Plasma Actuator Aircraft Control System
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Solution Overview
Problem
Conventional control surfaces for supersonic and hypersonic aircraft are inefficient due to high frequency disturbances and the weight of control surfaces, which limits response rates and aircraft efficiency.
Innovation Solution
The implementation of plasma actuators and fuel injectors integrated with control surfaces to create a plasma-ignited combustion system, where plasma is generated to ignite fuel and stabilize combustion, allowing for enhanced control and stability by modifying shockwaves and aerodynamic conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If conventional control surfaces are used for supersonic and hypersonic aircraft, then the aircraft can maintain basic flight control, but the response rate is insufficient due to high frequency disturbances and the heavy weight of control surfaces
Solution Approach 1:
The patent replaces conventional mechanical control surfaces with a plasma-based actuation system. Plasma actuators generate ionized gas that directly interacts with the airflow over the aircraft surface, creating aerodynamic forces without moving mechanical parts. This substitution eliminates the weight of traditional control surfaces while enabling faster response times since plasma can be activated and deactivated electronically at high frequencies.
Solution Approach 2:
The patent uses plasma (ionized gas) as a pneumatic actuation medium to control aircraft flight. The plasma actuators generate localized regions of ionized gas that modify airflow characteristics and create aerodynamic forces. This pneumatic approach replaces heavy mechanical actuators with a lightweight gas-based system that responds rapidly to control inputs.
2Device complexity
If conventional control surfaces are used, then the aircraft structure can be simple, but the system weight increases and efficiency decreases
Solution Approach 1:
The patent replaces mechanical control surfaces with plasma actuators that are integrated into the aircraft skin. The plasma generation system consists of electrodes and power supply components that can be mounted flush with the aircraft surface, eliminating the need for heavy moving control surfaces while maintaining structural simplicity.
Solution Approach 2:
The plasma actuation system serves multiple functions: it provides flight control, generates thrust augmentation, and can potentially serve as a heating element for thermal protection. This multi-functionality reduces the need for separate systems, simplifying the overall device complexity while reducing total weight.
3Productivity
If conventional control surfaces are used, then the system is mechanically simple, but the response frequency is limited and cannot handle high frequency disturbances
Solution Approach 1:
The patent replaces mechanical control surfaces with plasma actuators that can be activated and deactivated electronically at very high frequencies. The plasma generation process responds almost instantaneously to electrical signals, enabling response frequencies far beyond what mechanical systems can achieve, thus handling high frequency disturbances effectively.
Solution Approach 2:
The plasma actuators operate through periodic pulsing at high frequencies to generate controlled aerodynamic forces. By modulating the plasma discharge in periodic cycles, the system can respond to high frequency disturbances and maintain precise control, with the periodic action enabling frequencies much higher than mechanical systems permit.
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
This solution enables faster response rates and increased efficiency by providing lighter control systems capable of operating at higher frequencies, essential for stable hypersonic flight, while reducing the weight and complexity of traditional control surfaces.
Implementation Method 1
at least one plasma actuator disposed along a substrate at a plasma location... The plasma from plasma actuator ignites fuel from the fuel injector proximate the plasma location
Implementation Method 2
The plasma from plasma actuator ignites fuel from the fuel injector proximate the plasma location
Data Source
AI summary
A combustion system includes at least one plasma actuator disposed along a substrate at a plasma location, and at least one fuel injector disposed along the substrate at an injection location. The fuel injector disperses fuel toward the plasma location. The plasma from plasma actuator ignites fuel from the fuel injector proximate the plasma location.