Optimum cruise climb tracking for reduced fuel consumption using vertical and lateral navigation

Patent metadata

Field	Value
Publication number	US-10345824-B2
Application number	US-201615256227-A
Country	US
Kind code	B2
Filing date	Sep 2, 2016
Priority date	Sep 2, 2016
Publication date	Jul 9, 2019
Grant date	Jul 9, 2019

Abstract

A method of optimizing a cruise climb of an aircraft. The method includes using vertical navigation and lateral navigation to track the cruise climb; and using tracking of the cruise climb to adjust a climb rate of the aircraft to match an optimal climb rate.

First claim

What is claimed is:

1. A method of operating an aircraft comprising:
computing an optimal climb rate profile representing optimized fuel consumption by the aircraft during a cruise climb to an optimal altitude where fuel consumption is minimized during a cruise, wherein the optimal climb rate profile is represented on a graph of altitude versus ground distance, and wherein the optimal climb rate profile represents an optimal climb rate;
initiating, after computing the optimal climb rate profile, the cruise climb for the aircraft;
tracking a three-dimensional position of the aircraft using both vertical navigation tracking of the aircraft and lateral navigation tracking of the aircraft, to form tracked information; and
adjusting a climb rate using the tracked information such that the climb rate about matches the optimal climb rate, wherein adjusting comprises calculating a flight level change that intercepts and then locks a vertical path of the aircraft to the optimal climb rate profile.

2. The method of claim 1 , further comprising:
calculating favorable lateral wind and temperature components as part of the lateral navigation tracking and using the favorable lateral wind and temperature components to further adjust the climb rate.

3. The method of claim 1 , wherein the climb rate is between about ten feet per minute and about fifty feet per minute.

4. The method of claim 1 , further comprising:
ending the cruise climb upon reaching the optimal altitude.

5. The method of claim 1 , further comprising:
automatically selecting a start point and an end point of the cruise climb.

6. The method of claim 1 , wherein the cruise climb comprises a negative vertical speed used to track the optimal altitude.

7. The method of claim 1 , wherein the climb rate is further maintained at or below one hundred feet per minute.

8. A method of operating an aircraft comprising:
computing an optimal climb rate profile representing optimized fuel consumption by the aircraft during a cruise climb to an optimal altitude where fuel consumption is minimized during a cruise, wherein the optimal climb rate profile is represented on a graph of altitude versus ground distance, and wherein the optimal climb rate profile represents an optimal climb rate;
wherein, before initiating, the aircraft is at an altitude that is above a corresponding altitude for a given ground distance on the optimal climb rate profile at which the aircraft is located;
maintaining, before initiating, the altitude until the aircraft reaches a second ground distance on the optimal climb rate profile that matches the altitude of the aircraft;
initiating, after computing the optimal climb rate profile, the cruise climb for the aircraft;
tracking a three-dimensional position of the aircraft using both vertical navigation tracking of the aircraft and lateral navigation tracking of the aircraft, to form tracked information; and
adjusting a climb rate using the tracked information such that the climb rate about matches the optimal climb rate.

9. A method of operating an aircraft comprising:
computing an optimal climb rate profile representing optimized fuel consumption by the aircraft during a cruise climb to an optimal altitude where fuel consumption is minimized during a cruise, wherein the optimal climb rate profile is represented on a graph of altitude versus ground distance, and wherein the optimal climb rate profile represents an optimal climb rate;
wherein, before initiating, the aircraft is at an altitude that is below a corresponding altitude for a given ground distance on the optimal climb rate profile at which the aircraft is located;
climbing, before initiating, at a climb rate greater than one hundred feet per minute but less than one thousand feet per minute, until the aircraft reaches a second altitude that corresponds to a second ground distance of the aircraft that is on the optimal climb rate profile;
initiating, after computing the optimal climb rate profile, the cruise climb for the aircraft;
tracking a three-dimensional position of the aircraft using both vertical navigation tracking of the aircraft and lateral navigation tracking of the aircraft, to form tracked information; and
adjusting the climb rate using the tracked information such that the climb rate about matches the optimal climb rate.

10. An aircraft comprising:
a fuselage;
a wing connected to the fuselage;
an engine connected to one of the wing and the fuselage; and
a computer located inside the fuselage and in communication with controls for operating the aircraft, the computer storing program code, which when executed by a processor of the computer, executes a method for automatically using the controls to operate the aircraft, the program code comprising:
program code for computing an optimal climb rate profile representing optimized fuel consumption by the aircraft during a cruise climb to an optimal altitude where fuel consumption is minimized during a cruise, wherein the optimal climb rate profile is represented on a graph of altitude versus ground distance, and wherein the optimal climb rate profile represents an optimal climb rate;
program code for initiating, after computing, the cruise climb for the aircraft;
program code for tracking a three-dimensional position of the aircraft using both vertical navigation tracking of the aircraft and lateral navigation tracking of the aircraft, to form tracked information; and
program code for adjusting a climb rate using the tracked information such that the climb rate about matches the optimal climb rate, wherein the program code for adjusting comprises program code for calculating a flight level change that intercepts and then locks a vertical path of the aircraft to the optimal climb rate profile.

11. The aircraft of claim 10 , wherein the program code further comprises:
program code for calculating favorable lateral wind and temperature components as part of the lateral navigation tracking and using the favorable lateral wind and temperature components to further adjust the climb rate.

12. The aircraft of claim 10 , wherein the climb rate is between about ten feet per minute and about fifty feet per minute.

13. The aircraft of claim 10 , wherein the program code is configured such that the climb rate is further maintained at or below one hundred feet per minute.

14. An aircraft comprising:
a fuselage;
a wing connected to the fuselage;
an engine connected to one of the wing and the fuselage; and
a computer located inside the fuselage and in communication with controls for operating the aircraft, the computer storing program code, which when executed by a processor of the computer, executes a method for automatically using the controls to operate the aircraft, the program code comprising:
program code for computing an optimal climb rate profile representing optimized fuel consumption by the aircraft during a cruise climb to an optimal altitude where fuel consumption is minimized during a cruise, wherein the optimal climb rate profile is represented on a graph of altitude versus ground distance, and wherein the optimal climb rate profile represents an optimal climb rate;
wherein, before initiating, the aircraft is at an altitude that is above a corresponding altitude for a given ground distance on the optimal climb rate profile at which the aircraft is located;
program code for maintaining, before initiating, the altitude until the aircraft reaches a second ground distance on the optimal climb rate profile that matches the altitude of the aircraft;
program code for initiating, after computing, the cruise climb for the aircraft

Assignees

• Boeing Co

Inventors

• Kim Geun Il
• Fregnani Jose Alexandre Tavares Guerreiro
• Rohr Timothy Charles

Classifications

• G05D1/0653

  during a phase of take-off or landing · CPC title

• G08G5/0052

  Physics · mapped topic

• G08G5/0013

  Physics · mapped topic

• G08G5/0021

  Physics · mapped topic

• G05D1/046

  to counteract a perturbation, e.g. gust of wind · CPC title