Aircraft Control Link With Redundant Impact-Resistant Load Paths
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Solution Overview
Problem
Existing aircraft control systems have a single point of failure in their control links, which can lead to catastrophic consequences if damaged or failed during flight operations, as they lack redundancy and impact resistance.
Innovation Solution
A redundant impact-resistant control link system is designed with an outer sacrificial structure that absorbs impact damage and an inner structure that maintains flight control functionality, featuring a dual load path where both structures can carry the anticipated loads independently, with optional filling between them to enhance impact resistance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a single control link structure is used, then the device complexity is low, but the reliability is poor due to single point of failure
Solution Approach 1:
The control link is divided into two separate structures: an outer sacrificial structure and an inner load-bearing structure. This segmentation allows the outer structure to absorb impact damage while the inner structure maintains flight control functionality, thereby improving reliability without creating a single point of failure.
Solution Approach 2:
The outer sacrificial structure is designed to absorb impact damage before it reaches the inner load-bearing structure. This beforehand cushioning protects the critical inner structure from impact forces, ensuring continued safe operation even when the outer structure fails.
2Object-affected harmful factors
If an outer sacrificial structure is added to absorb impact, then the impact resistance improves, but the device complexity increases
Solution Approach 1:
The control link is divided into two separate structures: an outer sacrificial structure and an inner load-bearing structure. This segmentation allows the outer structure to absorb impact damage while the inner structure maintains flight control functionality, thereby improving reliability without creating a single point of failure.
Solution Approach 2:
The outer structure is designed as a sacrificial, disposable component that absorbs impact damage and can be replaced after failure. This allows the critical inner structure to be protected, and the outer structure to serve its impact absorption function at lower cost and complexity.
3Reliability
If both outer and inner structures carry anticipated loads independently, then the reliability improves through redundancy, but the weight increases
Solution Approach 1:
The control link is divided into two separate structures: an outer sacrificial structure and an inner load-bearing structure. This segmentation allows the outer structure to absorb impact damage while the inner structure maintains flight control functionality, thereby improving reliability without creating a single point of failure.
Solution Approach 2:
The load distribution parameters are optimized so that the outer sacrificial structure carries a portion of the anticipated loads independently, while the inner load-bearing structure carries the remaining loads. This parameter optimization reduces the total weight compared to having the inner structure carry 100% of the loads.
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
This design ensures continued safe operation of the flight control system even if the outer structure fails, as the inner structure can handle loads independently, providing enhanced safety and reliability by distributing and mitigating impact forces effectively.
Implementation Method 1
The space or cavity between the inner and outer structures may be filled with a material, such as a closed-cell foam, to improve the impact resistance of the outer structure.
Data Source
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AI summary
Control link (600) for an aircraft (101, 201) comprising an impact-resistant structure with a redundant load path. The control link (600) has an inner structure (602) that is sized to carry the anticipated load of the flight control system and to meet all safety factors. The control link (600) also has an outer structure (601) that is sacrificial and configured to absorb impact damage during operation, thereby protecting the inner structure (602). The outer structure (601) is also designed to carry the anticipated load of the flight control system on its own, independent of the inner structure (602), and to meet all safety factors. If the outer structure (601) fails, the inner structure (602) allows for continued safe operation of the flight control system. The space or cavity (604) between the inner and outer structures (601,602) may be filled with a material, such as a closed-cell foam, to improve the impact resistance of the outer structure (601).