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.

Abstract: An apparatus and method for estimating future pitch and roll angles of an aircraft to compensate for a time delay caused by a flight instrumentation system calculating the aircraft's pitch and roll. The apparatus may output signals to an aircraft autopilot system. The apparatus may comprise various inputs and outputs, at least one compensation module, and at least one addition module. The compensation module may multiply a gain value by the pitch rate of the aircraft and by the roll rate of the aircraft to determine a pitch compensation amount and a roll compensation amount. Then the pitch compensation amount may be added to the pitch of the aircraft, and the roll compensation amount may be added to the roll of the aircraft to solve for a compensated pitch and a compensated roll to send to the autopilot system.

Abstract: An aircraft audio panel includes a plurality of audio inputs each configured for receiving audio communications from an audio source; a plurality of audio outputs each configured for outputting the audio communications to audio equipment in the aircraft; selecting circuitry for selecting the audio communications between the audio inputs and the audio outputs; a single selector for permitting selection of one of the audio inputs or audio outputs for adjustment; and a single audio controller for permitting adjustment of an audio characteristic of the selected audio input or audio output. The audio panel may also include an audio characteristic indicator for indicating an audio characteristic of the selected audio input or audio output. The selecting circuitry may also implement a routing mode in which a user may first initiate the routing mode, then select one of the audio inputs for routing, and then select any one of the audio outputs for receiving audio communications from the selected audio input.

Abstract: An aircraft audio panel includes a plurality of audio inputs each configured for receiving audio communications from an audio source; a plurality of audio outputs each configured for outputting the audio communications to audio equipment in the aircraft; selecting circuitry for selecting the audio communications between the audio inputs and the audio outputs; a single selector for permitting selection of one of the audio inputs or audio outputs for adjustment; and a single audio controller for permitting adjustment of an audio characteristic of the selected audio input or audio output. The audio panel may also include an audio characteristic indicator for indicating an audio characteristic of the selected audio input or audio output. The selecting circuitry may also implement a routing mode in which a user may first initiate the routing mode, then select one of the audio inputs for routing, and then select any one of the audio outputs for receiving audio communications from the selected audio input.

Abstract: An avionics system for a mechanically-controlled aircraft configured to provide envelope protection for deterring a pilot from flying outside of acceptable flight parameter limits for flight parameters such as banking angle, pitch attitude, g loading, proximity to terrain and/or obstacles, angle of attack, and/or airspeed. The avionics system may comprise at least one servo actuator and a computing device. The computing device may engage envelope protection by engaging the at least one servo actuator if the aircraft reaches a maximum or minimum limit for any of the flight parameters, such that the at least one servo actuator provides a force to urge a flight control device in a direction to bring the aircraft back within the acceptable flight parameter limits. The servo actuator may be disengaged when the aircraft flight parameters reach an end value corresponding to the start value that triggered envelope protection to engage.

Abstract: An assisted flight computer program and method which assist a non-pilot or partially incapacitated pilot to gain control of an aircraft, summon help, and then land the aircraft under the guidance of a tower controller. The assisted flight computer program is integrated into an avionics system and provides a guided, menu-driven user interface that is simple enough for non-pilots and partially incapacitated pilots to understand and follow in distress situations.

Abstract: A planetary drive servo actuator comprises a drive assembly operable to turn an output shaft. The drive assembly includes an outer cylinder configured to rotate within the housing and an inner cylinder configured to rotate within the outer cylinder. A clutch is operable to prevent the outer cylinder from rotating within the housing and to allow the inner cylinder to be rotated within the outer cylinder to turn the output shaft.

Abstract: Techniques are described that allow information to be acquired by an ADS-B system of an aircraft without the installation of ADS-B dedicated flight crew controls or wired data interfaces in the aircraft. In one or more implementations, a receiver is associated with the ADS-B system in the aircraft. The receiver is configured to receive reply transmissions from a transponder of the aircraft, such as a Mode A/C or Mode S radar, or the like. A transmitter may also be associated with the ADS-B system to transmit an interrogation to the transponder of the aircraft that is configured to cause the transponder of the aircraft to transmit the reply transmission. Information used by the ADS-B system is extracted from the received reply transmissions and furnished to the ADS-B transceiver for broadcast over the ADS-B data link.