Aircraft Thrust Load Device Reducing Bearing Wear

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Solution Overview

Problem

The existing thrust force recovery device generates out-of-plane forces that can cause premature wear of ball bearings, necessitating a design modification to maintain horizontal connecting rod mounting while reducing wear.

Innovation Solution

The thrust force recovery device incorporates inclined force transmission axes and a rudder with distinct connections to the connecting rods, avoiding out-of-plane forces and incorporating a secondary force recovery interface to manage potential failures, ensuring continuous operation and reduced wear.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If a horizontally mounted connecting shaft is used to connect the connecting rods to the rocker arm, then compactness and accessibility for operators are optimized, but out-of-plane forces are generated that cause premature wear of the spherical bushings

Engineering Contradiction:
Improveaccessibility for operatorsVSAvoidwear of spherical bushings
Core Design Contradiction:
Ease of operationVSReliability

Solution Approach 1:

The invention inverts the traditional connection approach by using a vertically mounted connecting shaft instead of a horizontal one. This inversion changes the direction of force transmission so that forces are applied along the vertical axis through the spherical bushings rather than creating out-of-plane moments, thereby eliminating the wear problem while maintaining accessibility

Inventive Principle:
Principle #13The other way round (Inversion)

Solution Approach 2:

The invention changes the mounting orientation parameter of the connecting shaft from horizontal to vertical. This parameter change fundamentally alters the force transmission path, converting out-of-plane bending moments into axial forces that the spherical bushings can handle without premature wear

Inventive Principle:
Principle #35Parameter changes

2Volume of moving object

If the connecting rods are mounted with a horizontally mounted connecting shaft, then compactness is optimized, but out-of-plane forces directed towards the sides are generated at each interface

Engineering Contradiction:
ImprovecompactnessVSAvoidout-of-plane forces
Core Design Contradiction:
Volume of moving objectVSObject-generated harmful factors

Solution Approach 1:

By inverting the connecting shaft orientation from horizontal to vertical, the force transmission path is reversed. This eliminates the generation of out-of-plane forces directed towards the sides, as the vertical mounting aligns the force vectors with the spherical bushing load-bearing capacity

Inventive Principle:
Principle #13The other way round (Inversion)

Applied Scientific Principles

This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.

Function Achieved in This Case

The design significantly reduces wear on ball bearings by eliminating out-of-plane forces and provides a secondary force path for failure scenarios, enhancing the durability and accessibility of the thrust force recovery system.

Implementation Method 1

The connecting shaft (L1, L2) extends along an axis L1, L2 included in the mean plane of transmission of thrust forces P and orthogonal to the force transmission axis T1, T2 of the first, respectively second connecting rod 101, 102

Methodology Applied
Scientific EffectMechanical Force: Mechanical Force

Data Source

PatentEP4151838B1Aircraft engine assembly comprising a thrust load-receiving device configured to be mounted to an aircraft
Publication Date: 2024.08.07 AIRBUS OPERATIONS (SAS)
  • EP4151838B1 patent drawingFigure 1
  • EP4151838B1 patent drawingFigure 2
  • EP4151838B1 patent drawingFigure 3

AI summary

The invention relates to a motorization assembly comprising a motor suspended under a mast by means of motor mounts including a thrust force absorption device (100), the motor having a longitudinal axis (X) and a median vertical plane (V) parallel to the longitudinal axis (X), the thrust force absorption device (100) comprising a main fitting (110) fixed under the mast and two connecting rods (101, 102) arranged on either side of the median vertical plane (V) and each having a rear end (101a, 102a) articulated to the main fitting (110) by means of a rocker arm (120) pivotally mounted on the main fitting (110) about an axis of rotation being, on the one hand, orthogonal to a mean thrust force transmission plane (P) parallel to the longitudinal axis (T1, T2) of each of the connecting rods and, on the other hand, disposed in the vertical plane median (V), each connecting rod (101,102) being articulated to the rocker arm (120) by means of a connecting axis (L1,L2) extending parallel to the average plane of transmission of thrust forces (P) and perpendicular to the longitudinal axis of the connecting rod.