Honeywell International Inc.

Prashanth Thirumalaivenjamur

Raghu Shamasundar

Umesh Hosamani

Arivazhagan V

Abdur Rab

Mohan Gowda Chandrashekarappa

Kiran Mancheiah Venkataramana

Akshay Sankeshwari

Sujith Kumar

An obstruction detection and warning system includes a plurality of edge light emitters, and a processing system. The edge light emitters are mounted on a structure that has a width and a height. Each edge light emitter is operable to emit a light beam at an angular rate, and that is encoded with data that indicates its position and its height. The processing system receives the light beam emitted from each edge light emitter and decodes the encoded data from the received light beam to determine the width and height of the structure, and to determine a distance from an aircraft to the structure. The processor also compares an active trajectory and current altitude of the aircraft to the width and height of the structure and the distance to the structure and, based on the comparison, generates and supplies situational cues to an operator of the aircraft.

Obstruction detection and warning system and method

An adaptive system in an aircraft for presenting speed and altitude recommendations for supersonic flight on an aircraft display unit is provided. The system is configured to: predict, based on received aircraft sensor inputs from on board aircraft sensors, an optimum speed and altitude profile while flying in a supersonic phase of flight between a plurality of waypoints for the current aircraft model, wind conditions, and mission; and determine using a SONIC boom prediction model whether the optimum speed and altitude profile would cause an acceptable BOOM effect per a predefined BOOM effect threshold limit during flight between the plurality of waypoints, wherein a BOOM effect is a perceived sound level on land due to unrestricted supersonic flight over land, and wherein a BOOM effect threshold limit is an acceptable perceived sound level on land due to supersonic flight over land.

Adaptive system and method for presenting speed and altitude recommendations for supersonic flight

Methods and systems are provided for monitoring conformance of an aircraft to an actual and predicted 4-dimensional (4D) trajectory with respect to a reference business trajectory (RBT). First, a flight plan for the aircraft is acquired from an onboard flight management system (FMS) computer. A predicted flight trajectory is generated based on the latitude, longitude, altitude, speed and time of the flight plan for the aircraft. An onboard trajectory conformance monitor that is independent of the FMS computer, monitors the present flight trajectory of the aircraft and anticipates any actual or future deviations from the RBT. The trajectory conformance monitor will generate an advisory of any actual or anticipated deviations from the RBT.

System and method for monitoring conformance of an aircraft to a reference 4-dimensional trajectory

A method is provided. The method comprises: identifying a vehicle; providing, to a remote processing system, an interval between the vehicle and a preceding vehicle; providing, to the remote processing system, the preceding vehicle identifier; obtaining, on the remote processing system, a location and a direction of the vehicle; obtaining, on the remote processing system, a location and a direction of the preceding vehicle; determining, on the remote processing system, a speed of the vehicle necessary to maintain the interval; and providing, to the vehicle from the remote processing system, the speed of vehicle necessary to maintain the interval.

System and method for virtual flight interval management

Technologically improved Flight Deck Interval Management Paired Approach (FIMPA) system and methods are provided that provide safe speed guidance to a trail aircraft. The FIMPA system comprises a processor operatively coupled to a memory and a database of aircraft-specific parameters. The processor is configured to: receive instantaneous target traffic state data; receive instantaneous state data of a trail aircraft; process the state data, target traffic state data, and aircraft-specific parameters to determine a safe speed zone to perform paired approach, and a recommended speed; render, on a cockpit display, a paired approach bar (PAB) with indicators for (i) a current location of the target traffic, (ii) a current trail aircraft speed, and (iii) the recommended speed; and wherein the indicators are separate and visually distinguishable from each other; determine a wake risk area; and render the wake risk area in a visually distinguishable manner on the PAB.

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Bengaluru, India

Prashanth Thirumalaivenjamur