Class / Patent application number | Description | Number of patent applications / Date published |
244129200 | Fire prevention devices | 22 |
20080290216 | Method for Extinguishing Fire in Aircraft Compartment - The inventive method for extinguishing fire in an aircraft cargo compartment ( | 11-27-2008 |
20090134276 | Aircraft firewall - The present invention relates to an aircraft firewall ( | 05-28-2009 |
20100001135 | Retaining Device - 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. | 01-07-2010 |
20100108811 | SYSTEM AND METHOD TO MAKE A FUEL TANK INERT - 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. | 05-06-2010 |
20100170991 | Low Weight Carpet Tile - 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. | 07-08-2010 |
20110042515 | ARRANGEMENT FOR PROVIDING ACTIVE FIRE PROTECTION IN AIRCRAFT - 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. | 02-24-2011 |
20110079683 | SAFETY SYSTEM FOR REDUCING THE EXPLOSION RISK OF A FUEL TANK - A safety system for reducing the explosion risk of a fuel tank comprises at least one fluid source and at least one fluid container with an inlet and an outlet for a fluid, wherein the fluid container has a structure that is flexible at least in some regions and is designed in such a manner that it can be positioned in a hollow space of the fuel tank, which hollow space is situated above the fuel, with said fluid container when fluid flows into the hollow space essentially occupying the space up to the top of the fuel tank. In this way it is possible to avoid the presence of a free air volume in the fuel tank, which counteracts any formation of a potentially explosive mixture and in this way reduces the explosion risk. | 04-07-2011 |
20110133033 | INERT GAS DISTRIBUTION ARRANGEMENT - An example inert gas distribution arrangement includes a first fuel tank and a second fuel tank mountable to an aircraft outboard the first fuel tank. A distribution conduit is configured to communicate inert gas to the first fuel tank through a first outlet and further configured to communicate inert gas to the second fuel tank through a second outlet. Fuel in the distribution conduit is biased to flow from the second fuel tank toward the first fuel tank when the aircraft is in selected aircraft attitudes. | 06-09-2011 |
20110147524 | FIRE DETECTION SYSTEM AND METHOD FOR CONFIGURING A FIRE DETECTION SYSTEM - The invention relates to a fire detection system comprising one or several fire sensors, in which fire detection system a monitoring unit communicates with the fire sensors and by way of a configuration unit may be configured by means of configuration data, wherein the configuration data comprises information relating to the fire sensors within the means of transport, which fire sensors are to be used in the means of transport. The invention further comprises a method for configuring a fire detection system and an aircraft comprising such a fire detection system. | 06-23-2011 |
20110240798 | Automated Fire and Smoke Detection, Isolation, and Recovery - Technologies are described herein for detecting and recovering from a fire event within an aircraft. The technologies receive sensor data from a number of sensors associated with an aircraft. A determination is made as to whether the sensor data exceeds predefined thresholds indicating the fire event within the aircraft. In response to determining that the sensor data exceeds the predefined thresholds indicating the fire event, the technologies determine a location of the fire event within the aircraft based on the sensor data and depower components of the aircraft associated with the fire event. The technologies then initiate a fire suppressant mechanism within the aircraft directed to the location of the fire event. | 10-06-2011 |
20120012709 | FIRING PREVENTION STRUCTURE OF FUEL TANK - A firing prevention structure of a fuel tank is provided with a double sleeve to pass through a hole formed in a rib, and a supporting structure to support a pipe to pass through the double sleeve. The supporting structure is attached to the rib. The supporting structure is provided with an insulating section which electrically insulates the pipe and the rib. The double sleeve is formed of electrically insulating material. Thus, an ignition source in the fuel tank is prevented. | 01-19-2012 |
20120273618 | Burnthrough Protection System - A burnthrough protection system including a fire protection laminate and a foam insulation material, wherein the fire protection laminate includes a fire barrier layer and a buffer layer, the buffer layer being disposed between the fire-barrier layer and the foam insulation material, wherein the buffer layer is adapted to prevent adhesion between the fire barrier layer and the foam insulation at elevated temperature. The burnthrough protection system may be capable of passing the flame propagation and burnthrough resistance test protocols of 14 C.F.R. §25.856(a) and (b), Appendix F, Parts VI and VII. Also, an aircraft including an exterior skin, an interior liner, and the burnthrough protection system disposed between the exterior skin and the interior liner. | 11-01-2012 |
20120318921 | FIRE PROTECTION SYSTEM, AIRCRAFT OR SPACECRAFT AND A METHOD FOR CONFINING AND SUPPRESSING A FIRE - The invention provides a fire protection system, in particular in the field of aviation and aerospace, comprising a compartment which is at least partly lined with fire-retardant material, a detection means which can detect a fire in the compartment, and a fire suppression means which is configured to introduce an inert gas into the compartment when the detection means detects a fire in the compartment, to thus reduce the oxygen content in the compartment and to thereby suppress the fire. | 12-20-2012 |
20130187004 | Fire protection device for aircraft - A joint attaching a structural element to a composite part comprising a metallic attachment, this joint being subjected to a fire source on one of its sides, the fire side. The joint comprises a retaining device located at the side of the joint opposite to the fire side, the cold side. The retaining device comprises a first surface that is in contact with the metallic attachment, and a second surface which is in contact with the composite part. The second surface has a larger area in contact with the composite part than the area of the first surface in contact with the metallic attachment. The retaining device is made of a material with a high thermal conductivity. Such a joint may be in an aircraft. | 07-25-2013 |
20130206910 | EMERGENCY SUPPLY SYSTEM FOR A TRANSPORTATION MEANS, METHOD FOR SUPPLYING ELECTRICAL POWER AND FOR INHIBITING FIRE AND AIRCRAFT WITH AN EMERGENCY SUPPLY SYSTEM - An emergency supply system for a transportation means is provided. The system includes at least one fuel cell, a hydrogen tank, an oxygen tank, an extinguishing agent container, an oxidant supply unit and an extinguishing-agent supply unit. The oxidant supply unit includes an oxygen inlet connectable to the oxygen tank, an air inlet connectable to an air source, and an oxidant outlet connected to an oxidant inlet of the fuel cell. The oxidant supply unit either conveys oxygen from the oxygen inlet or air from the air inlet to the oxidant outlet. The extinguishing-agent supply unit includes a first extinguishing agent inlet connected to an exhaust air outlet of the fuel cell, a second extinguishing agent inlet connected to the extinguishing agent container, and an extinguishing agent outlet that is connectable to an extinguishing-agent inlet unit of at least one space of the transportation means. | 08-15-2013 |
20130306796 | OUTER FUEL TANK ACCESS COVER, WING AND AIRCRAFT DESCRIPTION - The present invention describes an outer fuel access tank cover (FTAC) of an aircraft, a wing comprising such outer FTAC of an aircraft and an aircraft. The invention belongs to the field of “designing auxiliary pieces in the wing of aircrafts to control the risk of gases from an explosion occurred in the FTAC entering the fuel tank”. | 11-21-2013 |
20140138487 | RETRACTABLE INFILL PANEL FOR HIGH-LIFT DEVICE - The present invention provides an aircraft assembly with a fixed structure and a high-lift device. The fixed structure has a spar, a forward part which provides a foremost edge of an aircraft wing, and a lower part which provides a lower surface of the aircraft wing. A high-lift device is downwardly movable relative to the fixed structure from a stowed configuration to a deployed configuration. The high-lift device has a forward part which provides a foremost edge of the aircraft wing and a lower part which provides a lower surface of the aircraft wing. Downward movement of the high-lift device causes progressive opening of a lateral gap between the lower part of the high-lift device and the lower part of the fixed structure. A retractable infill panel is arranged to progressively extend from a retracted configuration to an extended configuration to fill the lateral gap. | 05-22-2014 |
20140166810 | Profiled Strip As A Fire Indication Device In An Aircraft - A door for a storage compartment of an aircraft includes a door leaf and a profiled strip connected to an edge of the door leaf. The profiled strip includes openings that provide a path for gas exchange such that smoke from the storage compartment is detectable outside of the storage compartment by passing the profiled strip. | 06-19-2014 |
20140252171 | NITROGEN BUBBLER SYSTEM IN FUEL TANK AND METHOD - An assembly of fuel tank and bubbler system comprises a fuel tank defining a storage volume adapted to receive fuel therein. The fuel tank comprises at least one fuel inlet, at least one fuel outlet, and at least one gas inlet adapted to be connected to an inert gas source to feed inert gas to fill an ullage in the storage volume. A bubbler system has at least one pipe extending into the fuel tank and adapted to be immersed into the fuel of the fuel tank. The pipe has a porous structure. The pipe is adapted to be connected to an inert gas source to inject inert gas via the porous structure into the fuel of the fuel tank. A method for treating fuel in a fuel tank is also provided. | 09-11-2014 |
20140353427 | FIRE EXTINGUISHING SYSTEM FOR AN AIRCRAFT - The invention relates to a system for extinguishing and preventing a fire on board of an aircraft. According to the invention, an aircraft is equipped with an On-Board-Inert Gas Generating-System (OBIGGS) unit comprising a device with an OBIGGS inflow port connected to a source of gas mixture, said gas mixture comprising an inert gas component and an outflow port, said OBIGGS unit being adapted to separate said inert gas component out of said source of gas mixture and to provide said inert gas component to said outflow port, a first connector in fluid connection with said outflow port, a first gas conduit connecting said first connector to said fuel tank for providing said inert gas component to a fuel tank, a second connector in fluid connection with said outflow port and a second gas conduit connecting said second connector to at least one target space selected from the cockpit space, the passenger cabin space, the cargo bay | 12-04-2014 |
20150360795 | Fire Seal for an Aircraft - A seal including an acute bend having a first end portion and a second end portion, a first engagement extension extending from the first end portion of the acute bend, and a second engagement extension extending from the second end portion of the acute bend, wherein the second engagement extension is at an acute angle relative to the first engagement extension to define a partially enclosed volume between the first engagement extension and the second engagement extension. | 12-17-2015 |
20160200447 | Fuel Cell System for an Aircraft and Method for Providing an Inert Gas in an Aircraft | 07-14-2016 |