Anisotropic Composite Laminate Design for Aircraft Airframes

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Solution Overview

Problem

The existing methods for designing anisotropic composite laminate structures in aircraft airframes do not fully optimize fiber orientation proportion and stacking sequence, limiting the utilization of anisotropic material properties and resulting in suboptimal weight reduction and structural performance.

Innovation Solution

A method is developed to divide the anisotropic composite laminate structure into regions based on stress directions, determining the fiber orientation proportion and stacking sequence for each region to optimize the laminate configuration, thereby reducing the number of composite layers and achieving lightweight airframes.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If existing design methods are used for anisotropic composite laminate structures, then the design process is simple, but the utilization of anisotropic material properties is not optimized

Engineering Contradiction:

Improveutilization of anisotropic material propertiesVSAvoiddesign process complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The design method segments the composite laminate structure into multiple regions based on stress distribution characteristics. Each region is assigned optimal fiber orientations and stacking sequences independently, allowing tailored optimization of anisotropic material properties for different structural zones while maintaining manageable design complexity through systematic regional classification.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The invention applies local quality by determining specific fiber orientation proportions and stacking sequences for each region according to local stress conditions. This enables each part of the structure to have optimized material properties matching its specific loading environment, maximizing the utilization of anisotropic composite material capabilities.

Inventive Principle:

Principle #3Local quality

2Weight of stationary object

If the number of composite layers is reduced for weight reduction, then weight decreases, but structural performance may be compromised

Engineering Contradiction:

Improveairframe weightVSAvoidstructural performance

Core Design Contradiction:

Weight of stationary objectVSStrength

Solution Approach 1:

The method optimizes structural performance by precisely controlling fiber orientation proportions and stacking sequences in each region. This parameter optimization allows the structure to achieve required strength and stiffness with fewer composite layers, thereby reducing weight while maintaining structural performance through enhanced material utilization efficiency.

Inventive Principle:

Principle #35Parameter changes

Data Source

PatentUS11745445B2Method of designing anisotropic composite laminate structure

Publication Date: 2023.09.05 SUBARU CORP

AI summary

A method of designing an anisotropic composite laminate structure to constitute a predetermined member of an airframe structure of an aircraft and includes a plurality of types of composite layers containing reinforcing fibers with different fiber orientations is provided. The method includes dividing the anisotropic composite laminate structure in the predetermined member into a plurality of regions in a thickness direction. The method includes determining, for each of the regions, at least a stacking sequence of the plurality of types of composite layers in accordance with a direction of stress acting on the predetermined member.