Abstract: An antenna system. The system includes a feed network with first input/output terminals and second output/input terminals, and antenna elements forming an array. In a first configuration: each of the second plurality of output/input terminals is connected to one of the antenna elements, the array operating according to a different radiation pattern based on which one of the first plurality of input/output terminals carries a signal into the feed network. In a second configuration: a selected antenna element is disconnected from the second plurality of output/input terminals and receives a direct signal, bypassing the feed network, and operates according to its independent radiation pattern. Also, in the second configuration each remaining antenna element is disconnected from the second plurality of output/input terminals and connected directly to a detuning network, causing these antenna elements to have a minimal effect on the independent radiation pattern of the selected antenna element.

Abstract: In one embodiment, a correlator of a global positioning system receiver in a global positioning system receives a sample satellite signal. The correlator includes a signal comparator configured to receive the sample signal, a first normalized estimate signal, and a second normalized estimate signal. The signal comparator generates a first accumulated output and a second accumulated output. The first accumulated output represents the integration of a correlation of the sample signal and the first normalized estimate signal. The second accumulated output represents the integration of a correlation of the sample signal and the second normalized estimate signal. Using time-multiplexing, the high speed of a digital signal processing core is leveraged to perform calculations of the signal comparator and threshold comparator in real time.

Abstract: An aircraft traffic alert system that minimizes false alarms and unnecessary alerts by automatically adjusting the sensitivity of the system based on proximity to an airport. The system also can use information from a flight management system (FMS) or GPS navigation system (GNS) to only adjust the sensitivity near a destination airport and to suppress potential alerts for possible collisions with other aircraft that will be moot based on planned course changes of the subject aircraft. The system also can suppress alerts related to another aircraft when the other aircraft is landing on a parallel runway to the runway on which the subject aircraft is landing. The system may use multiple sensitivity levels based on different airspace classes, each class being associated with a different sensitivity level.

Abstract: In one embodiment, a correlator of a global positioning system receiver in a global positioning system receives a sample satellite signal. The correlator includes a signal comparator configured to receive the sample signal, a first normalized estimate signal, and a second normalized estimate signal. The signal comparator generates a first accumulated output and a second accumulated output. The first accumulated output represents the integration of a correlation of the sample signal and the first normalized estimate signal. The second accumulated output represents the integration of a correlation of the sample signal and the second normalized estimate signal. Using time-multiplexing, the high speed of a digital signal processing core is leveraged to perform calculations of the signal comparator and threshold comparator in real time.

Abstract: An aircraft avionics system and method for automatically determining an aircraft position. The system and method determine distances to UAT ground stations based on timing signals in transmissions from the UAT ground stations and determines one or more possible positions for the aircraft at which the aircraft is at the determined distances from respective UAT ground stations. The system and method may use three or more UAT ground stations to reduce the possible positions for the aircraft to a single possible position. The system and method also may use dead reckoning or VOR or ADF signals to reduce the possible positions for the aircraft to a single possible position. The system and method may also determine the position of an aircraft by determining true bearings to SSR ground stations and determining the possible positions for the aircraft at which the aircraft is at respective bearings to each SSR ground station.

Abstract: An aircraft traffic alert system that minimizes false alarms and unnecessary alerts by automatically adjusting the sensitivity of the system based on proximity to an airport. The system also can use information from a flight management system (FMS) or GPS navigation system (GNS) to only adjust the sensitivity near a destination airport and to suppress potential alerts for possible collisions with other aircraft that will be moot based on planned course changes of the subject aircraft. The system also can suppress alerts related to another aircraft when the other aircraft is landing on a parallel runway to the runway on which the subject aircraft is landing. The system may use multiple sensitivity levels based on different airspace classes, each class being associated with a different sensitivity level.

Abstract: Disclosed is a system and method for diverting from a flight plan without adjusting an autopilot by treating a heading change as the new leg of a flight plan. The present invention allows the pilot of an aircraft to enter a heading to follow into a flight management system, which treats the heading as the current leg of a flight plan otherwise being followed by the flight management system. The present invention graphically displays the heading leg as the predicted track so that the pilot is able to see the airplane's expected path. Such a change allows the autopilot to continue following commands from the flight management system rather than being changed to a mode in which the autopilot follows heading commands directly from the pilot.

Abstract: A lightning detector designed for aircraft carried applications provides for improved lightning discrimination and display. The instrument employs a relatively wide band receiver so as to retain the received waveform or digital replicas thereof. This allows more precise discrimination between desired lightning signals and noise. Signals are processed to provide for effective display of the available information. The display modes that are enabled by the signals include flash and cell mode as well as a combined flash and cell mode. The cell mode provides for generating and displaying a cumulative weight of lightning activity, giving each strike a regional effect as opposed to illustrating it as a point. Color is used to improve the user's grasp of the displayed information; the color illustrating increased intensity from the blue-green to the yellow-red. Flash mode shows locations of the different flashes within the range scale; this mode too may use color for a similar effect.

Abstract: Disclosed is a system and method for diverting from a flight plan without adjusting an autopilot by treating a heading change as the new leg of a flight plan. The present invention allows the pilot of an aircraft to enter a heading to follow into a flight management system, which treats the heading as the current leg of a flight plan otherwise being followed by the flight management system. The present invention graphically displays the heading leg as the predicted track so that the pilot is able to see the airplane's expected path. Such a change allows the autopilot to continue following commands from the flight management system rather than being changed to a mode in which the autopilot follows heading commands directly from the pilot.

Abstract: An efficient voice activity detection method and system suitable for real-time operation in low SNR (signal-to-noise) environments corrupted by non-Gaussian non-stationary background noise. The method utilizes rank order statistics to generate a binary voice detection output based on deviations between a short-term energy magnitude signal and a short-term noise reference signal. The method does not require voice-free training periods to track the background noise nor is it susceptible to rapid changes in overall noise level making it very robust. In addition a long-term adaptation mechanism is applied to reject harmonic or tonal interference.

Abstract: Disclosed is a system and method for diverting from a flight plan without adjusting an autopilot by treating a heading change as the new leg of a flight plan. The present invention allows the pilot of an aircraft to enter a heading to follow into a flight management system, which treats the heading as the current leg of a flight plan otherwise being followed by the flight management system. The present invention graphically displays the heading leg as the predicted track so that the pilot is able to see the airplane's expected path. Such a change allows the autopilot to continue following commands from the flight management system rather than being changed to a mode in which the autopilot follows heading commands directly from the pilot.

Abstract: A method for creating minimal data representing a source image is presented. The source image is divided into a grid of cells. A color is selected for each cell corner based on sampling an area defined by the cell corner. An indication of the selected color is stored in an array dependent on the co-ordinates of the cell corner in the source image.

Abstract: The present invention provides a method and system for displaying critical navigational data on a primary flight display to a pilot of an aircraft. The method includes providing an image representative of weather information on a primary fight display and superimposing an image representative of a terrain warning indicator over at least part of the image representative of weather information.

Abstract: Entering an identifier to select a navigational waypoint requires “head-down” time, resulting in less time for operating a vehicle. Accordingly, a technique for selecting a navigational waypoint for use is provided. The present invention includes receiving a partially entered identifier identifying, in part, a navigational waypoint for use, searching for the navigational waypoint for use from amongst a plurality of identifiers using the partially entered identifier and a search criterion other than a criterion based on a pre-existing ordering of the plurality of identifiers, and completing the partially entered waypoint identifier based on results from the searching. The completed waypoint identifier forms a user-selectable navigational waypoint for use.

Abstract: Flight display systems are provided that present a pilot with a three dimensional view of an area within a potential flight path of an aircraft. The three dimensional view may include representations of potential obstacles and avoidance zones surrounding the potential obstacles. The view may also include cardinal compass representation aligned with the visual horizon. Aircraft traffic obstacle symbols may be variable based on the type of aircraft represented.

Abstract: Entering an identifier to select a navigational waypoint requires “head-down” time, resulting in less time for operating a vehicle. Accordingly, a technique for selecting a navigational waypoint for use is provided. The present invention includes receiving a partially entered identifier identifying, in part, a navigational waypoint for use, searching for the navigational waypoint for use from amongst a plurality of identifiers using the partially entered identifier and a search criterion other than a criterion based on a pre-existing ordering of the plurality of identifiers, and completing the partially entered waypoint identifier based on results from the searching. The completed waypoint identifier forms a user-selectable navigational waypoint for use.

Abstract: A method for creating minimal data representing a source image is presented. The source image is divided into a grid of cells. A color is selected for each cell corner based on sampling an area defined by the cell corner. An indication of the selected color is stored in an array dependent on the co-ordinates of the cell corner in the source image.

Abstract: A display panel includes a light guide with a housing that has at least one elliptical shaped surface including a first focal point and a second focal point disposed along a major longitudinal axis. The display panel also has at least one light emitting diode being positioned in proximity to the first focal point and a reflector associated with an inner surface of the housing. The display panel further includes an optical film positioned in proximity to an outlet of the housing. The outlet communicates with the display screen. Light that is emitted from the at least one light emitting diode passes through the first focal point and is reflected to the second focal point. The light from the second focal point is then directed through the optical film so that the light is diffused to the display screen.

Abstract: A dynamic miscompare module indicates instrumentation datum reliability by comparing a calculated difference between received instrumentation data and a total of a measured change in the received instrumentation data and a threshold value. The comparison varies dynamically with the measured change in the received instrumentation data. In an event the calculated difference exceeds the total, there is a miscompare condition and the related instrumentation datum is unreliable. The dynamic miscompare module alerts an operator of the condition by indicating a miscompare message indicator. The indicator is formed from a miscompare cue and a miscompare descriptor. The dynamic miscompare module further indicates the condition by interposing a leader between the miscompare message indicator and the unreliable instrumentation datum. Alternatively, the dynamic miscompare module locates the miscompare message indicator proximal to the unreliable instrumentation datum.

Abstract: A critical point on a runway indicates a point at which an aircraft may experience a runway overrun if landing beyond the critical point. A path projection is extended from the aircraft at a descent slope angle to determine whether the aircraft will land beyond the critical point at the current descent slope. Timely alerts may be provided by accounting for the time required to announce a distance value, and the distance traveled during the announcement.