Aircraft Interior Buffer Zone for Fuselage Flexure

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Solution Overview

Problem

Aircraft fuselage flexure creates dynamic gaps between interior features, affecting aesthetic appearance and requiring significant production time due to manufacturing and installation tolerances.

Innovation Solution

The implementation of buffer zones using flexible edges and soft seal elements that overlap transition inserts, allowing edges to slide and maintain contact with surfaces, minimizing or eliminating gaps between aircraft features.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Shape

If rigid interior panels and features are installed with tight tolerances to minimize gaps, then aesthetic appearance is improved, but production time increases significantly due to cutting and fitting requirements

Engineering Contradiction:

Improvegap minimizationVSAvoidproduction time

Core Design Contradiction:

ShapeVSProductivity

Solution Approach 1:

The patent applies dynamics by making the buffer zone elements flexible rather than rigid. The buffer zone includes a flexible edge portion that can dynamically adjust its position and shape to accommodate fuselage flexure, eliminating the need for precise cutting and fitting while maintaining gap-free appearance.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The patent changes the physical state of the buffer zone from rigid to flexible. By using a flexible material for the edge portion of the buffer zone, the system can adapt to dimensional changes caused by fuselage flexure without requiring tight manufacturing tolerances or extensive installation time.

Inventive Principle:

Principle #35Parameter changes

2Strength

If rigid interior features are used to maintain structural integrity, then strength is improved, but gaps appear between features during fuselage flexure, worsening aesthetic appearance

Engineering Contradiction:

Improvestructural integrityVSAvoidgap formation

Core Design Contradiction:

StrengthVSShape

Solution Approach 1:

The patent applies local quality by differentiating the mechanical properties of different components. The buffer zone's edge portion is made flexible to accommodate movement and prevent gaps, while the main structural elements remain rigid to maintain strength. This localized flexibility resolves the contradiction between structural integrity and gap prevention.

Inventive Principle:

Principle #3Local quality

3Manufacturing precision

If precise cutting and fitting of each component is performed to account for aircraft flexure, then manufacturing precision is improved, but production time increases significantly

Engineering Contradiction:

Improvecomponent fitVSAvoidinstallation time

Core Design Contradiction:

Manufacturing precisionVSProductivity

Solution Approach 1:

The patent applies self-service by designing the buffer zone to automatically adjust itself during fuselage flexure. The flexible edge portion self-adjusts to maintain contact with adjacent features without requiring precise pre-cutting or complex installation procedures, thereby reducing both manufacturing precision requirements and installation time.

Inventive Principle:

Principle #25Self-service

4Adaptability or versatility

If buffer zones with flexible edges are used to accommodate fuselage flexure, then adaptability is improved, but device complexity increases due to additional components

Engineering Contradiction:

Improveflexure accommodationVSAvoidcomponent structure

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The patent applies segmentation by dividing the buffer zone into distinct functional portions: a main body and a flexible edge portion. This segmentation allows the flexible edge to specifically address adaptability requirements while the main body maintains structural function, preventing overall system complexity from becoming excessive.

Inventive Principle:

Principle #1Segmentation

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

This solution reduces or eliminates unsightly gaps between aircraft features, enhancing the aesthetic appearance and reducing production time by accommodating fuselage flexure while maintaining a high-quality finish.

Implementation Method 1

a first soft seal element disposed in the first cavity, the first soft seal element biased to press the first edge against a surface of the transition insert

Methodology Applied

Scientific EffectElasticity: Elasticity

Data Source

PatentUS11772772B2Buffer zone for interior aircraft features

Publication Date: 2023.10.03 BOMBARDIER INC

AI summary

Several embodiments of buffer zones are provided that are contemplated to be disposed with respect to two or more adjacent elements on an aircraft. The buffer zones adjust for dynamic spacing between the elements to help control different gapping requirements between the elements installed in the aircraft. Embodiments include an aircraft interior panel configuration, an aircraft interior wall panel configuration, an adjustable width aircraft bulkhead, and an aircraft personal service unit.