Surface-Integrated EAD Thrusters for Low-Drag Wing Propulsion
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Solution Overview
Problem
Conventional electroaerodynamic (EAD) thrusters with ion sources and ion collectors external to an aircraft wing generate significant drag, affecting efficiency and thrust capacity.
Innovation Solution
Integrate ion sources and ion collectors into the surface of the aircraft wing, configuring the wing as a lifting surface, and utilize a multi-stage thruster arrangement with alternating polarity or increasing voltage differentials to minimize drag and enhance thrust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If ion sources and ion collectors are positioned external to the aircraft wing, then the thruster can generate thrust, but significant drag is generated affecting efficiency
Solution Approach 1:
The patent merges the ion source and ion collector with the aircraft wing structure. The wing itself serves as the ion collector, eliminating the need for separate external components. This integration combines the lifting surface function with the electroaerodynamic thrust generation function, thereby reducing drag while maintaining thrust capability.
Solution Approach 2:
The aircraft wing is designed to perform multiple functions: it provides aerodynamic lift as a lifting surface and simultaneously serves as the ion collector for EAD thrust generation. This multi-functionality eliminates the need for separate dedicated components, reducing overall drag and improving efficiency.
2Power
If conventional EAD thruster configuration is used with separate ion sources and collectors, then thrust is generated, but device complexity increases
Solution Approach 1:
The patent reduces structural complexity by merging the ion collector function into the wing structure itself. Instead of requiring separate external ion source and collector components, the wing integrates the collector function, simplifying the overall device architecture while maintaining thrust generation capability.
Solution Approach 2:
The wing structure serves dual purposes as both a lifting surface and an ion collector, reducing the total number of components required in the system. This multi-functionality inherently simplifies the device structure and reduces complexity compared to conventional separate-component configurations.
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
Reduces drag by 5-15% and increases thrust output, improving lift-to-drag ratio and aircraft endurance by integrating ion sources and collectors into the wing surface, particularly with multi-stage configurations.
Implementation Method 1
A potential difference is applied across the electrodes (i.e., a voltage differential), such that ions produced at the ion source flow towards the ion collector under the action of the resulting electric field
Implementation Method 2
When the ions flow from the ion source towards the ion collector, the ions collide with neutrally charged molecules, generating ionic wind (i.e., thrust)
Data Source
AI summary
Embodiments disclosed herein relate to electroaerodynamic (EAD) thrusters for use in thrust generation. An EAD thruster may include one or more ion sources, one or more ion collectors, and one or more airfoils. In some embodiments, the one or more of the one or more ion sources and/or ion collectors may be integrated into a surface of the one or more airfoils. The EAD thruster arrangement may also include multiple EAD stages in some embodiments.