Ionic Propulsion for Wing-Tip Boundary Layer Reattachment
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing technologies lack a practical ionic propulsion system for aircraft wings that can improve boundary layer adherence at the wing tips by local acceleration of the air stream.
Innovation Solution
An ionic propulsion system with a first and second conductor, disposed within the airfoil, extends from the airfoil to ionize air particles, creating a flow of ionized particles between the conductors to enhance boundary adherence.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a swept back wing with low aspect ratio is used to reduce drag and increase lift at high speeds, then aerodynamic efficiency is improved, but boundary separation occurs at the wing tip causing loss of control surface effectiveness
Solution Approach 1:
The patent applies ionic propulsion specifically at the wing tip region where boundary separation occurs, rather than modifying the entire wing. The first and second conductors are positioned to create localized ionized air flow that reattaches the boundary layer at the critical wing tip area, preserving the overall aerodynamic efficiency of the swept back low aspect ratio wing while locally resolving the boundary separation problem.
Solution Approach 2:
The patent replaces traditional mechanical flow control methods (such as vortex generators or adjustable control surfaces) with an ionic propulsion system. The dielectric barrier discharge plasma actuators generate ionized air flow that actively controls boundary layer separation, providing a non-mechanical solution that maintains control surface effectiveness without adding moving parts or complex mechanical structures.
2Reliability
If dielectric barrier discharge plasma actuators are used to control flow separation, then boundary layer adhesion is improved, but the system complexity and energy consumption increase
Solution Approach 1:
The patent integrates the ionic propulsion system into the existing wing structure, where the first and second conductors can serve multiple functions: flow control through dielectric barrier discharge, structural support as wing components, and potential sensor integration. This multi-functionality reduces overall system complexity by combining several systems into a unified structure rather than adding separate complex subsystems.
Solution Approach 2:
The patent employs periodic or pulsed dielectric barrier discharge to control boundary layer separation. By using intermittent rather than continuous plasma generation, the system reduces energy consumption and simplifies the power supply requirements compared to continuous operation. The periodic action allows the boundary layer to be actively controlled during critical moments while minimizing overall system complexity and energy demands.
3Ease of manufacture
If conventional aerodynamic prediction methods are used to design swept back wings, then design process is simplified, but stall characteristics cannot be accurately predicted due to spanwise pressure gradients
Solution Approach 1:
The patent incorporates sensors that monitor boundary layer conditions and provide feedback to a control system. This feedback mechanism allows real-time adjustment of the ionic propulsion system to maintain optimal flow attachment, enabling accurate prediction and control of stall characteristics. The feedback from sensors about actual flow conditions compensates for the limitations of conventional prediction methods.
Solution Approach 2:
The patent dynamically changes operational parameters such as the voltage applied to the dielectric barrier discharge actuators based on detected flow conditions. By adjusting these parameters in response to real-time sensor data, the system can adapt to varying flight conditions and maintain accurate control throughout the flight envelope, overcoming the static limitations of conventional design prediction methods.
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 effectively reduces boundary separation and improves airflow adherence at the wing tips, particularly at high angles of attack, enhancing aerodynamic performance.
Implementation Method 1
supplying current to the first conductor and the second conductor to ionize the air particles in the vicinity of the first conductor and the end of the airfoil to create a flow of the ionized particles from the first conductor toward the second conductor
Implementation Method 2
create a flow of the ionized particles from the first conductor toward the second conductor
Data Source
AI summary
An ionic propulsion system for an aircraft having an airfoil includes a first conductor and a second conductor, the first conductor and the second conductor being disposed at least partially within the airfoil when not in use. The propulsion system includes an actuator for extending the first conductor and the second conductor from an end of the airfoil such that the first conductor and the second conductor are in the airstream of the aircraft, the first conductor being upstream of the second conductor in the airstream. The propulsion system includes a power supply for supplying current to the first conductor and the second conductor to ionize the air particles in the vicinity of the first conductor and the end of the airfoil to create a flow of the ionized particles from the first conductor toward the second conductor.