Systems and methods for providing thrust guidance related to flight path angle

Patent metadata

Field	Value
Publication number	US-11120694-B2
Application number	US-201916672096-A
Country	US
Kind code	B2
Filing date	Nov 1, 2019
Priority date	Dec 19, 2018
Publication date	Sep 14, 2021
Grant date	Sep 14, 2021

Abstract

Technologically improved flight guidance systems and methods that generate thrust guidance related to a potential flight path angle are provided. The thrust guidance is provided as acceleration commands that may be communicated to the pilot in an intuitive manner, such as with an acceleration cue on a primary flight display (PFD) system. The provided acceleration cues are uniform across the flight envelope and present consistently for two basic thrust guidance modes.

First claim

What is claimed is:

1. A processor-implemented method for providing thrust guidance on a primary flight display (PFD) of an aircraft, the method comprising:
receiving an intended airspeed;
receiving, from a source of state data, a current airspeed and a current flight path angle (FPA);
receiving, from a source of avionics data, real time engine thrust (T) level, real time throttle level angle (TLA), and real-time weight;
at a control module comprising a thrust director algorithm, executing the thrust director algorithm to thereby perform the operations of,
referencing aircraft constraint data to obtain a T max and T idle , wherein T max is a maximum thrust and T idle is a thrust at idle;
calculating a projected potential flight path angle for the real time TLA (PPFPA TLA ) at T max as a function of the weight and a maximum TLA;
calculating a PPFPA TLA at T idle as a function of the weight and a minimum TLA;
generating an acceleration command (PFPA CMD ) as a function of the PPFPA TLA at T max and PPFPA TLA at T idle ; and
commanding the PFD to render symbology representing the acceleration command.

2. The method of claim 1 , further comprising:
determining a true airspeed error;
converting the true airspeed error into a desired acceleration command; and
wherein the desired acceleration command is acceleration limited with constraint data from a T versus TLA table.

3. The method of claim 2 , wherein the constraint data further includes comfort modifications.

4. The method of claim 3 , further including:
receiving configuration data for the aircraft; and
performing acceleration limiting on PPFPA TLA at T max and PPFPA TLA at T idle based on the configuration data.

5. The method of claim 4 , further comprising, commanding the PFD to render symbology representing an FPA that could be maintained at the current airspeed.

6. The method of claim 5 , further including: preforming display filtering before rendering the acceleration command.

7. The method of claim 6 , wherein the symbology representing the acceleration command is a thrust director cue shaped as 3 contiguous sides of a hexagram, scaled to the same units as a PFPA cue.

8. A system for providing thrust guidance on a primary flight display (PFD) of an aircraft, comprising:
a source of an intended airspeed;
a source of state data, providing a current airspeed and a current flight path angle (FPA);
a source of avionics data, providing real time engine thrust (T) level, real time throttle level angle (TLA), and real-time weight; and
a control module comprising a processor programmed to:
reference aircraft constraint data to obtain a T max and T idle , wherein T max is a maximum thrust and T idle is a thrust at idle
calculate a projected potential flight path angle for the real time TLA (PPFPA TLA ) at T max as a function of the weight and a maximum TLA;
calculate a PPFPA TLA at T idle as a function of the weight and a minimum TLA;
generate an acceleration command (PFPA CMD ) as a function of the PPFPA TLA at T max and PPFPA TLA at T idle ; and
command the PFD to render symbology representing the acceleration command.

9. The system of claim 8 , wherein the processor is further programmed to:
determine a true airspeed error;
convert the true airspeed error into a desired acceleration command; and
wherein the desired acceleration command is acceleration limited with constraint data from a T versus TLA table, creating an acceleration output.

10. The system of claim 9 , wherein the constraint data further includes comfort modifications.

11. The system of claim 10 , wherein the processor is further programmed to:
receive configuration data for the aircraft; and
perform acceleration limiting on PPFPA TLA at T max and PPFPA TLA at T idle based on the configuration data.

12. The system of claim 11 , wherein the processor is further programmed to command the PFD to render symbology representing a FPA that could be maintained at the current airspeed, referred to as a PFPA cue.

13. The system of claim 12 , wherein the processor is further programmed to preform display filtering before rendering the acceleration command.

14. The system of claim 13 , wherein the processor is further programmed to generate the symbology representing the acceleration command as a thrust director cue shaped as 3 contiguous sides of a hexagram, scaled to the same units as the PFPA cue.

15. The system of claim 14 , wherein the processor is further programmed to:
translate the acceleration output into a delta flight path angle (delta FPA);
add the delta FPA to a reference FPA to obtain an unlimited potential flight path command; and
use the unlimited potential flight path command in the generation of the acceleration command (PFPA CMD ).

16. An aircraft, comprising:
a primary flight display (PFD);
a source of an intended airspeed;
a source of state data, providing a current airspeed and a current flight path angle (FPA);
a source of avionics data, providing real time engine thrust (T) level, real time throttle level angle (TLA), and real-time weight; and
a thrust director control module, comprising a processor programmed to:
determine a true airspeed error;
convert the true airspeed error into a desired acceleration command;
acceleration limit the desired acceleration command with constraint data, creating an acceleration output, wherein the constraint data provides a T max and a T idle , wherein T max is a maximum thrust and T idle is a thrust at idle;
calculate a projected potential flight path angle for the real time TLA (PPFPA TLA ) at T max as a function of the weight and a maximum TLA;
calculate a PPFPA TLA at T idle as a function of the weight and a minimum TLA;
generate an acceleration command (PFPA CMD ) as a function of the PPFPA TLA at T max and PPFPA TLA at T idle ; and
command the PFD to render symbology representing the acceleration command.

17. The aircraft of claim 16 , wherein the constraint data includes an engine-specific T versus TLA table.

18. The aircraft of claim 17 , wherein the processor is further programmed to:
receive configuration data for the aircraft; and
perform acceleration limiting on PPFPA TLA at T max and PPFPA TLA at T idle based on the configuration data.

19. The aircraft of claim 18 , wherein the processor is further programmed to:
translate the acceleration output into a delta flight path angle (delta FPA);
add the delta FPA to a reference FPA to obtain an unlimited potential flight path command; and
use the unlimited potential flight path command in the generation of the acceleration command (PFPA CMD ).

20. The aircraft of claim 19 , wherein the processor is further programmed to:
command the PFD to render symbology representing an FPA that could be maintained at the current airspeed, referred to as a PFPA cue; and
generate the symbology representing the acceleration command as a thrust director cue shaped as 3 contiguous sides of a hexagram, scaled to the same units as the PFPA cue.

Assignees

• Honeywell Int Inc

Inventors

• Melendez Luis
• Sin Philip
• Koenig John
• Mast Michael

Classifications

• G08G5/55

  for a single aircraft · CPC title

• G08G5/50

  Navigation or guidance aids · CPC title

• G08G5/32

  for flight plan preparation · CPC title

• G08G5/76

  for monitoring atmospheric conditions · CPC title

• G08G5/53

  for cruising · CPC title