Systems and methods for providing throttle guidance as a function of flight path acceleration

Patent metadata

Field	Value
Publication number	US-11299285-B2
Application number	US-201916672105-A
Country	US
Kind code	B2
Filing date	Nov 1, 2019
Priority date	Dec 20, 2018
Publication date	Apr 12, 2022
Grant date	Apr 12, 2022

Abstract

Technologically improved vehicle control systems and methods are described. The provided vehicle control systems and methods embody an inner loop auto-throttle control for causing delta-throttle changes, i.e., servo changes, to achieve desired acceleration targets. The system generates an error on a potential flight path angle using a received thrust acceleration command. The error on the potential flight path angle is converted into an equivalent acceleration. A throttle rate command TLA_rate cmd is generated by converting the equivalent acceleration into the throttle rate command TLA_rate cmd .

First claim

What is claimed is:

1. A processor-implemented method for providing throttle rate control, comprising:
receiving aircraft constraints;
receiving a potential flight path angle command, PFPA cmd , which is a function of a flight path acceleration;
receiving a throttle level angle (TLA), which is a real time (RT) throttle setting;
receiving a RT thrust (T) setting;
using the potential flight path angle command, PFPA cmd to generate an error on a potential flight path angle;
converting the error on the potential flight path angle into an equivalent flight path acceleration;
generating a throttle rate command TLA_rate cmd by converting the equivalent flight path acceleration into the throttle rate command TLA_rate cmd ;
detecting a change in real time settings for one or more of flaps, gear handles, bank angle, and flight director commands;
estimating a delta drag as a function of the change;
determining a first adjustment to acceleration required to compensate for the delta drag, responsive to estimating the delta drag; and
generating the throttle rate command TLA_rate cmd by further adding the first adjustment to the equivalent flight path acceleration.

2. The processor-implemented method of claim 1 , further comprising:
monitoring a difference between RT thrust (T actual ) and a target thrust (T target );
determining a second adjustment to acceleration that is a function of the difference between T actual and T target ; and
generating the throttle rate command TLA_rate cmd by further adding the second adjustment to the equivalent flight path acceleration.

3. The processor-implemented method of claim 2 , further comprising:
employing a spool function that modifies a magnitude of the difference between T actual and T target, ; and
wherein the second adjustment is a function of the magnitude of the difference between T actual and T target , modified by the spool function.

4. The processor-implemented method of claim 2 , further comprising:
employing a spool threshold; and
wherein, when a magnitude of the difference between T actual and T target exceeds the spool threshold, the second adjustment is a threshold compensation term.

5. The processor-implemented method of claim 3 , further comprising:
generating the throttle rate command TLA_rate cmd by referencing engine-specific TLA versus T data to normalize the equivalent flight path acceleration command.

6. The processor-implemented method of claim 4 , further comprising:
generating the throttle rate command TLA_rate cmd by referencing engine-specific TLA versus T data to normalize the equivalent flight path acceleration command.

7. A system for providing throttle rate control, comprising:
a source of aircraft state data;
a source of aircraft constraints;
a source of a potential flight path angle command, PFPA cmd , which is a function of a flight path acceleration;
a source of a real time (RT) throttle level angle (TLA) that is a throttle setting;
a source of a RT thrust (T) setting;
a processor operationally coupled to the source of aircraft constraints, the source of a thrust acceleration command, the source of a RT TLA, and the source of a RT T, the processor programmed to:
use the potential flight path angle command, PFPA cmd to generate an error on a potential flight path angle;
convert the error on the potential flight path angle into an equivalent flight path acceleration;
generate a throttle rate command TLA_rate cmd by converting the equivalent flight path acceleration into the throttle rate command TLA_rate cmd ;
detect a change in real time settings for one or more of flaps, gear handles, and flight director commands
estimate a delta drag as a function of the detected change;
determine a first adjustment to acceleration required to compensate for the delta drag, responsive to estimating the delta drag; and
generate the throttle rate command TLA_rate cmd by further adding the first adjustment to the equivalent flight path acceleration.

8. The system of claim 7 , wherein the processor is further programmed to:
monitor a difference between RT thrust (T actual ) and target thrust (T target );
determine a second adjustment to acceleration that is a function of the difference between T actual and T target ; and
generate the throttle rate command TLA_rate cmd by further adding the second adjustment to the equivalent flight path acceleration.

9. The system of claim 8 , wherein the processor is further programmed to:
employ a spool function that modifies a magnitude of the difference between T actual and T target, ; and
wherein the second adjustment is a function of the magnitude of the difference between T actual and T target , modified by the spool function.

10. The system of claim 8 , wherein the processor is further programmed to:
employ a spool threshold; and
wherein, when a magnitude of the difference between T actual and T target exceeds the spool threshold, the second adjustment is a threshold compensation term.

11. The system of claim 9 , wherein the processor is further programmed to:
reference engine-specific TLA versus T data to normalize the equivalent flight path acceleration command.

12. The system of claim 10 , wherein the processor is further programmed to:
referencing engine-specific TLA versus T data to normalize the equivalent flight path acceleration command.

13. An aircraft, comprising:
a source of aircraft state data;
a source of aircraft constraints;
a source of a potential flight path angle command, PFPA cmd , which is a function of a flight path acceleration;
a source of a real time (RT) throttle level angle (TLA);
a source of a RT thrust (T) setting;
a processor operationally coupled to the source of aircraft constraints, the source of a thrust acceleration command, the source of a RT TLA, and the source of a RT T, the processor programmed to:
use the potential flight path angle command, PFPA cmd to generate an error on a potential flight path angle;
convert the error on the potential flight path angle into an equivalent flight path acceleration;
generate a throttle rate command TLA_rate cmd by converting the equivalent flight path acceleration into the throttle rate command TLA_rate cmd ;
detect a change in real time settings for one or more of flaps, gear handles, and flight director commands;
estimate a delta drag as a function of the detected change;
determine a first adjustment to acceleration required to compensate for the delta drag, responsive to estimating the delta drag; and
generate the throttle rate command TLA_rate cmd by further adding the first adjustment to the equivalent flight path acceleration.

14. The aircraft of claim 13 , wherein the processor is further programmed to:
monitor a difference between RT thrust (T actual ) and target thrust (T target );
determine a second adjustment to acceleration that is a function of the difference between T actual and T target ; and
generate the throttle rate command TLA_rate cmd by further adding the second adjustment to the equivalent flight path acceleration.

15. The aircraft of claim 14 , wherein the processor is further programmed to:
employ a spool function that modifies a magnitude of the difference between T actual and T target, ; and
wherein the second adjustment is a function compensation term.

16. The aircraft of claim 15 , wherein the processor is further programmed to:
employ a spool threshold; and
wherein, when a magnitude of the difference between T actual and T target exceeds the spool threshold, the second adjustment

Assignees

• Honeywell Int Inc

Inventors

• Melendez Luis
• Sin Philip
• Koenig John

Classifications

• B64D31/06 Primary

  actuated automatically · CPC title

• G05D1/0607 Primary

  specially adapted for aircraft · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title