公开(公告)号：US10696380B2

公开(公告)日：2020-06-30

申请号：US15654963

申请日：2017-07-20

Applicant: Hamilton Sundstrand Corporation

Inventor： Christian Miller ,  Yuniya S. Bishop ,  Erik Harrington

IPC: B64C13/34 ,  B64C13/28 ,  B64C13/16 ,  B64C9/18

Abstract: Control surface operating systems for controlling aerodynamic control surfaces of aircraft are provided. The systems includes a drive system operably connected to a drive shaft, the drive system including a continuously variable transmission, at least one actuator operably connected to the drive shaft and arranged to convert rotational movement of the drive shaft to move at least a portion of the aerodynamic control surface, and at least one control surface operably connected to the at least one actuator, wherein the at least one control surface is adjusted by the at least one actuator.

公开(公告)号：US10589871B2

公开(公告)日：2020-03-17

申请号：US15721268

申请日：2017-09-29

Applicant: Hamilton Sundstrand Corporation

Inventor： Erik Harrington ,  Christian Miller ,  Yuniya S. Bishop ,  Jason B. Kreienheder ,  Michael Skirtich ,  Gregory T. Wallen

IPC: B64D45/00 ,  G07C5/08 ,  B64C13/24 ,  B64C13/28 ,  B64C13/38

Abstract: A method of prognostic health monitoring is provided for use with an aircraft. The method includes generating torque for controlling positions of controllable surfaces at right- and left-hand-sides (RHS and LHS) of the aircraft in a power drive unit (PDU) based on torque-limiter (TL) thresholds, performing real-time monitoring of the torque at the RHS and LHS of the aircraft, generating RHS and LHS torque information from results of the performing of the real-time monitoring, analyzing the RHS and LHS torque information and controlling operations of the PDU based on results of the analysis by at least one of modifying, tuning and defining the TL thresholds.

公开(公告)号：US20180273199A1

公开(公告)日：2018-09-27

申请号：US15469740

申请日：2017-03-27

Applicant: Hamilton Sundstrand Corporation

Inventor： Erik Harrington ,  Christian Miller ,  Yuniya S. Bishop

IPC: B64D45/00 ,  B64C9/18 ,  B64D47/02

CPC classification number: B64D45/0005 ,  B64C9/16 ,  B64C9/22 ,  B64C13/28 ,  B64D45/00 ,  Y02T50/44

Abstract: Actuator systems and methods for controlling aerodynamic control surfaces of aircraft including a first actuator receiving a first input and a first linear translation element that moves based thereon, the first linear translation element operably connected to a first portion of the control surface. A first sensor assembly is disposed relative to the first actuator that generates an output based on a displacement of the first translation element. A second actuator receives a second input and a second linear translation element moves based on the second input, the second linear translation element operably connected to a second portion of the control surface. A second sensor assembly is disposed relative to the second actuator that generates a second sensor output based on a displacement of the second translation element. A controller generates the inputs and receives the sensor outputs to determine if an error condition exists for the system.