Low throttle rate command compensation via full authority engine trim

Patent metadata

Field	Value
Publication number	US-10864994-B2
Application number	US-201816023060-A
Country	US
Kind code	B2
Filing date	Jun 29, 2018
Priority date	Jun 29, 2018
Publication date	Dec 15, 2020
Grant date	Dec 15, 2020

Abstract

An example method includes: determining a throttle command for a servomotor configured to control a position of a throttle lever, where the position of the throttle lever indicates a commanded thrust for the first engine of the aircraft; determining a trim command for the first engine to equalize the thrust of the first engine with the respective thrust of the second engine; determining that a magnitude of the throttle command is less than a magnitude of a threshold throttle command indicative of a dead zone of the servomotor, where the servomotor is irresponsive to a given throttle command within the dead zone; modifying the trim command based on the throttle command to generate a modified trim command that compensates for irresponsiveness of the servomotor to the throttle command; and changing the thrust generated by the first engine based on the modified trim command.

First claim

What is claimed is:

1. A method comprising:
determining, by a thrust management computer of an aircraft having at least a first engine and a second engine, a throttle command for a servomotor configured to control a position of a throttle lever, wherein the position of the throttle lever indicates a commanded thrust for the first engine of the aircraft;
determining, by the thrust management computer based on detecting a difference between a thrust generated by the first engine and a respective thrust generated by the second engine, a trim command for the first engine to equalize the thrust of the first engine with the respective thrust of the second engine;
determining, by the thrust management computer, that a magnitude of the throttle command is less than a magnitude of a threshold throttle command indicative of a dead zone of the servomotor, wherein the servomotor is irresponsive to a given throttle command within the dead zone;
modifying, by the thrust management computer, the trim command based on the throttle command to generate a modified trim command that compensates for irresponsiveness of the servomotor to the throttle command; and
providing, by the thrust management computer, the modified trim command to an electronic engine controller of the first engine, thereby changing the thrust generated by the first engine.

2. The method of claim 1 , wherein the trim command comprises an engine power setting for the first engine, and wherein modifying the trim command comprises:
integrating the throttle command over time to generate an integrated throttle command;
converting the integrated throttle command to a respective engine power setting; and
determining a summation of the respective engine power setting with the engine power setting of the trim command to generate the modified trim command.

3. The method of claim 1 , further comprising:
determining that a respective magnitude of the modified trim command is less than a magnitude of a trim limit value, wherein changing the thrust generated by the first engine is responsive to determining that the modified trim command is less than the magnitude of the trim limit value.

4. The method of claim 1 , further comprising:
determining that a respective magnitude of the modified trim command is greater than a magnitude of a trim limit value;
responsively, determining a time derivative of the modified trim command; and
modifying the throttle command based on the time derivative of the modified trim command to generate a modified throttle command for the servomotor.

5. The method of claim 4 , wherein the magnitude of the trim limit value is greater than the magnitude of the threshold throttle command, such that modifying the throttle command based on the time derivative of the modified trim command to generate the modified throttle command for the servomotor comprises generating the modified throttle command such that the modified throttle command is greater than the threshold throttle command and outside the dead zone of the servomotor.

6. The method of claim 4 , further comprising:
converting the time derivative of the modified trim command to a respective throttle command; and
determining a summation of the respective throttle command with the throttle command to generate the modified throttle command for the servomotor.

7. The method of claim 1 , further comprising:
providing a command having a value of zero to the servomotor so as to maintain the position of the throttle lever while providing the modified trim command to the electronic engine controller to change the thrust generated by the first engine.

8. A non-transitory computer readable medium having stored therein instructions that, in response to execution by a thrust management computer of an aircraft having at least a first engine and a second engine, cause the thrust management computer to perform operations comprising:
determining a throttle command for a servomotor configured to control a position of a throttle lever, wherein the position of the throttle lever indicates a commanded thrust for the first engine of the aircraft;
determining, based on detecting a difference between a thrust generated by the first engine and a respective thrust generated by the second engine, a trim command for the first engine to equalize the thrust of the first engine with the respective thrust of the second engine;
determining that a magnitude of the throttle command is less than a magnitude of a threshold throttle command indicative of a dead zone of the servomotor, wherein the servomotor is irresponsive to a given throttle command within the dead zone;
modifying the trim command based on the throttle command to generate a modified trim command that compensates for irresponsiveness of the servomotor to the throttle command; and
providing the modified trim command to an electronic engine controller of the first engine, thereby changing the thrust generated by the first engine.

9. The non-transitory computer readable medium of claim 8 , wherein the trim command comprises an engine power setting for the first engine, and wherein modifying the trim command comprises:
integrating the throttle command over time to generate an integrated throttle command;
converting the integrated throttle command to a respective engine power setting; and
determining a summation of the respective engine power setting with the engine power setting of the trim command to generate the modified trim command.

10. The non-transitory computer readable medium of claim 8 , wherein the operations further comprise:
determining that a respective magnitude of the modified trim command is less than a magnitude of a trim limit value, wherein changing the thrust generated by the first engine is responsive to determining that the modified trim command is less than the magnitude of the trim limit value.

11. The non-transitory computer readable medium of claim 8 , wherein the operations further comprise:
determining that a respective magnitude of the modified trim command is greater than a magnitude of a trim limit value;
responsively, determining a time derivative of the modified trim command; and
modifying the throttle command for the servomotor based on the time derivative of the modified trim command to generate a modified throttle command for the servomotor.

12. The non-transitory computer readable medium of claim 11 , wherein the magnitude of the trim limit value is greater than the magnitude of the threshold throttle command, such that modifying the throttle command for the servomotor based on the time derivative of the modified trim command to generate the modified throttle command for the servomotor comprises generating the modified throttle command such that the modified throttle command is greater than the threshold throttle command and outside the dead zone of the servomotor.

13. The non-transitory computer readable medium of claim 11 , wherein the operations further comprise:
converting the time derivative of the modified trim command to a respective throttle command; and
determining a summation of the respective throttle command with the throttle command for the servomotor to generate the modified throttle command for the servomotor.

14. The non-transitory computer readable medium of claim 8 , wherein the operations further comprise:
providing a command having a value of zero to the servomotor so as to maintain the position of the throttle lever while providing the modified trim command to the electronic engine controller to change the thrust generated by the first engine.

15. A thrust management computer of an

Assignees

• Boeing Co

Inventors

• Alaimo Jr John W
• Martindale Ian C

Classifications

• B64D31/08 Primary

  for keeping cruising speed constant · CPC title

• B64D31/06 Primary

  actuated automatically · CPC title

• F02D29/02 Primary

  peculiar to engines driving vehicles; peculiar to engines driving variable pitch propellers · CPC title

• F02D35/0007

  using electrical feedback (F02D35/0015 takes precedence) · CPC title

• F05D2270/54

  by electronic means, e.g. electronic tubes, transistors or IC's within an electronic circuit · CPC title