Abstract: Fuel tank inerting systems and methods for aircraft are provided. The systems include a fuel tank, a first reactant source fluidly connected to the fuel tank, the first source arranged to receive fuel from the fuel tank, a second reactant source, a catalytic reactor arranged to receive a first reactant from the first source and a second reactant from the second source to generate an inert gas that is supplied to the fuel tank to fill a ullage space of the fuel tank, and an inert gas recycling system located downstream of the catalytic reactor and upstream of the fuel tank, wherein the inert gas recycling system is arranged to direct a portion of the inert gas to the catalytic reactor.

Abstract: An example ullage-recirculating catalytic inerting system includes: (i) a plurality of fuel tanks having (a) respective inert gas ports for discharging the inert gas within a respective fuel tank, and (b) respective ullage gas ports for drawing ullage gas from the respective fuel tank; and (ii) an inert gas generating system including (a) an ullage gas inlet port fluidly coupled to the respective ullage gas ports, (b) an inert gas outlet port fluidly coupled to the respective inert gas ports, (c) a catalytic reactor for chemically converting ullage gas received through the ullage gas inlet port to inert gas for discharge through the inert gas outlet port, and (d) a prime mover for moving gas through the inert gas generating system.

Abstract: A cooling system includes a first conduit positioned within a cavity and extends from a radially inner casing aperture to a radially outer casing aperture. The cooling system also includes a second conduit coupled in flow communication with the first conduit and extending into the cavity. The cooling system further includes at least one valve positioned within the first conduit and the second conduit. The at least one valve and the first conduit are configured to channel a first fluid from the radially inner casing aperture to the radially outer casing aperture during a first mode of operation. The at least one valve, the second conduit, and the first conduit are configured to channel a second fluid from the radially outer casing aperture to the cavity during a second mode of operation.

Abstract: A system includes a turbo pump configured to convert a tank compressed gas or an engine compressed gas into at least one of electrical power, hydraulic power, or pneumatic power. The system also includes a storage tank configured to store the tank compressed gas. The system also includes a bleed line configured to port the engine compressed gas from the gas turbine engine to the turbo pump. The system also includes a propellant selector valve having an off position in which the turbo pump is prevented from receiving either the tank compressed gas or the engine compressed gas, a tank position in which the tank compressed gas from the storage tank is ported through the propellant selector valve to the turbo pump, and an engine position in which the engine compressed gas from the bleed line is ported through the propellant selector valve to the turbo pump.

Abstract: An inflator includes an inflator body that produces an inflation gas by burning a gas generating agent and a sensor that is mounted on the inflator body and is capable of detecting a degradation of the gas generating agent. The sensor is preferably composed of at least either one of a gas sensor, a pressure sensor, or a temperature sensor.

Abstract: A method can include transmitting, from a light source, light through a fuel tank ullage, and determining, by a processing device, an amount of absorption of at least one wavelength of the transmitted light. The method can further include determining, by the processing device based on the amount of absorption of the at least one wavelength of the transmitted light, a chemical composition of the fuel tank ullage.

Abstract: A curtain divider for an aircraft interior containing pivot stow bins includes a first fabric curtain, having an outboard end and an inboard end, which is attachable to the aircraft interior only at the outboard and inboard ends. The first fabric curtain includes a vertical portion, and a horizontal portion. The vertical portion has a substantially straight bottom edge, and an arcuate top edge defining a space sufficient for opening the pivot stow bins. The horizontal portion is flexibly attached to the vertical portion along the top edge and extends from the outboard end to the inboard end, having a substantially continuous curvature. The horizontal portion is adapted to impart forward and aft stability to the curtain support member at the top edge.

Abstract: 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.

Abstract: A scalable cargo-fire-suppression agent distribution system and method is disclosed. A supply source unit subset of a set of fire-suppression agent supply source units is selected based on an operation condition to provide a selected supply source unit subset, and a fire-suppression agent from the selected supply source unit subset is distributed during the operation condition.

Abstract: The invention relates to a system for extinguishing and preventing a fire on board of an aircraft.

Abstract: 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.

Abstract: An insulation package is provided for insulating a cabin of a vehicle that includes, but is not limited to at least one wrapping foil and at least one core layer of an insulation material. The wrapping foil envelopes the core layer at least in some regions and includes, but is not limited to at least one opening for feeding-through a holding element. On the wrapping foil a fastening element is arranged that is designed to establish a mechanical connection with the holding element fed through the opening. This can be a positive-locking or a non-positive-locking connection. By integrating the fastening element in the insulation package, the expenditure for separate fasteners can be saved so that the installation time and the different components can be reduced.

Abstract: A local fire shield is provided for protecting an attachment point of a fireproof system in an engine during a fire event. The local fire shield includes a mounting plate mounted on the attachment point; and a cover coupled to the mounting plate for covering the attachment point during the fire event.

Abstract: 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.

Abstract: A fire fighting system for extinguishing a fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the fire source.

Abstract: A fuel vapor removal method includes removing fuel vapor from ullage of a fuel tank of a vehicle, adsorbing the fuel vapor removed from the ullage onto adsorption media on the vehicle, and desorbing the fuel vapor from the adsorption media while on the vehicle. A fuel vapor removal method includes purging fuel vapor from ullage of a fuel tank using air added into the ullage, reducing a fuel-air ratio in the ullage using the air purging, and adsorbing the purged fuel vapor onto adsorption media. A fuel vapor removal system includes a fuel tank having ullage, an adsorption system including fuel vapor adsorption media fluidically connected to the ullage and to an ullage purging system, and a controller. The controller includes a flammability determination system and is configured to start fuel vapor removal by the purging system from the ullage onto the adsorption media before the ullage exhibits flammability.

Abstract: An aircraft fire prevention system provides oxygen depleted (hypoxic) air for the fuel tank and/or cargo compartment protection; the system does not employ compressed air for the production of hypoxic air, which allows to save energy and fuel and to reduce negative impact on the earth atmosphere.

Abstract: 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.

Abstract: A hybrid cargo-fire-suppression agent distribution system and method is disclosed. The hybrid cargo-fire-suppression agent distribution system comprises vehicle ducting means operable to distribute at least one fire-suppression agent. Further, preliminary fire-suppression supply source means is coupled to the vehicle ducting means and is operable to provide a high volume flow of a preliminary fire-suppression agent.

Abstract: 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.

Abstract: A fireproof system is provided for protecting a structure during a fire event. The system includes a fire resistant panel defining a first attachment opening and disposed adjacent to the structure; a canister including a side wall defining a first end and a second end, and an end wall enclosing the first end and defining a second attachment opening that is aligned with the first attachment opening; a fastener extending through the canister at the second attachment opening and the fire resistant panel at the first attachment opening such that the canister, the fire resistant panel, and the structure are fastened together; and a fire retardant agent disposed within the canister in an inactive condition and configured to transition out of the second end of the canister in an active condition at a predetermined temperature.

Abstract: The present invention provides a fireproof bulkhead, having a highly porous structure with an intumescent coating, the highly porous structure being formed as a reticulated foam or as a highly porous pimple or nub structure.

Abstract: In one of the embodiments of the disclosure, there is provided an aircraft insulation system and method for providing fire penetration resistance and/or thermal and acoustic protection. The aircraft insulation system comprises one or more insulation blankets, each having an inboard side and an outboard side. The aircraft insulation system further comprises a fire penetration resistant cover material having a heat seal adhesive, wherein the fire penetration resistant cover material covers the outboard side of the one or more insulation blankets. The aircraft insulation system further comprises an insulation cover film having a heat seal adhesive, wherein the insulation cover film covers the inboard side of the one or more insulation blankets. The aircraft insulation system further comprises a thermal heat seal that joins the fire penetration resistant cover material and the insulation cover film together to form a continuous insulation blanket assembly.

Abstract: 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”.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A fire retardant, transparent panel and method of making the panel, that is especially well suited for use on mobile platforms, and particularly on aircrafts. The panel is a composite of a transparent matrix and a plurality of fire-retardant nanoparticles. The nanoparticles have a diameter less than the visible spectrum of light, and in one form between about 0.1 nm to about 400 nm in diameter. The nanoparticles may be arranged randomly or in predetermined patterns within the matrix during manufacturing of the panel. The panel is lightweight, transparent and yet highly fire retardant.

Abstract: 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.

Abstract: 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.

Abstract: A fireproof, bi-directional decompression panel includes a frame member and a pressure relief panel member that is releasably retained to the frame member to removably cover a decompression vent opening of an aircraft partition, such as a sidewall of an aircraft cargo compartment. During a decompression event, the pressure relief panel member is released bi-directionally in either of two opposing directions from the frame member when a predetermined pressure differential exists across the partition. The decompression panel assembly is fire resistant, and has reduced weight and fewer parts than prior conventional decompression panel assemblies.

Abstract: A fire protection device for an aircraft or spacecraft is disclosed. The fire protection device can include a fireproof bulkhead and an adjusting device, the fireproof bulkhead can be adjusted from a ventilating position I into a screening position II. This may prevent a stream of smoke and heat from penetrating into the cabin when there is a fire underneath the fuselage.

Abstract: The present invention relates to sandwich panels used as aircraft interior parts. In addition to provide a finishing function, the sandwich panels need to have certain mechanical properties and have sufficient fire resistance to retard the spread of fire within the vehicle interior. The present invention provides an aircraft interior panel with skins comprising natural fibre reinforced composites based either on an inorganic thermoset resin or a thermoplastic resin. Such panels provide the required flame and heat resistance, allow easy recycling and disposal, are cheaper and offer significant weight savings over conventional sandwich panels.

Abstract: A fuel tank safety system includes a heat exchanger in flow communication with a cabin conditioning system, a blower configured to withdraw a quantity of ullage gas from a vehicle fuel tank for routing through the heat exchanger, and conduit interconnecting the fuel tank, the blower, and the heat exchanger. The heat exchanger is configured to reduce a temperature of the ullage gas using cooling providing by the cabin conditioning system and thus reduce the fuel content (or fuel-air ratio) of the ullage below threshold required for combustion.

Abstract: An aircraft pylon is disclosed, the pylon including a strut, a modular fluid containment structure and a modular firewall. The strut presents an open structure and connects an aircraft external element to the aircraft. The fluid containment structure is associated with a fluid transfer component, wherein the fluid containment structure contains escaped fluid from the fluid transfer component and channels the escaped fluid away from the aircraft. Both the fluid containment component and the firewall are modular and separable from the strut.

Abstract: A fire suppression system and a method for providing fire suppression onboard of an aircraft by rapidly establishing a breathable hypoxic atmosphere onboard of an aircraft, which can be generated by an air separation device utilizing a positive pressure of the bleed air and a negative pressure of the outside atmosphere; breathable hypoxic fire-extinguishing agent, containing 12%-18% of oxygen, can flood protected compartments of an aircraft in case of a fire and/or can be used as propellant for generating water mist or foam.

Abstract: 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.

Abstract: 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.

Abstract: A laminate is provided for forming an aesthetically pleasing fire worthy exterior surface on an object, for example a decorative interior sidewall used in a commercial aircraft. A first film layer forms an exterior surface of the sidewall, and an ink layer is disposed adjacent to the first film layer to provide color and/or images in an aesthetically pleasing manor, and to protect the subsequent layer from damaging UV light exposure. An embossing resin layer is disposed adjacent to the ink layer to improve the fire worthiness of the laminate by being situated adjacent to the exterior surface of the laminate. A second film layer is disposed adjacent to the embossing resin layer and a surface of the sidewall. The location of the embossing resin layer enhances the fire worthiness of the laminate by operating to absorb thermal energy released by the sidewall in the event the sidewall is exposed to fire or to a high temperature sufficient to otherwise cause higher thermal energy release of a conventional laminate.

Abstract: 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.

Abstract: The design and attachment of an insulation package near the fuselage structure to protect the cabin region of an aircraft against fire acting on the insulation package from outside the aircraft environment, thus clearly facilitating evacuation of the passengers from the vehicle. The insulation package arrangement may comprise several fuselage insulation packages of an elongated form. These packages may adjoin the aircraft fuselage structure in the direction of the longitudinal axis of the aircraft. They may be completely enclosed by a burn-through-proof foil which is arranged in a space enclosed by interior paneling and by the panels of the outer skin.

Abstract: When a fire breaks out, air flows that promote the spread of fire may occur in the region between the load bay and the skin of the aircraft. According to one embodiment of the present invention, a fire barrier is disclosed that allows rapid decompression of the passenger cabin in the normal operating mode of the aircraft and prevents flashovers in case of a fire. In this case, the fire barrier may be arranged at different positions in the intermediate wall space of the aircraft.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to an aircraft fuselage (12) comprising at least one space arranged in the aircraft fuselage and at least one wall (16). According to the invention, the wall resists burnthrough for a period of at least four minutes from outside the aircraft fuselage towards the space, wherein the region of the aircraft fuselage (12) underneath the space does not comprise burnthrough-resistant insulation. The space can be a cargo compartment of the aircraft or a passenger cabin, while the wall can be designed as a cargo compartment floor, passenger cabin floor or wing/fuselage fairing (belly-fairing). The design, according to the invention, of the aircraft fuselage results in burnthrough resistance that meets the requirements of FAR §25.856 (b) without any additional burnthrough-resistant insulation in the aircraft fuselage.

Abstract: 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.

Abstract: What is described is a locally yielding structure (1) with high energy absorption for aeronautical applications, the said structure being substantially closed and substantially rigid, characterized in that at least one wall (3) of the said substantially closed structure comprises at least one vent valve (8) which can be opened when a pressure exceeding a predetermined value is present within the substantially closed structure (1). In a particularly advantageous application, the invention is used in connection with a helicopter tank and enables the subfloor to be used to absorb energy by being deformed during any impact on the ground. The present invention is also advantageous for limiting the damage caused by explosions in an aircraft fuselage.

Abstract: An aircraft fire-extinguishing system provides automatic fire prevention and/or suppression simultaneously in fuel tanks, cargo compartments and, when needed, in cabin using injection of hypoxic (oxygen-depleted) air produced onboard in an air-separation device utilizing the flow and pressure of the bleed air. The same air-separation device allows supplying passengers and crew with unlimited amounts of oxygen for as long as needed. New methods of a rapid fire suppression utilizing the propulsion of water mist or fire-extinguishing foam by hypoxic air are presented. The combination of water mist or foam with hypoxic air allows to present two innovative fire-extinguishing compositions.