An overheat detection system for an aircraft, the system comprising a first bleed monitoring computer, BMC1, configured to identify leakages in a pneumatic system, the BMC1 including a first optical controller, a second bleed monitoring computer, BMC2, the BMC2 including a second optical controller, an optical fiber link connecting the first optical controller of the BMC1 and the second optical controller of the BMC2 for communication between the BMC1 and the BCM2 and between the first optical controller and the second optical controller, wherein the first and the second optical controllers are configured to detect overheat of the optical fiber link based on a wavelength shift of a modulated optical signal transmitted through the optical fiber link, and transmit signals to the first BMC1 and the second BMC2 based at least on the detected overheat.

Disclosed is a flame protection fabric provided for vehicle cushions, in particular for aircraft cushions, the flame protection fabric including the following layers: at least one first abrasion-resistant layer as an abrasion layer including at least one textile material with high abrasion resistance of at least one fiber type, and at least one second layer as a barrier layer including at least one fibrous fleece of at least one flame-proof fiber type. The at least one abrasion layer is provided as a first layer on at least one side of the at least one barrier layer as a second layer.

Oil system for a turbomachine, making it possible to continue the supply of oil to the pieces of equipment of the turbomachine in case of occurrence of a fire within the turbomachine, including an oil circuit, at least one oil-consuming piece of equipment, supplied by the oil circuit, a pumping unit, including at least one speed-pilotable electrically driven pump, supplying the oil circuit, and an electronic control unit, configured to pilot the electrically driven pump, wherein the electronic control unit includes two separate logics of piloting the electrically driven pump, and wherein the electronic control unit is configured to pilot the electrically driven pump according to the first logic by default and to switch to the second logic in case of receipt of a signal representative of the presence of a fire or of an overheating.

A detection system in an aircraft includes an optical fiber arranged along a structure of the aircraft and affixed to the structure with clamps that are spaced apart along the structure. The optical fiber includes two or more sets of fiber Bragg gratings (FBGs). The system also includes a light source to generate light with two or more wavelengths for injection into the optical fiber, and processing circuitry to identify an overheat condition and monitor vibration experienced by the optical fiber based on reflected signals generated by the two or more sets of FBGs. Integrity of the clamps is indicated by monitoring the vibration.

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.

A mounting fixture for mounting a sensor circuit to a support rail is disclosed. In various embodiments, the mounting fixture includes a bracket having a base portion and a first flange member extending from the base portion; a clamp fixture connected to the first flange member, the clamp fixture including a plate member; a first pin extending through the first flange member and the plate member; and a first fastener threaded on to the first pin and configured to secure the plate member to the first flange member.

A vision-based aircraft cabin light monitoring/control system is used to maintain the light intensity level within the aircraft cabin at a desired level. The system uses video cameras to continuously monitor the ambient light entering the passenger cabin windows, analyzes the video stream/feed to identify the light intensity level within the cabin, identifies the window whose state should be controlled, and generates commands to control the window through central cabin controllers. The system further compensates for light sources internal to the cabin and monitors the phase of flight to ensure compliance to specific light conditions within the aircraft cabin.

An aircraft includes an airframe defining a first enclosed space, an engine bay disposed within the first enclosed space, and a cooling system. The engine bay includes a firebox defining a second enclosed space and an engine disposed at least partially within the second enclosed space. The cooling system is configured to selectively fluidly couple the first enclosed space with the second enclosed space.

The present invention is a system and method for modifying a passenger aircraft and converting it for use as a cargo aircraft, wherein the steps include removing all structures that were previously put into the aircraft to accommodate passengers including walls, storage, and seating, wherein the seat tracks are left in the floor to function as secure attachment points, moving pallet sections into the aircraft that can fit through the existing doorways, and assembling the pallet sections together to create pallet assemblies, wherein the pallet assemblies function as a bridging system upon which cargo loads may be disposed without causing damage to the existing unreinforced floor of the aircraft, wherein each of the pallet assemblies is connected to the existing seat tracks in the floor in order to secure the pallet assemblies to the aircraft frame.

A temperature monitoring apparatus configured to monitor a temperature of a portion of a vehicle's electrical energy distribution network is disclosed. The apparatus includes a first optical fibre including one or more temperature sensing sections, each temperature sensing section being for thermal contact with a portion of a vehicle's electrical energy distribution network. Each temperature sensing section is arranged to produce, in response to an optical input signal, an optical output signal indicative of the temperature of the temperature sensing section. The apparatus is arranged to determine a temperature of the portion of the vehicle's electrical energy distribution network based on one or more of the output optical signals in use.