Airfoil Tip Plasma Actuation for Wake Vortex Breakdown
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Solution Overview
Problem
Existing passive flow-control devices for dissipating tip vortices on aircraft wings and helicopter blades are ineffective and adversely affect overall rotor performance.
Innovation Solution
Employing active flow control methods using fan-shaped and serpentine plasma actuators positioned on the airfoil surfaces to generate vortices that counteract and break down tip vortices, reducing their strength and duration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If passive flow-control devices are used to dissipate tip vortices, then tip vortex dissipation is achieved, but rotor performance deteriorates
Solution Approach 1:
The patent replaces passive mechanical flow-control devices with active plasma actuators that use electrohydrodynamic forces to generate counter-vortices. This substitution allows for dynamic control of tip vortex dissipation without the performance penalties associated with passive mechanical devices, resolving the contradiction between vortex dissipation and rotor performance maintenance.
Solution Approach 2:
The patent changes the physical state and control parameters by using plasma actuators that can dynamically adjust their output based on flight conditions. This allows optimization of vortex dissipation effectiveness while minimizing impact on rotor performance, unlike fixed passive devices that operate suboptimally across varying conditions.
2Object-generated harmful factors
If conventional plasma actuators are used, then tip vortex reduction is achieved, but device complexity increases
Solution Approach 1:
The patent divides the airfoil surface into multiple discrete actuator locations (leading edge, trailing edge, tip regions) with each plasma actuator independently controlled. This segmentation allows targeted vortex control at specific locations without requiring a complex integrated system, reducing overall device complexity while maintaining effectiveness.
Solution Approach 2:
The patent employs plasma actuators that can serve multiple functions: generating counter-vortices for tip vortex dissipation, controlling boundary layer flow, and potentially reducing drag. This multi-functionality reduces the need for separate dedicated devices for each function, thereby reducing overall system complexity.
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
Effectively dissipates tip vortices, improving aircraft safety by minimizing wake turbulence and reducing noise, while maintaining rotor performance.
Implementation Method 1
fan-shaped plasma actuators positioned on an end surface of a tip of one or more airfoils of an aircraft
Data Source
AI summary
The present disclosure presents systems, apparatuses, and methods of active flow controls for dissipating tip vortices. In this regard, a method comprises positioning one or more fan-shaped plasma actuators on an end surface of a tip of one or more airfoils of an aircraft, wherein the fan-shaped plasma actuators are surface compliant with the surface of the tip of the one or more airfoils; and activating the one or more fan-shaped plasma actuators during a flight of the aircraft, wherein at least one tip vortex generated by a flight of the aircraft is reduced by an introduction of one or more vortices generated by the one or more fan-shaped plasma actuators on the end surface of the tip of the one or more airfoils of the aircraft. Other systems, apparatuses, and methods are also presented.