Cockpit display systems and methods for generating cockpit displays including direct approach energy management symbology

Patent metadata

Field	Value
Publication number	US-10388171-B2
Application number	US-201715433272-A
Country	US
Kind code	B2
Filing date	Feb 15, 2017
Priority date	Feb 15, 2017
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

Cockpit display systems and methods are provided for generating energy management symbology on cockpit displays, which aid pilot decision-making when evaluating and executing direct approaches. In an embodiment, the cockpit display system includes a cockpit display device on which a first cockpit display, such as a vertical situation display or a horizontal navigation display, is generated. A controller is operably coupled to the cockpit display device and configured to: (i) identify a direct approach (DA) path to a configuration point located over a destination airfield; (ii) calculate a first DA energy estimate for the aircraft to fly the DA path under engine idle conditions and arrive at the configuration point with an airspeed less than a configuration airspeed; and (iii) generate symbology on the first cockpit display indicative of the first DA energy estimate.

First claim

What is claimed is:

1. A cockpit display system onboard an aircraft, the cockpit display system comprising:
a cockpit display device on which a first cockpit display is generated; and
a controller operably coupled to the cockpit display device and configured to:
identify a direct approach (DA) path to a configuration point located over a destination airfield;
calculate a first DA energy estimate for the aircraft to fly the DA path under engine idle conditions and arrive at the configuration point with an airspeed less than a configuration airspeed; and
generate symbology on the first cockpit display indicative of the first DA energy estimate,

wherein the first cockpit display comprises a Vertical Situation Display (VSD) including an aircraft icon, and wherein the controller is configured to adjust a position of the symbology on the VSD relative to the aircraft icon as the first DA energy estimate varies with respect to a current energy content of the aircraft, and the controller is configured to adjust a vertical position of the symbology on the VSD relative to the aircraft icon such that the symbology is: (i) located vertically above the aircraft icon when the current energy content of the aircraft is less than the first DA energy estimate, and (ii) located vertically below the aircraft icon when the energy content of the aircraft is greater than the first DA energy estimate.

2. The cockpit display system of claim 1 wherein the controller is configured to repeatedly perform the steps of identifying, calculating, and generating, while the aircraft flies a multi-leg approach route terminating at the destination airfield.

3. The cockpit display system of claim 2 wherein the first cockpit display comprises a horizontal navigation display, and wherein the controller is configured to generate the horizontal navigation display to include:
a multi-leg approach route graphic representative of the multi-leg approach route; and
a DA path graphic representative of the DA path.

4. The cockpit display system of claim 3 wherein the controller is configured to vary the appearance of the DA path graphic, as generated on the horizontal navigation display, based upon a disparity between the first DA energy estimate and a current energy content of the aircraft.

5. The cockpit display system of claim 1 wherein the first cockpit display comprises a Vertical Situation Display (VSD), wherein the controller is further configured to generate a horizontal navigation display concurrently with the VSD, and wherein the controller is configured to generate the horizontal navigation display to include a DA path graphic representative of the DA path.

6. The cockpit display system of claim 1 wherein the controller is configured to determine the configuration point based, at least in part, on an intersection point between the DA path and a configuration ring centered about a touchdown reference point.

7. The cockpit display system of claim 6 wherein the controller is configured to locate the touchdown reference point at:
a default location corresponding to the destination airfield when a destination runway is unknown to the cockpit display system; and
at a touchdown zone of the destination runway when the destination runway is known to the cockpit display system.

8. The cockpit display system of claim 7 wherein the first cockpit display comprises a horizontal navigation display, the controller configured to generate the horizontal navigation display to include:
a configuration ring graphic representative of the configuration ring; and
a glide slope intercept ring graphic substantially concentric with the configuration ring graphic and the touchdown reference point.

9. The cockpit display system of claim 1 wherein the controller is configured to generate the symbology to comprise at least one marker having a position representative of an instantaneous energy estimate for the aircraft to fly the DA path under engine idle conditions and arrive at the configuration point with an airspeed less than the configuration airspeed.

10. The cockpit display system of claim 1 wherein the controller is configured to generate the symbology to comprise a first vertical profile graphic visually denoting a projected rate at which an energy content of the aircraft will dissipate when flying the DA path under a first energy dissipation scheme.

11. A cockpit display system onboard an aircraft, the cockpit display system comprising:
a cockpit display device on which a first cockpit display is generated; and
a controller operably coupled to the cockpit display device and configured to:
identify a direct approach (DA) path to a configuration point located over a destination airfield;
calculate a first DA energy estimate for the aircraft to fly the DA path under engine idle conditions and arrive at the configuration point with an airspeed less than a configuration airspeed; and

generate symbology on the first cockpit display indicative of the first DA energy estimate,
wherein the first DA energy estimate comprises a maximum DA energy estimate, and wherein the controller is configured to calculate the maximum DA energy estimate based upon a projected vertical descent profile of the aircraft during which an auxiliary drag device is deployed.

12. The cockpit display system of claim 11 wherein the controller is configured to generate the cockpit display to include a deployment cue indicating an anticipated timing of the deployment of the auxiliary drag device as the aircraft flies the projected vertical descent profile.

13. The cockpit display system of claim 11 wherein the controller is further configured to:
calculate a minimum DA energy estimate for the aircraft to fly the DA path under engine idle conditions and arrive at the configuration point with an airspeed less than the configuration airspeed without deployment of the auxiliary drag device; and
generate symbology on the first cockpit display indicative of the minimum DA energy estimate.

14. The cockpit display system of claim 13 wherein the controller is configured to generate the symbology to comprise a substantially bar-shaped graphic having an upper edge representative of the maximum DA energy estimate and a lower edge representative of the minimum DA energy estimate.

15. A method carried-out by a cockpit display system onboard an aircraft, the method comprising:
identifying a direct approach (DA) path to a configuration point located over a destination airfield;
calculating a first DA energy estimate for the aircraft to fly the DA path under engine idle conditions and arrive at the configuration point with an airspeed less than a configuration airspeed, wherein the first DA energy estimate comprises a maximum DA energy estimate, and the maximum DA energy estimate is based upon a projected vertical descent profile of the aircraft during which an auxiliary drag device is deployed; and
generating symbology on a first cockpit display indicative of the first DA energy estimate.

16. The method of claim 15 wherein the first cockpit display comprises a Vertical Situation Display (VSD) including an aircraft icon, and wherein the method further comprising varying a vertical position of the symbology on the VSD relative to the aircraft icon as the first DA energy estimate varies with respect to a current energy content of the aircraft.

Assignees

• Honeywell Int Inc

Inventors

• Liberman Aric Charles
• Holder Barbara

Classifications

• B64D45/08

  optical · CPC title

• B64D45/04

  Landing aids; Safety measures to prevent collision with earth's surface · CPC title

• G01C23/00

  Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration · CPC title

• G09G2380/12

  Avionics applications · CPC title

• B64D43/00 Primary

  Arrangements or adaptations of instruments · CPC title