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:
Feb. 09, 2021

Filed:

Mar. 22, 2016
Applicant:

The Boeing Company, Huntington Beach, CA (US);

Inventor:

Neal Van Huynh, Bellevue, WA (US);

Assignee:

The Boeing Company, Chicago, IL (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B64C 13/50 (2006.01); B64C 13/04 (2006.01); G05D 1/00 (2006.01); G05D 1/08 (2006.01); B64C 13/12 (2006.01); G07C 5/08 (2006.01);
U.S. Cl.
CPC ...
B64C 13/505 (2018.01); B64C 13/04 (2013.01); B64C 13/044 (2018.01); B64C 13/0423 (2018.01); B64C 13/12 (2013.01); B64C 13/507 (2018.01); G05D 1/0077 (2013.01); G05D 1/0808 (2013.01); G07C 5/0808 (2013.01);
Abstract

An aircraft control system includes pilot and co-pilot flight control systems that each include a first shaft mechanically coupled to and displaced apart from a second shaft, the shafts defining and being rotatable about independent longitudinal axes. A connecting link enables rotation of one of the first shafts to rotate a corresponding one of the second shafts. A position transducer is mechanically coupled to each shaft and configured to communicate an electrical signal corresponding to the rotation of the respective shaft. A flight control unit electrically communicates with the position transducers and is configured to (a) receive the electrical signal from each position transducer, (b) detect a failure of the flight control system by detecting differences in the position transducers' electrical signals, and (c) communicate the electrical signal from the position transducer to a flight control surface actuation system to compensate for the detected failure.


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