Hybrid torque limiting rotary no-back device

Patent metadata

Field	Value
Publication number	US-11097830-B2
Application number	US-201916660477-A
Country	US
Kind code	B2
Filing date	Oct 22, 2019
Priority date	Jul 18, 2014
Publication date	Aug 24, 2021
Grant date	Aug 24, 2021

Abstract

A rotary device assembly is provided and includes an input shaft coupled to a torque generating device, an output shaft and a rotary device disposed to transmit first torque from the input shaft to the output shaft and configured with no-back capability to prevent second torque applied to the output shaft from being transmitted to the input shaft in an event the second torque deceeds a torque-limiting threshold and the no-back capability and torsional lock-up capability to prevent an overload of the torque generating device in an event the second torque exceeds the torque-limiting threshold.

First claim

The invention claimed is:

1. A flight control actuation system, comprising:
a dynamic surface pivotable relative to a static surface; and
a rotary device assembly comprising:
an output portion with a skewed roller assembly loaded by pre-load springs and a ball ramp assembly such that the skewed roller assembly provides variable drag torques which are variable based on the loads of the pre-load springs and the ball ramp assembly; and a high gain cone brake assembly,
the high gain cone brake assembly comprising:
a dynamic cone portion, which comprises a conical surface having radial and axial facing components whereby the output portion has a first torque pathway and a second torque pathway; and
a static cone portion, which comprises a conical surface having radial and axial facing components complementing those of the dynamic cone portion and with which the dynamic cone portion is engageable,
the rotary device assembly being configured for input-output shaft torque transmission to control a pivoting of the dynamic surface along the first torque pathway while preventing output-input shaft torque transmission if torque applied to an output shaft deceeds a threshold and along the second torque pathway while preventing an overload of a torque generating device to which an input shaft is coupled if the torque applied to the output shaft exceeds the threshold whereupon the dynamic cone portion engages with the static cone portion.

2. The flight control actuation system according to claim 1 , wherein the static surface comprises a wing and the dynamic surface comprises a flap or a slat.

3. The flight control actuation system according to claim 1 , wherein the torque applied to the output shaft is applied via the dynamic surface.

4. The flight control actuation system according to claim 1 , wherein the torque generating device comprises a motor.

5. The flight control actuation system according to claim 1 , wherein:
the rotary device assembly further comprises an input torque pathway, and
the first and second torque pathways are disposed in a reverse orientation relative to the input torque pathway.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Barger Victor

Classifications

• B64C9/16

  at the rear of the wing · CPC title

• F16D59/00

  Self-acting brakes, e.g. coming into operation at a predetermined speed · CPC title

• B64C9/22 Primary

  at the front of the wing · CPC title

• B64C13/28

  mechanical · CPC title

• F16D2125/36

  Helical cams, Ball-rotating ramps · CPC title