Solid State Supersonic Flow Actuator Using Plasma Discharge
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Solution Overview
Problem
Existing flow control actuators for aerospace applications, particularly for supersonic flows, face limitations in operating frequency and momentum flux, with mechanical and synthetic jet actuators requiring complex auxiliary equipment and suffering from fatigue and limited frequency due to moving parts and small piezo-electric diaphragm constraints.
Innovation Solution
A repetitive spark micro-actuator (RSMA) device that uses electrical discharges to create plasma and expel air at high velocities without moving aerodynamic structures, achieving sonic or supersonic exhaust velocities and higher momentum throughput, and is a zero net mass flux device, eliminating the need for a fuel source and reducing weight and complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If piezoelectric diaphragms are made smaller to achieve higher oscillation frequency, then frequency is improved, but momentum flux and displacement are reduced
Solution Approach 1:
The patent replaces the mechanical piezoelectric diaphragm system with an electrical discharge-based plasma actuation system. Electrical discharges create plasma that heats and expands gas, generating thrust without mechanical moving parts. This substitution enables higher frequencies without the mass and displacement limitations of piezoelectric materials.
Solution Approach 2:
The patent changes the operating parameters by using electrical discharges to create plasma, which fundamentally alters how the actuator generates thrust. Instead of mechanical oscillation, the system uses thermal expansion from plasma heating to drive gas flow, achieving both high frequency and sufficient momentum flux.
2Quantity of substance
If combustion-driven jet actuators are used to achieve high momentum flux, then momentum flux is improved, but device complexity and auxiliary equipment requirements increase
Solution Approach 1:
The patent extracts and eliminates the complex auxiliary systems required for combustion actuators (fuel storage, pumping, metering, ignition timing devices) by using a simplified electrical discharge-based plasma actuation system. The core function of generating thrust is achieved through direct electrical energy conversion to thermal and kinetic energy.
Solution Approach 2:
The patent replaces the mechanical combustion system with an electrical discharge system. Instead of burning fuel to generate thrust, the system uses electrical discharges to create plasma, which directly heats and expands gas to produce the required momentum flux without mechanical moving parts or auxiliary equipment.
3Ease of operation
If mechanical actuators with moving parts are used, then flow control capability is achieved, but reliability decreases due to fatigue
Solution Approach 1:
The patent replaces mechanical actuators with moving parts with a solid-state plasma actuation system. Electrical discharges create plasma that directly interacts with the gas flow to generate control forces, eliminating mechanical components that would fatigue and fail. The system maintains flow control capability through direct electromagnetic-thermal-gas interaction.
Solution Approach 2:
The plasma actuator system is self-contained with no external moving parts. The electrical discharge system automatically creates plasma, heats the gas, and generates thrust without requiring external mechanical actuation or auxiliary systems, thereby achieving both operational capability and high reliability.
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 RSMA device enables high-speed synthetic jets with velocities an order of magnitude higher than conventional actuators, allowing for more reliable and efficient control of supersonic flows, suitable for various aerospace applications including steering munitions and airflow control, with potential for weight savings and increased reliability.
Implementation Method 1
creating high pressure in the chamber by using an electrical discharge to create plasma inside of the chamber, rapidly heating air
Implementation Method 2
using an electrical discharge to create plasma inside of the chamber, rapidly heating air
Implementation Method 3
Pressure is relieved by exhausting the heated air through the discharge orifice. Sufficient driving pressure is created by the exhausted air to influence supersonic boundary layers.
Implementation Method 4
The high exhaust velocities of the actuator device may reach sonic levels on the order of Mach 1 or higher
Data Source
AI summary
A method and device are provided for manipulating high-speed flows without moving aerodynamic structures. More particularly, a flow control actuator device is provided that is capable of producing a pulsating synthetic jet with high exhaust velocities for manipulating high-speed flows without moving aerodynamic structures. The high exhaust velocities of the actuator device may reach sonic levels of Mach 1 or greater. In one embodiment, the device may be constructed as an array of devices. In such an embodiment, each individual device is preferably reduced to a very small size. In such an embodiment, each individual device can then be fired in temporal patterns to create high-speed synthetic jets of air extending above the surface of the each device.