-
公开(公告)号：US20230124999A1
公开(公告)日：2023-04-20
申请号：US17548910
申请日：2021-12-13
Applicant: Goodrich Corporation
Inventor： Adam George , Alex Zadell , Galdemir Cezar Botura , Casey Slane , Sugumaran Selvaraj , Andrew Taylor
IPC: B64D15/12
Abstract: A system for heating an aircraft surface having a thermally disadvantaged zone includes a carbon nano-tube (CNT) sheet heating element having a power inlet configured to receive power from an external electrical power source and provide it to the CNT sheet heating element that extends across the thermally disadvantaged zone. The CNT sheet heating element is configured and arranged such upon application of power from the external electrical power source to the CNT sheet heating element, the CNT sheet heating element produces a first heat output in a first zone and a second heat output in the thermally disadvantaged zone with the second heat output being greater than the first heat output.
-
公开(公告)号：US20220396361A1
公开(公告)日：2022-12-15
申请号：US17343969
申请日：2021-06-10
Applicant: Goodrich Corporation
Inventor： Galdemir Cezar Botura , Andrew Taylor
Abstract: An ice protection system adapted to protect at least one ice-susceptible flight surface of an aircraft includes a mechanical ice protection device attached to the flight surface. A controller controls a power source that causes the mechanical ice protection device to change in shape and, thereby, change an aerodynamic characteristic of the flight surface. This change in shape happens only when the current thickness of ice on the surface exceeds a minimum thickness.
-
公开(公告)号：US20180305031A1
公开(公告)日：2018-10-25
申请号：US15903656
申请日：2018-02-23
Applicant: Goodrich Corporation
Inventor： Alan J. Fahrner , Andrew Taylor , James Putt
Abstract: A de-icing assembly for a surface of an aircraft includes a carcass, seams, inflation passages, a manifold, and a reinforcement stitchline. The carcass includes a first layer, a second layer, and a carcass centerline. The seams are sewn into the carcass and join the first and second layers of the carcass together. The inflation passages are formed by the seams and are disposed between the first and second layers of the carcass. The manifold includes a width and a manifold centerline oriented approximately perpendicular to the carcass centerline and is fluidly connected to and is disposed beneath the carcass. The first reinforcement stitchline is sewn into the carcass adjacent to one of the plurality of seams and is disposed at a location on the carcass overlapping with the manifold. The first reinforcement stitchline is disposed approximately perpendicular to the manifold centerline and extends across the width of the manifold.
-
公开(公告)号：US10780984B2
公开(公告)日：2020-09-22
申请号：US15903656
申请日：2018-02-23
Applicant: Goodrich Corporation
Inventor： Alan J. Fahrner , Andrew Taylor , James Putt
Abstract: A de-icing assembly for a surface of an aircraft includes a carcass, seams, inflation passages, a manifold, and a reinforcement stitchline. The carcass includes a first layer, a second layer, and a carcass centerline. The seams are sewn into the carcass and join the first and second layers of the carcass together. The inflation passages are formed by the seams and are disposed between the first and second layers of the carcass. The manifold includes a width and a manifold centerline oriented approximately perpendicular to the carcass centerline and is fluidly connected to and is disposed beneath the carcass. The first reinforcement stitchline is sewn into the carcass adjacent to one of the plurality of seams and is disposed at a location on the carcass overlapping with the manifold. The first reinforcement stitchline is disposed approximately perpendicular to the manifold centerline and extends across the width of the manifold.
-
公开(公告)号：US20230249834A1
公开(公告)日：2023-08-10
申请号：US18300614
申请日：2023-04-14
Applicant: Goodrich Corporation
Inventor： Galdemir Cezar Botura , Andrew Taylor
Abstract: An ice protection system adapted to protect at least one ice-susceptible flight surface of an aircraft includes a mechanical ice protection device attached to the flight surface. A controller controls a power source that causes the mechanical ice protection device to change in shape and, thereby, change an aerodynamic characteristic of the flight surface. This change in shape happens only when the current thickness of ice on the surface exceeds a minimum thickness and the minimum thickness is based on attitude of the aircraft.
-
Patent Agency Ranking
公开(公告)号：US20200163160A1
公开(公告)日：2020-05-21
申请号：US16198179
申请日：2018-11-21
Applicant: Goodrich Corporation
Inventor： John J. Gangloff, JR. , Andrew Taylor , James A, Mullen , Danielle L. Grolman , Peter J. Walsh
Abstract: A passive anti-icing and/or deicing device can include an icephobic outer layer configured to prevent ice from forming and/or building up on the outer layer by preventing ice from adhering to the outer layer. The device can include a backer film attached to an underside of the icephobic outer layer, and an adhesive attached to the backer film on an opposite side of the backer film relative to the icephobic outer layer.
-
公开(公告)号：US20190016467A1
公开(公告)日：2019-01-17
申请号：US15650566
申请日：2017-07-14
Applicant: Goodrich Corporation
Inventor： Galdemir Cezar Botura , David L. Brittingham , Jin Hu , Andrew Taylor
Abstract: A pneumatic deicer includes a base layer, a forming layer, a first chamber, and a first sensor. The base layer has an inlet, a first side, and a second side. The forming layer is connected to the base layer along at least two seams and has inner side and an outer side with the outer side being distant from the base layer. The first chamber is formed between the base layer and the forming layer and configured to be inflated by air passing into the first chamber through the inlet in the base layer. The first sensor is situated within the first chamber.
-
公开(公告)号：US20170266753A1
公开(公告)日：2017-09-21
申请号：US15442785
申请日：2017-02-27
Applicant: Goodrich Corporation
Inventor： Samual Steven Riczo Schomer , Alan J. Fahrner , Kurt M. Tauscher , Andrew Taylor , James R. Hunter , David L. Brittingham
CPC classification number: B23K20/10 , B29C65/04 , B29C65/08 , B29C65/1403 , B29C65/1467 , B29C65/62 , B29C66/1122 , B29C66/232 , B29C66/244 , B29C66/438 , B29C66/71 , B29C66/7292 , B29C66/81417 , B29C66/81427 , B29C66/8322 , B29L2022/02 , B29L2024/006 , B29L2031/3076 , B64D15/166 , B64F5/10 , B29K2021/00
Abstract: A method of manufacturing a de-icer assembly includes disposing a first welded-material layer and a second welded-material layer beneath a horn of a horn-based welding system, controlling the horn to move along a welded-portion pattern configured to weld the first welded-material layer to the second welded-material layer in the pattern of the welded-portion pattern such that inflatable portions are formed within the welded-portion pattern formed in the de-icer assembly between non-welded sections of the first welded-material layer and the second welded-material layer, and applying high-frequency energy to the first welded-material layer and a second welded-material layer using the horn such that the first welded-material layer and the second welded-material layer are welded together at areas in the shape of the welded-portion pattern to form a welded de-icer assembly.
-
公开(公告)号：US11427336B2
公开(公告)日：2022-08-30
申请号：US16829855
申请日：2020-03-25
Applicant: GOODRICH CORPORATION
Inventor： Alex Zadell , Andrew Taylor
IPC: B64D15/12
Abstract: A heater mat for heating an airfoil having a chord, a leading edge, and a trailing edge includes a first zone element configured to heat a first chord-wise segment of the airfoil. The system further includes a second zone element configured to heat a second chord-wise segment of the airfoil that is adjacent to the first chord-wise segment of the airfoil. The system further includes a first zone busbar located at the leading edge of the heater mat and electrically coupled to the first zone element.
-
公开(公告)号：US20210300572A1
公开(公告)日：2021-09-30
申请号：US16829855
申请日：2020-03-25
Applicant: GOODRICH CORPORATION
Inventor： Alex Zadell , Andrew Taylor
IPC: B64D15/12
Abstract: A heater mat for heating an airfoil having a chord, a leading edge, and a trailing edge includes a first zone element configured to heat a first chord-wise segment of the airfoil. The system further includes a second zone element configured to heat a second chord-wise segment of the airfoil that is adjacent to the first chord-wise segment of the airfoil. The system further includes a first zone busbar located at the leading edge of the heater mat and electrically coupled to the first zone element.
-
-
-
-
-
-
-
-
-
Search Results
12
records
(took 0.012 seconds)
