Fuselage Structural Interfaces for Variable Tail Configurations
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Solution Overview
Problem
Current aircraft fuselage designs require significant modifications when changing the size, shape, or sweep angles of vertical tails, horizontal tails, or canards, leading to high costs and inefficiencies in redesigning structural interfaces.
Innovation Solution
The aircraft fuselage is designed with multiple interchangeable structural interfaces for vertical, horizontal, and canard tails, allowing for connection of tails of different sizes and configurations without requiring extensive redesign, by providing multiple front and rear structural interfaces along the fuselage's crown and centerline.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the fuselage is designed with traditional single structural interfaces for vertical tail and horizontal tail, then the structural design is simple, but significant modifications are required when changing tail size, shape, or sweep angles
Solution Approach 1:
The fuselage is designed with multiple structural interfaces (first and second front vertical structural interfaces, first and second rear vertical structural interfaces, first and second front horizontal structural interfaces, first and second rear horizontal structural interfaces) that can accommodate different vertical tail and horizontal tail configurations. These interfaces are positioned at different locations along the fuselage (crown, centerline, side of body) to provide universal compatibility with various tail sizes, shapes, and sweep angles without requiring fuselage modifications.
Solution Approach 2:
The structural interface system is segmented into multiple discrete connection points distributed along the fuselage length. By dividing the interface system into separate front and rear vertical interfaces and front and rear horizontal interfaces at different longitudinal positions, the design enables selective configuration of tail components without redesigning the entire fuselage structure.
2Adaptability or versatility
If the fuselage includes multiple interchangeable structural interfaces for different tail configurations, then adaptability to various tail sizes and shapes is improved, but the structural complexity of the fuselage increases
Solution Approach 1:
The multiple structural interfaces are designed with universal compatibility to accommodate different vertical tail and horizontal tail configurations. Each interface type (front vertical, rear vertical, front horizontal, rear horizontal) is positioned to work with specific tail geometries, allowing the same fuselage to support multiple tail configurations without modification.
Solution Approach 2:
The structural interfaces are distributed across multiple spatial dimensions along the fuselage - vertically at the crown, horizontally at the centerline, and laterally at the side of body. This multi-dimensional arrangement allows different tail configurations to be accommodated by selecting appropriate interfaces from different spatial locations rather than increasing complexity within a single plane.
3Ease of manufacture
If traditional structural interfaces are used for connecting tails to fuselage, then manufacturing costs are lower, but redesign costs increase when changing tail configurations
Solution Approach 1:
The fuselage is manufactured with multiple structural interfaces pre-positioned at different locations (crown, centerline, side of body) during the initial build. This preliminary inclusion of multiple interface options eliminates the need for subsequent redesign and modification work when tail configurations need to be changed, saving significant time and resources in later stages.
Solution Approach 2:
The multiple structural interfaces are designed to be universally compatible with different tail configurations from the outset. This universal design allows the same fuselage structure to accommodate various vertical tail and horizontal tail configurations without requiring costly redesign or custom manufacturing for each tail type.
4Device complexity
If structural interfaces are positioned only at traditional locations (crown for vertical tail, centerline for horizontal tail), then the structural design is simplified, but the ability to accommodate different tail configurations is limited
Solution Approach 1:
The interface system is segmented into multiple discrete connection points at different longitudinal and lateral positions along the fuselage. By dividing the interface locations into front and rear vertical interfaces and front and rear horizontal interfaces, the design provides flexibility to accommodate different tail configurations while maintaining relatively simple individual interface structures.
Solution Approach 2:
Structural interfaces are positioned across multiple spatial dimensions - vertically at the crown, horizontally at the centerline, and laterally at the side of body. This multi-dimensional distribution of interfaces provides tail configuration flexibility without requiring complex individual interface designs, as each interface remains relatively simple but the system as a whole gains adaptability.
Data Source
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AI summary
An aircraft (10) includes a fuselage (17) with structural interfaces for connection to any one or more of a variety of vertical tails, horizontal tails and canards. Vertical tails, horizontal tails and/or canards of different sizes, shapes, sweep angles, box chords, and/or root chords may connect to the fuselage (17) without changing the structural layout or configuration of the fuselage (17) structural interfaces.