The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Dec. 29, 2020

Filed:

May. 22, 2018
Applicant:

The Boeing Company, Chicago, IL (US);

Inventors:

Joseph G. Irwin, III, Landenberg, PA (US);

David G. Miller, Mount Laurel, NJ (US);

Nathaniel T. Morgan, Downingtown, PA (US);

Assignee:

THE BOEING COMPANY, Chicago, IL (US);

Attorney:
Int. Cl.
CPC ...
G05D 1/08 (2006.01); B64C 27/22 (2006.01); G05B 13/04 (2006.01); B64C 27/56 (2006.01); B64C 29/00 (2006.01); B64C 27/57 (2006.01); B64C 19/00 (2006.01); B64C 27/52 (2006.01); B64C 13/50 (2006.01); G05D 1/04 (2006.01); B64C 27/82 (2006.01);
U.S. Cl.
CPC ...
G05D 1/0808 (2013.01); B64C 13/506 (2018.01); B64C 19/00 (2013.01); B64C 27/22 (2013.01); B64C 27/52 (2013.01); B64C 27/56 (2013.01); B64C 27/57 (2013.01); B64C 29/0033 (2013.01); G05B 13/048 (2013.01); G05D 1/042 (2013.01); G05D 1/0816 (2013.01); G05D 1/0858 (2013.01); B64C 2027/8227 (2013.01); B64C 2027/8236 (2013.01);
Abstract

A control circuitry includes a propulsor trim prediction circuitry configured to generate a predicted propulsor collective blade pitch trim value for a target state of an aircraft based on an aircraft velocity and a pitch attitude deviation from a reference. The control circuitry further includes an output circuitry configured to output a propulsor collective blade pitch angle command based on the predicted propulsor collective blade pitch trim value. The propulsor collective blade pitch angle command is configured to cause an adjustment in a blade pitch angle of a propulsor of the aircraft. Additionally or alternatively, the control circuitry includes a pitch attitude trim prediction circuitry configured to generate a predicted pitch attitude trim value. The output circuitry is configured to output an aircraft pitch attitude trim command, configured to cause an adjustment in a pitch angle of the aircraft, based on the predicted pitch attitude trim value.


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