Plasma-Actuated Aircraft Lifting Surface for Flap Separation Control

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Solution Overview

Problem

Existing technologies fail to effectively manage boundary layer separation at the transition between lift and control surfaces of an aircraft, such as between a wing and a flap or an elevator, which adversely affects aerodynamic performance and maneuverability.

Innovation Solution

An aircraft lifting surface with articulated lift and control surfaces, equipped with embedded electrodes that create a plasma upon application of an ionizing tension, generating an ionic wind to delay boundary layer separation and maintain airflow continuity.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If electrodes are placed on the extrados of lift or control surfaces to delay stall at high angle of attack, then the aerodynamic performance is improved, but the problem of boundary layer separation at the transition between two lift and control surfaces remains unsolved

Engineering Contradiction:

Improveaerodynamic performanceVSAvoidboundary layer separation control

Core Design Contradiction:

ReliabilityVSAdaptability or versatility

Solution Approach 1:

The invention divides the lifting surface into multiple segments (fixed aerodynamic surface and articulated control surfaces) and places electrodes on each segment. This segmentation allows independent control of boundary layer separation on each surface, enabling the system to address the transition zone problem between different lifting surface segments.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The invention introduces plasma as an intermediary substance between the electrodes and the airflow. The plasma generated by the electrodes acts as a mediator to control boundary layer separation at the transition zones between different lifting surface segments, enabling improved aerodynamic performance without compromising control surface articulation.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Ease of operation

If the control surface is articulated to form an angle with the aerodynamic surface, then the maneuverability is improved, but the boundary layer separation occurs at the transition between surfaces

Engineering Contradiction:

ImprovemaneuverabilityVSAvoidaerodynamic behavior

Core Design Contradiction:

Ease of operationVSReliability

Solution Approach 1:

The invention makes the control surface articulated and movable relative to the fixed aerodynamic surface, allowing dynamic adjustment of the angle between surfaces. The plasma control system adapts to these dynamic configurations, maintaining effective boundary layer separation control regardless of the control surface position, thus preserving both maneuverability and aerodynamic performance.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The invention changes the physical state of the air between electrodes from normal atmospheric state to plasma state by applying ionizing tension. This parameter change enables the system to maintain attached flow at the transition zones even when the control surface is articulated at various angles, preventing boundary layer separation while preserving maneuverability.

Inventive Principle:

Principle #35Parameter changes

3Reliability

If electrodes are embedded at the surface to create plasma, then the boundary layer separation is delayed, but the device complexity increases

Engineering Contradiction:

Improveboundary layer controlVSAvoidelectrode embedding structure

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The invention applies electrodes only at specific critical locations where boundary layer separation occurs, particularly at the transition zones between different lifting surface segments. This localized approach, rather than covering the entire surface, reduces the complexity of electrode embedding while maintaining effective plasma control for boundary layer separation delay.

Inventive Principle:

Principle #3Local quality

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 solution enhances airflow continuity and improves lift generation capabilities, particularly at high angles of attack, by using electrodes to generate a plasma-induced ionic wind that counteracts increasing static pressure and maintains attached flow.

Implementation Method 1

the first electrode and the second electrode are arranged and adapted to create a plasma in air upon application of a predetermined electrical tension, called ionizing tension, between the first electrode and the second electrode

Methodology Applied

Scientific EffectPlasma: Plasma

Implementation Method 2

The application of a high voltage between the first electrode and the second electrode creates a plasma that induces an ionic wind in the air right above and between the electrodes

Methodology Applied

Scientific EffectIonic wind: Ion Wind

Data Source

PatentUS12583574B2Aircraft lifting surface and aircraft comprising such lifting surface

Publication Date: 2026.03.24 AIRBUS OPERATIONS SL

AI summary

An aircraft lifting surface comprising an aerodynamic surface with a first electrode embedded at its surface, and a control surface articulated to the aerodynamic surface, the control surface comprises a second electrode embedded at its surface, and that the first electrode and the second electrode are arranged and adapted to create a plasma in air upon application of a predetermined electrical tension, called ionizing tension, between the first electrode and the second electrode.