123results about "Electronic flight bags adaptations" patented technology

Systems and methods for monitoring and reporting a quick access recorder (QAR) data in real time. The system includes a QAR for recording fault information, a removable portable hardware component that stores, analyzes and displays the fault information, an onboard data communication network that enables the QAR and the portable hardware component to exchange information, and an air-ground data transmitting device for transmitting the fault information from the vehicle. The removable portable hardware component may be an Electronic Flight Bag (EFB) that hosts a QAR Manager application and communication technologies to manage and report all applications on the EFB.

A convertible clamp device including a C-shaped frame having first and second substantially opposing interconnected arms; a clamping rod carried by the first arm for longitudinal movement in a first clamping direction toward an internal face of the second arm and in a second opposite direction away from the second arm; different first and second movable clamping jaws removably coupleable to a portion of the clamping rod between the arms of the frame; and different first and second stationary clamping anvils being disposable on the internal face of the second arm.

An electronic flight bag for an aircraft includes a display device and a processing system. The display device is operable to render various images. The processing system is in operable communication with the display. The processing system is configured to receive various types of data from various aircraft systems and is operable, upon receipt of the data, to supply display commands to the display device that cause the display device to automatically render various images. These images may include, among other things, flight manual pages, checklists, approach charts, maintenance data, and various navigation displays. The electronic flight bag may also implement the functions of various other aircraft systems and devices.

Systems and methods for monitoring and reporting a quick access recorder (QAR) data in real time. The system includes a QAR for recording fault information, a removable portable hardware component that stores, analyzes and displays the fault information, an onboard data communication network that enables the QAR and the portable hardware component to exchange information, and an air-ground data transmitting device for transmitting the fault information from the vehicle. The removable portable hardware component may be an Electronic Flight Bag (EFB) that hosts a QAR Manager application and communication technologies to manage and report all applications on the EFB.

A convertible clamp device including a C-shaped frame having first and second substantially opposing interconnected arms; a clamping rod carried by the first arm for longitudinal movement in a first clamping direction toward an internal face of the second arm and in a second opposite direction away from the second arm; different first and second movable clamping jaws removably coupleable to a portion of the clamping rod between the arms of the frame; and different first and second stationary clamping anvils being disposable on the internal face of the second arm.

An aircrew automation system that provides a pilot with high-fidelity knowledge of the aircraft's physical state, and notifies that pilot of any deviations in expected state based on predictive models. The aircrew automation may be provided as a non-invasive ride-along aircrew automation system that perceives the state of the aircraft through visual techniques, derives the aircraft state vector and other aircraft information, and communicates any deviations from expected aircraft state to the pilot.

An aviation clamp device formed of a substantially rigid elongated jaw structure formed with an open throat portion formed between spaced apart and relatively angularly canted opposing drive and anvil plates and a backing plate and having an elongated mouth opening thereinto between the opposing drive and anvil plates and partially extending around peripheries thereof to the backing plate, the drive plate being formed with a pair of threaded apertures therethrough spaced adjacent to opposite ends thereof, and a ball-end coupler formed of a resiliently deformable part-spherical head projected from one of the drive and anvil plates on a substantially rigid reduced diameter stem relatively upstanding thereon; and a plurality of threaded thumb screws each structured for cooperating with one of the threaded apertures by threading therethrough from an external surface of the elongated jaw structure into the throat portion thereof.

A tablet mount assembly for mounting an electronic device (e.g., an Apple® iPad®) in the cockpit of an aircraft, and more specifically on the steering control of the aircraft. The tablet mount includes a receiving piece and a pivot mount assembly that includes an upper portion and a lower portion. The upper portion is rotatable with respect to the lower portion. The upper portion includes a slot for connecting to the receiving piece, and the lower portion includes a securing mechanism and a positioning flange. The upper portion of the assembly is rotatable with respect to the lower portion, thereby allowing the electronic device to be mounted to be rotated from a portrait to a landscape orientation without removing the same from the mount. An indexing position system may be integrated between the lower and upper portions of the mount assembly and provides predetermined rotation increments for the device.

A computer-implemented method for managing the data of an aircraft flight plan comprises collecting initial data of an operational flight plan from a flight planning system FPS by an electronic device of electronic flight bag EFB type; converting the initial data and communicating the converted data to the avionics system of the flight management system FMS, the FMS being able to compute an avionic flight plan on the basis of the converted data; and retrieving the avionic flight plan data such as processed by the flight management system FMS. Developments describe notably the verification of the security and / or of the integrity of the converted initial data by means of predefined compliance rules; the emulation of avionics protocols and the use of the encipherment of the data. System aspects and software aspects are described.

A spring-loaded clamp device including a C-shaped frame having first and second substantially opposing arms interconnected by an intermediate shank, the first arm having a substantially hollow carrier sleeve aligned substantially along a clamping direction oriented substantially transverse of the second arm, and the second arm having a thin and flat anvil portion positioned opposite from the carrier sleeve and further comprising an interior clamping surface that is oriented substantially transverse of the clamping direction. A clamping rod is carried in the hollow of the sleeve for longitudinal movement in the clamping direction toward an internal face of the second arm and in an opposite unclamping direction away from the second arm. An expansive biasing member is coupled for expanding the clamping rod for longitudinal movement along the clamping direction.

A method implemented by a computer for managing meteorological data for the management of the flight of an aircraft, comprises the steps of receiving a cartographic background and meteorological data associated with the flight plan, selecting one or more meteorological events; displaying graphic representations associated with the meteorological events selected on a strip representing the flight plan; based on the updating of the meteorological data, refreshing the display of the meteorological data. Developments notably describe the re-refreshing of the display corresponding to a revision of the flight plan, taking into account of the severity of the meteorological events, the emission of alerts and / or selectable notifications, the distinction between meteorology of regulatory type and of non-regulatory type. Software and system aspects are described (e.g. electronic flight bag EFB).

An enhanced vision system and method for use with vision systems with an imager sensitive to infrared radiation of less than 2-microns in wavelength, to produce a first image signal. Another imager sensitive to infrared radiation at least 3-microns in wavelength may be used to produce a second image signal. Preferably, the first image signal represents sensed electric light sources, and the second image signal represents sensed background such as terrain, runways, structures, and obstacles. A signal processor combines an image signal representing locally maximum values of the first image signal with the second image signal to create a displayed image.

Various methods for regulating and / or for integrating avionic systems with non-avionic or open systems are described. Developments of the invention describe in particular various methods for synchronizing data via a sharing space, methods for modifying the data, human-machine interactions, steps of optimizing calculations and bandwidth, of determining alerts relating to the risks associated with calculation differences, and mechanisms for securing the secured storage space. Software and system aspects are described (EFB and FMS).

A spring-loaded clamp device including a C-shaped frame having first and second substantially opposing arms interconnected by an intermediate shank, the first arm having a substantially hollow carrier sleeve aligned substantially along a clamping direction oriented substantially transverse of the second arm, and the second arm having a thin and flat anvil portion positioned opposite from the carrier sleeve and further comprising an interior clamping surface that is oriented substantially transverse of the clamping direction. A clamping rod is carried in the hollow of the sleeve for longitudinal movement in the clamping direction toward an internal face of the second arm and in an opposite unclamping direction away from the second arm. An expansive biasing member is coupled for expanding the clamping rod for longitudinal movement along the clamping direction.

According to one embodiment, an electronic flight bag mounting system a cockpit mounting member coupled to an electronic flight bag mounting member. The cockpit mounting member is configured to mount to a cockpit of an aircraft, while the electronic flight bag mounting member is configured to be coupled to an electronic flight bag. The electronic flight bag mounting member is movable from a deployed position in which a display of the electronic flight bag faces a cockpit seat configured in the cockpit to a storage position in which the electronic flight bag faces away from the cockpit seat.

A device for mixing at least two separate streams of components which, when mixed, form a combined fluid stream. The device comprises a conduit with at least two separate passageways leading to exit openings at an end face of the conduit. Each passageway communicates with a separate component stream and is arranged to direct the separate component stream in a downstream direction. The exit openings each have a predetermined cross-sectional flow area. A separate channel is located at a downstream end of each passageway exit opening. The channels are arranged to redirect the flow from each passageway to an axial direction. A single mixing chamber communicates with all of the separate channels, the mixing chamber being arranged to receive each of the component streams at an upstream end thereof and to permit a mixing of the component streams. An outlet is arranged downstream of the mixing chamber through which the combined fluid stream is dispensed.

A multifunction avionics server provide for the execution of both certified and uncertified applications in data-serving capacities in which one certified application provides near real-time transmission of flight data recorder type of data. By combining these functions, improved aircraft monitoring is obtained without significant cost or weight penalties.

The present invention relates to a novel design of the front portion of an aircraft cockpit. The invention provides a viewing device which comprises a screen pivotably mounted on a mounting that allows height adjustment. The invention also suggests placing a screen at the top central portion of the instrument panel. Said central screen is movable between an extended position and a retracted position in which said screen does not block the view of the pilots through the cockpit windscreen. A cowl, made at least partially of a taut fabric or the like, is used to cover the viewing screens, except optionally the mobile central screen which can pass through the cowl via an opening provided for said purpose. The invention also suggests arranging an avionics rack in front of the screens of the instrument panel, in which the mounting is advantageously also used to support other devices (rudder control system, writing shelves, etc.).

A method implemented by computer for the management of the flight of an aircraft comprises the steps of receiving flight directives and flight information associated with these directives; determining a flight context of the aircraft; as a function of the context determined, selecting information from among that associated with the formulation of a directive and / or with a current flight directive and / or with a change of a flight directive; sensorially restoring the selected information. Various developments are described, notably links to documentary resources, the determination of anomalies, the use of predefined logic rules and configuration options. System aspects and software aspects are described.

A method and apparatus for operating an aircraft. An aircraft system comprises a housing, a standby aircraft management system, and a backup power system. The standby aircraft management system is associated with the housing and is configured to provide communications, navigation, and control of a number of aircraft systems needed for safe flight and landing of an aircraft in which the standby aircraft management system is located. The backup power system is configured to supply power to the standby aircraft management system when the power is unavailable from the aircraft.

According to one embodiment, an electronic flight bag mounting system a cockpit mounting member coupled to an electronic flight bag mounting member. The cockpit mounting member is configured to mount to a cockpit of an aircraft, while the electronic flight bag mounting member is configured to be coupled to an electronic flight bag. The electronic flight bag mounting member is movable from a deployed position in which a display of the electronic flight bag faces a cockpit seat configured in the cockpit to a storage position in which the electronic flight bag faces away from the cockpit seat.

The invention is a mount for an electronic display device. The mount comprises a mount member that has a top face and a bottom face. Portions of the mount member are configured to engage portions of a mounting surface within the cockpit of an airplane. The mount also comprises a containment member spaced therefrom the mount member. A joint member is disposed in frictional contact with portions of the respective mount member and containment member. A base member, which can be configured for engagement with a portion of the electronic display device, can be connected to the joint member.

A method implemented by a computer for managing meteorological data for managing the flight of an aircraft, comprises the steps of receiving a cartographic background and selections of meteorological products; receiving meteorological data associated with the flight plan of the aircraft, according to a first space scale; determining one or more types of graphic symbols; as a function of a second space scale, determining one or more graphic declinations of the types of graphic symbols, the graphic superimpositions predefined; and displaying the cartographic background and the determined graphic declinations. Developments describe the management of the visual density of the display, the taking into account of the flight context and / or of the physiology of the pilot, the deactivation on request of the adjustments of the display. Software and system aspects (e.g. electronic flight bag, gaze monitoring) are also described.

A micro-computer based aircraft system that creates aural messages based upon system-detected threats (e.g., low oil pressure). The messages are unique to the make and model of aircraft. Speech recognition allows the pilot to request aircraft-specific, customized aurally-delivered checklists and to respond via a challenge and response protocol. This permits a hands-free, timely, complete and prudent response to the threat or hazardous situation, while allowing the pilot the relative freedom to do what is paramount: first, fly the airplane (with minimum distraction).

A system and method for identifying a recommended configuration for operating an aircraft in wind shear conditions. A processor unit receives information associated with an operation to be performed by the aircraft. The processor unit receives an indication that wind shear may be present during the operation. Responsive to receiving the indication that the wind shear may be present during the operation, the processor unit identifies the recommended configuration for the aircraft to perform the operation using the information associated with the operation to be performed by the aircraft and rules for operating the aircraft in the wind shear conditions.

A method for managing avionic data between a flight management system FMS and one or more clients, the FMS comprising resources accessible through avionic services Ci (1,n); the execution of the Ci (1,n) determining an avionic functionality Fj (1,m); each of the Fj (1,m) associated with an intrusiveness parameter Ik and a criticality parameter Ck; the method comprises the steps of receiving a request specifying the call to an Fj (1,m); and determining a predefined execution right for a Ci (1,n), dependent on the predefined intrusiveness and / or criticality parameters associated with the Fj (1,m). Developments describe particularly the comparison of the execution rights, notice of a rejection, various avionic services and functionalities, the management of criticality ranges, consideration of the flight context, etc. Software and system aspects are described (e.g. equipment of EFB type).

A computer implemented method of computing performance for an aircraft, comprises the steps of collecting data from a plurality of data sources comprising data sources of avionics type and external data sources of non-avionics type; processing the data collected in an electronic device of EFB or electronic flight bag type; and undertaking the performance computation. Developments describe the extraction of data from images or audio streams; the manipulation of data of alarm, INOP, aircraft status, air conditioning and anti-ice, runway, ATIS, meteorological and / or NOTAM type; the interfaces with an FPS or flight planning system and / or a CMS or centralized maintenance system. System aspects and software aspects are described.

A mounting bracket for an electronic flight bag (EFB) includes a frame having a track and a mounting assembly that is having a base and a support that is moveably connected to the base and can be selectively fixed in position on the track. The mounting bracket may allow for singlehanded adjustment of the position of the mounting assembly with respect to track at one of at least two discrete locations along the track, or at any desired position along the track. Further, the mounting bracket may provide a single mechanism for both securing the EFB to the mounting assembly and orienting the support with respect to the base.