公开(公告)号：US11866163B1

公开(公告)日：2024-01-09

申请号：US17701472

申请日：2022-03-22

Applicant: Piasecki Aircraft Corporation

Inventor： Frederick W. Piasecki ,  Dinesh Barwey ,  Shane A. Lewis

IPC: B64C27/82 ,  B64C27/26

CPC classification number: B64C27/82 ,  B64C27/26 ,  B64C2027/8227 ,  B64C2027/8236 ,  B64C2027/8272

Abstract: A parking tail rotor for a rotary wing aircraft stops rotating at a high forward aircraft speed when aircraft control surfaces have adequate control authority to balance main rotor torque without the rotating tail rotor. When stopped, the blades of the parking tail rotor move due to the force of the relative wind to a parked position in which the span of the blades extend in the aft direction, reducing air resistance to the forward motion of the aircraft.

公开(公告)号：US11554860B1

公开(公告)日：2023-01-17

申请号：US17354707

申请日：2021-06-22

Applicant: Piasecki Aircraft Corporation

Inventor： Luigi U Ricci Moretti ,  Frederick W. Piasecki ,  George L. Firpi ,  Shane A. Lewis

IPC: B64C27/82 ,  B64C13/12 ,  B64C27/22

Abstract: A compound aircraft includes a convertible thruster that pivots between an anti-torque position, a forward thrust position, and intermediate positions. A pilot has two inceptors to control thruster rotor pitch in the anti-torque and forward thrust positions. A mixer mechanically blends the signals from the two inceptors during transition between the anti-torque and forward thrust positions. A transfer rod coaxial with the pivot axis of the convertible thruster conveys convertible thruster pitch commands from the pilot to a pitch control actuator. The pitch control actuator may be located partially within the rotor of an electric motor that rotates the convertible thruster rotor. The electric motor and pitch control actuator are unitary. Both the electric motor and pitch control actuator pivot with the convertible thruster. The pitch actuator output shaft is coaxial to and disposed within a hollow electric motor output shaft.