A gas inerting system employs a carbon dioxide separation unit to remove carbon dioxide and water from an oxygen depleted gas stream generated from a catalytic oxidation unit and subsequently provides a nitrogen rich inerting gas to a fuel tank and/or to a cargo hold. A method of producing an inert gas passes an oxygen depleted gas stream from a catalytic oxidation unit through a carbon dioxide separation unit and provides a nitrogen rich inerting gas for fuel tank inerting and/or cargo hold fire suppression.

methods, apparatuses, and systems for harvesting inert gas exhausted from an engine and using the harvested inert gas to prevent an ignition event and/or extinguish an ignition event. The temperature of the harvested inert gas may need to be lowered. Unwanted components may be removed from the harvested inert gas. Combustion components may be completely burned from the harvested inert gas prior to providing the harvested inert gas to a fire protection system. The fire protection system uses the harvested inert gas to extinguish an ignition event and/or to provide a purge flow to prevent an ignition event. The fire protection system may be on an aircraft. Sensors may be used to detect an ignition event. Pressure sensors may be used to monitor the pressure of the harvested inert gas as well as to monitor the purge pressure of areas receiving a continuous purge flow of harvested inert gas.

Fireworthy sealants may have a variety of compositions and be made by a variety of techniques. In certain implementations, a fireworthy sealant may include a body comprised of a cured, tacky, soft, deformable non-adhesive gel. The gel body may have an upper surface, a lower surface, and a perimeter, wherein the upper and lower surfaces of the gel body, in an uncompressed state, define a body thickness. The sealant may, in an uncompressed state, be dimensioned to fit in a first opening between a wall and an aircraft component surface and deformable when under compression to fit in a second opening, smaller than the first opening. The sealant may be flame retardant and produce low smoke density and low smoke toxicity.

Fire seal assemblies for aircraft engines are described herein. An example fire seal assembly includes a first L-cap having a first leg and a second leg extending outward from the first leg, and a second L-cap having a third leg and a fourth leg extending outward from the third leg. The first and third legs are to be coupled to a core service disconnect (CSD) on a pylon of an aircraft, and the second and fourth legs are to extend outward and engage sides of a firewall of an engine of the aircraft. The first seal assembly further includes a seal coupled to the first and third legs and disposed between the second and fourth legs, a first end plug disposed between a first end of the seal and the second leg, and a second end plug disposed between a second end of the seal and the fourth leg.

The disclosure relates to a redundant electric machine for driving a propulsion means with increased operational safety. The machine may include two systems, with each system including a stator winding system and a rotor assigned thereto with permanent magnets, wherein the rotors are fastened on a common shaft for driving the propulsion means. If a fault occurs in one of the stator winding systems, the rotor, which continues to rotate, has to be prevented from inducing electric voltages in the stator winding system because this may lead to a fire in the machine. A demagnetization apparatus is therefore provided which, in a targeted manner, demagnetizes the permanent magnets of the rotor assigned to the faulty stator winding system such that the inducing of electric voltages is prevented.

Disclosed is an optical fiber overheat detection testing apparatus including an optical fiber having a first end and a second end, the optical fiber having a predetermined length associated with a predetermined attenuation based on an overheat detection instrument loop. The apparatus includes a first interrupt disposed equidistant between the first end and the second end defining a first half of the optical fiber and a second half of the optical fiber, the first half and the second half having equal length, the first interrupt having a first actuator operable by a first electric current to attenuate light wave traversal of the optical fiber. The apparatus includes a second interrupt disposed on the first half and spaced from the first end at least six tenths of a meter, the second interrupt having a second actuator operable by a second electric current to attenuate light wave traversal of the optical fiber.

Disclosed is an optical fiber overheat detection testing apparatus. The apparatus includes an optical fiber having a first end and a second end, the optical fiber having a predetermined length associated with a predetermined attenuation based on an overheat detection instrument loop. The apparatus includes a first fiber Bragg grating disposed on the optical fiber having a first wavelength spectrum based on a first temperature detection apparatus. The apparatus includes a second fiber Bragg grating disposed on the optical fiber having a second wavelength spectrum based on at least one of a plurality of overheat detection apparatuses.

A smoke and temperature detection system includes a plurality of fiber optic cables terminating in a plurality of nodes positioned to monitor a fire or smoke condition at one or more protected spaces, and a temperature detection fiber optic cable having a plurality of fiber Bragg gratings arrayed along the temperature detection fiber optic cable. A control system is operably connected to the plurality of fiber optic cables and to the temperature detection fiber optic cable. The control system includes a first light sensitive device configured to receive a scattered light signal from the plurality of fiber optic cables, and a second light sensitive device configured to receive a reflected light signal from the fiber Bragg gratings. The control system is configured to detect a temperature at the fiber Bragg gratings based on one or more properties of the reflected light signal received at the second light sensitive device.

An apparatus for inerting a space includes a metal-air battery, a feed channel for the introduction of air from an air source to the metal-air battery, and a discharge channel for the discharge of air from the metal-air battery to a volume of the space. A control unit controls an electrochemical reaction of the metal-air battery as a function of a fire situation within the space. A method for inerting a space, an inerting system, an inerting method and an aircraft or spacecraft are also provided.

A trash can device for an aircraft lavatory unit is provided, including: a waste container in a storage chamber of the aircraft lavatory unit; a chute, disposed above the waste container, including a trash feed opening formed at a section of the chute corresponding to a trash feed port of a panel sectioning off the storage chamber; and a waste flap that opens and closes the trash feed opening. A fire spreading prevention space is formed below the chute in a state when the waste flap is positioned in a closed position in which the trash feed opening is closed by the waste flap. The trash can device is provided with a holding/moving portion of the waste flap, the holding/moving portion holds the waste flap in an open position in which the trash feed opening is opened and moves the waste flap to the closed position when exposed to heat.