公开(公告)号：US20220242555A1

公开(公告)日：2022-08-04

申请号：US17612622

申请日：2020-05-22

Applicant: Moog Inc.

Inventor： Christopher A. Moore

IPC: B64C13/32 ,  F16C3/02 ,  B29D99/00

Abstract: Presented are a method and apparatus for an aircraft flight surface actuation system including a motor having an output shaft. A gearbox is coupled with the output shaft, whereby a first driving force output via the motor is converted to a second driving force. A torque shaft assembly is driveably coupled with the gearbox. The torque shaft assembly includes a first tube, a second tube located at least partially through the first tube and located coaxial therewith, wherein the first tube comprises an axial preload operable to mitigate lateral deflection, and wherein the first tube comprises a torsional preload operable to mitigate torsional deflection. In addition, the aircraft flight surface actuation system includes an eccentric cam mechanism driveably coupled with the torque shaft assembly, and a flight surface coupled with the eccentric cam mechanism.

公开(公告)号：US10066715B2

公开(公告)日：2018-09-04

申请号：US14695321

申请日：2015-04-24

Applicant: Moog Inc.

Inventor： Lowell Van Lund Larson ,  Christopher A. Moore

IPC: F16H25/00 ,  F16H25/20 ,  B64C13/28 ,  F16H25/22 ,  F16H25/24

Abstract: An electromechanical actuator (“EMA”) is provided with redundant load paths for driving the actuator stroke. The EMA includes a rotatable screw, a nut mated with the screw and having an external toothed surface, and a rotatable spline member having a splined surface engaging the external toothed surface of the nut. An actuator rod is coupled to the nut for linear movement with the nut. A first motor is operable to rotate the screw relative to the nut to cause the nut to travel linearly along the screw, and a second motor is operable to rotate the spline member and nut such that the nut travels linearly along the screw. Consequently, the actuator rod moves linearly by operation of the first motor alone, by operation of the second motor alone, and by simultaneous operation of the first and second motors. A no-back device may be incorporated into each load path.

公开(公告)号：US20160312867A1

公开(公告)日：2016-10-27

申请号：US14695321

申请日：2015-04-24

Applicant: Moog Inc.

Inventor： Lowell Van Lund Larson ,  Christopher A. Moore

IPC: F16H25/20 ,  B64C13/42

CPC classification number: F16H25/205 ,  B64C13/28 ,  F16H25/2015 ,  F16H25/2204 ,  F16H25/2454

Abstract: An electromechanical actuator (“EMA”) is provided with redundant load paths for driving the actuator stroke. The EMA includes a rotatable screw, a nut mated with the screw and having an external toothed surface, and a rotatable spline member having a splined surface engaging the external toothed surface of the nut. An actuator rod is coupled to the nut for linear movement with the nut. A first motor is operable to rotate the screw relative to the nut to cause the nut to travel linearly along the screw, and a second motor is operable to rotate the spline member and nut such that the nut travels linearly along the screw. Consequently, the actuator rod moves linearly by operation of the first motor alone, by operation of the second motor alone, and by simultaneous operation of the first and second motors. A no-back device may be incorporated into each load path.

Abstract translation: 机电致动器（“EMA”）具有用于驱动执行器行程的冗余负载路径。 EMA包括可旋转螺钉，与螺钉配合并具有外齿表面的螺母，以及具有接合螺母的外齿表面的花键表面的可旋转花键构件。 致动器杆联接到螺母，用于与螺母线性运动。 第一电动机可操作以相对于螺母旋转螺杆，以使螺母沿着螺杆线性运动，并且第二电动机可操作以使花键构件和螺母旋转，使得螺母沿螺杆线性行进。 因此，致动器杆单独通过第一电动机的操作而线性移动，并且通过单独操作第二电动机，并且同时操作第一和第二电动机。 每个负载路径中可以并入无背装置。

公开(公告)号：US12151803B2

公开(公告)日：2024-11-26

申请号：US17612622

申请日：2020-05-22

Applicant: Moog Inc.

Inventor： Christopher A. Moore

IPC: B64C13/32 ,  B29D99/00 ,  F16C3/02

Abstract: Presented are a method and apparatus for an aircraft flight surface actuation system including a motor having an output shaft. A gearbox is coupled with the output shaft, whereby a first driving force output via the motor is converted to a second driving force. A torque shaft assembly is driveably coupled with the gearbox. The torque shaft assembly includes a first tube, a second tube located at least partially through the first tube and located coaxial therewith, wherein the first tube comprises an axial preload operable to mitigate lateral deflection, and wherein the first tube comprises a torsional preload operable to mitigate torsional deflection. In addition, the aircraft flight surface actuation system includes an eccentric cam mechanism driveably coupled with the torque shaft assembly, and a flight surface coupled with the eccentric cam mechanism.