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公开(公告)号：US12134477B2
公开(公告)日：2024-11-05
申请号：US17856334
申请日：2022-07-01
Applicant: GOODRICH CORPORATION
Inventor： Anagha Shivaprakash Gowda , Sugumaran Selvaraj
IPC: B64D15/04
Abstract: Ice may form along the leading edge of an aircraft wing. A pneumatic deicing system may be configured to crack and dislodge ice along the leading edge of the wing. The pneumatic deicing system may comprise a deicing boot assembly having a deicing boot attached to the leading edge, and a gas generator fluidly coupled to the deicing boot assembly. The gas generator may comprise a propellant and may decompose the propellant, liberating a compressed gas. The compressed gas may be directed to the deicing boot assembly, inflating the deicing boot, which may crack and dislodge the ice.
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公开(公告)号：US20210231592A1
公开(公告)日：2021-07-29
申请号：US16887186
申请日：2020-05-29
Applicant: GOODRICH CORPORATION
Inventor： Alex Zadell , Galdemir Cezar Botura , Sugumaran Selvaraj , El Hassan Ridouane , Karthik Debbadi
Abstract: A multi-layered ice detector apparatus includes a first heater strip, a second heater strip, and a plurality of temperature sensors. The first heater strip is configured to be mounted to a surface, the first heater strip forming a first heater layer of the multi-layered ice detector apparatus. The second heater strip is coupled in proximity to the first heater strip, the second heater strip forming a second heater layer of the multi-layered ice detector apparatus. The plurality of temperature sensors are coupled to at least one of the first heater strip and the second heater strip, wherein the plurality of temperature sensors are configured to detect a temperature profile of the multi-layered ice detector apparatus, wherein the temperature profile is indicative of an extent of icing.
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公开(公告)号：US20230312110A1
公开(公告)日：2023-10-05
申请号：US17856334
申请日：2022-07-01
Applicant: GOODRICH CORPORATION
Inventor： Anagha Shivaprakash Gowda , Sugumaran Selvaraj
IPC: B64D15/04
CPC classification number: B64D15/04
Abstract: Ice may form along the leading edge of an aircraft wing. A pneumatic deicing system may be configured to crack and dislodge ice along the leading edge of the wing. The pneumatic deicing system may comprise a deicing boot assembly having a deicing boot attached to the leading edge, and a gas generator fluidly coupled to the deicing boot assembly. The gas generator may comprise a propellant and may decompose the propellant, liberating a compressed gas. The compressed gas may be directed to the deicing boot assembly, inflating the deicing boot, which may crack and dislodge the ice.
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公开(公告)号：US11649058B2
公开(公告)日：2023-05-16
申请号：US17462751
申请日：2021-08-31
Applicant: Goodrich Corporation
Inventor： Sugumaran Selvaraj , Sathish Thangavel
CPC classification number: B64D15/12 , B64D15/04 , F02C7/047 , F05D2220/323
Abstract: Disclosed is an ice protection system for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system having: a perforated sheet configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source disposed to draw ice melted by the heating source through the perforated sheet and heating source.
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公开(公告)号：US20250042556A1
公开(公告)日：2025-02-06
申请号：US18788756
申请日：2024-07-30
Applicant: Goodrich Corporation
Inventor： Sugumaran Selvaraj , Shyam Kumar Dattatri , Manjunath Hiremath , Rhushikesh Patil
Abstract: A target material removal (TMR) element is provided and includes a body region; thermal elements within the body region; and vibration elements within the body region. The TMR element is controlled to perform TMR operations that include one or more of the thermal elements generating heat that is transmitted through the body region to a target material in a manner that defines one or more zones of the target material. The TMR operations further include, subsequent to the one or more of the thermal elements beginning generating the heat that is transmitted through the body region to the target material, the one or more of the vibration elements generating vibrations that are transmitted through the body region to the one or more zones of the target material.
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Patent Agency Ranking
公开(公告)号：US20230073073A1
公开(公告)日：2023-03-09
申请号：US17518777
申请日：2021-11-04
Applicant: Goodrich Corporation
Inventor： Gururaja Bambila , Sugumaran Selvaraj
Abstract: A valve includes a valve body having an input port and an outlet port. The valve body defines a fluid passageway extending between input port and an outlet port. The valve also includes a valve element disposed in the fluid passageway that controls a flow a fluid through the valve body from the input port to the outlet port. One or more of the fluid passageway and the valve control element is coated with a phobic coating.
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公开(公告)号：US20200039655A1
公开(公告)日：2020-02-06
申请号：US16145355
申请日：2018-09-28
Applicant: Goodrich Corporation
Inventor： Sugumaran Selvaraj
IPC: B64D15/16
Abstract: An aircraft flight surface deicing system includes an electromagnetic field generator and a deicing boot configured for attachment to an aircraft flight surface. The boot includes: one or more inflation regions including a first inflation region; one or more magnetic fluid reservoirs in fluid communication with the first inflation region, the one or more fluid reservoirs including a first fluid reservoir; a magnetic fluid contained in a combination of the first inflation regions and the one or more magnetic fluid reservoirs. In a first state, the magnetic fluid is contained in the first fluid reservoir and, in a deicing state, the electromagnetic field generator generates one or more fields that cause the magnetic fluid to exit the first fluid reservoir and travels along a length of the inflation region.
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公开(公告)号：US20200017223A1
公开(公告)日：2020-01-16
申请号：US16176443
申请日：2018-10-31
Applicant: Goodrich Corporation
Inventor： Sugumaran Selvaraj , Sathish Thangavel
Abstract: Disclosed is an ice protection system for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system having: a perforated sheet configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source disposed to draw ice melted by the heating source through the perforated sheet and heating source.
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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.
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公开(公告)号：US11459111B2
公开(公告)日：2022-10-04
申请号：US16145355
申请日：2018-09-28
Applicant: Goodrich Corporation
Inventor： Sugumaran Selvaraj
IPC: B64D15/16
Abstract: An aircraft flight surface deicing system includes an electromagnetic field generator and a deicing boot configured for attachment to an aircraft flight surface. The boot includes: one or more inflation regions including a first inflation region; one or more magnetic fluid reservoirs in fluid communication with the first inflation region, the one or more fluid reservoirs including a first fluid reservoir; a magnetic fluid contained in a combination of the first inflation regions and the one or more magnetic fluid reservoirs. In a first state, the magnetic fluid is contained in the first fluid reservoir and, in a deicing state, the electromagnetic field generator generates one or more fields that cause the magnetic fluid to exit the first fluid reservoir and travels along a length of the inflation region.
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