Pulsed DC Plasma Actuator for Aerodynamic Flow Control
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Solution Overview
Problem
Existing dielectric barrier discharge (DBD) plasma actuators for flow control, particularly those using alternating current (AC), face inefficiencies due to asymmetrical electron source behavior and voltage dependencies, limiting their aerodynamic control effectiveness.
Innovation Solution
A pulsed direct current (DC) plasma actuator design with staggered electrodes and a dielectric barrier, utilizing a solid-state switch to deliver micro-pulses, which enhances force generation and efficiency by eliminating the reversing electron cycle and optimizing plasma distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If AC voltage is used to drive the plasma actuator, then the electrodes can be supplied with alternating current to cause weak ionization of air, but the asymmetrical electron source behavior and reversing electron cycle reduce aerodynamic control effectiveness
Solution Approach 1:
The patent applies periodic pulsed DC action instead of continuous AC action. The solid state switch delivers micro-pulses of DC voltage to the electrodes, creating plasma only during the pulse duration. This periodic activation eliminates the reversing electron cycle inherent in AC operation, improving aerodynamic control effectiveness while maintaining energy efficiency through duty cycle control.
Solution Approach 2:
The patent changes the electrical input parameter from AC voltage to pulsed DC voltage. By using DC voltage applied in pulses rather than AC voltage, the electron source behavior becomes symmetrical and non-reversing, directly addressing the technical problem of asymmetrical electron source behavior reducing control effectiveness.
2Force
If AC plasma actuator is used, then the electrodes are supplied with AC voltage causing weak ionization, but thrust generation is limited and non-linear with voltage
Solution Approach 1:
The patent changes the electrical parameter from AC voltage to pulsed DC voltage, which fundamentally alters the plasma generation mechanism. This parameter change results in linear thrust generation proportional to the DC voltage magnitude, eliminating the non-linearity and voltage dependency limitations of AC operation.
Solution Approach 2:
The pulsed DC operation allows for controlled periodic plasma generation where the thrust output becomes linearly proportional to the pulse voltage. The periodic switching enables precise control over the plasma generation process, improving thrust generation efficiency compared to continuous AC operation.
3Power
If pulsed DC micro-pulses are delivered using a solid state switch, then force generation is enhanced and efficiency is improved, but device complexity increases
Solution Approach 1:
The patent replaces mechanical or complex control systems with a solid state switch that can be controlled by simple electrical signals. The solid state switch enables pulsed DC operation through electrical control rather than mechanical switching, enhancing force generation capability while keeping the control system relatively simple and integrable.
4Adaptability or versatility
If pulsed DC plasma actuator is used, then aerodynamic control is improved particularly in high-pressure environments, but the system requires optimization of plasma distribution
Solution Approach 1:
The patent applies local quality by using staggered electrodes with different configurations to optimize plasma distribution in different regions. The electrode geometry is designed to create uniform plasma distribution across the actuator surface, which is particularly important for high-pressure environment applications where plasma uniformity directly affects aerodynamic control effectiveness.
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 pulsed DC plasma actuator achieves significantly higher thrust levels compared to AC designs, with thrust generation linearly proportional to DC voltage, and demonstrates improved aerodynamic control, particularly in high-pressure environments, while maintaining stability and reducing non-uniformity.
Implementation Method 1
pulsed direct current powering system for a dielectric barrier discharge (DBD) plasma actuator
Implementation Method 2
causes the air over the covered electrode to weakly ionize
Implementation Method 3
The ionized air, in the presence of the electric field produced by the geometry of electrodes, results in a body force vector field that acts on the ambient air
Implementation Method 4
utilizing a solid-state switch to deliver micro-pulses
Data Source
AI summary
A plasma generating device intended to induce a flow in a fluid via plasma generation includes a dielectric separating two electrodes and a power supply. The first electrode is exposed to a fluid flow while the second electrode is positioned under the dielectric. The power supply is electrically coupled to a switch and the first and second electrodes. When the power supply is energized by repeated action of the switch, it causes a pulsed DC current between the electrodes which causes the fluid to ionize generating a plasma. The generation of the plasma induces a force with a velocity component in the fluid.