1500results about "Aircraft crew accommodation" patented technology

Electrochromic device control systems and methods are disclosed. In one embodiment, a window system includes a plurality of transparent windows, a plurality of electrochromic devices, a plurality of control modules, and a main controller. Each transparent window has an electrochromic device operatively associated therewith. A control module is operatively coupled to each electrochromic device and is adapted to controllably adjust an electric field to activate and de-activate the electrochromic device. Finally, the main controller is operatively coupled to the plurality of control modules and adapted to simultaneously adjust the electric fields of the plurality of electrochromic devices to activate and de-activate the plurality of electrochromic devices in unison. In one particular embodiment, a window dimming control system in accordance with the present invention may advantageously be incorporated into an existing cabin services system of a passenger aircraft.

The present invention relates to a personal user agent acting on behalf of a group of member device agents in a communication network. The personal user agent provides its group of member device agents with a specialized proxy function, while representing the group to the network as a single user agent. To devices on the communication network, the personal user agent behaves and is viewed as a user agent. To the group of member device agents, the personal user agent behaves and is viewed as both a registrar and a proxy server.

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 lighting fixture and lighting system for a transportation vehicle is disclosed that provides color variations for lighting the passenger cabin of an airplane, train, bus or other type of transportation vehicle. The lighting fixture and system further provide ultraviolet light that helps to disinfect the circulating air in the passenger cabin. A fixture in an exemplary lighting system provides visible light for lighting up the passenger cabin and germicidal ultraviolet light directed toward or into an output vent(s) of the air circulation system of the passenger vehicle. The ultraviolet light is segregated from the visible light such that ultraviolet light is only directed toward or into the circulation vents of the vehicle's air circulation system.

In an anti-hijacking system for autopilot equipped aircraft, a transceiver communicates with at least one remote guidance facility. A panic button is activated by flight crew in case of hijacking. A manager is coupled to the transceiver and the panic button, as well as existing avionics including the aircraft's master computer and autopilot. Optionally, a relay is coupled between the pilot controls and selected aircraft flight systems. The manager recognizes predetermined override inputs, such as activation of the panic button or receipt of override signals from the remote guidance facility. Responsive to the override input, the manager deactivates on-board control of selected aircraft flight systems and the autopilot system, and directs the autopilot to fly the aircraft to a safe landing. Flight routing and landing instructions are obtained from the remote guidance facility, or by self-evaluating nearby airports in view of the aircraft's position and various preestablished criteria.

An electro-optical device includes a display panel having an electro-optical layer, a first resin film stacked on the display panel to cover a first surface on the side of a display area of the display panel, and a second resin film stacked on the display panel to cover a second surface opposite the first surface, and at least one reinforcing member disposed on at least one of the first resin film and the second resin film.

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.

Electrochromic window assemblies and methods for providing electrochromic window assemblies are disclosed. In one embodiment, a window assembly includes a first transparent portion and a first trim portion. The first trim portion is located adjacent to the first transparent portion. The window assembly also includes a second transparent portion and a second trim portion. The second trim portion is located adjacent to the second transparent portion. The window assembly further includes an electrochromic assembly. The electrochromic assembly is disposed between the first transparent portion and the second transparent portion so that it is adjacent to both transparent portions.

Combined aircraft hybrid fuel cell auxiliary power unit and environmental control system and methods are disclosed. In one embodiment, an auxiliary power unit includes a fuel cell component which chemically converts combustible fuel into electrical energy. Unutizlied fuel emitted by the fuel cell component is combusted by a burner to generate heated gas. The heated gas is received by and drives a turbine, which in turn drives a drive shaft. A compressor, coupled to the drive shaft, compresses a source of oxidizing gas for supplying compressed oxidizing gas to the fuel cell component and to an environmental control system. A heat exchanger controls the temperature of the pressurized air leaving the environmental control system to provide the cabin air supply. Finally, a generator is coupled to the drive shaft to be driven by the turbines to generate additional electrical energy.

There is proposed a spotlight, in particular a reading light in cabins of vehicles and craft, in particular aircraft, which has preferably white light-emitting light-emitting diodes (1) which are radially encased by a body, wherein a lens body (6) is fitted on the end light exit opening of the body, as the lighting source and a frame (9) which carries the lighting source and which is pivotable or rotatable about at least one horizontal and/or vertical axis and is adapted to be fixed in the respective selected position. The frame (9) can be received by a receiving body (13) and is supported therein pivotably or rotatably about at least a horizontal axis (14). The receiving body (13) is held in a fixing ring (21) and is rotatable about a vertical axis. The frame (9) with the receiving body (13) and/or the receiving body (13) with the fixing ring (21) are latchable respectively through a spring and in a resiliently latched manner.

A system and a method is provided for fitting an aircraft cabin with modular sidewall panels, window reveals, and foam insulation blocks in an integrated manner. The system comprises a sidewall panel which may have one or more openings therethrough to receive a window reveal held by snap-fit fastenings. The bezel of the window reveal may be held by snap-fit fasteners for easy removal to allow removal and cleaning of the inner dust cover disassembly of the sidewall panel. Foam insulation blocks may be molded to fit in the cavity between the outer wall of the aircraft and the sidewall panels, held in place by compressive pressure between the frames of the airframe. The outer extent of the window reveal is tapered inwardly to guide the window reveal to mating contact with an outer window assembly in the aircraft fuselage without further adjustment of the sidewall panel.

This invention relates generally to the field of aircraft technology and systems utilized for protection of aircraft, occupants, and operators thereof from hijackers, terrorists, and other anomalous problems while in flight. More particularly, the present invention relates to a device used in conjunction with walls, floor, and ceiling of a cockpit's entry/exit passageway for protecting the cockpit crew from weapons, hostility, decompression, and/or physical intrusions. A light weight protective shield for the cockpit of an aircraft (i.e. bullet-proof door) along with a internal locking and release device, none of which is provided by prior art. The protective shield can absorb repeated blows, provide pressure relief in the event of aircraft decompression, resist penetration of firearms, knives, and explosive devices, and is compliant with FAA regulations. The protective shield provides a new level of protection for the crew of a passenger or cargo airplane and protects the cockpit of an aircraft from hijacking attempts as well as other anomalous events and is comprised of a light weight weapon-proof protective shield that when closed fits snugly with the flight deck's adjoining floor, walls, and ceiling. This protective shield system is intended to readily install inside existing aircraft (e.g. over-night retrofit installation) or be installed into new aircraft as they are assembled.

The present invention provides apparatus and methods for multi-color electrochromic devices. In one embodiment, pixels of a first color electrochromic material (i.e. pigment) are arranged in first areas on a substrate with pixels of a second color electrochromic material in second areas to define a two-dimensional pattern of the first and second color on the substrate. When the applied electric field or current supplied to each pixel is changed, the device may produce the respective colors of the electrochromic materials and may produce a blended color because of the arrangement of the pixels. In accordance with further aspects of the invention, the electrochromic materials may form a design, pattern, logo, or picture when the electrochromic materials are activated. In yet further aspects of the invention, a substrate is masked and unmasked as a plurality of colors are applied to the substrate to produce a multi-color electrochromic display.

An adaptive energy absorption system for a vehicle seat is disclosed, utilizing an adaptive energy absorber or variable profile energy absorber (VPEA) for mitigating occupant injury due to extreme vehicle movement (e.g., during a vehicle shock event), and/or for mitigating vibration experienced by an occupant of the vehicle seat during normal vehicle operating conditions. The adaptive energy absorption system achieves the aforementioned objectives for a wide range of occupant weights and load levels. An alternate configuration of a dual-goal energy absorption system is also disclosed that enables both shock mitigation and vibration isolation.

A thermal management system for an aircraft is provided. The aircraft includes a primary air conditioning system which compresses and cools outside air to create inside air. The inside air pressurizes the internal volume of the aircraft and ventilates a first object in the internal volume. An exhaust exhausts a portion of the inside air to allow more outside air to be drawn into the aircraft. A cooler cools a coolant which in turn controls temperature of at least two objects in the internal volume.