Aircraft Lifting Surface Plasma Electrodes for Boundary Layer Control
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Solution Overview
Problem
Existing technologies fail to effectively address 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 negatively impacts aerodynamic performance and control at high angles of attack.
Innovation Solution
An aircraft lifting surface with embedded electrodes on both the aerodynamic and control surfaces that generate a plasma upon application of an ionizing tension, creating an ionic wind to delay boundary layer separation and maintain airflow attachment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If plasma is generated between electrodes on aerodynamic and control surfaces, then boundary layer separation is delayed and airflow attachment is maintained, but device complexity increases due to additional electrodes and ionizing tension application system
Solution Approach 1:
The lifting surface is divided into distinct aerodynamic surface and control surface portions, each with its own embedded electrode. This segmentation allows independent electrode placement and plasma generation at specific locations where boundary layer separation is most critical, particularly at the transition zone between surfaces.
Solution Approach 2:
A plasma field is introduced as an intermediary between the electrode system and the airflow. The plasma acts as a mediator that transfers momentum from the ionic wind to the boundary layer, delaying separation without requiring direct mechanical intervention. The plasma field serves as the active medium that connects the electrical input to the aerodynamic outcome.
2Reliability
If ionizing tension is applied to generate plasma, then boundary layer separation is delayed, but energy consumption increases
Solution Approach 1:
The ionizing tension and plasma generation are applied locally only at critical regions where boundary layer separation is most likely to occur, specifically at the transition between aerodynamic and control surfaces and at high-angle-of-attack regions. This localized application minimizes overall energy consumption while maintaining effectiveness.
Solution Approach 2:
The electrode system can be activated periodically or on-demand based on flight conditions such as angle of attack, rather than operating continuously. This allows the system to consume energy only when boundary layer control is actually needed, reducing overall energy consumption while maintaining reliability when required.
3Reliability
If electrodes are embedded at the transition between aerodynamic and control surfaces, then airflow continuity is improved, but manufacturing precision requirements increase
Solution Approach 1:
The electrodes are embedded within the surface structure of the aerodynamic and control surfaces, merging the electrode function with the existing surface geometry. This integration reduces the need for separate electrode mounting structures and simplifies the manufacturing process while maintaining precise electrode positioning at the transition zone.
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
Improves airflow continuity and lift generation capabilities by delaying boundary layer separation, especially at high angles of attack, enhancing maneuverability and efficiency.
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
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
Data Source
Figure 1
Figure 2~3
AI summary
The invention relates to an aircraft lifting surface comprising an aerodynamic surface (11) with a first electrode (21) embedded at its surface, and a control surface (12) articulated to the aerodynamic surface (11), characterized in that the control surface (12) comprises a second electrode (22) embedded at its surface, and that the first electrode (21) and the second electrode (22) are arranged and adapted to create a plasma (36) in air upon application of a predetermined electrical tension, called ionizing tension, between the first electrode (21) and the second electrode (22).