75 results about "Cockpit display system" patented technology

Methods, systems, and apparatuses for the use of a wireless portable avionics device in conjunction with on-board flight systems and/or off-board service providers. The device may be used by aircraft personnel such as pilots and may act as a command/data entry and/or display tool to augment cockpit display systems. The device can receive flight data (e.g., a flight plan) from an off-board provider and automatically transfer it, as well as any previously prepared commands or data, to a flight management system and/or cockpit display systems. Commands and/or data (including pre-existing ones and ones entered in real-time) can be wirelessly transferred to the on-board flight systems which are not in direct physical contact with the device. Thus, the device can be easily manipulated during turbulence or under poor readability conditions. The device can be used to manipulate items shown on cockpit display systems in a timely and accurate manner.

Systems and apparatus are provided for head-mountable cockpit displays for providing information related to an aircraft system to a user. A cockpit display system comprises an eyeglass frame adapted for wearing on the head of the user. The eyeglass frame has a perimeter defining a field of view. A display element is mechanically coupled to the eyeglass frame and aligned with a bottom portion of the field of view. Display electronics are coupled to the display element, and an avionics system is coupled to the display electronics. The display electronics are configured to render an image of a cockpit instrument panel associated with the avionics system on the display element.

A motor vehicle cockpit display system includes display units for displaying information arranged at different positions in a passenger compartment of the motor vehicle. A control arrangement controls the content of the information which is respectively displayed on the display units. A recording device senses in a contactless fashion an assignment of a user's limb to a first display unit and a gesture-dependent change in the assignment to a further display unit. Information relating to the change in the assignment is fed to the control arrangement, and the further display unit can be actuated to display the information of the first display unit by the control arrangement in accordance with the change in the assignment.

Cockpit display systems and methods for generating navigation displays including landing diversion symbology are provided. In one embodiment, the cockpit display system includes a cockpit monitor and a controller coupled to the cockpit monitor. The controller is configured to assess the current feasibility of landing at one or more diversion airports in a range of an aircraft on which the cockpit display system is deployed. The controller is further configured to assign each diversion airport to one of a plurality of predetermined landing feasibility categories, and generate a horizontal navigation display on the cockpit monitor including symbology representative of the feasibility category assigned to one or more of the diversion airports.

A client-server type computer system for graphical applications is provided, that is to say, for displaying data in the form of software units called “widgets” on display screens called “display units”, said system being intended to control the operation of a machine, the machine including at least one human-machine interface allowing interaction with the widgets, said system managing critical data or functions. The computer system includes a securing engine controlling the integrity of the display of the critical widgets, the sending of commands which is performed by means of the human-machine interface, the input and display of the critical data. The main provisions of this securing engine are the use of computer “signatures”, the provision of “feedback” circuits and the use of guard mechanisms or dedicated confirmation dialogue boxes. Preferably, the machine is an aircraft, the computer system is the avionics on board said aircraft and the display screens are the cockpit display systems.

The invention discloses a cockpit display control system software architecture management platform including a modeling toolset. The modeling toolset includes an application instance architecture definition tool, an AADL/MARTE/SYSML model transformation tool, a non-functional requirement analysis tool, a display and control design pattern customization tool and a code integration tool. The invention provides a software architecture management platform with a friendly man-machine interface and easy to set up and maintain the software framework for the development of the cockpit display system software architecture of the modern large and medium-sized civil aircraft.

A present novel and non-trivial system, device, and method for generating object symbology are disclosed. A system may be comprised one or more aircraft systems and a cockpit display system comprised of a system configuration file, a plurality of definition files, and a windows generator (“WG”). The WG may be configured to perform initialization and run-time operations. The initialization operation may be comprised of retrieving a system configuration file; retrieving a first definition file comprised of a first layer; and retrieving one or more second definition files comprised of one or more second layers. The run-time operation may be comprised of receiving a first-layer widget data set; receiving one or more second-layer widget data sets; determining the screen position of each object located within a view frustum; and generating a pixel data set in response to the determination.

Avionics display system is provided for deployment onboard an aircraft and includes an air traffic data source that provides the avionics display system with data indicative of at least position and velocity of a neighboring aircraft. The system comprises a cockpit display system, and a monitor included within the cockpit display system. The cockpit display system receives and displays position and velocity data pertaining to the neighboring aircraft on the cockpit monitor as a position symbol and a velocity vector graphic. A processor operatively coupled to the monitor is configured to generate an air traffic display on the monitor including symbology indicative of (1) the current position of the neighboring aircraft (2) a velocity of the neighboring aircraft, and (3) the rate-of-change of the velocity of the neighboring aircraft.

Cockpit display systems and methods are provided for generating cockpit displays including symbology useful in assessing whether enhanced flight visibility requirements are satisfied during approach and landing. In one embodiment, the cockpit display system includes an Enhanced Flight Vision System (EFVS) sensor configured to monitor a region forward of the aircraft for runway reference features, a cockpit display device on which an EFVS image is generated utilizing EFVS sensor data, and a controller coupled to the EFVS sensor and to the display device. The controller determines an enhanced flight visibility requirement for a runway approached by the aircraft, and then visually indicates on the EFVS image whether enhanced flight visibility requirement is currently satisfied by, for example. generating an enhanced flight visibility indicator (EFVI) graphic on the EFVS image visually identifying a ground location beyond which the appearance of a runway reference feature satisfies the enhanced flight visibility requirement.

Cockpit display systems and methods are provided for generating energy management symbology on cockpit displays, which aid pilot decision-making when evaluating and executing direct approaches. In an embodiment, the cockpit display system includes a cockpit display device on which a first cockpit display, such as a vertical situation display or a horizontal navigation display, is generated. A controller is operably coupled to the cockpit display device and configured to: (i) identify a direct approach (DA) path to a configuration point located over a destination airfield; (ii) calculate a first DA energy estimate for the aircraft to fly the DA path under engine idle conditions and arrive at the configuration point with an airspeed less than a configuration airspeed; and (iii) generate symbology on the first cockpit display indicative of the first DA energy estimate.

Systems and methods for incorporating virtual network computing (“VNC”) into a cockpit display system (“CDS”) and controlling an aircraft system and a remote system simultaneously with a VNC-incorporated CDS are disclosed. A system for incorporating VNC into the CDS is comprised of a VNC server of a remote system, at least one first user application (“UA”), a second UA, a pilot input device, and a CDS comprised of, in part, a processing module (“PM”) configured with a method employing an aviation-industry standard protocol (e.g., ARINC 661) and a VNC protocol. A system for controlling the remote system aircraft system with a VNC-incorporated CDS is comprised with a VNC server of the aircraft system and/or the non-aircraft system, a UA, a pilot input device, a display surface format, and a CDS comprised of, in part, a PM configured with a method employing an aviation-industry standard protocol and a VNC protocol.

Systems and methods for selecting a runway record for a target runway are provided. The system includes: a first database having a first runway record with a first runway threshold; a second database having a second runway record with a second runway threshold; a transceiver for receiving an ILS signal; and a computer system. The computer system is configured to determine when the ILS signal is substantially zero. When the ILS signal is substantially zero, the computer system is configured to receive, from one or more databases, a plurality of runway records including corresponding runway thresholds; and select a most accurate runway record from the plurality of runway records based, at least in part, on which of the corresponding runway thresholds deviates least from the aiming point. In various embodiments, the most accurate runway record is then utilized for rendering images in a cockpit display system.

Cockpit display systems and methods are provided for performing Glide Slope (G/S) validation processes during Instrument Landing System (ILS) approaches. In one embodiment, the cockpit display system utilizes validated G/S signals to selectively correct the viewpoint of a Synthetic Vision System (SVS) scene generated on a Synthetic Vision Primary Flight Display (SV-FPD). In such an embodiment, the cockpit display system may include an ILS receiver, a cockpit display device on which the SV-PFD is generated, and a controller operably coupled to the cockpit display device and to the ILS receiver. During an ILS approach, the controller selectively performs a G/S validation algorithm to determine the validity of the G/S signals received during the ILS approach. If determining that the G/S signals are valid, the controller then repeatedly updates the SVS viewpoint during the ILS approach based, at least in part, on the validated G/S signals.

The invention discloses an image-recognition-based automatic test method for a cockpit display system. Analyses are carried out on a non-ARINC661 standard display picture model and an ARINC661 standard display picture model to obtain minimum identifiable units of display picture sand attributes of all units; and with the image recognition technology, all minimum identifiable units are identified and tested. According to the invention, the automatic test of the cockpit display system can be realized based on construction of the minimum identifiable units; the traditional status of relying on the manual test is changed; and thus the efficiency and accuracy of the cockpit display system test are improved effectively. The image-recognition-based automatic test method and system have the greatpromotion and application values.

The invention discloses a plane a plane cockpit display system server software testing method conforming to the ARINC661 standard. The method includes the steps of firstly, extracting testing basis; secondly, determining the testing manner; thirdly receiving the DF file structure designed by a user if the testing manner is determined as manual testing; performing automatic testing if the testing manner is determined as automatic testing; fourthly, generating testing input and testing expected result. Compared with the prior art, the testing method is capable of conveniently and fast generating testing input and testing expected result, software testing efficiency and accuracy are increased, testing cycle is shortened, and testing expense is lowered.

Systems and methods are disclosed for periodic real-time reporting of in-flight turbulence experienced by aircraft using the existing ADS-B messaging system. The invention includes both broadcast to and reception from other aircraft and ground stations using the ADS-B system. Systems and methods for displaying the received turbulence reports on a cockpit display system are also disclosed. The disclosed systems and methods accomplish the objectives of the invention on a non-interference basis with existing ADS-B system functionality by utilizing currently reserved message types and/or unused data fields for the turbulence reporting. The invention is applicable to both 1090ES and 978 UATADS-B systems.

A cabin display system supporting multi-user synchronous operation is disclosed, including a display unit, the display unit may be divided into one or more non-overlapping display windows, each display window consists of one or more different layers, each layer consists of a form part, the cockpit display system supporting multi-user synchronous operation also includes a display profile loading module, definition file load module, a data reception processing module of an external device, user application command receiving and processing module, the logic processing module and the graphics drawing module, the system can manage the display content according to the window through the modules, realize the function support of the cabin display system to the multi-user synchronous operation, andmake the man-machine interaction between the cabin display system and the crew more convenient and efficient. The user application command receiving and processing module, the logic processing moduleand the graphics drawing module can manage the display content according to the window, and realize the function support of the cabin display system to the multi-user synchronous operation.