-09-20

申请人： Goodrich Corporation

发明人： Jin Hu ,  Galdemir Cezar Botura

IPC分类号： H05B3/34 ,  B32B5/02 ,  B32B7/12 ,  H05B1/02 ,  B64D15/12

CPC分类号： H05B3/342 ,  B32B5/02 ,  B32B7/12 ,  B32B2255/02 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2262/101 ,  B32B2262/105 ,  B32B2262/106 ,  B32B2307/206 ,  B32B2307/302 ,  B32B2457/00 ,  B32B2605/18 ,  B64D15/12 ,  B64D45/00 ,  H05B1/0236 ,  H05B3/14 ,  H05B3/34 ,  H05B2203/015 ,  H05B2203/017 ,  H05B2214/02 ,  H05B2214/04

摘要： Disclosed is the use of a boron nitride nanotube (BNNT) fabric as a skin for protection of nano-carbon heaters used for de-icing aircrafts or other vehicles. This allows the heaters to be resistant to hail, bird, and other mechanical striking damages, and can be applied to parts of aircraft that require acoustic protection.

公开(公告)号：US20180084612A1

公开(公告)日：2018-03-22

申请号：US15271009

申请日：2016-09-20

申请人： Goodrich Corporation

发明人： Jin Hu ,  Galdemir Cezar Botura

IPC分类号： H05B3/34 ,  B64D15/12

CPC分类号： H05B3/34 ,  B64D15/12 ,  H05B3/14 ,  H05B2203/017 ,  H05B2214/02 ,  H05B2214/04

摘要： A nano alumina fabric protects heaters used for de-icing aircraft or other vehicles. This allows heaters to withstand mechanical foreign object damage (FOD), is environmentally safe, and is a cost-efficient alternative to other protection fabrics.

公开(公告)号：US09919812B2

公开(公告)日：2018-03-20

申请号：US15231568

申请日：2016-08-08

申请人： THE BOEING COMPANY

发明人： Fong Shi

IPC分类号： B64F5/00 ,  G08B31/00 ,  G08B21/18 ,  B64D45/00 ,  G08B21/20

CPC分类号： B64F5/60 ,  B64D15/12 ,  B64D45/00 ,  B64D2045/0085 ,  B64F5/0045 ,  G08B21/182 ,  G08B21/185 ,  G08B21/20 ,  G08B31/00 ,  H02H3/33

摘要： A system and method for monitoring a critical component (e.g., an electrical deicing heater) on an aircraft. A first electrical current is input into the critical component, a second electrical current is returned from the critical component, and an electrical differential current of the critical component is detected. The electrical differential current is the difference between the first electrical current and the second electrical current. An electrical differential current signal is generated from the detected electrical differential current. The electrical differential current signal is compared to a differential current threshold, and precautionary action is triggered based on the comparison. A deterioration trend of the critical component is monitored by tracking variations in the electrical differential current of the critical component over time.

公开(公告)号：US09896964B2

公开(公告)日：2018-02-20

申请号：US14969774

申请日：2015-12-15

申请人： United Technologies Corporation

发明人： Steven Clarkson ,  Daniel K. Van Ness, II ,  Paul Thomas Rembish

IPC分类号： F01D25/02 ,  F01D25/24 ,  F01D25/10 ,  F01D21/10 ,  F01D17/10 ,  B64D27/10 ,  B64D15/12 ,  B64D29/00 ,  F02C7/047 ,  F02C7/05 ,  F04D29/54 ,  F04D29/58 ,  F04D27/02

CPC分类号： F01D25/02 ,  B64D15/12 ,  B64D27/10 ,  B64D29/00 ,  F01D17/105 ,  F01D21/10 ,  F01D25/10 ,  F01D25/24 ,  F02C7/047 ,  F02C7/05 ,  F04D27/0215 ,  F04D27/023 ,  F04D29/545 ,  F04D29/584 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/20 ,  F05D2270/096

摘要： A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.

公开(公告)号：US20180037338A1

公开(公告)日：2018-02-08

申请号：US15231568

申请日：2016-08-08

申请人： THE BOEING COMPANY

发明人： Fong Shi

IPC分类号： B64F5/00 ,  G08B21/18 ,  B64D45/00 ,  G08B31/00

CPC分类号： B64F5/60 ,  B64D15/12 ,  B64D45/00 ,  B64D2045/0085 ,  B64F5/0045 ,  G08B21/182 ,  G08B21/185 ,  G08B21/20 ,  G08B31/00 ,  H02H3/33

摘要： A system and method for monitoring a critical component (e.g., an electrical deicing heater) on an aircraft. A first electrical current is input into the critical component, a second electrical current is returned from the critical component, and an electrical differential current of the critical component is detected. The electrical differential current is the difference between the first electrical current and the second electrical current. An electrical differential current signal is generated from the detected electrical differential current. The electrical differential current signal is compared to a differential current threshold, and precautionary action is triggered based on the comparison. A deterioration trend of the critical component is monitored by tracking variations in the electrical differential current of the critical component over time.

公开(公告)号：US09856027B2

公开(公告)日：2018-01-02

申请号：US14878650

申请日：2015-10-08

申请人： Honeywell International Inc.

发明人： Morris Anderson ,  Grant A. Gordon ,  Yates Wong ,  Richard Bonvouloir

IPC分类号： B64D15/12 ,  B64D15/14 ,  B64D43/00 ,  H05B3/56 ,  G01P5/165

CPC分类号： B64D15/12 ,  B64D15/14 ,  B64D43/00 ,  G01P5/165 ,  H05B3/56 ,  H05B2214/02

摘要： An air data probe comprises an elongated body structure having a proximal end and a distal end, with the elongated body structure including an outer surface and an opposing inner surface that defines an interior channel. A probe tip is located at the distal end of the elongated body structure, with the probe tip including an outer surface and an inner surface that are contiguous with the outer an inner surfaces of the elongated body structure. The probe tip has an opening in communication with the interior channel that allows outside air to pass from the probe tip into the interior channel. An electrical heater cable is coupled to the elongated body structure and the probe tip. The electrical heater cable comprises a compact double layer helix portion coupled to the elongated body structure or the probe tip, or coupled to both the elongated body structure and the probe tip.

公开(公告)号：US09849993B2

公开(公告)日：2017-12-26

申请号：US15220428

申请日：2016-07-27

申请人： THALES

发明人： Claude Sarno ,  Romain Hodot

IPC分类号： G01F1/68 ,  B64D15/06 ,  B64D15/12 ,  B64D43/02 ,  F28D15/02 ,  G01P5/165 ,  B33Y10/00 ,  B64F5/10 ,  B33Y80/00 ,  B33Y50/02 ,  B64D33/08 ,  F28D21/00

CPC分类号： B64D15/06 ,  B33Y10/00 ,  B33Y50/02 ,  B33Y80/00 ,  B64D15/12 ,  B64D33/08 ,  B64D43/02 ,  B64F5/10 ,  F28D15/02 ,  F28D15/0266 ,  F28D2021/0021 ,  G01P5/165

摘要： An aircraft provided with at least two pieces of aeronautic equipment, a first piece of equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (80) of the second piece of equipment (81) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator (14), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

公开(公告)号：US09839073B2

公开(公告)日：2017-12-05

申请号：US15250340

申请日：2016-08-29

申请人： Metis Design Corporation ,  Massachusetts Institute of Technology

发明人： Seth S. Kessler ,  Ajay Raghavan ,  Brian L. Wardle

IPC分类号： H05B1/02 ,  H05B3/14 ,  H01B1/02 ,  G01N25/72 ,  G01N25/00 ,  B64D15/20 ,  B64D15/12 ,  C08K3/04 ,  B82Y99/00 ,  B64C1/00 ,  B64D45/00

CPC分类号： H05B3/145 ,  B64C2001/0072 ,  B64D15/12 ,  B64D15/20 ,  B64D2045/0085 ,  B82Y99/00 ,  C08K3/04 ,  C08K3/041 ,  G01N25/00 ,  G01N25/72 ,  H01B1/02 ,  H05B2203/003 ,  H05B2203/021 ,  H05B2214/02 ,  H05B2214/04 ,  Y02T50/43 ,  Y10S977/742

摘要： Various applications for structured CNT-engineered materials are disclosed herein. In one application, systems are disclosed, wherein a structured CNT-engineered material forms at least part of an object capable of providing its own structural feedback. In another application, systems are disclosed, wherein a structured CNT-engineered material forms at least part of an object capable of generating heat. In yet another application, systems are disclosed, wherein a structured CNT-engineered material forms at least part of an object capable of functioning as an antenna, for example, for receiving, transmitting, absorbing and/or dissipating a signal. In still another application, systems are disclosed, wherein a structured CNT-engineered material forms at least part of an object capable of serving as a conduit for thermal or electrical energy.