Fire Prevention Devices Patents (Class 244/129.2)
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Publication number: 20110042515Abstract: The invention relates to an arrangement for providing active fire protection in aircraft by means of at least one protective shield. According to the invention, the at least one protective shield is formed with an intumescent material, which in the event of a fire can be activated, in particular made to expand, in a controlled manner well below the initial temperature otherwise usual for intumescent materials of the order of 250° C. by means of an electrical heating device. The current temperature in the hold (preferably at various temperature measuring points) of the aircraft is measured by means of at least one temperature sensor and transmitted to a controlling and regulating device. In the event of a fire, the heating devices are activated and the intumescent reactions of the protective shields for providing fire protection are initiated within a temperature interval between 90° C. and 150° C.Type: ApplicationFiled: February 11, 2009Publication date: February 24, 2011Applicant: AIRBUS OPERATIONS GMBHInventors: Berend Schoke, Heinz-Peter Busch
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Publication number: 20100253528Abstract: A smoke detector comprises a first housing to face an area in which to detect smoke, a second housing secured to the first housing, electronics to detect smoke within the area, and a flameproof barrier positioned between the first and second housings.Type: ApplicationFiled: April 2, 2009Publication date: October 7, 2010Inventor: Kenneth Frazer Bell
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Patent number: 7757776Abstract: Reactive fire suppression transport agents may be used to release catalytic fire suppression agents, in reaction zones, which may then be transported by naturally occurring flows paths downstream to the vicinity of flame holding regions for fire suppression for example, in aircraft. The reactive fire suppression agents may be delivered in projectiles.Type: GrantFiled: January 12, 2006Date of Patent: July 20, 2010Assignee: Eclipse Aerospace, Inc.Inventors: Peter D. Haaland, Ken Harness
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Publication number: 20100170991Abstract: Low weight and non-square carpet tile suitable for use in mass transit vehicles, particularly passenger aircraft. The carpet tile preferably weighs less than about 82 ounces per square yard. The carpet tile of this invention may have a carpet pile and at least one backing layer. The backing layer may use a low weight filler material. The carpet tiles satisfy transportation industry standards for flame, smoke and toxicity.Type: ApplicationFiled: September 2, 2009Publication date: July 8, 2010Applicant: Interface, Inc.Inventors: James Hobbs, Joel Sheppard, Stuart Jones, James Woods, JR., John P. Bradford
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Publication number: 20100163669Abstract: An aircraft structure is provided. The aircraft structure for an aircraft includes a fuselage, front wings, rear small wings, vertical winglets, and four levels. The fuselage has a cross-section of substantially a half circle fuselage shape. Being is wide enough to provide lifting force, and includes four levels separated by multi partition structure. The front wings are disposed horizontally in front portions of the fuselage. The rear small wings are disposed horizontally in rear portions of the fuselage. The vertical winglets are disposed at the wingtips of the rear small wings. The first level disposed at a bottom of the four levels includes a fuel tank storages and a plurality of landing gear bays. The second level disposed at a middle of the four levels includes cargo bay. The third level may comprise a top cockpit and a plurality of passenger cabins. The fuselage provides major portion of lifting force and the wings provides steering force, and lifting force.Type: ApplicationFiled: December 29, 2008Publication date: July 1, 2010Inventor: Sunstar Im
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Patent number: 7726409Abstract: Non-reactive test agents may be used to test fire suppression systems in which reactive fire suppression agents may be used to release catalytic fire suppression agents for transport by naturally occurring flows paths downstream to the vicinity of flame holding regions for fire suppression for example, in aircraft.Type: GrantFiled: June 29, 2006Date of Patent: June 1, 2010Assignee: Eclipse Aerospace, Inc.Inventors: Peter D. Haaland, Ken Harness
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Patent number: 7721812Abstract: A fire suppression system adapted for use in a lavatory of an aircraft. The system includes a supply coupled to one or more fluid discharge nozzles via one or more fluid flow lines. A pressure source in communication with the fluid flow lines provides pressure to assist in supplying a pressurized flow of fluid through the flow line(s) to the nozzles(s). Furthermore, the system is capable of using the potable water supply of the aircraft or it can be self-contained with its own water supply reservoir. If self-contained, the system includes a pressurized fluid source to assist in supplying water to the discharge nozzle(s).Type: GrantFiled: May 2, 2005Date of Patent: May 25, 2010Assignee: The Boeing CompanyInventor: Thomas L Reynolds
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Publication number: 20100108811Abstract: A fuel tank safety system includes an ullage cooling assembly and a system controller. The ullage cooling assembly includes a compressor configured to extract a quantity of ullage gas from the fuel tank, a heat exchanger coupled in flow communication downstream of the compressor, wherein the heat exchanger is configured to receive the quantity of ullage gas from the compressor and reduce a temperature of the ullage gas. The ullage cooling assembly includes a turbine coupled in flow communication downstream of the heat exchanger, wherein the turbine is configured to further reduce the temperature of the ullage gas and facilitate channeling the ullage gas to the fuel tank. The system controller is operatively coupled to the ullage cooling assembly and is configured to transmit to the ullage cooling assembly one of a start signal to activate the ullage cooling assembly or a stop signal to deactivate the ullage cooling assembly.Type: ApplicationFiled: February 18, 2009Publication date: May 6, 2010Inventor: Alankar Gupta
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Patent number: 7690438Abstract: Characterized in that in a first stage are loaded or produced on board in a mother aircraft at least a product or mixed of products to act on forest fires, pests or atmospheric phenomena; in a second stage the said product is stored in a glider container with gliding flight ability and equipped with a precision guidance system; in a third stage the glider container is dropped from the mother aircraft and guided towards the release point of the load; in a fourth stage the glider container releases of its interior the load of product on the release point, and in a fifth stage the glider container is recovered for a following reusing.Type: GrantFiled: January 25, 2006Date of Patent: April 6, 2010Inventor: Luís María Bordallo Álvarez
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Publication number: 20100001135Abstract: A retaining device includes a fireproof core enclosed by a non-fireproof case, wherein a pre-tensioned fireproof device is integrated in the case and attached to the core. The fireproof device relaxes in such a way, when the case melts, that a construction element is reliably held between the carrier and the device.Type: ApplicationFiled: September 19, 2006Publication date: January 7, 2010Applicant: Airbus Deutschland GmbHInventors: Lutz Zeuner, Hans-Peter Guthke
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Publication number: 20090134276Abstract: The present invention relates to an aircraft firewall (12) separating first and second compartments (1 and 2) of said aircraft, said first compartment (1) containing a plurality of elements. The firewall (12) is provided with a first wall (3) inserted in the structure (5) of the aircraft and having a first surface (3?) facing said first compartment (1), and said firewall (12) is provided with regulator means (4, 13) for maintaining the maximum temperature of said first surface (3?) of the first wall (3) at a predetermined temperature value lower than the self-combustion temperature of said elements.Type: ApplicationFiled: September 6, 2007Publication date: May 28, 2009Applicant: EUROCOPTERInventor: Daniel Chaniot
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Patent number: 7510022Abstract: A fire-suppression system for use in an aircraft having at least one cargo compartment is disclosed. Methods of suppressing a fire in the cargo compartment are also disclosed. The fire-suppression system, under one aspect of the present invention, can include at least one fire-suppressant vessel, at least one discharge conduit coupled to the at least one fire-suppressant vessel, and a valve arrangement coupled to the fire-suppressant vessel and the discharge conduit. The valve arrangement can have a first setting to discharge a fire suppressant at a first discharge rate after activation of the fire-suppression system, a second setting to discharge the fire-suppressant at a second discharge rate less than the first discharge rate, and a third setting to discharge the fire-suppressant at a third discharge rate greater than the second discharge rate during descent of the aircraft.Type: GrantFiled: June 26, 2006Date of Patent: March 31, 2009Assignee: The Boeing CompanyInventor: Anthony K. Lazzarini
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Publication number: 20080290216Abstract: The inventive method for extinguishing fire in an aircraft cargo compartment (3) consists in injecting a substantially pure nitrogen from high-pressure storage cylinders (12), in simultaneously actuating a device (5) for separating air and supplying nitrogen and in continuously introducing the nitrogen produced by said air separation device (5) into the compartment (3).Type: ApplicationFiled: March 23, 2006Publication date: November 27, 2008Inventors: Stephane Lessi, Olivier Vandroux
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Patent number: 7419124Abstract: A mount for an aircraft secures insulation material to a structure of the aircraft in which a plate-shaped element and a connecting element that are implemented from a very heat-resistant material are provided. The remainder of the hanger may be implemented from plastic. Under the effect of strong heat, the plastic may melt. An insulation mat is nonetheless secured against falling down/detaching by the plate-shaped element, which is supported using the connecting element.Type: GrantFiled: March 7, 2005Date of Patent: September 2, 2008Assignee: Airbus Deutschland GmbHInventors: Lutz Zeuner, Hans-Georg Plate, Lueder Kosiankowski, Hans-Peter Guthke
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Patent number: 7331401Abstract: Fire that has started in an enclosed space in an aircraft is smothered by closing or at least partly closing any air flow inlet and any air flow outlet of the enclosed space in response to a temperature rise caused by a fire in the enclosed space such as a toilet or crew quarters, galley cabinets, or the like. For this purpose fireproof, intumescent material is installed next to and along any apertures or openings in the enclosed space. When the temperature in the enclosed space exceeds the expansion temperature of the fireproof intumescent material the material expands into these apertures, thereby sealing or at least partly sealing these apertures, whereby air and thus oxygen access to the fire is reduced or even prevented, thereby smothering the fire. Preferably a guide surface guides the expanding intumescent material into the apertures or openings at least when the expansion starts.Type: GrantFiled: April 22, 2004Date of Patent: February 19, 2008Assignee: Airbus Deutschland GmbHInventor: Axel Bobenhausen
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Patent number: 7284726Abstract: A helicopter with one or more components formed from a self extinguishing composite primary structure material to provide increased passenger safety. The self extinguishing composite primary structure material has a core formed from a fire retardant material, which core has a first surface and a second surface, and at least one ply of a structural graphite prepreg material bonded to each of the first surface and the second surface.Type: GrantFiled: February 17, 2004Date of Patent: October 23, 2007Assignee: Sikorsky Aircraft CorporationInventors: Edward J. Fabian, Lauren Robert Napier, James S. Giampapa
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Patent number: 7232097Abstract: Provided is a method for providing fire shield protection to an aircraft auxiliary power unit, or portion thereof, or to other aircraft systems.Type: GrantFiled: March 10, 2006Date of Patent: June 19, 2007Assignee: Pratt & Whitney Canada Corp.Inventors: Noel Noiseux, Martin Bernard, Michael Owen Whiting
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Patent number: 7121512Abstract: A drain, for example for an aircraft engine support strut, arranged on the trailing edge of the rear secondary structure of the strut. The drain includes a conduit with a substantially horizontal axis and a substantially rectangular cross-section, taken in a plane parallel to the trailing edge, the conduit closed at an outer extremity by a terminal portion with a substantially ogival cross-section taken in the axis of the conduit and including at least one opening for drainage with an elongated shape on at least one of the opposing lateral walls.Type: GrantFiled: December 17, 2004Date of Patent: October 17, 2006Assignee: Airbus FranceInventor: Cyril Bonnaud
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Patent number: 7093666Abstract: A fire protection apparatus for an oil cooler in an aircraft auxiliary power unit compartment adapted to at least partially cover the oil cooler to thereby at least partially block flames from directly impinging the oil cooler in the event of a fire in the compartment. An associated means and method are also disclosed.Type: GrantFiled: February 20, 2003Date of Patent: August 22, 2006Assignee: Pratt & Whitney Canada Corp.Inventor: Ronald Francis Trumper
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Patent number: 7040576Abstract: Provided is a method and system for providing fire shield protection to an aircraft auxiliary power unit, or portion thereof, or to other aircraft systems.Type: GrantFiled: December 18, 2003Date of Patent: May 9, 2006Assignee: Pratt & Whitney Canada Corp.Inventors: Noel Noiseux, Martin Bernard, Michael Owen Whiting
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Patent number: 7007893Abstract: Methods and systems for controlling fuel tank flammability control systems are disclosed herein. In one embodiment, a system for use with an aircraft or other vehicle includes a flammability control system and a controller operably coupled to the flammability control system. The flammability control system can be configured to control the development of flammable vapors in a fuel tank of the vehicle. The controller can be configured to receive one or more signals relating to a condition of the fuel tank and control operation of the flammability control system at least partially in response to the one or more fuel tank condition signals. In another embodiment, the controller can be configured to receive one or more signals relating to an operational phase of the aircraft and control operation of the flammability control system at least partially in response to the one or more aircraft operation signals.Type: GrantFiled: February 27, 2004Date of Patent: March 7, 2006Assignee: The Boeing CompanyInventors: Kevin L. Loss, David A. Adkins
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Patent number: 6899184Abstract: A fire suppression system adapted for use in a lavatory of an aircraft. The system includes a water supply coupled to one or more fluid discharge nozzles via one or more fluid flow lines. A pressure source in communication with the fluid flow lines provides pressure to assist in supplying a pressurized flow of fluid through the flow line(s) to the nozzles(s). The fire suppression system creates a spray of water capable of suppressing fires within a waste container area or within the entire lavatory area. Heat sensitive valves enable the system to automatically detect the start of a fire. Furthermore, the system is capable of using the potable water supply of the aircraft or it can be self-contained with its own water supply reservoir. If self-contained, the system includes a pressurized fluid source to assist in supplying water to the discharge nozzle(s).Type: GrantFiled: July 30, 2001Date of Patent: May 31, 2005Assignee: The Boeing CompanyInventor: Thomas L. Reynolds
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Patent number: 6676081Abstract: A system for extinguishing and suppressing a fire in an enclosed space includes a Halon storage container and a nitrogen generator that are both connected by a duct system to extinguishing nozzles arranged in the enclosed space. Halon is supplied as a first extinguishing agent from the container to achieve a rapid initial extinguishing of the fire. Nitrogen enriched air is supplied as a second extinguishing agent from the nitrogen generator to achieve a continuous long-term fire suppression, commencing simultaneously with or after the introduction of the Halon. The nitrogen generator may include a molecular sieve to continuously generate the nitrogen enriched air from an inlet flow of environmental air.Type: GrantFiled: October 28, 2002Date of Patent: January 13, 2004Assignee: Airbus Deutschland GmbHInventors: Thomas Grabow, Alexander Scheidt, Konstantin Kallergis
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Publication number: 20030136879Abstract: A system for extinguishing and suppressing a fire in an enclosed space includes a Halon storage container and a nitrogen generator that are both connected by a duct system to extinguishing nozzles arranged in the enclosed space. Halon is supplied as a first extinguishing agent from the container to achieve a rapid initial extinguishing of the fire. Nitrogen enriched air is supplied as a second extinguishing agent from the nitrogen generator to achieve a continuous long-term fire suppression, commencing simultaneously with or after the introduction of the Halon. The nitrogen generator may include a molecular sieve to continuously generate the nitrogen enriched air from an inlet flow of environmental air.Type: ApplicationFiled: October 28, 2002Publication date: July 24, 2003Inventors: Thomas Grabow, Alexander Scheidt, Konstantin Kallergis
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Publication number: 20030010867Abstract: A connecting device for joining a windshield with a fuselage side frame of a viewing port of an aircraft, especially a cockpit frame of a helicopter. The connecting device includes a fastening element which is fixed into position on a section of a peripheral region of the windshield through a bore hole and into a congruent bore hole of the fuselage side frame and in a fastening part with a spring device. A peripheral slit filled with a sealant is arranged in a peripheral region between the fuselage side frame and windshield. The fastening part includes a retaining nut and a spring device which can be moved and guided within a seating element and connected with the fuselage side frame. The spring device is arranged between the retaining nut and the frame.Type: ApplicationFiled: June 27, 2002Publication date: January 16, 2003Applicant: Eurocopter Deutschland GmbHInventors: Klaus Wojatschek, Mark Drewe
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Publication number: 20020158167Abstract: There is produced (at 2) air enriched in inert gas, from a source (9) of compressed air internal to the aircraft, and this enriched air is admitted (via 10) into the fuel tank (12). During the cruising phase of the aircraft, there is produced a first fraction of air having a first inert gas content, and this first fraction is admitted into the fuel tank (12) at a first flow rate. Moreover, during the descent phase, there is produced a second fraction of enriched air having a second inert gas content substantially less than the first content, and the second fraction is admitted to the reservoir (12) at a second flow rate substantially greater than the first flow rate.Type: ApplicationFiled: April 24, 2002Publication date: October 31, 2002Inventors: Nicolas Schmutz, Olivier Vandroux
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Publication number: 20020125372Abstract: A mechanically operable actuating device for opening a circular entry in the fuselage wall of an Aircraft. This device moves a plug attached to the shaft of a pneumatic piston inwards to expose an opening which allows smoke from a fire in any area of the plane to be expelled outside through a network of flexible tubing and computer directed shut off valves and nozzles that route the smoke outside by the nearest mechanism automatically. The smoke expulsion is achieved by the huge pressure differentially inside the plane and the outside forcing the mixture of smoke and pressurized air outside. When a plane on fire lands at an Airport the Firefighters attach hoses with an interlocking Storz receiving adapter that permits interior water spraying on the burning passengers by the same tubing network. The Flight Deck Computer controls all operations but the Pilot may alter any move. A back up Computer is located in the cabin.Type: ApplicationFiled: February 27, 2001Publication date: September 12, 2002Inventor: Henry Shooflar
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Patent number: 6435455Abstract: A decompression panel assembly (12) for use in an aircraft separation structure (14). The panel assembly includes a support pan (26) having an opening (28), a bull nose (64) extending outwardly from the support pan at the opening's edge, and a recess (62) surrounding the bull nose. An inner seal (70) is sized and located within the recess (62). A retaining ring (22) is provided and includes a number of fingers (84) formed from spaced-apart slits (86) extending into the retaining ring (22) from the ring's inner edge. The assembly (12) further includes a pressure relief panel (24) shaped similar to the support pan opening shape, though sized slightly larger. The pressure relief panel (24) is held between the support pan bull nose (64) and the retaining ring (22) during non-decompression use. A number of index pins (94) interconnect between the retaining ring and the support pan. A grill (30) is attached to the support pan to protect the pressure relief panel.Type: GrantFiled: September 8, 2000Date of Patent: August 20, 2002Assignee: The Boeing CompanyInventors: Wrenn P. Holman, Robert W. Dost, Ernest E. Williams, Jr., John A. Wilson, Raymond H. Horstman
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High capacity air conditioning system with redundant staged recirculation air mixing for an aircraft
Patent number: 6389826Abstract: In an air conditioning system for an aircraft, two pre-mixing units respectively mix cold air from two air conditioning units with recirculated fuselage interior air from two recirculation units, to prepare two pre-mixed air flows that are both directed into and mixed together in a common air distribution mixing chamber, from which mixed air distribution lines branch off to respectively associated separate air conditioning zones within the fuselage. Post-mixing units are respectively interposed in the mixed air distribution lines and respectively mix additional quantities of recirculated fuselage interior air into the mixed air distribution lines. Thereby, the admixture of recirculated air is divided into at least two stages, the system provides redundant failure tolerant operation, and the danger of ice formation in the air lines is reliably prevented even while the air conditioning units provide cold air at a temperature below the water freezing point.Type: GrantFiled: March 8, 2001Date of Patent: May 21, 2002Assignee: Airbus Deutschland GmbHInventors: Uwe Albert Buchholz, Thomas Scherer -
Patent number: 6306032Abstract: An aircraft air-conditioning system provides ventilation, air-conditioning and fire protection for a below-deck stairwell and cargo hold that may be equipped with passenger sleeping compartment containers. An air mixing unit mixes fresh air and recycled air to supply mixed air through a first supply air main line (31) and a supply air unit (21) into the freight hold (4), and through a second supply air main line (32) into the stairwell (5). A trimming air unit (7A) provides hot bleed air from the aircraft engines into the mixed air supplied through the first and second supply air main lines (31, 32). An exhaust air line (11) extracts exhaust air from the freight hold (4), while an exhaust air supplemental line (15) extracts exhaust air from the stairwell (5), both of which are connected to an exhaust air main line with an exhaust air ventilator (16) that blows the exhaust air overboard. A bypass line (8) provides bypass air if needed for the demands of the ventilator (16).Type: GrantFiled: June 16, 2000Date of Patent: October 23, 2001Assignee: DaimlerChrysler Aerospace Airbus GmbHInventors: Hans-Joachim Scheffler, Michael Markwart, Uwe Buchholz
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Patent number: 6293525Abstract: Apparatus for facilitating the mixing, absorption and/or retention of carbon dioxide ‘CO2’ in hydrocarbon fuel to economically produce a safety-enhanced and/or improved-combustion fuel. The apparatus includes at least one mixing receptacle having at least one coupling with a controllable inert gas supply; at least one coupling with a controllable hydrocarbon fuel supply; and at least one coupling with a CO2-enriched fuel fuel-line. The mixing receptacle(s) is configured to retain a volume of fuel and a volume of CO2 such that CO2-enriched fuel having a controllable gas-fuel ratio is the product of the mixing receptacle(s) and the gas of the ratio(s) exceeds 0.1 volume of CO2 per volume of fuel and is less than approximately 3 volumes per volume of fuel when conveyed from the receptacle(s). The apparatus controls the exposure of hydrocarbon fuel molecules to an optimal volume of CO2 within the receptacle(s).Type: GrantFiled: June 14, 1999Date of Patent: September 25, 2001Inventors: Irwin Ginsburgh, Darrell Jay Metcalf, Clyde LeRoy Tichenor