Segmented Aircraft Fuselage Component with Mesh and Solid Sections
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Solution Overview
Problem
Current structural components for aircraft and spacecraft are heavy, leading to increased fuel consumption and costs, while maintaining sufficient rigidity remains a challenge.
Innovation Solution
The development of a structural component with a combination of solid and mesh-like sections, optimized using computer-based systems and additive manufacturing techniques, where mesh sections are used in low-load areas and solid sections in high-load areas to achieve optimal stiffness and weight balance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If solid sections are used throughout the structural component, then strength and rigidity are improved, but weight increases
Solution Approach 1:
The patent applies local quality by differentiating between solid sections and mesh sections within the same structural component. Solid sections are positioned in high-load areas where maximum strength is required, while mesh sections are used in low-load areas where full solid construction would be excessive. This localized differentiation optimizes the strength-to-weight ratio by providing material only where structurally necessary.
Solution Approach 2:
The structural component is segmented into distinct solid sections and mesh sections rather than using a uniform construction throughout. This segmentation allows each region to be optimized for its specific functional requirements, with solid portions providing strength where needed and mesh portions reducing weight where full solidity is not required.
2Weight of moving object
If mesh sections are used throughout the structural component, then weight is reduced, but rigidity decreases
Solution Approach 1:
The patent implements local quality by strategically placing solid sections in high-load areas where rigidity is critical, while using mesh sections only in low-load areas where weight reduction is prioritized. This ensures that rigidity is maintained where structurally necessary while achieving weight reduction where possible.
Solution Approach 2:
The component is segmented into solid and mesh sections, with solid sections positioned to provide structural rigidity in critical areas. This segmentation allows the structure to maintain adequate rigidity through strategic solid portions while achieving overall weight reduction through mesh sections in non-critical areas.
3Weight of moving object
If complex optimized designs with mixed solid and mesh sections are implemented, then weight and fuel consumption are reduced, but manufacturing complexity increases
Solution Approach 1:
The patent merges the solid sections and mesh sections into a single integrally formed structural component using additive manufacturing. This combining approach eliminates the need for separate manufacturing and assembly processes for different sections, reducing manufacturing complexity despite the complex geometry. The integral construction allows the mixed solid-mesh design to be produced as one piece, simplifying production.
4Use of energy by moving object
If integrally formed mixed solid and mesh sections are used, then fuel consumption is reduced, but manufacturing precision requirements increase
Solution Approach 1:
The patent replaces traditional mechanical manufacturing methods with additive manufacturing technology. This substitution enables the precise creation of complex mixed solid-mesh geometries that would be difficult or impossible to achieve with conventional machining or assembly processes. The additive process inherently provides the required manufacturing precision for the integrally formed component with its varying section densities.
Data Source
AI summary
A structural component for reinforcing the fuselage of an aircraft or spacecraft is integrally formed and segmented into surface-like stiffening sections, whereby at least one stiffening section is formed as a rigid mesh section, and at least one stiffening section is formed as a solid section.