Composite Aircraft Stanchion With Variable Ply Load Dissipation

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Solution Overview

Problem

Existing aircraft stanchions lack efficient energy dissipation and load distribution mechanisms, particularly during high-load scenarios such as emergency landings, leading to potential structural failure.

Innovation Solution

A stanchion design featuring composite channels with varying ply counts symmetrically arranged about a central segment, bonded and fastened together, and optionally incorporating a stiffening plate and pivotable connections to enhance structural integrity and energy management.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If a conventional stanchion design is used, then the structure is simple, but energy dissipation and load distribution are insufficient during high-load scenarios

Engineering Contradiction:

Improvestructural integrity during high-load eventsVSAvoidstanchion structure complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The stanchion is divided into multiple longitudinal segments with varying ply counts, allowing different regions to respond differently to loads. This segmentation enables progressive energy dissipation while maintaining overall structural integrity during high-load events.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Adjacent longitudinal segments have different ply counts, creating local variations in stiffness and strength. This local quality variation allows the stanchion to distribute loads more effectively and dissipate energy in controlled regions during high-load scenarios.

Inventive Principle:

Principle #3Local quality

2Ease of manufacture

If uniform ply count is used in all longitudinal segments, then manufacturing is simpler, but load distribution efficiency is reduced

Engineering Contradiction:

Improvemanufacturing simplicityVSAvoidload distribution efficiency

Core Design Contradiction:

Ease of manufactureVSStrength

Solution Approach 1:

The stanchion employs varying ply counts in adjacent longitudinal segments, creating local quality variations that optimize load distribution. This allows each segment to be manufactured with appropriate thickness and strength for its specific structural role.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The ply count parameter is changed between adjacent longitudinal segments to create an optimized load distribution pattern. This parameter variation allows the structure to efficiently manage stresses while remaining manufacturable through standard composite fabrication processes.

Inventive Principle:

Principle #35Parameter changes

3Reliability

If symmetric ply arrangement is implemented, then structural response is optimized, but manufacturing precision requirements increase

Engineering Contradiction:

Improvestructural response optimizationVSAvoidply arrangement precision

Core Design Contradiction:

ReliabilityVSManufacturing precision

Solution Approach 1:

While individual segments have symmetric ply arrangements about their central segment, the overall structure employs asymmetric variations in ply count between adjacent segments. This approach optimizes structural response while maintaining manufacturability through standard symmetric fabrication processes.

Inventive Principle:

Principle #4Asymmetry

Solution Approach 2:

Each longitudinal segment maintains symmetric ply arrangement about its central segment, providing local structural optimization. This local symmetry simplifies manufacturing while the variation between segments provides overall structural efficiency.

Inventive Principle:

Principle #3Local quality

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 provides enhanced energy dissipation and load distribution, reducing the risk of structural failure during high-load events by optimizing the stanchion's structural response.

Implementation Method 1

The design provides enhanced energy dissipation and load distribution, reducing the risk of structural failure during high-load events by optimizing the stanchion's structural response

Methodology Applied

Scientific EffectEnergy dissipation: Damping

Implementation Method 2

a first composite body defining a first channel having a first web extending between a first pair of spaced apart flanges. The first composite body also includes a first multitude of longitudinal segments each having a ply count that varies between adjacent longitudinal segments

Methodology Applied

Scientific EffectComposite material behavior: Composite Materials

Implementation Method 3

bonded and fastened together

Methodology Applied

Scientific EffectBonding: Adhesive

Implementation Method 4

The stanchion includes fasteners extending through the first web and the second web

Methodology Applied

Scientific EffectMechanical fastening: Mechanical Fastener

Data Source

PatentUS20250368312A1Stanchion for aircraft structure

Publication Date: 2025.12.04 THE BOEING CO

AI summary

The stanchion for an aircraft includes a first composite body defining a first channel having a first web extending between a first pair of spaced apart flanges. The first composite body also includes a first multitude of longitudinal segments each having a ply count that varies between adjacent longitudinal segments of the first multitude of longitudinal segments. The stanchion also includes a second composite body defining a second channel having a second web extending between a second pair of flanges. The second composite body also includes a second multitude of longitudinal segments each having a ply that varies between adjacent longitudinal segments of the second plurality of longitudinal segments with the first composite body being fixed relative to the second composite body.