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:
Nov. 12, 2024

Filed:

Jun. 10, 2021
Applicant:

Lockheed Martin Corporation, Bethesda, MD (US);

Inventor:

Navid Dadkhah Tehrani, Providence, RI (US);

Assignee:

Lockheed Martin Corporation, Bethesda, MD (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
G05D 1/00 (2024.01); B64C 11/00 (2006.01); B64C 27/10 (2023.01); B64C 27/82 (2006.01); B64D 31/02 (2006.01); B64D 31/06 (2024.01); G08G 5/00 (2006.01);
U.S. Cl.
CPC ...
G05D 1/101 (2013.01); B64C 11/00 (2013.01); B64C 27/10 (2013.01); B64C 27/82 (2013.01); B64D 31/02 (2013.01); B64D 31/06 (2013.01); G08G 5/0047 (2013.01); B64C 2027/8236 (2013.01);
Abstract

Systems and methods for controlling a coaxial rotary-wing aircraft including a co-axial main rotor assembly and a pusher-propeller. One system includes an electronic controller configured to receive a reference velocity of the aircraft and receive a reference flight path angle of the aircraft. The electronic controller is also configured to simultaneously control the co-axial main rotor assembly and the pusher-propeller based on the reference velocity of the aircraft and the reference flight path angle of the aircraft, by simultaneously generating a commanded thrust of the pusher-propeller and a commanded thrust of the co-axial main rotor assembly using a multiple input, multiple output algorithm applying dynamic inversion.


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