Honeywell International Inc.

Jim R Rumbo

James Kenneth Haberstock

Sivakumar Kanagarajan

Marko Bacic

Rajesh Chaubey

Glenn A Knight

Kiran Mancheiah Venkataramana

Zdenek Moravek

Dorothee De Villele

Ivan Lacko

Marek Batelka

Michael R Jackson

Zdenek Jancik

Daniel Corbel

Brian E O'Laughlin

Adib Bouanani

Roger D Peckham

Dennis David Loots

Chad E Gaier

Gregory C Carlucci

Michael R Seastrand

Deuk Gi Min

John C Hadley

Gregory S Hill

Ganesh Shabadi

Ryan Glaser

Natasha Proctor

A method for controlling a desired change in course for an aircraft is provided. The method comprises: determining a roll angle for a constant radius curve in a constant roll attitude lateral path segment of a lateral path to achieve the desired change in course; determining, for each of a first plurality of derivative lateral path segments between a first straight lateral path segment of the lateral path and the constant roll attitude lateral path segment and a second plurality of derivative lateral path segments between the constant roll attitude lateral path segment and a second straight lateral path segment of the lateral path, a derivative roll parameter to apply in the lateral path segment, wherein the derivative roll parameter comprises a constant roll acceleration value or a constant roll rate value; and causing the aircraft to sequentially execute a maneuver specified by the roll angle and, derivative roll parameters.

System and method for improved aircraft and UAM control path accuracy including derivative segments control

Provided are enhanced flight guidance systems and methods for an aircraft. The method includes recognizing when the aircraft is in manual operation and an active flight path is different than the planned flight path. An interrupt is received and categorized as one of (i) obstacle, (ii) equipment/fuel, or (iii) pilot health monitor. A managed mode begins, including identifying a rejoining leg of the planned flight path at which to rejoin and a location on the rejoining leg at which to rejoin. A recapture path strategy is selected from (i) lateral, (ii) vertical, and (iii) mixed lateral and vertical. A recapture path to the location on the rejoining leg is computed. The computed recapture path includes speed targets and configuration requirements at dedicated points along the recapture path. Aircraft state data along the recapture path is predicted and guidance controls for the aircraft along the recapture path are generated.

Systems and methods for generating a recapture path for an aircraft

A computer-implemented method in an aircraft for identifying a flight plan modification that has a favorable impact from jet streams is provided. The method includes: retrieving an entered flight plan for the aircraft; retrieving available jet stream data identifying one or more jet streams in proximity to a proposed flight path from the entered flight plan, wherein the jet stream data includes jet stream vector, altitude, width, and thickness data; projecting the jet stream data around the proposed flight path as points of interest around the proposed flight path; identifying a flight plan modification that has the most favorable impact from jet streams at the points of interest; and displaying the identified flight plan modification on a user interface.

System and method to compute optimum cruise level by considering atmospheric conditions

A system and method are provided for controlling turbine blade tip-to-static structure clearance in a gas turbine engine installed on an aircraft. Mode control data are processed to determine that a fuel-saving mode is enabled, and aircraft data are processed to determine that the aircraft gas turbine engine is generating a substantially constant thrust. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is minimized upon determining that both the aircraft gas turbine engine is generating a substantially constant thrust and the fuel-saving mode is enabled. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is then selectively increased to a predetermined clearance, and a change in aircraft gas turbine engine thrust is prevented until the predetermined clearance is achieved.

System and method for turbine blade clearance control

A system is provided for controlling the speed of an aircraft with a speed brake during flight. The system includes a guidance system configured to determine a target speed for the aircraft; a speed brake control system coupled to the guidance system and configured to compare the target speed to a current speed to generate speed brake guidance; and a display unit coupled to the speed brake control system and configured to display a visual representation of the speed brake guidance to a pilot of the aircraft.

Systems and methods for controlling the speed of an aircraft

A system and method are provided for generating a flight plan between an initial position and a destination. An input device is configured to receive inputs related to the destination; a memory configured to store data related to the destination; and a processor is configured to retrieve data from the memory and to generate the flight plan from the initial position to the destination. The flight plan includes a plurality of legs and an initial plurality of transitions between the legs. The processor is further configured to determine whether each of the initial plurality of transitions between the legs are flyable and to provide a flyable transition between the legs if the transition is not flyable.

System and method for generating flyable paths for an aircraft

The present invention provides a set of holding pattern entry algorithms used to define flight segments for entry into holding patterns. These geometries preferably describe the specific location and distance of various segments used in the holding pattern and holding pattern racetrack, with each segment defined as a curved or straight segment between endpoints. The algorithms also preferably include criteria used to determine entry extension, maximum initial turn angle, and minimum distance between a hold fix and an entry turn point. The geometry also preferably extends entry distance to avoid excessive iterative calculations. The algorithms are preferably utilized by a flight management system and method that determines segment sequencing during entry into holding patterns and the holding patterns themselves. The flight management system and method monitors the aircraft's progress along the active segment of the flight plan to determine what is the appropriate next segment in the algorithm and when to switch control from the active segment to the next segment.

Flight management system using holding pattern entry algorithms

The instant invention provides a system and method for controlling the flight of an aircraft to meet an RTA. The system comprises a speed profile generator that communicates with a trajectory generator to produce a speed profile signal that enables the aircraft to reach a waypoint substantially at a predetermined time. In the system of the instant invention, the speed profile generator receives a nominal speed command signal, a time error signal and a sensitivity signal. Based on these inputs, the speed profile generator produces a speed profile signal. The trajectory generator receives the speed profile signal and a required time of arrival signal. Based on these signals, the trajectory generator produces a time error signal and a sensitivity signal. This sensitivity signal represents the sensitivity of the time error signal to changes in the speed profile signal.

Aircraft control system for reaching a waypoint at a required time of arrival

Growing community of inventors

Glendale, AZ, United States of America

Jim R Rumbo