公开(公告)号：US20250100680A1

公开(公告)日：2025-03-27

申请号：US18472933

申请日：2023-09-22

Applicant: Textron Innovations Inc.

Inventor： Lancer Drake Halcom ,  Kyle Thomas Cravener

IPC: B64C27/72 ,  B64C27/50

Abstract: An aircraft that has a blade position control system (BPCS). The BPCS includes an actuator, a multilobe component configured for at least one of longitudinal movement along a mast axis as a function of actuation of the actuator and rotational movement relative to the mast axis as a function of actuation of the actuator. Movement of the multilobe component selectively restricts at least one of pitch movement and folding of a plurality of rotor blades.

公开(公告)号：US20250100674A1

公开(公告)日：2025-03-27

申请号：US18472897

申请日：2023-09-22

Applicant: Textron Innovations Inc.

Inventor： Kyle Cravener ,  Andrew Harloff ,  Lancer Drake Halcom ,  Andrew Maresh

IPC: B64C27/72 ,  B64C27/50 ,  B64C29/00

Abstract: A rotor-blade assembly has a lock system to enable and disable a folding degree of freedom and a pitching degree of freedom of a rotor blade. A grip couples a blade to a hub, the blade being pivotable about a fold axis relative to the grip, the blade and grip being pivotable together about a pitch axis relative to the hub. A fold lock prevents folding of the blade in a fold-lock position and allows folding of the rotor blade in a pitch-lock position, and a pitch lock allows pitch movement of the rotor blade in a fold-lock position and prevents pitch movement of the rotor blade in the pitch-lock position. A rotary actuator carried by the grip has actuator arms coupled through linkage to the pitch lock and fold lock, and the actuator is configured for moving the pitch lock and fold lock between the fold-lock and pitch-lock positions.