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1.发明授权公开(公告)号：US10304588B2
公开(公告)日：2019-05-28
申请号：US15736571
申请日：2016-06-17
申请人： BOMBARDIER INC.
摘要： There is described herein a harness (106) that remains neutral until configured by a configuration device (110). Wires that connect to specific pins responsible for the configuration of a system are taken out and connected to a configuration port (108) on the harness (106). The configuration port (108), when mated with the configuration device (110), sets a configuration setting of the system. The configuration device (110) may be used to set the power and/or signal parameters of the harness (106) for a system or to configure various options within the system itself or another system.
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公开(公告)号：US10940341B2
公开(公告)日：2021-03-09
申请号：US14771924
申请日：2014-02-24
申请人： BOMBARDIER INC.
摘要： Apparatus and methods related to fire suppression in cargo compartments of aircraft are disclosed. An exemplary apparatus provides an interface (38) between a fire suppressant conduit (18) and a cargo panel (28) of a cargo compartment (12) of an aircraft (10). The apparatus comprises an adaptor (40) configured to provide the fire suppressant conduit (18) access to the cargo compartment (12) through the cargo panel (28) and a sealing member (42) configured to provide a seal between the adaptor (40) and the fire suppressant conduit (18). The adaptor (40) comprises an aperture (56) for receiving the fire suppressant conduit (18) where the aperture (56) is sized to permit passage of a nozzle (36) of the fire suppressant conduit (18) therethrough. Associated methods (600, 700) for removing the cargo panel (28) of the cargo compartment (12) of the aircraft (10) without disassembly of the nozzle (36) of the fire suppressant conduit (18) are also disclosed.
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公开(公告)号：US10071816B2
公开(公告)日：2018-09-11
申请号：US14769889
申请日：2014-03-06
申请人： BOMBARDIER INC.
CPC分类号： B64D37/32 , B64D37/005 , B64D37/02
摘要： A tank wall connector system for use with a composite tank, the connector comprises a connector having a body extending from an interior of the tank to an exterior of the tank when installed through a hole in the composite tank. The connector has a first electrical conductivity property. An interface is positioned between the connector and a wall of the composite tank when installed to the tank thereby preventing physical contact between the connector and the tank wall in the interior of the tank, the interface having a second electrical conductivity property, different from the first electrical conductivity property.
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公开(公告)号：US10023291B2
公开(公告)日：2018-07-17
申请号：US15874252
申请日：2018-01-18
申请人： BOMBARDIER INC.
摘要： A system for shielding of at least one component within an aircraft includes a floor panel disposed at least partially between joists supporting a floor within the aircraft and a ground plane connected to a bottom surface of the floor panel. The ground plane extends at least partially between adjacent joists. At least one bracket electrically connects the ground plane to at least one of the joists.
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公开(公告)号：US09969483B2
公开(公告)日：2018-05-15
申请号：US14772429
申请日：2014-02-26
申请人： Bombardier Inc.
摘要： A system for shielding of at least one component (28) within an aircraft (10) includes a floor panel disposed at least partially between joists (38) supporting a floor (30) within the aircraft and a ground plane (44) connected to a bottom surface of the floor panel. The ground plane extends at least partially between adjacent joists. At least one bracket (52) electrically connects the ground plane to at least one of the joists.
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公开(公告)号：US09718531B2
公开(公告)日：2017-08-01
申请号：US14770588
申请日：2014-02-24
申请人： Bombardier Inc.
CPC分类号： B64C1/1453 , B64D41/00
摘要： A drain for expelling fluids from an interior of an aircraft to an exterior of the aircraft, the drain including a drain tube disposed at the interior of the aircraft having a first end disposed in fluid communication with an aircraft equipment to be drained and an opposite second end, wherein the drain tube terminates at the second end at a location within the interior of the aircraft, a seal which extends between the second end of the drain tube and an outer skin of the aircraft, delimiting a drainage cavity, and a drainage pathway extending from the cavity through the outer skin to the exterior of the aircraft.
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