Tapered Wing Rib Interfaces to Reduce Fuselage Eccentric Loading

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Solution Overview

Problem

Existing fuselage sections with flat surfaces for wing rib interfaces lead to eccentric loading, increased weight, and unfavorable airflow characteristics due to abrupt surface transitions, necessitating additional structural components and higher costs.

Innovation Solution

Implementing fuselage sections with tapered wing rib interfaces and blended contours to achieve smoother geometric and surface transitions, reducing eccentric loading and improving aerodynamic efficiency.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Shape

If a flat portion is used in the fuselage cross section to align with the wing rib, then the wing rib interface alignment is improved, but eccentric loading increases and structural components must be added to alleviate the loading

Engineering Contradiction:

Improvefuselage cross section shapeVSAvoideccentric loading

Core Design Contradiction:

ShapeVSStrength

Solution Approach 1:

The patent replaces the conventional flat fuselage cross-section portion with a curved surface that is tangent to the wing rib. This curvature allows the fuselage skin to smoothly blend with the wing rib without requiring a flat portion, thereby eliminating eccentric loading while maintaining proper alignment and load transmission.

Inventive Principle:

Principle #14Spheroidality (Curvature)

2Shape

If a flat portion is used in the fuselage cross section to align with the wing rib, then the wing rib interface alignment is improved, but the weight and labor increase due to additional structural components

Engineering Contradiction:

Improvefuselage cross section shapeVSAvoidfuselage weight

Core Design Contradiction:

ShapeVSWeight of moving object

Solution Approach 1:

The curved fuselage cross-section eliminates the need for additional reinforcing structural components that would be required with a flat portion design. By using a tangent curved surface, the fuselage skin itself provides adequate structural support, reducing overall weight while maintaining alignment with the wing rib.

Inventive Principle:

Principle #14Spheroidality (Curvature)

3Shape

If blending wing-to-fuselage surfaces with the flat portion is performed, then the surface alignment is improved, but abrupt surface transitions occur causing unfavorable airflow characteristics

Engineering Contradiction:

Improvesurface alignmentVSAvoidairflow characteristics

Core Design Contradiction:

ShapeVSObject-generated harmful factors

Solution Approach 1:

The curved fuselage cross-section with tangent surface to the wing rib creates smooth, continuous surface transitions instead of abrupt changes. This curvature eliminates sharp edges and discontinuities that would cause unfavorable airflow characteristics, thereby improving aerodynamic performance.

Inventive Principle:

Principle #14Spheroidality (Curvature)

4Object-generated harmful factors

If a tapered wing rib interface is implemented, then aerodynamic performance is improved by minimizing drag, but the manufacturing complexity increases

Engineering Contradiction:

Improvedrag coefficientVSAvoidfuselage section manufacturing

Core Design Contradiction:

Object-generated harmful factorsVSEase of manufacture

Solution Approach 1:

The patent employs a tapered wing rib interface where the fuselage cross-section transitions from a larger diameter at the wing rib location to a smaller diameter forward. This parameter change creates a tangent curved surface that provides smooth aerodynamic transitions, minimizing drag while the taper itself simplifies the blending process compared to creating complex curved surfaces from flat portions.

Inventive Principle:

Principle #35Parameter changes

Data Source

PatentEP3805092B1Fuselage sections having tapered wing rib interfaces

Publication Date: 2026.01.07 THE BOEING CO

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AI summary

Fuselage sections (300) having tapered wing rib interfaces (306) are disclosed. A disclosed example apparatus includes a rib (306) associated with a fuselage section (300), and a wing interface surface defined by the rib (306), where the wing interface surface is tapered relative to a longitudinal axis (330) of the fuselage section from an aft end of the fuselage section (300) to a fore end of the fuselage section (300).