Deployable Vortex Generators With Superelastic Torsional Springs
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Solution Overview
Problem
Conventional static vortex generators cause interference during flap retraction in modern aircraft with thin wing designs, leading to unnecessary drag and increased fuel consumption, and existing deployable systems face issues with actuation mechanisms that are either costly or aerodynamically inefficient.
Innovation Solution
Deployable vortex generators using superelastic shape memory alloy torsional springs that rotate between stowed and deployed positions in response to aerodynamic loads, allowing for a compact design that minimizes drag and optimizes deployment based on flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If conventional static vortex generators are used, then noise reduction and flow control are improved, but drag increases and fuel consumption increases
Solution Approach 1:
The vortex generator is designed to be dynamically deployable and stowable rather than static. The spring mechanism allows the vortex generator to be deployed during takeoff and landing when noise reduction is needed, and automatically stowed during cruise to minimize drag and fuel consumption.
Solution Approach 2:
The invention changes the operational parameter of the vortex generator from continuously deployed (static) to conditionally deployed (dynamic). By controlling the deployment state based on flight conditions, the system optimizes the balance between noise reduction and fuel efficiency.
2Ease of operation
If conventional static vortex generators are used, then flow control is improved, but interference with flap retraction occurs
Solution Approach 1:
The vortex generator transitions from a static configuration to a dynamic one that can be deployed or stowed based on operational needs. During flap retraction, the vortex generator can be stowed to avoid interference, while still providing flow control when deployed during takeoff and landing.
3Adaptability or versatility
If deployable vortex generators with shape memory alloy actuators are used, then deployment control is improved, but cost increases
Solution Approach 1:
The spring mechanism is designed to be self-actuating through aerodynamic loads and elastic recovery. The vortex generator automatically deploys when aerodynamic forces require it and retracts when not needed, eliminating the need for complex powered actuators and reducing system cost.
Solution Approach 2:
The invention replaces complex powered actuation systems (such as shape memory alloy actuators) with a simpler elastic spring mechanism that uses aerodynamic forces and elastic recovery to achieve deployment and retraction.
4Adaptability or versatility
If deployable vortex generators with torsion springs are used, then deployment capability is improved, but the springs are too large to embed within the wing skin
Solution Approach 1:
The spring mechanism uses superelastic shape memory alloy with transformed martensitic structures that allow for compact storage. The phase transformation enables the spring to be compressed into a small volume within the wing skin while maintaining full deployment capability when activated by aerodynamic 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
The solution reduces noise and drag by deploying vortex generators only when needed, enhancing aircraft performance and reducing fuel consumption without interfering with wing aerodynamics.
Implementation Method 1
a spring operatively coupled to the vane, the spring comprising an elongate tube comprising a superelastic shape memory alloy
Implementation Method 2
The elongate tube is configured to undergo a stress-induced phase transformation as a result of activation of the spring that twists the elongate tube in the first direction
Implementation Method 3
A vortex generator is an aerodynamic device, consisting of a small vane or flap that may be mounted on an aerodynamic surface to create a vortex in air flowing over the surface
Implementation Method 4
A turbulent boundary layer is less likely to separate than a laminar one, and therefore is desirable to ensure effectiveness of trailing-edge control surfaces
Data Source
AI summary
Vortex generators include a vane that rotates between a stowed position and a deployed position. In the deployed position, the vane is configured to reduce noise created by an airflow around or along the aerodynamic surface. A spring controls deployment of the vane and includes an elongate tube formed of a superelastic shape memory alloy. To deploy or stow the vane, the elongate tube is twisted due to a stress-induced response caused by airflow around or along the aerodynamic surface, thereby building up and storing torque in the elongate tube. A mounting base receives the vane when it is in the stowed position, and operatively couples the vortex generator to the aerodynamic surface. To create the torque in the elongate tube, a first end of the elongate tube is fixed with respect to the aerodynamic surface while a second end of the elongate tube is free to rotate.