A decompression panel assembly for use in an aircraft includes a frame including a first surface and an opposing second surface, wherein the frame defines a grille opening and at least partially defines a flow path opening. The decompression panel assembly also includes a face panel having a first surface retained against the frame second surface such that the face panel at least partially covers the grille opening. A retention mechanism is coupled to the face panel and is configured to retain the face panel against the frame in a closed position.

A fall damage reducing system includes a flying device and a vehicle-mounted device. The flying device: performs a wireless communication under a vehicle to vehicle communication standard; determines a falling possibility of the flying device; and transmits falling information indicating an estimated falling position of the flying device in response to the falling possibility being determined. The vehicle-mounted device: performs a wireless communication under the vehicle to vehicle communication standard; executes a vehicle control on a subject vehicle to avoid the estimated falling position in response to the falling information being received; and transmits traveling information indicating the vehicle control executed on the subject vehicle. In response to the traveling information from a different vehicle being received, the vehicle-mounted device executes a collision avoidance process to avoid a collision with the different vehicle.

An interior aircraft light includes a mounting structure for mounting the interior aircraft light to an aircraft seat; a UV radiation source; and an optical system, configured to direct UV radiation from the UV radiation source towards a floor portion underneath the aircraft seat.

An air mobility control system is provided. The system includes one or more shock absorbing units that are mounted in an aircraft and are configured to absorb a vertical force impacting on the air mobility vehicle. A distance sensor is mounted in the air mobility vehicle and is configured to sense the distance to a ground or an approaching object. A safety controller is configured to detect an abnormal descent of the air mobility vehicle and to operate the one or more shock absorbing units to be deployed according to the distance sensed by the distance sensor.

An air mobility control system is provided. The system includes one or more shock absorbing units that are mounted in an aircraft and are configured to absorb a vertical force impacting on the air mobility vehicle. A distance sensor is mounted in the air mobility vehicle and is configured to sense the distance to a ground or an approaching object. A safety controller is configured to detect an abnormal descent of the air mobility vehicle and to operate the one or more shock absorbing units to be deployed according to the distance sensed by the distance sensor.

An apparatus comprising a float bag comprising an air bladder configured to inflate when an aircraft lands in the water, a girt coupled to the air bladder and configured to attach the air bladder to the aircraft via at least one airframe fitting, and a load attenuator coupled to the girt and configured to be positioned between the girt and the airframe fitting when the float bag is attached to the aircraft, wherein the plurality of load attenuators are configured to mechanically deform in a progressive failure fashion from a first effective length to a second effective length greater than the first length in response to an applied tensile load on the load attenuators coupled to the plurality of girts and the aircraft airframe, wherein the load attenuators are selected to reduce the force with a total length that minimizes buoyancy depth of the aircraft.

An apparatus comprising a float bag comprising an air bladder configured to inflate when an aircraft lands in the water, a girt coupled to the air bladder and configured to attach the air bladder to the aircraft via at least one airframe fitting, and a load attenuator coupled to the girt and configured to be positioned between the girt and the airframe fitting when the float bag is attached to the aircraft, wherein the plurality of load attenuators are configured to mechanically deform in a progressive failure fashion from a first effective length to a second effective length greater than the first length in response to an applied tensile load on the load attenuators coupled to the plurality of girts and the aircraft airframe, wherein the load attenuators are selected to reduce the force with a total length that minimizes buoyancy depth of the aircraft.

A rotating system comprising two or more blades 3 mounted on a hub installed on a rotatable propeller shaft 1, each blade provided with a respective sensor 4 arranged to detect response of the respective blade to harmonic excitation; and the system further comprising means configured to compare the response of the respective blade to that of the other blade(s).

Autoland systems and processes for landing an aircraft without pilot intervention are described. In implementations, the autoland system includes a memory operable to store one or more modules and at least one processor coupled to the memory. The processor is operable to execute the one or more modules to identify a plurality of potential destinations for an aircraft. The processor can also calculate a merit for each potential destination identified, select a destination based upon the merit; receive terrain data and/or obstacle data, the including terrain characteristic(s) and/or obstacle characteristic(s); and create a route from a current position of the aircraft to an approach fix associated with the destination, the route accounting for the terrain characteristic(s) and/or obstacle characteristic(s). The processor can also cause the aircraft to traverse the route, and cause the aircraft to land at the destination without requiring pilot intervention.

Autoland systems and processes for landing an aircraft without pilot intervention are described. In implementations, the autoland system includes a memory operable to store one or more modules and at least one processor coupled to the memory. The processor is operable to execute the one or more modules to identify a plurality of potential destinations for an aircraft. The processor can also calculate a merit for each potential destination identified, select a destination based upon the merit; receive terrain data and/or obstacle data, the including terrain characteristic(s) and/or obstacle characteristic(s); and create a route from a current position of the aircraft to an approach fix associated with the destination, the route accounting for the terrain characteristic(s) and/or obstacle characteristic(s). The processor can also cause the aircraft to traverse the route, and cause the aircraft to land at the destination without requiring pilot intervention.