US 11,753,154 B2
Tilt rotor aircraft noise reduction
Matthew P. Misiorowski, Arlington, TX (US); and Joseph H. Schmaus, Fort Worth, TX (US)
Assigned to Textron Innovations Inc., Providence, RI (US)
Filed by Bell Textron Inc., Fort Worth, TX (US)
Filed on Jul. 8, 2021, as Appl. No. 17/370,817.
Prior Publication US 2023/0009101 A1, Jan. 12, 2023
Int. Cl. B64C 27/605 (2006.01); B64C 27/00 (2006.01); B64C 29/00 (2006.01)
CPC B64C 27/001 (2013.01) [B64C 27/605 (2013.01); B64C 29/0033 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A control system for a tilt rotor aircraft, comprising:
two or more rotors each configured to rotate two or more blades;
a stationary swashplate on each of the two or more rotors, the stationary swashplate coupled to two or more control inputs and configured to be stationary relative to the two or more rotors, the two or more control inputs operable to adjust an angle of the stationary swashplate;
a rotational swashplate on each of the two or more rotors and located above the stationary swashplate, each rotational swashplate coupled to the two or more blades by two or more pitch links, each rotational swashplate configured to rotate with the two or more rotors, the two or more pitch links configured to adjust a pitch angle of the two or more blades; and
a computing device operable to receive input from one or more users, to manipulate the two or more control inputs and to manipulate the two or more pitch links to allow the two or more blades to flap during at least a portion of a flight, the computing device further operable to manipulate the two or more control inputs to simultaneously cant the two or more blades of each of the two or more rotors away from a fuselage comprising the tilt rotor aircraft so as to increase a distance between the two or more blades and the fuselage.