Aircraft Flow Control Using Plasma Actuators for Pressure Distribution
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Solution Overview
Problem
Current aircraft control systems face challenges in accurately controlling air flows around aircraft structures, particularly in optimizing pressure distributions to enhance aerodynamics and attitude control, due to limitations in sensing and actuation technologies.
Innovation Solution
An integrated aircraft control system that includes sensors for air and structural data acquisition, a control information generation system using CFD analysis, and flow control devices like plasma actuators, synthetic jet actuators, and membrane actuators, which are controlled to achieve a target pressure distribution based on detected physical quantities, optimizing air flow and structural deformation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If conventional moving surfaces (ailerons) are used to control air flows, then the aircraft can achieve basic flow control, but the precision and effectiveness of pressure distribution control is insufficient
Solution Approach 1:
The patent replaces conventional mechanical moving surfaces (ailerons) with plasma actuators that use electromagnetic fields to control air flows. The plasma actuators generate body forces directly in the fluid through ionization, eliminating the need for mechanical linkages and surfaces, thereby achieving more precise pressure distribution control without proportionally increasing mechanical complexity
Solution Approach 2:
The patent changes the control parameter from mechanical surface deflection angles to electrical parameters (voltage, current, frequency) applied to plasma actuators. This allows for continuous and precise adjustment of air flow characteristics by varying electrical input parameters, achieving superior pressure distribution control precision
2Measurement precision
If plasma actuators are used to control air flows, then flow control precision is improved, but energy consumption increases
Solution Approach 1:
The patent employs periodic pulsed operation of plasma actuators instead of continuous operation. By applying plasma discharge in periodic pulses synchronized with the airflow characteristics, the system achieves effective flow control while minimizing energy consumption during non-active periods
Solution Approach 2:
The patent applies plasma actuation only in specific critical regions where flow control is most needed, rather than across the entire aircraft surface. This partial application strategy achieves the necessary flow control precision while significantly reducing overall energy consumption compared to full-surface actuation
3Measurement precision
If multiple sensors and actuators are integrated for precise control, then control accuracy is improved, but system complexity and manufacturing difficulty increase
Solution Approach 1:
The patent designs the plasma actuator system with multi-functional capabilities where the same actuator array serves both flow control and sensing functions. The system can operate in different modes (different plasma discharge patterns) to achieve various control objectives, reducing the need for separate dedicated components and simplifying manufacturing
Solution Approach 2:
The patent achieves different control functions by changing electrical parameters (frequency, amplitude, pulse width) of the plasma actuators rather than requiring different physical components. This parameter-based functionality allows a single hardware configuration to perform multiple control tasks, greatly easing manufacturing 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
The system enables precise control of air flows and pressure distributions, reducing air resistance and improving the lift-to-drag ratio, thus enhancing aircraft performance and stability during flight and landing.
Implementation Method 1
use of a plasma actuator (PA) as an auxiliary device for controlling flows of air around wings of an aircraft
Data Source
AI summary
An aircraft control system includes a flow control device and a control circuit. The flow control device is configured to control a flow of air around an aircraft. The control circuit is configured to control the flow control device so that a pressure distribution loaded on a surface of a structure that constitutes the aircraft is equal to a control value of a pressure distribution calculated based on a physical quantity detected by a sensor provided in the aircraft. The physical quantity relates to the air.