Abstract: A preexisting FMS system may be upgraded to increase its functionality while still taking advantage of certain components of the legacy system previously provided on the aircraft and replacing other preexisting components with different components for enhancing the functionality of the FMS system. The preexisting IRU, CADC, DME receiver and DFGC in the upgraded FMS system are in communication with the legacy AFMC but, instead of employing the legacy EFIS which existed in the preexisting FMS system, the EFIS is replaced by a data concentrator unit as well as the display control panel and integrated flat panel display, and a GPS receiver. The upgraded FMS system is capable of such increased functionality as increased navigation database storage capacity, RNP, VNAV and RNAV capability utilizing a GPS based navigation solution, and RTA capability, while still enabling the legacy AFMC to exploit its aircraft performance capabilities throughout the flight.

Abstract: A method and system for highlighting a parameter image representative of a flight parameter of an aircraft to a user in a multi-parameter aircraft instrument display, such as a flat panel display. An electronic instrument display is configured to present parameter images, at least one of which includes a first indicator configured to indicate a specific value (e.g., a target value) for a flight parameter and a second indicator configured to indicate an actual flight parameter value that changes according to variations in the flight parameter. A graphics rendering controller is configured to generate the parameter images and to enlarge a portion of the parameter image when the actual flight parameter value is within a predetermined range from the target value.

Abstract: The present invention relates to a system and method for minimizing or preventing runway incursion at airports by utilizing data packets of information transmitted over the voice communication channel used by pilots at the airport. The data packets of information contain the latitudinal and longitudinal position of the aircraft provided by an on board GPS receiver and a unique identifier for the aircraft, such as the tail number, which is then received by other aircraft on the same ground frequency, and the tower, and displayed on a geo-referenced map display of the airport provided to the pilots and the tower ground controller. The information may be updated by polling the various aircraft In this manner, information received from all active aircraft within an airport can be displayed on an electronic map of the airport which can be viewable by the pilots on the ground as well as the ground controller.

Abstract: A method and system for providing an easily recognizable visual feedback to a user in a multi-parameter aircraft instrument display, such as a flat panel display, of manually induced variations in individually selected manually adjustable data associated with a selected one of a plurality of displayable parameters in a simultaneous display of these parameters. The method and system provides visual confirmation of the parameter being manually varied in response to such manual variations by enlarging the display of the selected parameter, such as by zooming out the displayed image of the selected parameter to between two and four times its normal size in response to the manual variation of this parameter, and returns the image size to its original size, such as by zooming in, in response to a cessation in the manual adjustments by the user of the associated dimensional data, such as within a predetermined interval after such cessation, such as two to four seconds thereafter.

Abstract: An improved aircraft instrument flight display system employs primary and secondary video graphics processors for generating graphics video imaging information. Both the primary and secondary video graphics processors have associated potential failure threads and are preferably chosen to have different potential failure .threads so that the same failure problem will not have a tendency to occur in both of the video graphics processors. The primary video graphics processor generates a graphical display of the aircraft flight information for use by the flight crew in operating the aircraft. The system also includes a video switch for switching between the primary and secondary video graphics processors under control of the integrity checking processor based on the integrity of the graphical display provided by the primary video graphics processor.

Abstract: Dynamic monitoring of the amount of fuel remaining in an aircraft fuel tank is effected by delivering a constant volume flow of an inert gas into the fuel through the respective open distal ends of a sensor conduit tube and a reference conduit tube, each of which extends from a proximal end exterior of the tank to its respective distal open end located within the fuel tank. The sensor conduit tube distal end is fixed closely proximate the bottom of the tank, and the reference conduit tube distal end is fixed proximate but at a vertical spacing h from the sensor conduit tube distal end. The pressure at which the gas is delivered into the fuel at the constant volumetric rate through each of the sensor and reference conduit tubes is monitored. The pressure difference between the monitored pressure in the sensor conduit tube and the pressure in the free space in the fuel tank above the surface of the remaining fuel is directly proportional to the weight of the fuel lying above the sensor conduit tube distal end.

Abstract: An aircraft cockpit flight deck data display system for displaying, on a viewable display screen, typically anti-aliased graphical imaging data derived from aircraft sensors, generates or receives graphics processing language (GPL) commands that define the information intended for presentation on the display screen. The GPL commands are input to a video graphics processor that is operable to interpret the received GPL commands and to generate therefrom video imaging data transferable to the display screen to populate the screen with the intended information. The same GPL commands are also input to a comparator processor that is operable to interpret the received GPL commands and to generate therefrom selected “points of light”, comprising a limited subset of the video imaging data generated by the video graphics processor.

Abstract: A backlit flat panel display includes a fluorescent tube positioned for illuminating the display, and a plurality of display illuminating LEDs on the periphery of the display. The fluorescent tube illuminates the display through a first range of brightness above a predetermined transition level and the LEDs illuminate the display through a second range of brightness below the transition level. When the illumination of the display is adjusted through the transition level to account for changes in ambient light, the LEDs and the fluorescent tube are operated together, so that the combined brightness of the illumination provided by the LEDs and the fluorescent tube will provide the desired display brightness; this advantageously compensates for delayed illumination of the fluorescent tube at start up and for persistence in the tube after shutdown.

Abstract: A system and method for facilitating user entry of a manually-adjustable data setting in an aircraft cockpit normally presents an image of the data setting on the display at a predetermined size. When the user commences to manipulate a control for manually adjusting the data setting, the imaged data setting on the display is automatically enlarged to a predeterminately enlarged size to thereby unambiguously direct the user's attention to the imaged data setting to be adjusted. The imaged data setting on the display is returned from its enlarged size to its normal size when user manipulation of the control has ceased, preferably a predetermined time interval after such user manipulation has ceased.

Abstract: A flat panel display system for an aircraft display includes a graphics rendering computer for rendering of anti-aliased graphical imaging data derived from aircraft sensors for full-field imaging on a cockpit display screen. A comparator processor independently generates, from the same sensor data, a selected subset or “points of light” of the display screen image and compares the points of light data to the data generated by the rendering computer for the same display screen pixel locations. The minimized processing requirements and simplified design of the comparator processor enable ready FAA certification of the comparator processor, whereas the extreme complexity and processing operations required of the rendering computer make FAA certification thereof unusually time consuming and expensive.

Abstract: A method and system for providing an easily recognizable visual feedback to a user in a multi-parameter aircraft instrument display, such as a flat panel display, of manually induced variations in individually selected manually adjustable data associated with a selected one of a plurality of displayable parameters in a simultaneous display of these parameters. The method and system provides visual confirmation of the parameter being manually varied in response to such manual variations by enlarging the display of the selected parameter, such as by zooming out the displayed image of the selected parameter to between two and four times its normal size in response to the manual variation of this parameter, and returns the image size to its original size, such as by zooming in, in response to a cessation in the manual adjustments by the user of the associated dimensional data, such as within a predetermined interval after such cessation, such as two to four seconds thereafter.

Abstract: A flat panel display system for an aircraft display includes a graphics rendering computer for rendering of anti-aliased graphical imaging data derived from aircraft sensors for full-field imaging on a cockpit display screen. A comparator processor independently generates, from the same sensor data, a selected subset or “points of light” of the display screen image and compares the points of light data to the data generated by the rendering computer for the same display screen pixel locations. The minimized processing requirements and simplified design of the comparator processor enable ready FAA certification of the comparator processor, whereas the extreme complexity and processing operations required of the rendering computer make FAA certification thereof unusually time consuming and expensive.

Abstract: A thin flat panel display for aircraft cockpits. These displays use a dual CPU/graphics generator system to produce simulated aircraft instrumentation displays which are color coded to indicate when one of the graphic generators has not correctly received data from the aircraft system bus. The displays use standard graphic generators and CPUs, and do not require additional software. The displays also allow the aircraft systems to be continuously tested while the aircraft is on the ground. Moreover, the inventive systems include input touch devices which access external memories to display necessary flight and landing information which allow the cockpit crew to expand in detail the external information for display on the flat panels.

Abstract: A vacuum vane pump for generating a vacuum condition for aircraft instruments includes a rotor having a peripheral surface eccentrically mounted in a housing having a confrontingly opposed inner surface so that the opposed surfaces define a crescent-shaped chamber. The rotor has a plurality of radial slots, each of which receives a vane which is slidably displaced radially outwardly along the slot as the rotor is rotatively driven so that the outer tips of the vanes are pressed in frictional abutment with the inner surface of the housing. Each slot has a radially inward facing shoulder and each vane has a corresponding radially outward facing shoulder for mutual contact engagement when the tip becomes worn to a predetermined degree.

Abstract: An improved flat panel display provides reduced reflection of incident light on the display to improve display visibility. The display includes a transparent top cover panel such as glass which is bonded or laminated to the display polarizer. The outer viewing surface of the top cover panel carries a plurality of integral surface features defined in the surface, which may comprise etched bumps or micro-machined tetrahedron-shaped protuberances that may be truncated, smoothed, and/or variously oriented and sized to further reduce incident light reflectivity. A multi-layer HEA coating on the featured surface defines a graduated transition layer with an index of refraction that gradually, and preferably smoothly, varies from layer to layer of the HEA coating from the index of refraction of the top cover panel to the index of refraction of the ambient air or other material which the outermost viewable surface of the display presents an image to an observer or viewer.

Abstract: A flat panel display system for an aircraft display includes a graphics rendering computer for rendering of anti-aliased graphical imaging data derived from aircraft sensors for full-field imaging on a cockpit display screen. A comparator processor independently generates, from the same sensor data, a selected subset or “points of light” of the display screen image and compares the points of light data to the data generated by the rendering computer for the same display screen pixel locations. The minimized processing requirements and simplified design of the comparator processor enable ready FAA certification of the comparator processor, whereas the extreme complexity and processing operations required of the rendering computer make FAA certification thereof unusually time consuming and expensive.

Abstract: A vacuum vane pump for generating a vacuum condition for aircraft instruments includes a rotor having a peripheral surface eccentrically mounted in a housing having a confrontingly opposed inner surface so that the opposed surfaces define a crescent-shaped chamber. The rotor has a plurality of radial slots, each of which receives a vane which is slidably displaced radially outwardly along the slot as the rotor is rotatively driven so that the outer tips of the vanes are pressed in frictional abutment with the inner surface of the housing. Each slot has a radially inward facing shoulder and each vane has a corresponding radially outward facing shoulder for mutual contact engagement when the tip becomes worn to a predetermined degree.

Abstract: A flat panel display for presenting graphical renderings of aircraft flight, operation and system status data to an aircraft pilot renders the data at various predetermined brightness levels depending on the category of data assigned to that data. Primary data appears on the screen at a full brightness level and secondary data appears on the screen at a brightness level less than the full brightness level. In this manner, a wide variety and range of aircraft flight, operation and system status data can be simultaneously conveyed to the pilot on a single display screen through selective illumination of particular classes or categories of the data on the display at predetermined brightness levels, thereby advantageously directing the pilot's attention specifically to the primary data which is presented at full brightness.

Abstract: A system and method for facilitating user entry of a manually-adjustable data setting in an aircraft cockpit normally presents an image of the data setting on the display at a predetermined size. When the user commences to manipulate a control for manually adjusting the data setting, the imaged data setting on the display is automatically enlarged to a predeterminately enlarged size to thereby unambiguously direct the user's attention to the imaged data setting to be adjusted. The imaged data setting on the display is returned from its enlarged size to its normal size when user manipulation of the control has ceased, preferably a predetermined time interval after such user manipulation has ceased.

Abstract: Dynamic monitoring of the amount of fuel remaining in an aircraft fuel tank is effected by delivering a constant volume flow of an inert gas into the fuel through the respective open distal ends of a sensor conduit tube and a reference conduit tube, each of which extends from a proximal end exterior of the tank to its respective distal open end located within the fuel tank. The sensor conduit tube distal end is fixed closely proximate the bottom of the tank, and the reference conduit tube distal end is fixed proximate but at a vertical spacing h from the sensor conduit tube distal end. The pressure at which the gas is delivered into the fuel at the constant volumetric rate through each of the sensor and reference conduit tubes is monitored. The pressure difference between the monitored pressure in the sensor conduit tube and the pressure in the free space in the fuel tank above the surface of the remaining fuel is directly proportional to the weight of the fuel lying above the sensor conduit tube distal end.