1523results about "Aircraft crew accommodation" patented technology

A light emitting diode lighting device and system that can be used for illuminating the interior and / or exterior of vehicles, aircraft, watercraft, signage or buildings is provided. It includes a voltage feedback constant current power supply circuitry and high power LEDs. The printed circuit assemblies are firmly mounted onto a continuous or semi-continuous mounting channel case that also works as a heat sink. By this means, it not only increases the reliability of the LED lighting tube but also it provides sufficient heat dissipation capability for the heat generated by the LEDs. Since the operating temperature of the LEDs is controlled and stays in cool condition, it dramatically increases the LED's lifetime and efficiency. The end caps of this LED lighting device are fully compatible with existing conventional fluorescent light fixtures and can directly replace those fluorescent lighting tubes in vehicles, mass-transit, watercrafts, aircrafts, signage or buildings with minimal modifications.

A method and system are provided for updating software configurations of line-replaceable unit (LRU) computers in a restricted architecture network such as an in-flight entertainment system (IFES). Operating in an efficient and parallel manner, each of the LRUs independently creates an individual configuration file that identifies current software components. Each of the LRUs transmits its respective configuration file to a configuration server either automatically upon startup or manually upon request. The configuration server updates a system configuration data file with the current configuration files received from the individual LRUs. In a downloading method, a download server sends a list of desired software components to the LRUs. Each of the LRUs independently and simultaneously transfer (download) the needed software from the download server. The LRU independently requests the download server to download the needed software components. To improve scalability and reliability, the file transfers utilize standard protocols, such as FTP.

A lighting fixture for providing illumination comprising a housing, a printed circuit board, and a plurality LEDs connected to the printed circuit board. Optionally an emergency LED may also be included. A heat sink is connected to the housing and printed circuit board. Each of the plurality of the LEDs is mounted on the heat sink. A reflector is disposed inside the housing such that the light from the LEDs is mixed together and projected out of the illumination end of the housing by the surface of the reflector. The lighting fixture is received into a mounting flange assembly. A method for providing illumination using the above.

Passenger service units in an aircraft are equipped with a passenger interface and supply adapter (10). Each adapter includes an individual processor (14) which is programmable independently of the aircraft central control through a programming input. The programmable interface (10) permits controlling passenger service components in the passenger cabin such as lamps in a cabin lighting system, a public address system, and so forth, directly by the interface (10) independently of the aircraft central control. The interface (10) with its own individual processor (14) and memory (15) is connected through a databus (11) to the aircraft central control (12), for example, for remote programming of the interface and for reporting the module's activities to the aircraft central control. The interface (10) reduces the memory capacity requirements for the aircraft central control and permits the individual programming of each passenger service unit also independently of any other passenger service unit thereby avoiding retesting of the entire cabin system when for example only one passenger service unit is reprogrammed.

An integrated environmental control system for an aircraft compartment and aircraft power system comprises first and second air compressors, an auxiliary power unit, and first and second environmental control systems. The first and second compressors receive and compress airflow from the aircraft exterior. The auxiliary power unit comprises a first shaft rotatably mounting a power turbine, a third air compressor to compress airflow from the aircraft exterior, and a first cooling turbine to cool the airflow. Each environmental control system comprises a first heat exchanger, a recycling heat exchanger, and a second shaft rotatably mounting a fourth compressor and a second cooling turbine for compressing and cooling the airflow. The first heat exchanger receives airflow from the first, second, and third air compressors and forwards airflow to the aircraft compartment. The recycling heat exchanger receives airflow from the aircraft compartment and recirculates airflow back to the aircraft compartment.

An aircraft seat assembly comprises a continuous row of a plurality of seats including a convertible aisle seat at one end of the row and one or more other seats. The seats are moveable between (i) a first configuration in which all of the seats are positioned in a useable position and a second configuration in which (a) the convertible seat is positioned in an unusable position in the row, (b) said one or more other seats are positioned in a useable position, and (c) the row of seats has a length, along the row, that is less than the length of the row in the first configuration for example by a distance of more than half the width of the convertible seat in the first configuration. The width of said one or more other seats may remain unchanged as between the first and second configurations.