Plasma-Actuated Movable Wing for Fast Aircraft Flow Control

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Solution Overview

Problem

Existing aircraft flow control systems face challenges in achieving high response speed with larger movable wings, which increase weight and reduce loading space, making it difficult to operate at high speeds effectively.

Innovation Solution

A flow control system that integrates a movable wing with a plasma actuator, where the steering angle of the movable wing works in conjunction with the operation of the plasma actuator to control air flow, allowing for reduced movable wing size and weight while maintaining effective flow control, by using a plasma actuator that induces dielectric barrier discharge to manipulate air flow.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Speed

If the size of the movable wing is increased to achieve high response speed, then the response speed is improved, but the weight increases and loading space decreases

Engineering Contradiction:

Improveresponse speedVSAvoidweight of movable wing

Core Design Contradiction:

SpeedVSWeight of moving object

Solution Approach 1:

The patent combines a plasma actuator with a movable wing to create an integrated flow control system. The plasma actuator is mounted on the movable wing surface, merging two separate components (plasma actuator and movable wing) into a unified system that achieves high response speed without requiring a large movable wing area.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The patent introduces a plasma actuator that uses electrical discharge to generate plasma, which then manipulates air flow through electromagnetic and thermal effects. This replaces or supplements purely mechanical flow control methods, enabling rapid response without increasing mechanical movable wing size.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

2Speed

If the size of the movable wing is increased to achieve high response speed, then the response speed is improved, but the loading space reduces

Engineering Contradiction:

Improveresponse speedVSAvoidloading space

Core Design Contradiction:

SpeedVSVolume of moving object

Solution Approach 1:

The plasma actuator is integrated with the movable wing structure, combining flow control functionality with the existing wing component. This merging allows the system to achieve high response speed without adding separate large-scale components that would occupy loading space.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The plasma actuator changes the physical parameters of air flow through plasma generation, creating localized flow control effects. This parameter-based control approach achieves high response speed without requiring large geometric changes to the movable wing structure.

Inventive Principle:

Principle #35Parameter changes

3Speed

If the plasma actuator is added to the movable wing, then the response speed is enhanced, but the device complexity increases

Engineering Contradiction:

Improveresponse speedVSAvoidcomplexity of flow control system

Core Design Contradiction:

SpeedVSDevice complexity

Solution Approach 1:

The plasma actuator serves multiple functions: it generates plasma for flow control, creates localized heating effects, and produces electromagnetic forces. This multi-functionality allows a single component to achieve complex flow control objectives, offsetting the added complexity with operational versatility.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The plasma acts as an intermediary between the electrical power source and the air flow. Instead of directly mechanically moving air, the electrical energy is converted to plasma, which then mediates the interaction with the air flow, providing a new mechanism for flow control that enhances response speed.

Inventive Principle:

Principle #24Intermediary (Mediator)

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 configuration enhances the response speed of the aircraft by allowing the plasma actuator to control air flow independently of the movable wing's steering angle, reducing the size and weight of the movable wing, and enabling optimal control of steering angles and plasma actuator outputs for desired orientations.

Implementation Method 1

A plasma actuator mountable on a surface of the movable wing... by using a plasma actuator that induces dielectric barrier discharge to manipulate air flow

Methodology Applied

Scientific EffectDielectric barrier discharge: Plasma

Data Source

PatentUS11214359B2Flow control system, flow control method, and aircraft

Publication Date: 2022.01.04 SUBARU CORP

AI summary

A flow control system includes a movable wing attachable to a wing of an aircraft, and a plasma actuator mountable on a surface of the movable wing. The flow control system is configured to control air flow around the wing by having the changing of the steering angle of the movable wing work in conjunction with the operation of the plasma actuator.