Integrated Aircraft Fuselage Frame with Lateral Extensions
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aircraft fuselage structures require complex and weight-increasing modifications to integrate lifting surfaces, such as wings and pylons, which disrupt load distribution and complicate assembly due to discontinuities in the fuselage skin and structural elements.
Innovation Solution
A novel fuselage frame design featuring a central element with lateral extensions that form an integrated, continuous structure with lifting surfaces, eliminating the need for separate junctions and allowing for a single-panel manufacturing of the skin and frames, thereby simplifying assembly and reducing weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If traditional separate junctions are used to integrate lifting surfaces with fuselage, then assembly complexity increases and weight increases, but structural integrity can be maintained
Solution Approach 1:
The frame is designed as an integrated piece that combines the fuselage frame structure with the lifting surface structure. The central element and lateral extensions form a single continuous structure that eliminates separate junctions, reducing assembly complexity while maintaining structural integrity through the unified design.
Solution Approach 2:
The integrated frame structure performs multiple functions simultaneously: it provides longitudinal reinforcement for the fuselage, supports the lifting surface, and eliminates the need for separate junction components. This multi-functionality reduces both assembly complexity and overall weight.
2Adaptability or versatility
If discontinuities are introduced in fuselage skin and structural elements to integrate lifting surfaces, then load distribution is disrupted, but integration flexibility is improved
Solution Approach 1:
The frame integrates the lifting surface support function directly into the fuselage structure without creating discontinuities. The central element and lateral extensions form a continuous load path that maintains load distribution efficiency while providing flexible integration of the lifting surface.
3Strength
If multiple tension bolts and shear rivets are used to join lateral boxes to fuselage, then connection strength is improved, but manufacturing and assembly complexity increases
Solution Approach 1:
The frame is manufactured as a single integrated piece, eliminating the need for multiple fasteners such as tension bolts and shear rivets. The unified structure provides inherent connection strength while dramatically simplifying manufacturing and assembly processes.
4Stability of the object's composition
If central part of pylon is located at centered position of fuselage height, then symmetry is maintained, but internal space availability is reduced
Solution Approach 1:
The lateral extensions are positioned at upper or lower locations relative to the central element, utilizing vertical space differently. This positioning maintains structural symmetry while creating additional internal space in the fuselage by moving the lifting surface attachment points away from the central height position.
Data Source
AI summary
An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.