Plasma Wing Instability Inhibitor
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Solution Overview
Problem
Swept wing aircraft designs face challenges with cross flow instabilities that lead to transition from laminar to turbulent flow, resulting in increased drag and fuel consumption, as existing Distributed Roughness Elements lack control over magnitude, spacing, and disturbance location, and pneumatically controlled solutions are complex and inefficient.
Innovation Solution
A cross flow instability inhibiting assembly using a dielectric base with electrodes to generate plasma disturbances periodically on the wing surface, preventing the amplification of vorticity and maintaining laminar flow by creating well-damped vorticity that dissipates downstream.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If fixed geometric bumps are used as Distributed Roughness Elements, then cross flow instabilities are inhibited, but control over magnitude, spacing, and disturbance location is lost
Solution Approach 1:
The patent applies the dynamics principle by replacing fixed geometric bumps with flexible membrane elements that can be dynamically actuated. The membrane can change its shape and position in response to control signals, allowing the disturbance characteristics (magnitude, spacing, location) to be adjusted dynamically during flight operations, thus resolving the contradiction between reliable instability inhibition and adaptability.
Solution Approach 2:
The patent implements parameter changes by using actuators to modify the physical parameters of the roughness elements. The membrane elements can change their displacement amplitude, frequency, and spatial distribution based on flight conditions, enabling optimal control of cross flow instabilities across different operating regimes while maintaining reliable inhibition.
2Adaptability or versatility
If pneumatically controlled Distributed Roughness Elements are used, then some control is achieved, but system complexity increases and limited control remains
Solution Approach 1:
The patent applies mechanics substitution by replacing the complex pneumatic control system with a simpler electromagnetic actuation system. The actuators directly control the membrane elements without requiring compressed air infrastructure, reducing system complexity while improving control capability through precise electrical signal management.
Solution Approach 2:
The patent utilizes flexible shells and thin films by employing membrane elements that can be actuated by simple mechanisms. These thin film membranes provide the necessary flexibility for shape change while being easily controllable, reducing the complexity associated with rigid or pneumatically actuated systems.
3Adaptability or versatility
If pneumatic bumps are used, then control is provided, but the bumps are smooth and create less vorticity
Solution Approach 1:
The patent applies curvature principles by designing the membrane elements with specific geometric profiles that enhance vorticity generation. The flexible membranes can be actuated to create sharper edges and more pronounced curvature changes compared to smooth pneumatic bumps, thereby generating the necessary vorticity to inhibit cross flow instabilities while maintaining control capability.
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 effectively inhibits cross flow instabilities, reducing drag and fuel consumption by maintaining laminar flow conditions on the wing, with the ability to control the magnitude and spacing of disturbances for optimal performance.
Implementation Method 1
The plurality of electrodes generates a plasma and an aerodynamic disturbance area disposed above or adjacent to each of the plurality of electrodes
Data Source
AI summary
A cross flow instability inhibiting assembly generates periodic aerodynamic disturbances on a swept wing. The cross flow instability inhibiting assembly is dynamic in that it can be selectively turned on and off as needed. The cross flow instability inhibiting assembly is a strip of material separating a set of electrodes from a set of electrodes. When energized, the fields created between the electrodes and electrodes create plasma disturbances around the electrodes. The electric fields and plasma create heating and body force disturbances on the air or surrounding fluid. These plasma generated disturbances disrupt development of unstable voriticity due to cross flow, inhibiting transition to turbulent flow of the wing to which it is attached. The electrodes may be connected to electrical power in series or they may be connected to an alternating configuration. The system allows for various uses based on the design of the wing and the conditions in which the host aircraft is flying.