Removable Compression Energy Absorber for Aircraft Structures
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Solution Overview
Problem
Existing aircraft compression energy absorption systems are inefficient in absorbing large amounts of energy, leading to increased aircraft mass and complexity, and lack a removable attachment system to minimize impact on surrounding elements.
Innovation Solution
An aircraft equipped with a removable compression energy absorption device featuring independent compression energy absorption modules connected via a Z-shaped attachment system, allowing for efficient energy absorption and easy assembly/disassembly without modifying the surrounding elements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If a dedicated fairing with complex shape is used to immobilize the honeycomb structure for energy absorption, then energy absorption capability is improved, but aircraft mass increases and consumption increases
Solution Approach 1:
The compression energy absorption device is divided into multiple independent honeycomb structures (first, second, and third honeycomb structures) that can be separately positioned and configured. Each honeycomb structure acts as an independent energy absorption unit, allowing optimized distribution without requiring a single complex dedicated fairing structure.
Solution Approach 2:
The invention uses existing aircraft structural elements (fuselage, tank, ventral fairing) that serve both their primary functions and act as mounting surfaces or boundaries for the compression energy absorption device. The attachment system connects to these existing structures, making them multi-functional without adding dedicated complex fairing structures.
2Loss of energy
If a compression energy absorption device with fixed attachment is used, then energy absorption is improved, but the complexity of the device and difficulty of maintenance increase
Solution Approach 1:
The attachment system uses removable connections (bolts, screws, or other detachable fasteners) that allow the compression energy absorption device to be easily assembled and disassembled. This dynamic attachment system replaces fixed permanent connections, enabling maintenance and replacement without complex operations.
Solution Approach 2:
The device is segmented into multiple independent honeycomb structures that can be attached separately to different aircraft elements. This modular segmentation simplifies the overall attachment system compared to a single complex fixed connection, and allows individual components to be replaced independently.
3Strength
If the compression energy absorption device is integrated with surrounding elements, then structural efficiency is improved, but the impact on surrounding elements increases
Solution Approach 1:
The attachment system acts as an intermediary between the compression energy absorption device and the surrounding aircraft elements (fuselage, tank, ventral fairing). This intermediary connection allows the device to be securely attached for structural efficiency while enabling easy removal to prevent lasting impact or damage to the surrounding elements.
Solution Approach 2:
The removable attachment system provides a dynamic connection that can be engaged when structural support is needed and disengaged when maintenance or replacement is required. This dynamic nature allows the device to provide structural efficiency during operation without permanently impacting the surrounding elements.
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 limits the impact of the compression energy absorption device on surrounding elements, enhances energy absorption capabilities, and simplifies the design by allowing for modular installation and removal.
Implementation Method 1
configured to be subjected to compression forces oriented in a compression direction
Implementation Method 2
at least one compression energy absorption module which comprises several first conduits oriented in the compression direction
Data Source
Figure 1
Figure 2
Figure 3
AI summary
The invention relates to an aircraft comprising first and second elements (32, 34) spaced apart from each other as well as at least one compression energy absorption device, positioned between the first and second elements (32, 34), comprising at least one compression energy absorption module (30) as well as at least one attachment system (48) removably connecting each compression energy absorption module (30) to at least one element among the first and second elements (32, 34), at least one compression energy absorption module (30) comprising several first conduits (36) oriented in a compression direction (DC) and being independent of the first and second elements (32, 34).