Honeywell International Inc.

Ruy C Brandao

James Burton Jones

Ruy L Brandao

Eduard Shestak

Christine Marie Haissig

Guoqing Wang

Eric A Euteneuer

Rong Zhang

Zhong Hai Chen

Paul Ferguson

John R Weed

Kevin J Conner

Mark C Virtue

Larry D King

Pal Meiyappan

Rand Ringwald

Yang Liu

Lei Wang

Charles D Bateman

Willard R True

Jing Zheng

Jon Riley

Michael L Olive

Dongsong Zeng

Kevin J Connor

Thomas W Hastings

Xiaoqiang Chen

Larry King

Guo Qing Wang

David C Oey

Kevin S Wilson

Robert A Champion

Dang Pham

LuAn Vanness

Vernon J Van Steenkist

Rosa Maria Nicole Weber

Steve Pratt

Ian Dougherty

Ray Zhang

Yingang Yu

Amy K Supple

Guoquing Wang

Zhong Chen

Charles Donald Bateman

David Oey

Ruy Lopes Brandao

Rand E Ringwald

Dang Di Pham

Christine M Haissig

Determine a GNSS based position malfunction and further estimate an own-ship position when determining that the GNSS position may be inaccurate. The system of this disclosure may use information either from any one or more of internal navigation systems and external information sources to determine whether a GNSS based position for the own-ship may be inaccurate and to provide a pseudo position for the own-ship as an independent position source. The system of this disclosure may determine the existence of the GNSS malfunction based on independent position information.

Spoofing detection based on ADS-B positions from multi-mode S transponder intruders

In some examples, a system includes a transceiver configured to transmit a first surveillance message at a first power level at or below a first maximum power level. The system also includes processing circuitry coupled to the transceiver, the processing circuitry configured to determine that a threshold condition exists. The processing circuitry is also configured to determine a second maximum power level in response to determining that the threshold condition exists, where the second maximum power level is lower than the first maximum power level. The transceiver is configured to transmit, in response to the processing circuitry determining that the threshold condition exists, a second surveillance message at a second power level, wherein the second power level is at or below the second maximum power level.

Interference limiting for surveillance messages

In some examples, a system is configured to mount on a first vehicle. The system include an antenna configured to transmit a first surveillance message by forming an omni-directional beam. The antenna is also configured to receive a second surveillance message from a second vehicle during a first time period. The antenna is further configured to receive a third surveillance message from a third vehicle during a second time period, where the first and second time periods at least partially overlap in time. The system also includes processing circuitry configured to demodulate the second surveillance message by forming a first beam and demodulate the third surveillance message by forming a second beam. The second beam is different than the first beam, and the first beam is simultaneous with the second beam.

Transmitting and receiving surveillance messages

Described herein is a calibration circuit for a multiple element antenna with two or more antenna transmit and receive elements. In some examples the multi-element antenna may also include a beamforming network that combine the multiple antenna radiating element inputs and outputs with controlled phase and amplitude relationships such that spatial beams can be formed by varying the phase and amplitudes of two or more signals applied to antenna input ports for the antenna. The calibration circuit of this disclosure may be used to obtain data to determine phase and amplitude offsets induced by the combined transmission elements, and any phase and amplitude offsets induced by the transmitter or receiver circuitry. The determined phase and amplitude offsets may then be removed from received signal measurements and compensated for in transmit signal generation.

Multi-element antenna array with integral comparison circuit for phase and amplitude calibration

A traffic collision avoidance system (TCAS), configured to transmit a wide transmit beam of approximately 180 degrees. The wide transmit beam may be, for example at the interrogation frequency or a transponder response frequency. The TCAS of this disclosure includes a directional antenna system with two signal input ports and two or more antenna elements. In some examples, the direction of the 180 degree beam may be controlled by the phase relationship between the signals input to the two port antenna. In other examples, the direction of the transmit beam from the antenna system is predefined to be in two complementary directions (e.g., forward and aft).

Simplified TCAS surveillance

A system for tracking a vehicle includes a transceiver configured to receive a first signal including first surveillance data from the vehicle at a first time, and receive a second signal from the vehicle at a second time. The system further includes processing circuitry configured to determine a first location and a first course of the vehicle at the first time based on the first surveillance data, and determine a change in power level from the first signal to the second signal. The processing circuitry is further configured to predict a maneuver for the vehicle based on the first location, the first course, and the change in power level from the first signal to the second signal.

Prediction of vehicle maneuvers based on signal characteristics

In one example, a method for generating air traffic alerts includes determining a predicted trajectory for a target air-craft, based at least in part on a comparison of information received on a recent trajectory of the target aircraft with a set of procedural trajectory information. The method further includes determining whether a violation of protected airspace is predicted between the target aircraft and an ownship, based at least in part on the predicted trajectory for the target aircraft and a predicted trajectory for the ownship. The method further includes generating an alert output in response to determining that the violation of protected airspace is predicted.

Air traffic system using procedural trajectory prediction

A system is described that is configured to receive surveillance data from a vehicle, determine a location of the vehicle based at least in part on the received surveillance data, and determine a course of the vehicle based at least in part on the received surveillance data. The system is further configured to predict a future vehicle maneuver for the vehicle based at least in part on the location and the course of the vehicle, and based at least in part on a set of protocol data indicating one or more standard procedures for one or more vehicle maneuvers. The system is further configured to determine, based at least in part on the predicted future vehicle maneuver, a modified protection volume for the vehicle that is modified relative to a baseline protection volume for the vehicle. The system is further configured to generate an output based on the modified protection volume.

Prediction of vehicle maneuvers

This disclosure is directed to systems and methods for generating outputs based on collected aircraft maneuver data. In one example, a system is configured to collect surveillance data from one or more aircraft. The system is further configured to identify, from the collected surveillance data, aircraft maneuver data indicative of maneuvers of the one or more aircraft. The system is further configured to store the aircraft maneuver data in a data store. The system is further configured to perform one or more analyses of the stored aircraft maneuver data in the data store. The system is further configured to generate an output based on the one or more analyses of the stored aircraft maneuver data.

Aircraft maneuver data management system

This disclosure is directed to systems and methods for aircraft collision avoidance with speed-based collision alert time thresholds. In one example, a system is configured to determine predicted trajectories for an own aircraft and a target aircraft. The system is further configured to determine whether a violation of protected airspace is predicted between the own aircraft and the target aircraft. The system is further configured to determine whether a predicted time to closest approach between the own aircraft and the target aircraft is less than an alert threshold time based on a speed of the own aircraft. The system is further configured to generate an alert output, in response to determining that a violation of protected airspace is predicted and that the predicted time to closest approach between the own aircraft and the target aircraft is less than the alert threshold time based on the speed of the own aircraft.

Collision avoidance system for high-performance non-commercial aircraft

In some examples described herein, a runway location is determined based on aircraft state information from at least one aircraft. For example, a processor may determine the coordinates of one or more points of a runway based on aircraft state information generated by one or more aircraft using the runway. In some examples, the processor may aggregate coordinates determined from the aircraft state information provided by a plurality of different aircraft in order to determine the location of the runway. The processor can be located onboard an aircraft providing the state information, onboard a different aircraft, or external to any aircraft.

Runway location determination

Provided are methods and systems for the automatic calculation and presentation of data on a display device alerting a pilot that a change in flight plan is desirable, possible and administratively compliant under air traffic control protocol. The methods and systems may automatically request the flight clearance over a data link or the pilot may override the data link.

Automated decision aid tool for prompting a pilot to request a flight level change

Systems and methods for calculating coherent bearing that allow one to reduce the number of TCAS antenna elements. In one embodiment, the bearing calculation takes into account signal-to-noise ratio (SNR) difference experienced from top and bottom antennas mounted on a vehicle.

TCAS bearing estimation with reduced antenna elements

Systems and methods for improving bearing initialization for a pair of two-element antennas. An exemplary system includes two-element antennas mounted on the bottom and top of an aircraft fuselage, an output device, and a processing device. The processing device receives phase-difference information based on phase of signals received at each element of a two-element antenna, determines if the received phase-difference information is within a predefined low-confidence region, and initializes bearing if the phase-difference information is not within the low-confidence region or the phase-difference information from a predefined number of consecutively received signals meets a predefined consistency requirement.

Systems and methods for improving bearing availability and accuracy

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Redmond, WA, United States of America

Ruy C Brandao