Honeywell International Inc.

Sripathi Ramachandra

Mark Pearson

Richard Snyder

Greg Carlucci

Mohammed Ibrahim Mohideen

Karel Mundel

Shobana Arumugam

PraveenKumar Ayyathurai

Thea Lynn Feyereisen

Balaji Vasan Srinivasan

Dinkar A Mylaraswamy

Kalimulla Khan

Anil Kumar Songa

Patricia May Ververs

Srihari Jayathirtha

Sabu Mathew

Chavdar Kirov

Michael R Jackson

Ruben Carrillo

Ryan Howe-Veenstra

Udipi Ranga Ananthram

Srikanth Desai

Randy Moore

Hyden Lopez

Samrat Kar

Christopher Raj Mariadoss

An aircraft flap malfunction detection and landing assist system and method includes supplying flap status data, from a flap status data source, that indicates at least aircraft flap configuration and operability, supplying aircraft state data, from an aircraft state data source, that indicates at least aircraft weight, aircraft speed, and aircraft position, supplying weather data, from a weather data source, that indicates current weather at a landing runway, processing, in a processing system the flap status data to determine if at least one flap is inoperable and, upon determining that the at least one flap is inoperable, processing the flap status data, the aircraft state data, and the weather data to selectively generate, and command a display device to render, at least one of forward slip landing parameters or side slip landing parameters.

Aircraft flap malfunction detection and landing assist system and method

Methods and systems are provided for providing a runway awareness system for an aircrew of an aircraft. The method comprises receiving a first data stream that provides operational characteristics of a primary aviation parameter on approach to the runway. A second data stream is also received that provides operational characteristics of an alternative aviation parameter on approach to the runway. The first data stream and the second data stream are then displayed in a comparative layout format on a flight display for the aircrew of the aircraft during the approach to the runway.

System and method for providing a runway awareness system for an aircrew of an aircraft

Systems and methods provide dynamically modifiable parameters in required time of arrival (RTA) speed regions of an assigned flight path of an aircraft. The system includes a vertical situation display (VSD) rendering thereon a vertical flight profile of the assigned flight path. A control module is coupled to the display system and configured to: demark the vertical flight profile with a plurality of RTA speed regions related to an initial speed profile; render an RTA speed band graphic having demarked sections vertically representing a speed minimum and speed maximum for an respective RTA speed region, the RTA speed band graphic representing a normalized speed range between zero and a maximum value for each respective RTA speed region. The control module accepts user modifications and updates the RTA speed band graphic and the current speed profile to reflect user input.

Dynamically modifiable parameters in required time of arrival (RTA) regions of an assigned flight path

Methods and systems are provided for presenting an energy state associated with an aircraft with respect to an operating envelope region for a procedure to restart an engine of the aircraft. One method involves providing a graphical user interface display having a first reference axis corresponding to a first energy state parameter and a second reference axis corresponding to a second energy state parameter different from the first energy state parameter, providing a graphical representation of an operating envelope region associated with a procedure for starting an engine of the aircraft with respect to the first and second reference axes, obtaining current values for the first and second energy state parameters for the aircraft, and providing a graphical representation of the aircraft positioned with respect to the first and second reference axes based on the current values for the first and second energy state parameters.

Engine relight visualization methods and systems

Systems and methods of searching stored flight plan information using a custom search query including at least one aircraft parameter condition or environmental parameter condition. The systems and method include receiving, using a user interface module, a custom search query comprising an aircraft parameter condition or an environmental condition; searching, using a processor module, stored flight plan information for instances in the stored flight plan information that satisfy the aircraft parameter condition or environmental condition; and displaying, using a display module, the instances in the stored flight plan information that satisfy the aircraft parameter condition or environmental condition.

Custom search queries for flight data

An aircraft and a method for operating the same may include, but is not limited to, a flight management system, a vertical situation display, and a processor configured to determine a first variable, a second variable and a third variable, determine flight plan data for the first, second and third variables, generate display data for the vertical situation display, the display data including the scale of the first second and third variables and a vector corresponding to the flight plan data of the first variable and second variable scaled to the first scale and the second scale, wherein the scale of the third variable is non-linear and varies based upon the flight plan data corresponding to the third variable relative to the vector, and output the generated display data to the vertical situation display for display on the vertical situation display.

Multi-dimensional uni-vectored flight display for aircraft

A method for providing flight data onboard an aircraft is provided. The method obtains avionics data, by a processor communicatively coupled to a display device onboard the aircraft; presents a graphical user interface (GUI), by the display device, wherein the GUI comprises at least a speed tape graphical element and an altitude tape graphical element; receives user input manipulations via a user interface communicatively coupled to the processor; executes the user input manipulations for the altitude tape graphical element or the speed tape graphical element, to generate a revised altitude tape graphical element or a revised speed tape graphical element; generates a revised GUI comprising the revised altitude tape graphical element or the revised speed tape graphical element; and presents the revised GUI, via the display device.

Systems and methods for providing user-manipulated primary flight display (PFD) data onboard an aircraft

Methods and systems for a flight display system are provided. The method includes: commanding a vertical situation display (VSD) and a lateral navigation display (ND) to render, concurrently, a viewing segment of a flight plan. The method includes receiving a user input selecting a section of the viewing segment, the user input being received on only one of the VSD and the ND. The method continues by commanding, concurrently, the VSD and the ND to visually distinguish the section, and to demark the section on the VSD with starting points and ending points. The method identifies a flight parameter, and for the flight parameter, includes (a) determining which display, among the VSD and the ND, is appropriate for the rendering of flight parameter information; (b) generating flight parameter information based on (a); and (c) overlaying the flight parameter information on the appropriate display.

Multiple flight data reference for a specific selection on a vertical and lateral display

Systems and methods that optimize landing performance are provided. The system determines a number, N, of equipment configurations (a combination of a brake setting and a thrust reverser configuration) supported by the aircraft. The system determines a deceleration airspeed to achieve a target taxi speed and, for each of the N equipment configurations, determines a respective deceleration distance. In various embodiments, the system further updates the deceleration distances by one or more of a brake's condition, aircraft historical data, brake warranty and life cycle data, and environmental conditions. The deceleration distances are used to identify a number P of exit-ways that can be used at the runway. Total costs (including brake usage and fuel cost) for each of the P exit-ways is determined, and the equipment configuration that delivers the lowest total cost delivers the optimize landing performance.

Systems and methods for optimizing landing performance

Improved systems and methods for the evaluation of runway changes that analyze the effect of the runway change on relevant factors, and provide intuitive visual feedback of the analysis, are provided. The provided systems and methods depict the original runway and the new runway, side by side, in a pictorial representation. Additionally, a selectable group of relevant factors for each runway is determined. The pictorial representation is overlaid with one or more symbolic indicators that distinctly demark each of the factors, alphanumeric descriptors may also be displayed alongside the symbolic indicators. The provided systems and methods additionally generate a tabular display of the information and factors. The tabular display provides a side by side comparison of the old runway, the new runway, and the relevant factors.

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Karnataka, India

Sripathi Ramachandra