Integrated Aircraft Pylon Front Installation Node for Torque Transmission

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Solution Overview

Problem

Conventional aircraft engine pylon designs are heavy, consume excessive fuel, and negatively impact aerodynamics due to the wide rear edge required for torque transmission, which complicates the integration of engine systems and increases weight.

Innovation Solution

An integrated design where the front installation joint is integral with the pylon frame, capable of transmitting vertical, lateral loads, and torque, reducing the width of the rear installation joint and thus the pylon's outer shape, while also serving as a standby for potential damage and security purposes.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Force

If the rear installation joint is designed with larger width to transmit torque, then torque transmission capability is improved, but the pylon's rear edge shape becomes wider affecting aerodynamic performance

Engineering Contradiction:
Improvetorque transmission capabilityVSAvoidpylon rear edge shape
Core Design Contradiction:
ForceVSShape

Solution Approach 1:

The front installation joint and front end frame are merged into a single integrated structure, eliminating the need for separate components. This integration allows the front installation joint to assume torque transmission responsibilities, thereby reducing the width requirements of the rear installation joint and optimizing the pylon's aerodynamic shape.

Inventive Principle:
Principle #5Merging (Combining)

2Ease of manufacture

If the front installation joint is designed as an individual component independent from the pylon, then ease of assembly is improved, but the overall structure becomes heavy and fuel consumption increases

Engineering Contradiction:
Improveassembly easeVSAvoidengine installation structure weight
Core Design Contradiction:
Ease of manufactureVSWeight of moving object

Solution Approach 1:

The front installation joint is integrated with the front end frame of the pylon, forming a unified structure. This merging eliminates redundant components and reduces the overall weight of the engine installation structure, thereby decreasing fuel consumption while maintaining assembly feasibility through modular design interfaces.

Inventive Principle:
Principle #5Merging (Combining)

3Weight of moving object

If the front installation joint is integrated with the pylon frame to reduce weight, then structural weight is reduced, but the complexity of integrating torque transmission function increases

Engineering Contradiction:
Improvepylon structure weightVSAvoidintegration complexity
Core Design Contradiction:
Weight of moving objectVSDevice complexity

Solution Approach 1:

The integrated front installation joint is designed to perform multiple functions simultaneously: it provides structural support, transfers vertical and lateral loads, and transmits torque. This multi-functionality reduces the need for separate components, simplifies the overall structure, and decreases weight while managing complexity through unified design.

Inventive Principle:
Principle #6Universality (Multi-functionality)

4Shape

If the rear installation joint width is reduced to improve aerodynamics, then aerodynamic performance is improved, but torque transmission capability is reduced

Engineering Contradiction:
Improvepylon rear edge shapeVSAvoidtorque transmission capability
Core Design Contradiction:
ShapeVSForce

Solution Approach 1:

By integrating the front installation joint with the front end frame, the design transfers torque transmission responsibilities to the front installation joint. This allows the rear installation joint to be narrower, improving aerodynamic performance, while the front installation joint maintains sufficient torque transmission capability through its enhanced structural design.

Inventive Principle:
Principle #5Merging (Combining)

Data Source

PatentEP2848535B1Front installation node integrated with aircraft pylon
Publication Date: 2018.10.17 COMMERCIAL AIRCRAFT CORP OF CHINA LTD
  • EP2848535B1 patent drawingFigure 1~2b
  • EP2848535B1 patent drawingFigure 3a~3b
  • EP2848535B1 patent drawingFigure 4~5

AI summary

Disclosed is a front installation node integrated with an aircraft pylon. The front installation node is suitable for integral forming with a front end frame (100) of an aircraft pylon and comprises: a first lug (10) and a second lug (20), both respectively protruding outwardly from two sides of the front end frame; and a first connecting rod (70) and a second connecting rod (80), one end thereof being respectively connected to the first lug and the second lug, and the other end thereof being respectively suitable for connecting to an aircraft engine, wherein the first connecting rod can pivotally connect to the first lug at a first connection point (1), the second connecting rod and the second lug are respectively connected at a second connecting point (2) and a third connecting point (3). The front installation node for engine is integrated with the pylon frame, saving on weight; and using the front installation node to transmit torque is beneficial in reducing the external width of a rear installation node, reducing engine fuel consumption.