Vortex Generator Shape Memory Alloy Actuation
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Solution Overview
Problem
Conventional vortex generators on aircraft are static and remain deployed during cruise phases, causing drag penalties even when not needed.
Innovation Solution
A vortex generator system utilizing shape memory alloys (SMAs) for actuation, allowing the vane to be stowed and deployed selectively based on ambient and flight conditions via thermal activation, using a combination of linear and rotary actuators and a control module for dynamic adjustment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional vortex generators are maintained in deployed position during cruise phase, then flight performance is improved during take-off and landing, but drag penalty increases during cruise
Solution Approach 1:
The vortex generator vane is transformed from a static component to a dynamic one through the integration of shape memory alloy actuators. The vane can now rotate between deployed and stowed positions based on flight phase, allowing it to adapt its configuration rather than remaining fixed in one position throughout all flight conditions
Solution Approach 2:
The system changes the operational parameter of the vane from a fixed deployed state to a variable state that can be positioned at different angles (deployed or stowed) based on thermal activation of the shape memory alloy actuators in response to flight condition signals
2Productivity
If static vortex generators are always deployed, then aircraft efficiency is improved during take-off and landing, but energy loss increases during cruise phase
Solution Approach 1:
The vortex generator system transitions from a static always-deployed configuration to a dynamic system that adjusts its state based on flight phase requirements, using shape memory alloy actuators to rotate the vane between deployed and stowed positions
Solution Approach 2:
The system implements parameter changes by thermally activating shape memory alloy actuators to reposition the vane, transitioning from a fixed deployed state to a variable configuration that optimizes energy efficiency across different flight conditions
3Object-generated harmful factors
If vortex generators are made movable with actuators, then drag is reduced during cruise, but device complexity increases
Solution Approach 1:
The complex control system is extracted and integrated into the shape memory alloy actuators themselves, which inherently provide the actuation mechanism without requiring separate motors, linkages, or control electronics at the vane location
Solution Approach 2:
The shape memory alloy actuators are self-actuating through thermal activation from Joule heating, eliminating the need for complex mechanical actuation systems. The actuators automatically respond to electrical signals by changing their shape through thermal effects, providing self-service actuation
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 reduces drag by stowing the vortex generator when not needed, enhancing flight efficiency by dynamically deploying it in response to flight conditions, thereby optimizing performance.
Implementation Method 1
thermal activation via one or more of joule heating, conduction, and induction
Implementation Method 2
The actuator, composed of a shape memory alloy (SMA), is operatively connected to the vane
Implementation Method 3
thermal activation via one or more of joule heating, conduction, and induction
Implementation Method 4
thermal activation via one or more of joule heating, conduction, and induction
Data Source
AI summary
A vortex generator, includes a vane, mountable on an aerodynamic surface of an aircraft, and an actuator that rotates the vane between a stowed position and a deployed position. The actuator includes a linear actuator, composed at least in part of a shape memory alloy (SMA), that when thermally activated facilitates rotation of the vane between the stowed position to the deployed position. Thermal activation of the SMA is caused via one or more of joule heating, conduction, and induction in response to one or more of an electronic command signal and a wireless command signal. The electronic command signal and the wireless command signal may be transmitted in response to ambient conditions, aircraft flight conditions, and aircraft mission.