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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.

Patent No.:

US 10167079 B1

PDFFull Text
Date of Patent:
Jan. 01, 2019

Filed:

Sep. 29, 2015

Main rotor rotational speed control for rotorcraft

Applicant:

Sikorsky Aircraft Corporation, Stratford, CT (US);

Inventors:

Steven D. Weiner, Orange, CT (US);

William J. Eadie, Cheshire, CT (US);

Assignee:

SIKORSKY AIRCRAFT CORPORATION, Stratford, CT (US);

Attorney:

Cantor Colburn LLP

Primary Examiner:

Tyler D Paige

Int. Cl.
CPC ...
G05D 1/00 (2006.01); B64C 27/82 (2006.01); B64C 27/10 (2006.01); B64C 27/12 (2006.01); B64C 27/14 (2006.01); B64C 13/04 (2006.01); B64C 13/18 (2006.01); G05D 1/08 (2006.01); B64C 13/50 (2006.01); B64C 27/57 (2006.01); G05D 1/02 (2006.01); B64C 27/00 (2006.01); B64D 39/00 (2006.01); B64D 39/06 (2006.01); B64C 27/80 (2006.01); B64D 35/06 (2006.01); F16H 37/02 (2006.01); B64C 27/51 (2006.01); B64C 27/52 (2006.01); B64C 27/32 (2006.01); B64C 27/33 (2006.01); B64C 27/473 (2006.01); B64C 27/48 (2006.01); B64C 27/16 (2006.01); B64C 1/00 (2006.01); B64C 19/00 (2006.01); B64C 27/54 (2006.01); B64C 27/78 (2006.01); B64C 27/467 (2006.01); B64C 7/00 (2006.01); B64D 45/02 (2006.01); F16D 13/52 (2006.01); F16D 13/72 (2006.01); F16D 13/74 (2006.01); B64C 27/08 (2006.01); G06F 19/00 (2018.01); F02C 9/28 (2006.01);
U.S. Cl.
CPC ...
B64C 27/82 (2013.01); B64C 1/0009 (2013.01); B64C 7/00 (2013.01); B64C 13/04 (2013.01); B64C 13/18 (2013.01); B64C 13/503 (2013.01); B64C 19/00 (2013.01); B64C 27/001 (2013.01); B64C 27/006 (2013.01); B64C 27/008 (2013.01); B64C 27/10 (2013.01); B64C 27/12 (2013.01); B64C 27/14 (2013.01); B64C 27/16 (2013.01); B64C 27/32 (2013.01); B64C 27/322 (2013.01); B64C 27/33 (2013.01); B64C 27/467 (2013.01); B64C 27/473 (2013.01); B64C 27/48 (2013.01); B64C 27/51 (2013.01); B64C 27/52 (2013.01); B64C 27/54 (2013.01); B64C 27/57 (2013.01); B64C 27/78 (2013.01); B64C 27/80 (2013.01); B64D 35/06 (2013.01); B64D 39/00 (2013.01); B64D 39/06 (2013.01); B64D 45/02 (2013.01); F16H 37/02 (2013.01); G05D 1/0077 (2013.01); G05D 1/0202 (2013.01); G05D 1/0816 (2013.01); G05D 1/0858 (2013.01); B64C 13/50 (2013.01); B64C 27/08 (2013.01); B64C 2027/004 (2013.01); B64C 2027/8209 (2013.01); B64C 2027/8227 (2013.01); B64C 2027/8236 (2013.01); B64C 2027/8263 (2013.01); B64C 2027/8272 (2013.01); B64C 2027/8281 (2013.01); B64C 2201/024 (2013.01); F02C 9/28 (2013.01); F05D 2220/329 (2013.01); F05D 2270/021 (2013.01); F16D 13/52 (2013.01); F16D 13/72 (2013.01); F16D 13/74 (2013.01); G05D 1/0204 (2013.01); G05D 1/08 (2013.01); G06F 19/00 (2013.01);
Abstract

An aircraft includes an airframe having an extending tail, a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly and a lower rotor assembly and a translational thrust system positioned at the extending tail and providing translational thrust to the airframe. A flight control computer is configured to control a main rotor rotational speed of the upper and the lower rotor assemblies of the main rotor assembly as a function of airspeed of the aircraft. A method of operating an aircraft includes retrieving a threshold main rotor rotational speed of the dual coaxial main rotor assembly and calculating an actual main rotor rotational speed according to an environment of the aircraft. The actual main rotor rotational speed is maintained to remain at or below the threshold main rotor speed according to an airspeed of the aircraft.

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