Composite Energy-Absorbing Beam for Aircraft Fuselage Impact
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Solution Overview
Problem
Aircraft fuselage structures made of composite materials face challenges in energy absorption during vertical impact scenarios, as they lack a significant plastic deformation domain and the behavior of existing energy-absorbing systems is difficult to control and predict, potentially leading to premature damage to other structures.
Innovation Solution
Incorporating energy-absorbing structural elements with a compression beam made of composite material, attached to fuselage frames and crossmembers via a gusset plate that includes guide means, a cutting element, and clearance grooves, designed to absorb and dissipate energy by progressive destruction along the longitudinal axis during impacts.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If composite materials are used for fuselage structure, then weight is reduced, but energy absorption capability deteriorates
Solution Approach 1:
The fuselage structure is segmented into load-bearing composite components and dedicated energy-absorbing elements. The energy-absorbing elements are further segmented into multiple beams arranged in parallel, allowing controlled progressive collapse while the main fuselage structure maintains its integrity for weight savings.
Solution Approach 2:
Dedicated energy-absorbing elements are introduced as intermediary components between the floor and the lower fuselage frames. These intermediaries absorb impact energy through controlled collapse, protecting the main composite fuselage structure from direct impact loads.
2Strength
If dedicated energy-absorbing elements are added, then energy absorption is improved, but device complexity increases
Solution Approach 1:
The energy-absorbing elements use the same composite material as the main fuselage structure, ensuring uniform material properties and simplifying manufacturing. The homogeneous material approach reduces the number of different material types and associated joining complexities.
Solution Approach 2:
The energy-absorbing elements are integrated into the existing fuselage framework by attaching them to floor crossmembers and lower fuselage frames. This merging approach incorporates the energy absorption function into the existing structural layout without requiring completely separate systems.
3Productivity
If composite material structure is used, then manufacturing efficiency is improved, but controllability of energy absorption deteriorates
Solution Approach 1:
The design parameters of the energy-absorbing beams (cross-sectional dimensions, stacking sequence, gauge points) are carefully controlled to ensure predictable collapse behavior. By adjusting these parameters, the collapse load and energy absorption characteristics can be precisely tailored while maintaining compatibility with composite manufacturing processes.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution effectively absorbs and dissipates energy during impacts, improving the structural response to vertical loads and enhancing passenger safety by controlled progressive collapse of the energy-absorbing elements, reducing the risk of premature damage to other aircraft components.
Implementation Method 1
unlike structural elements made of metallic materials which have a large plastic deformation domain before yielding, composite materials have practically no plastic domain before yielding
Implementation Method 2
a structure made of composite material will restore a large proportion of the energy absorbed during elastic deformation
Implementation Method 3
a cutting element for cutting the compression beam into at least two strips, in the direction of the longitudinal axis Z
Implementation Method 4
guide means for guiding the beam substantially along its longitudinal axis Z
Data Source
AI summary
An aircraft fuselage has at least one reinforcement frame (13), at least one crossbar (14) and at least one energy-absorbing structural element (2) that includes a compression beam (21) having a longitudinal axis Z and oriented substantially in the direction of compression forces to be absorbed upon an impact, the compression beam being attached at a first end (213) thereof to the crossbar (14) and at a second end (214) thereof to the reinforcement frame (13). The compression beam (21) is attached at least one of its ends (213, 214) via a shoulder bracket (22), wherein the shoulder bracket further has the function of cutting the compression beam (21) in case of an impact.