Systems and methods are provided for applying cold spray erosion protection to an airfoil. One embodiment is a method for applying an abrasion coating to a fiber-reinforced composite substrate. The method includes applying a bond layer to the fiber-reinforced composite substrate by emitting, with a supersonic nozzle of a High Pressure Cold Spray (HPCS) system, a first gas stream including a first metal powder at a first speed below supersonic speed. The method further includes applying a cold spray deposit layer to the bond layer by emitting, with the supersonic nozzle, a second gas stream including a second metal powder at a second speed above supersonic speed.

A propeller blade comprises a composite blade spar and at least one cover shell section adhesively bonded to the blade spar by a thermoplastic adhesive.

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.

A ventilation device for controlling an air flow through at least one air inlet into an interior space of a gas turbine engine, comprises: at least one actuable closure device for the at least one air inlet, which has an open position for exposing the air inlet and can be transferred by actuation into a closed position for closing the air inlet; and a fire extinguishing device having an extinguishing agent arranged in a reservoir, wherein the fire extinguishing device is connected or can be connected to the interior space and the closure device in such a way that activation of the fire extinguishing device both leads to admission of extinguishing agent from the reservoir into the interior space and brings about actuation of the closure device to transfer the closure device into the closed position.

A fire detection system for monitoring an aircraft compartment and supporting a cockpit crew with taking remedial action in case of a fire alarm with a fire detector within the compartment; a monitoring system within the compartment to provide live monitoring data on cargo; a cargo tracking system configured to provide cargo data of the cargo; an aircraft control system configured to provide aircraft status data; a system control configured to assess a fire warning data, the cargo data and the aircraft status data and to provide a recommended remedial procedure based on the assessment in case the fire detector raises a fire alarm at least in an affected portion of the compartment; and a display device configured to display the live monitoring data and the recommended remedial procedure to the cockpit crew in case of a fire alarm

A device for suppressing and/or extinguishing a fire associated with a container may include a housing defining a hollow sleeve and a column configured to be received within the hollow sleeve. The column may define a first chamber, a second chamber, at least one aperture, and a piercing end configured to pierce a barrier. The first chamber may be configured to receive an expansion agent, and the second chamber may be configured to receive a fire extinguishing agent. The device may be configured such that upon activation of the expansion agent, the column extends from the housing so as to enable the piercing end to penetrate the container and to enable the fire extinguishing agent to be delivered into an interior of the container via the at least one aperture.

A gas detection system that detects gas inside an enclosed space of an aircraft system on board in an aircraft. The system is used in a method for determining the presence of a gas inside an aircraft system by means of a detection system installed on the aircraft system. The system monitors and/or detects a vacuum leak or of fire inside an aircraft system arranged in an aircraft.

A fire extinguishing system of an air mobility vehicle includes a refrigerant flow line in which a refrigerant flows, and including a compressor, a condenser, a first expansion valve, and an evaporator, a fire extinguishing liquid flow line connected to the refrigerant flow line via a connection valve, and configured to spray a mixed liquid of a fire extinguishing liquid and the refrigerant, a mixing part connected to the fire extinguishing liquid flow line, and configured to mix the refrigerant and the fire extinguishing liquid, and a fire extinguishing liquid storage part configured to store the fire extinguishing liquid and to discharge the fire extinguishing liquid into a mixing space of the mixing part.

A propulsion system for an aerial vehicle having a wing structure operating in a wildfire environment, wherein the wing structure includes a drive extending through a top and a bottom surface of the wing structure and configured to provide a thrust through the top and bottom surface of the wing structure along a vertical axis of the aerial vehicle. The drive may be magnetohydrodynamic drive or an open Nacelle Fan assembly. The drive may be magnetohydrodynamic drive or an open Nacelle Fan assembly The Open Nacelle Propulsion Fan uses a drive mechanism with an induced magnetic field generated by an induction coil housed within the fan assembly open to the ambient environment, a counter-rotating fan assembly including a first fan rotating clockwise, and configured to adjust the pitch of the propulsion fan, thereby enabling the aerial vehicle's thrust to be vectored as determined by the command module.

An apparatus for detecting and evaluating turbulence for an aircraft. The apparatus contains a measuring device for acquiring a value, which indicates a movement of the aircraft relative to the earth, and a second measuring device for acquiring a second value, which indicates a movement of the aircraft relative to the air. The apparatus contains a computing system which receives the two values and determines a difference between the first value and the second value and, on the basis of the difference, a turbulence intensity. The computing system compares the second value with a predefined value range and classifies turbulence as classified turbulence if the second value departs from the predefined value range. The computing system determines the frequency of occurrence of such classified turbulences and detects a turbulent flight state on the basis of the determined turbulence intensity and the frequency of occurrence of the classified turbulences.