Abstract: An electronic device is described that includes a range indicator for conveying a range of travel until the electronic device ceases operation due to loss of power. In implementations, the electronic device includes a display device, a memory operable to store one or more modules, and at least one processor coupled to the display device and the memory. The processor is operable to execute the one or more modules to cause display of navigation information at the display device. The navigation information includes a map graphic representing an area an aircraft is traversing. The navigation information also includes an end of use situation that represents a range of travel for the aircraft until the electronic device ceases operation due to a loss of power.

Abstract: A controller for an integrated avionics system and a method of operation of the controller is described herein. The controller includes a keyboard and a touch screen. Further, the controller provides hybrid functionality, such that a user can enter inputs (e.g., navigational data) into the controller via a keyboard-initiated input sequence, or via a touch screen-initiated input sequence. This hybrid functionality provides a user interface having the speed advantages associated with keyboard (scratchpad line select) input entry, while also providing the intuitive touch screen interface.

Abstract: An aircraft radio comprises a receiver, an audio output, and a processing element. The receiver is tuned to a first radio frequency which provides a first audio signal and a second radio frequency which provides a second audio signal. The audio output provides an audio signal to a listening device. The processing element is coupled to a memory element and is configured to tune the receiver to the first radio frequency for a first time period, present the first audio signal to the audio output during the first time period, tune the receiver to the second radio frequency for a second time period to detect presence of the second audio signal, and present audio derived from the first audio signal to the audio output during at least a portion of the second time period.

Abstract: An ADS-B system associated with an aircraft is configured to furnish an indication whether the aircraft is within coverage of air traffic information transmitted by an air traffic control ground station. The ADS-B system receives transmissions from an air traffic control ground station that include air traffic information and a client list comprising identification addresses of aircraft included in the air traffic information. The ADS-B system determines whether the aircraft is within a range of a second aircraft and whether the second aircraft is included in the air traffic information by comparing an identification address of the second aircraft with the identification addresses in the client list. The ADS-B system furnishes an indication that the aircraft is within coverage of the air traffic information when the second aircraft is included in the air traffic information and the aircraft is within the range of the second aircraft.

Abstract: Techniques are described that allow a system, such as a portable ADS-B-enabled device, to automatically determine whether the aircraft in which the system is employed is included in air traffic information (e.g., TIS-B air traffic information) broadcast by an air traffic control (ATC) ground station. The system includes a receiver assembly to receive a first transmission from a transponder of the aircraft that includes an identification address (e.g., an ICAO address) that identifies the aircraft. The receiver assembly also receives a second transmission from the ATC ground station that includes air traffic information and a client list including identification addresses of aircraft included in the air traffic information. The identification address of the aircraft is retrieved from the first transmission and used to determine whether the aircraft is included in the air traffic information by comparing the identification address with the identification addresses in the client list.

Abstract: A system and method of providing aerial navigation for an aircraft comprises presenting an enlarged virtual runway for an identified runway on a display, where the virtual area of the virtual runway remains substantially constant as the aircraft approaches the runway.

Abstract: An avionics control and display unit (CDU) in an integrated avionics system includes a display unit having a touch screen configured to detect touch input. The CDU is configured to have a first mode of operation or a second mode of operation. When the first mode of operation is selected, the display unit is configured to display control indicia to facilitate the control of one or more functions associated with the avionics system. When the second mode of operation is selected, the display unit is configured to enable a cursor control area to facilitate manipulation of indicia displayed by a display device such as a primary flight display (PFD) or a multifunction display (MFD), and so forth, via touch input to the touch screen over the cursor control area.

Abstract: A multi-product avionics control and display unit (CDU). In implementations, the CDU may include a display and a processor coupled with the display. The processor is configurable to operate in a first mode to cause the display to present standby primary flight information associated with the aircraft and a second mode to control and display operation of one or more aircraft systems associated with the aircraft.

Abstract: Techniques are described to determine that an electrical short has occurred on a communication channel based on monitoring a power level of the communication channel with respect to a reference power level. In an implementation, the aviation communication apparatus includes a first voltage source that provides a first voltage input to a first communication channel of a stereo jack for a headset, a voltage monitor that monitors a voltage level of the first communication channel with respect to a reference voltage level of the first communication channel and determines that an electrical short has occurred on the first communication channel based on the monitoring. Accordingly, an electrical short indicator may indicate responsive to the voltage monitor determining that the electrical short has occurred.

Abstract: An avionics control and display unit (CDU) in an integrated avionics system includes a display unit having a touch screen configured to detect touch input. The CDU is configured to have a first mode of operation or a second mode of operation. When the first mode of operation is selected, the display unit is configured to display control indicia to facilitate the control of one or more functions associated with the avionics system. When the second mode of operation is selected, the display unit is configured to enable a cursor control area to facilitate manipulation of indicia displayed by a display device such as a primary flight display (PFD) or a multifunction display (MFD), and so forth, via touch input to the touch screen over the cursor control area.

Abstract: Techniques are described to determine that an electrical short has occurred on a communication channel based on monitoring a power level of the communication channel with respect to a reference power level. In an implementation, the aviation communication apparatus includes a first voltage source that provides a first voltage input to a first communication channel of a stereo jack for a headset, a voltage monitor that monitors a voltage level of the first communication channel with respect to a reference voltage level of the first communication channel determines that an electrical short has occurred on the first communication channel based on the monitoring. Accordingly, an electrical short indicator may indicate responsive to the voltage monitor determining that the electrical short has occurred.

Abstract: Touchscreen electronics for detecting touches on a display screen broadly comprises a plurality of transmitters, a plurality of receivers, and a controller. Each transmitter may transmit at least one beam across the display screen, wherein the beam may be switched on and off in a repeated pattern. The receivers may detect the beams from the transmitters, and each receiver may generate an “on” value that corresponds to the beam being switched on and an “off” value that corresponds to the beam being switched off. The controller communicates with the transmitters and the receivers and may be configured to determine that a touch has occurred when the “on” value generated by one of the receivers transitions in a sequence from greater than an upper level to less than a lower level.

Abstract: A touchscreen system for adapting a user interface broadly comprises a controller and a display screen, the display screen comprising a touchscreen. The display screen is operable to present the user interface. The controller may be configured to detect a defect in an area of the touchscreen, determine a location on the display screen related to the defect, and adapting the user interface on the display screen to compensate for the defect.

Abstract: A multi-product avionics control and display unit (CDU). In implementations, the CDU may include a display and a processor coupled with the display. The processor is configurable to operate in a first mode to cause the display to present standby primary flight information associated with the aircraft and a second mode to control and display operation of one or more aircraft systems associated with the aircraft.

Abstract: Touchscreen electronics for detecting debris on a display screen of a touchscreen system and alerting a user to the presence of the debris broadly comprises a plurality of transmitters, a plurality of receivers, and a controller. Each transmitter may transmit at least one beam across the display screen. The receivers may detect the beams from the transmitters, and each receiver may generate a receive signal. The controller communicates with the transmitters and the receivers and may be configured to analyze the receive signals to determine if debris may be present on the display screen. If so, then the controller may generate an alert signal to indicate that the display screen needs to be cleaned or examined.

Abstract: An apparatus having a graphical touch screen for flight planning and navigation of an aircraft by a pilot. The touch screen may be a graphical interface operable to detect the presence and location of a physical object on or in proximity to the touch screen. The touch screen may be used to perform functions previously only accessible by knobs and buttons on avionic navigational and/or flight planning units. The apparatus may comprise the touch screen and a control device configured to receive and interpret signals from the touch screen. The control device may command the touch screen to display a map and to modify a stored route, such as a flight plan, based on pilot selections input via various gestures of the object on or proximate to the touch screen.

Abstract: Touchscreen electronics for detecting touches on a display screen broadly comprises a plurality of transmitters, a plurality of receivers, and a controller. Each transmitter may transmit at least one beam across the display screen, wherein the beam may be switched on and off in a repeated pattern. The receivers may detect the beams from the transmitters, and each receiver may generate an “on” value that corresponds to the beam being switched on and an “off” value that corresponds to the beam being switched off. The controller communicates with the transmitters and the receivers and may be configured to determine that a touch has occurred when the “on” value generated by one of the receivers transitions in a sequence from greater than an upper level to less than a lower level.

Abstract: A system for receiving controller pilot data link communications (CPDLC) in an aircraft comprises a radio for receiving CPDLC messages transmitted by a plurality of remote radio systems; a processing system for determining which of the CPDLC messages are intended for a target remote radio system; and a display for displaying the CPDLC messages intended for the target remote radio system in association with an identifier for the target remote radio system.

Abstract: An optical overlay filters radiation striking the overlays at a non-planar incidence angle while passing and focusing in-plane signals. In embodiments, an optical overlay comprises an inner wall, an outer wall, an upper wall, and a lower wall. The inner wall may be formed to include a planar surface. The outer wall may be spaced apart from the inner wall and may be formed to include a convex surface. The combination of the planar surface of the inner wall and the convex surface of the outer wall may form a plano-convex lens. The upper wall may include a first plurality of ridges that are generally parallel to the inner wall. The lower wall may include a second plurality of ridges that are generally parallel to the inner wall. The combination of the first plurality of ridges and the second plurality of ridges may form an optical filter.

Abstract: A multi-product avionics control and display unit (CDU). In implementations, the CDU may include a display and a processor coupled with the display. The processor is configurable to operate in a first mode to cause the display to present standby primary flight information associated with the aircraft and a second mode to control and display operation of one or more aircraft systems associated with the aircraft.