Fuselage Collision Load Distribution Through Wing and Rear Structures
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Solution Overview
Problem
Conventional urban air mobility (UAM) systems fail to ensure passenger safety during collisions due to heavy collision loads being transferred to the boarding space, compromising stability and deformation of the fuselage.
Innovation Solution
A collision load distribution structure comprising a front unit, rear unit, support unit, and wing unit that transfers and distributes loads in the length and height directions to minimize deformation and reduce loads in the boarding space, using a support unit to connect these components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional fuselage structure is used, then structure simplicity is maintained, but collision loads are heavily transferred to the boarding space compromising passenger safety
Solution Approach 1:
The fuselage structure is segmented into distinct functional zones: a front unit with roof frames for length-direction load transfer, a rear unit with rear frames for height-direction load transfer, and a support unit with support fitting members to connect these segments. This segmentation allows each zone to specialize in transferring specific load directions away from the boarding space, improving passenger safety while maintaining manageable structural complexity through modular design.
Solution Approach 2:
The support unit acts as an intermediary component between the front unit and rear unit, incorporating support fitting members that connect to wing fitting members. This intermediary structure facilitates load transfer from the fuselage to the wing unit and rear fuselage, distributing collision loads away from the boarding space while maintaining structural integrity without requiring overly complex reinforcement.
2Force
If collision load distribution structure is implemented, then loads are distributed to wing unit and rear part reducing boarding space loads, but structural complexity increases
Solution Approach 1:
The support fitting members within the support unit serve multiple functions: they connect the front unit to the rear unit, interface with the wing unit for load transfer, and provide structural reinforcement. This multi-functionality reduces the need for separate dedicated components for each function, thereby distributing collision loads effectively while minimizing the increase in overall structural complexity.
Solution Approach 2:
The support unit merges the connection between front and rear units with the load transfer mechanism to the wing unit and rear fuselage into a single integrated structure. By combining these functions, the design achieves comprehensive load distribution without requiring multiple separate structural systems, thus controlling complexity while improving force distribution.
Data Source
AI summary
A collision load distribution structure of a fuselage includes a front unit configured to be located at front ends relative to wings attached to the fuselage, a rear unit configured to be located at rear ends relative to the wings attached to the fuselage, a support unit configured to be located between the front unit and the rear unit, and a wing unit. The support unit is configured to transfer loads applied to the fuselage in case of a crash of the fuselage. The wing unit is configured to be located in the support unit, and connected to the support unit so as to transfer the loads in case of the crash of the fuselage. Loads in a length direction of the fuselage are passed through to the front unit, and are distributed to the wing unit through the support unit.