Aircraft Flap Deployment System Impact Protection
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Solution Overview
Problem
Current flap deployment systems in aircraft are prone to fuel tank leaks when an impact load is applied to the bottom portion, as fasteners connecting the system to the wing rear spar can fail, compromising the integrity of the fuel tank.
Innovation Solution
A collapsible flap deployment system designed to absorb impact by using shear pins and strategically positioned fasteners that fail before those connecting the fuel tank, allowing the support and carrier beams to rotate away from the rear spar, thereby protecting the fuel tank.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If fasteners connect the flap deployment system to the wing rear spar, then the system achieves structural strength and stability, but the fuel tank may leak upon impact load application
Solution Approach 1:
The fastening system is divided into two distinct groups: first fasteners that connect the support beam to the rear spar and penetrate the fuel tank, and second fasteners that connect the carrier beam to the support beam and are positioned outside the fuel tank. This segmentation allows the second fasteners to fail first upon impact, preventing fuel tank damage while maintaining the structural integrity provided by the first fasteners.
Solution Approach 2:
The second fasteners are pre-positioned outside the fuel tank and designed with lower strength characteristics than the first fasteners. Upon impact load application, these second fasteners are intended to fail first as a preliminary protective action, sacrificing themselves to prevent the more critical first fasteners from failing and compromising the fuel tank integrity.
2Stability of the object's composition
If the support beam and carrier beam are rigidly connected to the rear spar, then the flap deployment system achieves stability during operation, but the system cannot collapse to protect the fuel tank upon impact
Solution Approach 1:
The connection system transitions from a static rigid connection to a dynamic progressive failure system. During normal operation, all fasteners maintain rigid connections providing stability. Upon impact, the system dynamically progresses through failure stages: second fasteners fail first, allowing controlled collapse, then first fasteners fail if necessary, maximizing fuel tank protection while maintaining operational stability during normal use.
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 system effectively prevents fuel tank leaks by ensuring that the fasteners outside the tank fail first, allowing the support and carrier beams to rotate and apply a bending force that causes the critical fasteners to fail, thus releasing the flap deployment components from the rear spar, ensuring the fuel tank remains intact.
Implementation Method 1
The first fuse pin is configured to shear upon the application of a first predetermined force
Implementation Method 2
The second plurality of fasteners may be configured to fail upon the application of a second predetermined bending force
Data Source
AI summary
A collapsible flap deployment system for an aircraft wing that includes a support beam pivotably connected to a carrier beam, which is connected to a wing flap. A rear spar fitting is connected to a wing rear spar by a first plurality of fasteners and a second plurality of fasteners connects the support beam to the rear spar fitting. A fuse pin connects a link to the rear spar fitting. The fuse pin is configured to shear upon the application of a first predetermined force. An impact load to the bottom of the support beam puts the link into compression applying a force to the fuse pin until the fuse pin shears releasing the link from the rear spar fitting. The impact load rotates the support beam and carrier beam causing the second plurality of fasteners to fail releasing the support beam and carrier beam from the wing rear spar.