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:
Jan. 17, 2017

Filed:

Aug. 21, 2014
Applicant:

Honeywell International Inc., Morristown, NJ (US);

Inventors:

Richard Ling, Scottsdale, AZ (US);

Grant Gordon, Peoria, AZ (US);

Kevin Moeckly, Chandler, AZ (US);

Assignee:

HONEYWELL INTERNATIONAL INC., Morris Plains, NJ (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
G08G 5/00 (2006.01); B64C 13/18 (2006.01); G07C 5/08 (2006.01); B64D 45/00 (2006.01); B64C 27/00 (2006.01);
U.S. Cl.
CPC ...
G08G 5/0056 (2013.01); B64C 13/18 (2013.01); B64C 27/006 (2013.01); B64D 45/00 (2013.01); G07C 5/0808 (2013.01); G08G 5/003 (2013.01); G08G 5/0086 (2013.01); G08G 5/0091 (2013.01); B64D 2045/0085 (2013.01);
Abstract

An emergency landing control system for an aircraft includes a landing site data source, a performance margin data source, an engine health data source, an aircraft health data source, and a processor. The landing site data source determines, continuously and in real-time, available landing sites. The performance margin data source conducts, continuously and in real-time, continuous performance analysis of an engine. The engine health data source determines, continuously and in real-time, available engine power as a function of time. The aircraft health data source determines, continuously and in real-time, available aircraft life as a function of time. The processor receives data from these data sources and, based on these data, continuously generates landing paths to one or more of the available landing sites, and selectively and continuously adjusts maximum available engine power up to emergency power limits, as needed, during execution of a landing maneuver to a landing site.


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