An exterior aircraft lighting device comprises: at least one light source; an optical element having a light entry side facing the at least one light source and a light exit side and being configured for modifying light emitted by the at least one light source; at least one photo detector, which is configured and arranged for detecting a portion of the light emitted by the at least one light source, which is reflected by the light entry side of the at least one optical element, the photo detector providing a detection value, representing the amount of detected light; and a control and evaluation unit which is configured for evaluating the state of wear of the at least one light source based on the detection value provided by the at least one photo detector.

An aircraft exterior light unit may comprise a magnetically controlled fluid drain valve configured to expel liquid water from the light unit. The valve may include a permanent magnet configured to induce a magnetic flux circuit that generates a magnetic force configured to close the valve. The valve may be configured to open when the pressure inside the light unit exceeds the magnetic force. As the valve opens and expels the water, the pressure within the light unit may decrease, equalizing with that of the external environment. As the magnetic force generated by the magnet increases as the valve is open and the water expelled, the magnet may be configured to close the valve once more. As such, the magnet may be configured to control a self-acting fluid drain valve in an aircraft exterior light.

An aircraft exterior light unit may comprise a magnetically controlled fluid drain valve configured to expel liquid water from the light unit. The valve may include a permanent magnet configured to induce a magnetic flux circuit that generates a magnetic force configured to close the valve. The valve may be configured to open when the pressure inside the light unit exceeds the magnetic force. As the valve opens and expels the water, the pressure within the light unit may decrease, equalizing with that of the external environment. As the magnetic force generated by the magnet increases as the valve is open and the water expelled, the magnet may be configured to close the valve once more. As such, the magnet may be configured to control a self-acting fluid drain valve in an aircraft exterior light.

Aerial vehicles may include one or more directional sensors embedded into wings, rudders, ailerons, flaps or other control surfaces. When the aerial vehicles are operating in modes that do not require the use of such surfaces, a surface having a directional sensor embedded therein may be repositioned or reoriented to align the directional sensor toward an area or axis of interest, and information may be gathered from the area or axis of interest using the directional sensor. One or more safety lights, running lights or other illuminators may cast light of a desired color, frequency or wavelength toward the area or axis of interest. The directional sensors may include cameras, radar or laser sensors, or any other reorientable sensors.

Aerial vehicles may include one or more directional sensors embedded into wings, rudders, ailerons, flaps or other control surfaces. When the aerial vehicles are operating in modes that do not require the use of such surfaces, a surface having a directional sensor embedded therein may be repositioned or reoriented to align the directional sensor toward an area or axis of interest, and information may be gathered from the area or axis of interest using the directional sensor. One or more safety lights, running lights or other illuminators may cast light of a desired color, frequency or wavelength toward the area or axis of interest. The directional sensors may include cameras, radar or laser sensors, or any other reorientable sensors.

In a method for producing a light program (22) for controlling lighting in an interior (80) of an aircraft (82) during a flight, a sequence list (2a, b) of phases of the day (4a-l) for a full day is set, wherein a time of day (6), a phase duration (8) and lighting data (La-l) for the lighting are assigned to each phase of the day (4a-l), the appropriate phase of the day (4a-l) is selected from the sequence list (2a, b) as first program section (14a) of a flight program (10) on the basis of the local time (12a) at which the flight starts and the proportional associated phase duration (8) is assigned to the first program section as section duration (16a), the appropriate phase of the day (4a-l) is selected from the sequence list (2a, b) as last program section (14b-e) of the flight program on the basis of the local time (12b) at which the flight lands and the proportional associated phase duration (8) is assigned to the last program section (14b-e) as section duration (16b-e), the flight program (10) between first program section (14a) and last program section (14b-e) is filled with the phases of the day (4a-l), lying therebetween as per the sequence list (2a, b), as program sections (14b-d) and the associated phase durations (8) are assigned to the program sections (14b-d) as section durations (16b-d), at least one of the section durations (16a-e) is scaled on the basis of a scaling prescription in such a way that the overall duration of the flight program (10) corresponds to the flight duration (TF), the flight program (10) runs in time during the flight on the basis of the elapsed flight time (t), wherein the lighting data (La-l) of the respective current program section (14a-e) are output as light program (22) at each instant of the flight time (t).

Aircraft, aircraft exterior speaker systems, and methods of projecting sound waves from an exterior of an aircraft are provided. An aircraft includes an outer skin membrane, a vibration actuator, and a controller. The outer skin membrane has an exterior surface that defines an exterior boundary of the aircraft. The vibration actuator is coupled for common vibration with the outer skin membrane. The controller is operatively coupled with the vibration actuator and is configured to generate a command for the vibration actuator based on audible content to be projected from the exterior surface. The controller is further configured to transmit the command to the vibration actuator. The vibration actuator is configured to vibrate in response to receiving the command.

Aircraft, aircraft exterior speaker systems, and methods of projecting sound waves from an exterior of an aircraft are provided. An aircraft includes an outer skin membrane, a vibration actuator, and a controller. The outer skin membrane has an exterior surface that defines an exterior boundary of the aircraft. The vibration actuator is coupled for common vibration with the outer skin membrane. The controller is operatively coupled with the vibration actuator and is configured to generate a command for the vibration actuator based on audible content to be projected from the exterior surface. The controller is further configured to transmit the command to the vibration actuator. The vibration actuator is configured to vibrate in response to receiving the command.

In some embodiments, a system is provided that includes a portable electronic device; and an application executable on the portable electronic device, the application including computer program code that (a) monitors acceleration data during a flight of an airplane; and (b) displays a representation of the acceleration data in relation to a threshold acceleration of the airplane. Numerous other aspects are provided.

In some embodiments, a system is provided that includes a portable electronic device; and an application executable on the portable electronic device, the application including computer program code that (a) monitors acceleration data during a flight of an airplane; and (b) displays a representation of the acceleration data in relation to a threshold acceleration of the airplane. Numerous other aspects are provided.