System and methods enabling aircraft energy dissipation for rapid decision making

Patent metadata

Field	Value
Publication number	US-11790795-B2
Application number	US-202016890614-A
Country	US
Kind code	B2
Filing date	Jun 2, 2020
Priority date	Apr 13, 2020
Publication date	Oct 17, 2023
Grant date	Oct 17, 2023

Abstract

A method in an aircraft for energy reduction is disclosed. The method includes: determining a starting point location, altitude and airspeed for a stable approach for landing at a diversion airport; and determining a vertical strategy for achieving the starting point altitude and airspeed by identifying a region of opportunity for adjusting the speed and altitude and identifying a plurality of energy reduction strategies for achieving the starting point altitude and airspeed while in the region of opportunity based on a speed mode during the stable approach. The method further comprises causing a graphic display to be displayed that lists for selection each of the plurality of identified strategies, detailed maneuver information for strategy implementation, and costs for implementing each identified strategy; and causing to be displayed, responsive to flight crew selection, a lateral view and vertical view of a proposed trajectory based on a selected identified strategy.

First claim

The invention claimed is:

1. A processor-implemented energy reduction system for generating a graphic display window for displaying a plurality of alternative energy reduction strategies on a display device on-board an aircraft, the energy reduction system comprising a controller comprising one or more processors configured by programming instructions on non-transitory computer readable media, the controller configured to:
determine a starting point location, altitude and airspeed for a stable approach for landing at a diversion location;
determine a lateral and vertical strategy for reaching the starting point location and achieving the starting point altitude and airspeed, wherein to determine the vertical strategy the controller is further configured to:
identify a region of opportunity for adjusting the speed and altitude of the aircraft to achieve the starting point altitude and airspeed, wherein the region of opportunity is a region between the current aircraft location and the starting point location for the stable approach; and
identify a plurality of energy reduction strategies for achieving the starting point altitude and airspeed while in the region of opportunity based on a speed mode for use by the aircraft during the stable approach;

generate, for display on the graphic display device, a first graphic display window having a plurality of columns and rows, the first graphic display window listing in separate rows in a first column an identifier for the plurality of identified strategies, detailed maneuver information for each of the plurality of identified strategies in separate rows in a second column wherein the detailed maneuver information includes a plurality of maneuvers to be performed and an order in which to perform the maneuvers to achieve the starting point altitude and airspeed while in the region of opportunity, and costs for implementing each of the plurality of identified strategies in separate rows in a third column including fuel consumption and time, wherein each row contains the identifier for an identified strategy in the first column, the detailed maneuver information for the identified strategy in the second column, and the cost for implementing the identified strategy in the third column, wherein the first graphic display page further includes an energy reduction strategy selection graphical element corresponding to each identified strategy;
display the first graphic display window on the graphic display device;
receive selection of an identified strategy of the plurality of identified strategies via actuation of an energy reduction strategy selection graphical element corresponding to a selected strategy;
generate, for display on the graphic display device responsive to flight crew selection of an identified strategy, a second graphic display window having a first window pane for displaying a lateral view of a proposed trajectory that graphically illustrates the plurality of maneuvers and the order in which to perform the maneuvers for the selected identified strategy on a proposed lateral path and a second window pane for displaying a vertical view of the proposed trajectory that graphically illustrates the plurality of maneuvers and the order in which to perform the maneuvers for the selected identified strategy on a proposed vertical path to a runway at the diversion location; and
display the second graphic display window on the graphic display device.

2. The energy reduction system of claim 1 , wherein the stable approach comprises a DEST-APPR-STAR (destination, approach, standard terminal arrival route).

3. The energy reduction system of claim 1 , wherein to identify a plurality of energy reduction strategies the controller is configured to:
calculate whether the starting point speed and starting point altitude can be achieved in the region of opportunity using each of a plurality of energy reduction strategies and calculate detailed maneuver information associated with each strategy that allows the starting point speed and starting point altitude to be achieved in the region of opportunity, wherein the plurality of energy reduction strategies include a level deceleration strategy, a direct descent strategy, a spiral with one circuit strategy, a spiral with a plurality of circuits strategy, and a decelerate and spiral descent strategy; and
identify each strategy from the plurality of energy reduction strategies and the detailed maneuver information associated with each identified strategy for which the starting point speed and starting point altitude can be achieved in the region of opportunity.

4. The energy reduction system of claim 1 , wherein the detailed maneuver information comprises a specific energy reduction maneuver, a speed mode, a speed, and an amount of opportunity region used for the strategy.

5. The energy reduction system of claim 1 , wherein the speed mode is one of:
best gliding speed, max sink rate speed, max angle speed, pilot entered speed, max flyable speed, and optimum speed.

6. The energy reduction system of claim 1 , wherein the controller is further configured to:
receive flight crew selection of one of the plurality of identified strategies for implementation; and
modify a flight plan with flight plan modifications to implement the strategy selected for implementation.

7. The energy reduction system of claim 6 , wherein the energy reduction system is implemented by a personal electronic device, electronic flight bag, tablet computer, or other computing device external to an aircraft flight management system and the controller is configured to send the flight plan modifications to the aircraft flight management system for implementation.

8. The energy reduction system of claim 6 , wherein the energy reduction system is implemented by an aircraft flight management system and the controller is configured to modify a flight plan in the aircraft flight management system with the flight plan modifications for implementation.

9. A processor-implemented method in an aircraft for generating a graphic display window for displaying a plurality of alternative energy reduction strategies on a display device, the method comprising:
determining a starting point location, altitude and airspeed for a stable approach for landing at a diversion location;
determining a lateral and vertical strategy for reaching the starting point location and achieving the starting point altitude and airspeed, the determining the vertical strategy comprising:
identifying a region of opportunity for adjusting the speed and altitude of the aircraft to achieve the starting point altitude and airspeed, wherein the region of opportunity is a region between the current aircraft location and the starting point location for the stable approach; and
identifying a plurality of energy reduction strategies for achieving the starting point altitude and airspeed while in the region of opportunity based on a speed mode for use by the aircraft during the stable approach;

generating for displaying on the graphic display device, a first graphic display window having a plurality of columns and rows, the first graphic display window listing in separate rows in a first column an identifier for the plurality of identified strategies, detailed maneuver information for each of the plurality of identified strategies in separate rows in a second column wherein the detailed maneuver information includes a plurality of maneuvers to be performed and an order in which to perform the maneuvers to achieve the starting point altitude and airspeed while in the region of opportunity, and costs for implementing each of the plurality of identified strategies in separate rows in a third column including fuel consumption and time, wher

Assignees

• Honeywell Int Inc

Inventors

• Chaubey Rajesh
• Mohan Rajeev
• Lewis Daniel E

Classifications

• G08G5/58

  for emergency situations, e.g. hijacking or bird strikes · CPC title

• G08G5/55

  for a single aircraft · CPC title

• G08G5/21

  located onboard the aircraft · CPC title

• G08G5/54 Primary

  for approach or landing · CPC title

• G08G5/025 Primary

  Physics · mapped topic