Aircraft Rear Engine Attachment With Parallel Detachable Link Elements

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Solution Overview

Problem

Existing rear engine attachment designs for aircraft result in bulk that affects aerodynamic performance and complicate dismantling due to binding phenomena.

Innovation Solution

The design incorporates first and second rods with detachable link elements oriented parallel to the rod direction, reducing overall width and improving aerodynamics, and featuring inclined link elements to simplify assembly and disassembly.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If the rear engine attachment uses a conventional design with link bars perpendicular to the rod direction, then the engine can be securely connected to the primary structure, but the overall width increases causing aerodynamic penalties and binding phenomena during dismantling

Engineering Contradiction:

Improveconnection reliabilityVSAvoidaerodynamic penalty and binding phenomena

Core Design Contradiction:

ReliabilityVSObject-affected harmful factors

Solution Approach 1:

The patent changes the orientation parameter of the link elements from perpendicular to parallel with respect to the rod direction. This parameter change reduces the overall width of the rear engine attachment, eliminating aerodynamic penalties and preventing binding phenomena during dismantling, while maintaining connection reliability through the optimized geometric configuration

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The patent reorients the link elements from a transverse arrangement (perpendicular to rod direction) to a longitudinal arrangement (parallel to rod direction). This dimensional reconfiguration reduces the width dimension while maintaining the necessary connection functionality, thereby resolving the aerodynamic and dismantling issues

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

2Ease of manufacture

If the link elements are oriented perpendicular to the rod direction, then the assembly structure is conventional and easy to manufacture, but the dismantling operation becomes difficult due to binding phenomena

Engineering Contradiction:

Improvemanufacturing simplicityVSAvoiddismantling ease

Core Design Contradiction:

Ease of manufactureVSEase of operation

Solution Approach 1:

By changing the orientation parameter of link elements to be parallel with the rod direction, the patent eliminates binding phenomena during dismantling. The new configuration allows smooth disassembly while the manufacturing process remains straightforward, as the link elements are still simple structural components that can be produced using conventional methods

Inventive Principle:

Principle #35Parameter changes

3Strength

If the rear engine attachment uses a wider configuration for structural stability, then the connection between engine and primary structure is more robust, but the aerodynamic performance of the pylon is degraded

Engineering Contradiction:

Improveconnection strengthVSAvoidaerodynamic performance degradation

Core Design Contradiction:

StrengthVSObject-affected harmful factors

Solution Approach 1:

The patent changes the geometric parameter of link element orientation from perpendicular to parallel with the rod direction. This parameter change maintains the structural strength and stability of the connection while significantly reducing the overall width, thereby eliminating aerodynamic performance degradation without compromising connection robustness

Inventive Principle:

Principle #35Parameter changes

Data Source

PatentUS11518532B2Rear engine attachment of an aircraft having two-part rods and aircraft comprising at least one such rear engine attachment

Publication Date: 2022.12.06 AIRBUS OPERATIONS (SAS)

AI summary

An aircraft rear engine attachment connecting a primary structure of a pylon and an engine of an aircraft. The rear engine attachment includes first and second rods, each of them including at least two parts, a first part including at least one support orifice, accommodating a support link bar, configured to connect the rod directly or indirectly to the primary structure, at least one second part including at least one engine orifice, accommodating an engine link bar, configured to connect the rod directly or indirectly to the engine, and also detachable link elements for connecting the first and second parts oriented parallel to the direction of the rod.