Abstract: A method for controlling an aircraft having a plurality of LEDs, light so as to emit a desired light intensity includes the steps of providing a reference LED located within or outside of the aircraft light, providing thermal conditions resulting in a thermal stress for the reference LED similar to the maximum thermal stress, and observing the reference LED by means of an optical sensor for monitoring the optical aging behavior of the reference LED throughout its lifetime. The desired light intensity of the aircraft light is achieved by controlling the plurality of LEDs in accordance with the monitored aging behavior of the reference LED.

Abstract: A method for controlling an aircraft having a plurality of LEDs, light so as to emit a desired light intensity includes the steps of providing a reference LED located within or outside of the aircraft light, providing thermal conditions resulting in a thermal stress for the reference LED similar to the maximum thermal stress, and observing the reference LED by means of an optical sensor for monitoring the optical aging behavior of the reference LED throughout its lifetime. The desired light intensity of the aircraft light is achieved by controlling the plurality of LEDs in accordance with the monitored aging behavior of the reference LED.

Abstract: The navigation lighting device for an aircraft, in particular a military aircraft and preferably a fighter aircraft is provided with several navigation light units with navigation lights, a power supply unit for the navigation tight units, and a central actuation unit for the actuation of the navigation light units in each one of several modes of operation. The navigation light units can be actuated for operation in a mode of operation by the central actuation unit sequentially in a predetermined sequence and thus with a time offset. Each navigation light unit comprises a control unit connected to the actuation unit for the actuation of its navigation light in the operation mode predetermined by the central actuation unit. The control units of the navigation light units comprise time-delay elements for the temporal delay of the actuation of the navigation lights on the receipt of an actuation signal of the central actuation unit.

Abstract: The navigation lighting device for an aircraft, in particular a military aircraft and preferably a fighter aircraft is provided with several navigation light units (22, 24, 26) with navigation lights (48, 50, 52), a power supply unit (28) for the navigation light units (22, 24, 26), and a central actuation unit (32) for the actuation of the navigation light units (22, 24, 26) in each one of several modes of operation. The navigation light units (22, 24, 26) can be actuated for operation in a mode of operation by the central actuation unit (32) sequentially in a predetermined sequence and thus with a time offset. Each navigation light unit (22, 24, 26) comprises a control unit (42, 44, 46) connected to the actuation unit (32) for the actuation of its navigation light (48, 50, 52) in the operation mode predetermined by the central actuation unit (32).