Shape Memory Alloy Boundary Layer Control Device
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Composite materials used in aircraft structures are sensitive to extreme temperatures generated by engines, leading to inconsistencies that reduce aerodynamic efficiency and require frequent maintenance.
Innovation Solution
A boundary layer control device with a shape memory alloy articulating portion that deploys when exposed to high temperatures, increasing the thickness of the boundary layer to deflect the heat flow field away from the aircraft structure, thereby maintaining aerodynamic efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If composite materials are used to decrease aircraft weight, then payload capacity and fuel efficiency are improved, but the aircraft structure becomes more sensitive to extreme temperatures from engines
Solution Approach 1:
A boundary layer control device is introduced as an intermediary element between the heat flow field and the composite aircraft structure. This device manipulates the boundary layer to increase the distance between the heat source and the composite material, thereby protecting the temperature-sensitive composite structure while maintaining the weight benefits of composite materials
Solution Approach 2:
The invention changes the parameter of boundary layer thickness dynamically. By increasing the boundary layer thickness near the aircraft structure, the effective distance between the heat flow field and the composite material is increased, reducing thermal exposure to the temperature-sensitive composite components
2Object-affected harmful factors
If the boundary layer thickness is increased to deflect heat flow field, then the distance of heat flow field from aircraft structure is increased, but the device complexity increases
Solution Approach 1:
The boundary layer control device utilizes the natural thermal environment to activate itself. When exposed to high temperatures, the shape memory alloy material automatically changes its shape to deploy the boundary layer control structure, eliminating the need for external sensors, actuators, or control systems. The device serves itself by using the harmful heat exposure as the activation mechanism
Solution Approach 2:
The invention employs shape memory alloy material that changes its physical parameter (shape) in response to temperature changes. This automatic parameter change allows the device to deploy when needed without complex control systems, reducing overall device complexity while still achieving the goal of increasing boundary layer thickness to deflect heat
3Extent of automation
If shape memory alloy is used for automatic deployment, then the extent of automation is improved, but the manufacturing precision requirements increase
Solution Approach 1:
The invention leverages the inherent property of shape memory alloy materials to change shape in response to temperature. By carefully selecting the alloy composition and heat treatment parameters during manufacturing, the material is programmed to deploy at specific temperature thresholds, achieving automation while managing manufacturing precision through material science rather than mechanical tolerances
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 manages heat exposure to aircraft structures, reducing temperature-induced inconsistencies and the need for maintenance by automatically adjusting the boundary layer thickness to maintain a safe distance from heat sources.
Implementation Method 1
The articulating portion is comprised of a shape memory alloy that moves from a stowed position towards a deployed position when the heat flow field flows over the articulating portion and the temperature of the articulating portion exceeds a threshold temperature
Implementation Method 2
A thickness of a boundary layer for the aircraft structure increases in a manner that increases a distance of a heat flow field from the aircraft structure
Data Source
AI summary
A method and apparatus for a boundary layer control device located relative to an aircraft structure. The boundary layer control device has a stowed position and a deployed position. The boundary layer control device moves from the stowed position to the deployed position. A thickness of a boundary layer for the aircraft structure increases in a manner that increases a distance of a heat flow field from the aircraft structure during operation of the aircraft.