Abstract: An apparatus for forecasting weather related threats aboard an aircraft includes a computer for sending and receiving meteorological data to and from other aircraft in a self-organizing mesh network of aircraft. The computer isolates meteorological sensor data originating from the other aircraft in a region along the flight path of the aircraft and uses that data to forecast weather related threats along the aircraft's flight path.

Abstract: The present disclosure is directed to a system and method for determining an ownship position of an aircraft. The method includes the steps of receiving data from a plurality of proximate aircraft and examining the data. Next, the method involves selecting a plurality of reference aircraft from the plurality of proximate aircraft, and receiving data from each reference aircraft. The data received from the reference aircraft is then correlated to a common time in order to create a reference frame for calculating the position of the aircraft. The next step of the method is to calculate the ownship position of the aircraft based on the data received from the reference aircraft and the common time. The system includes a receiver, processor, display, and transmitter, which are used to determine the ownship position of an aircraft.

Abstract: The present invention is directed to an avionics system. The avionics system may include a plurality of multi-function antennas. Each multi-function antenna includes a plurality of antenna elements and an antenna electronics system, the antenna electronics system being communicatively coupled with the plurality of antenna elements. The multi-function antennas are configured for being mounted to an exterior surface of a pressure vessel (ex—an exterior surface of an aircraft). The avionics system may further include a plurality of LRUs connected to the antennas via fiber optical cables, the LRUs being located in an interior of the aircraft. The LRUs receive communication control inputs from a communication system and establish settings of the LRUs based upon the received communication control inputs. The multi-function antennas are configured for performing operations (exs.—transmit operations, receive operations) based upon the settings established by the LRUs and based upon the communication control inputs.

Abstract: Aircraft operating environment information is sensed. The aircraft operating environment information is encapsulated in at least one sensor object. The at least one sensor object is transferred to a sensor object processing system. The at least one sensor object is processed.

Abstract: An avionics system including a software defined radio (SDR) is provided. The SDR includes configurable avionics function implementation circuitry configured to implement each of multiple avionics functions. Also included in the SDR is a priority arbitrator. The priority arbitrator is configured to receive priority control parameters and, based on a make-up of the received priority control parameters, responsively direct the configurable avionics function implementation circuitry to implement a particular priority-based subset (less than all) of the multiple avionics functions.

Abstract: The present disclosure is directed to systems and methods for providing attenuation alerts for a radar-based terrain warning. A method for providing radar-based terrain warning attenuation alerts may comprise: (a) receiving a radar return; (b) detecting a region of atmospheric disturbance limiting the range of the radar return; and (c) providing a notification of radar-based terrain awareness warning system attenuation in the region of atmospheric disturbance.

Abstract: The present invention is a high availability digital radio architecture which includes an analog interface subsystem and a baseband digital processing subsystem. The analog interface subsystem includes an antenna switching network and a digital antenna group translator. The translator includes a set of analog and digital building blocks for each communication, navigation and surveillance (CNS) waveform. The set of blocks includes a receive signal processing chain and/or a transmit signal processing chain with digital interfaces to a multi-channel transceiver. The switching network provides connectivity between antennas and the translator. The baseband digital processing system includes a network switch and said multi-channel transceiver. The transceiver includes a digital modem and protocol processing components for implementing behavior of each CNS waveform.

Abstract: A switched beam forming network is disclosed having an antenna array and an integral beam forming network configured to selectively provide directional and omnidirectional antenna radiation patterns. Four 90-degree hybrids are serially interconnected to form a 4×4 hybrid matrix. The hybrid matrix receives and transmits signals through antenna monopoles and is configured to selectively switch between directional and omnidirectional operation. At least four antenna terminals connect the hybrid matrix to the antenna monopoles. Four input/output ports connect the hybrid matrix to a transmit/receive network through connecting lines. A plurality of switches are selectively actuatable to form the beam forming network.

Abstract: The present invention is a combined aircraft TCAS/Transponder with common antenna system and transmitter. Common TCAS/Transponder multi-monopole top and bottom antennas may be connected to a top and bottom antenna modules, the top and bottom antenna modules being electrically coupled to the combined TCAS/Transponder transmitter/receiver block through connection lines.

Abstract: A directional/omnidirectional antenna system is disclosed. A first printed circuit board has capacitive hats disposed thereon. Each capacitive hat is in association with one of an array of folded monopoles. A second printed circuit board has a switched beam forming network formed thereon. The switched beam forming network is configured to provide a predetermined omnidirectional antenna operation at a first switching position, and a predetermined directional antenna operation at a second switching position. Each of a plurality of feeding elements is associated with one of the folded monopoles. Each feeding element is coupled to one of the capacitive hats and to an antenna terminal. Shorting elements of the folded monopoles are coupled to the capacitive hats and to a ground plate of the antenna. A plurality of decoupling elements improve the antenna pattern for directional and omnidirectional modes and provide greater antenna gain.

Abstract: A traffic alert and collision and avoidance system (TCAS) is disclosed. The TCAS comprises a first transponder and a first interrogator associated with a first aircraft. The first transponder sends an interrogation request. The TCAS also comprises a second transponder associated with a second aircraft. The second transponder responds to the interrogation request. The response comprises enhanced surveillance data that was asked for in the request.

Abstract: A surveillance system for an aircraft includes a first antenna comprising a four radiating element antenna. The first antenna is configured for electrical coupling to a first air traffic control transponder and a first traffic alert and collision avoidance system, and a second antenna comprises a single element antenna configured for electrical coupling to a second air traffic control transponder. The surveillance system also comprises a second antenna comprising a single radiating element antenna configured for electrical coupling to a second air traffic control transponder. The surveillance system also comprises a first mounting interface configured for coupling the first antenna to the aircraft. The surveillance system also comprises a second mounting interface configured for coupling a second antenna to the aircraft. The mounting interface of the first antenna has a size and a shape corresponding to a size and shape of the mounting interface of the second antenna.

Abstract: An integrity monitor for TCAS mutual suppression checks the interface circuits and cabling of the suppression system that lies between the TCAS processor and the transponder. The monitor starts by interrogating the transponder while disabling suppression. If no reply is received, the transponder is not functional. If a reply is received, interrogation of the transponder occurs again, however, this time suppression is enabled. If a reply is received, the suppression system has failed and TCAS alarms will be inhibited. If a reply is not received, the suppression system is working.

Abstract: Apparatus for providing pulses at a rate limited by an input analog control signal. The analog control signal is compared to a ramp voltage, and an output pulse is generated when the ramp voltage reaches the control voltage level.

Abstract: A variable phase shifter and comparator useable, for example, in a scalloping suppression system within a V.H.F. Omni Range (VOR) aircraft bearing determining system. The digital phase shifter-comparator network is employed to cause a phase of the reference signal to follow a phase of the variable phase signal. The phase shifter is comprised of two counters and the phase comparator is comprised of a bistable multivibrator. The delayed reference signal is the output of the system, and an analog rate controller is employed to limit the rate at which the reference signal can follow the variable phase signal.

Abstract: A scalloping suppression system and method for use in a V.H.F. Omni Range (VOR) aircraft bearing determining system. The system is arranged to respond to changes in phase of the received radial which are due to position changes of the aircraft but not to respond to the generally more rapid changes in phase which are due to scalloping. A digital phase shifter-comparator network is employed to cause the phase of the reference signal to follow the phase of the variable phase signal. The phase shifter is comprised of two counters and the phase comparator is comprised of a bistable multivibrator. The delayed reference signal is the output of the system and an analog rate controller is employed to limit the rate at which the reference signal can follow the variable phase signal. The limiting is effected in proportion to DME distance which is inputted to the rate controller as an analog voltage.