Freighter Cargo Floor Structure for Composite Wing Load Distribution

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Existing metal freighter aircraft architectures are not compatible with composite wing structures due to increased sensitivity to out-of-plane and highly concentrated loads, which poses a challenge in distributing cargo loads effectively.

Innovation Solution

A cargo floor structure featuring over wing floor beams, intercostals, and a truss box structure that couples with the composite wing's upper skin panel to distribute and shear spanwise loads, reducing out-of-plane and concentrated loads, thereby ensuring compatibility with composite wings.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If a traditional metal freighter architecture is used, then cargo support structure is simple and effective, but it is not compatible with composite wing structures due to increased sensitivity to out-of-plane and highly concentrated loads

Engineering Contradiction:

Improvecompatibility with composite wingsVSAvoidout-of-plane loads and highly concentrated loads

Core Design Contradiction:

Adaptability or versatilityVSObject-affected harmful factors

Solution Approach 1:

The cargo floor structure is divided into multiple components: floor beams extending longitudinally, intercostals extending spanwise, and a truss box structure. This segmentation distributes loads across multiple elements rather than concentrating them, making the structure compatible with composite wings while maintaining effective cargo support.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The truss box structure acts as an intermediary element between the floor beams and the composite wing upper skin panel. It transfers and distributes spanwise loads from the intercostals into the upper skin panel, reducing out-of-plane and highly concentrated loads while maintaining structural compatibility.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Force

If cargo load support is increased for freighter operations, then cargo carrying capacity is improved, but the composite wing structure experiences increased out-of-plane and concentrated loads that may cause damage

Engineering Contradiction:

Improvecargo load support capacityVSAvoidcomposite wing integrity

Core Design Contradiction:

ForceVSStrength

Solution Approach 1:

The load support function is distributed across multiple structural elements including floor beams, intercostals, and a truss box structure. This segmentation allows the system to support increased cargo loads while distributing the forces to prevent damage to the composite wing structure.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The truss box structure introduces a three-dimensional load distribution system that transfers spanwise loads into the upper skin panel. This dimensional approach distributes loads across multiple axes, increasing cargo support capacity while protecting composite wing integrity.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

Data Source

PatentUS11702185B2Freighter configuration for aircraft with composite wings

Publication Date: 2023.07.18 THE BOEING CO

AI summary

Embodiments for commercial freighter configuration for aircraft with composite wings. One embodiment is cargo floor structure for a wing center section of an aircraft. The cargo floor structure includes over wing floor beams extending longitudinally between a rear spar and a front spar of the aircraft. The over wing floor beams are coupled with an upper skin panel of a composite wing. The cargo floor structure also includes intercostals extending spanwise across the over wing floor beams. The intercostals suspended over the upper skin panel of the composite wing. The cargo floor structure also includes a truss box structure disposed between a middle pair of the over wing floor beams and configured to shear a spanwise load from the intercostals into the upper skin panel of the composite wing.