Ducted Electroaerodynamic Thrusters for Higher Thrust Density
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Solution Overview
Problem
Traditional electroaerodynamic devices face a performance tradeoff where increasing thrust density reduces efficiency, limiting their thrust-to-power ratio and overall performance.
Innovation Solution
The use of ducted and multi-stage electroaerodynamic devices, which incorporate a duct and multiple stages with ion sources and collectors, enhances thrust density and thrust-to-power ratio by optimizing fluid flow and reducing turbulence.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If traditional electroaerodynamic devices increase thrust density, then thrust output improves, but efficiency deteriorates
Solution Approach 1:
The device is divided into multiple stages, each with its own ion sources and collectors arranged in series. This segmentation allows the thrust generation process to be broken into discrete steps, where each stage contributes to overall thrust while maintaining optimal energy efficiency. The multi-stage configuration enables independent optimization of each stage's performance characteristics.
Solution Approach 2:
The patent introduces a ducted configuration that adds a spatial dimension to the traditional open EAD design. The duct confines and directs the ion flow path, creating a controlled three-dimensional flow structure. This dimensional change allows for better utilization of ion momentum and reduces energy losses to the surrounding environment.
2Force
If traditional electroaerodynamic devices increase thrust output, then propulsion capability improves, but thrust-to-power ratio deteriorates
Solution Approach 1:
By segmenting the thrust generation into multiple stages with series-connected ion sources and collectors, the device achieves higher total thrust through cumulative effect while maintaining efficient power utilization at each stage. The segmented approach prevents energy waste that would occur in a single high-power stage.
Solution Approach 2:
The multi-stage configuration ensures continuous ion generation and acceleration throughout the duct length. Each stage continuously produces ions that are accelerated and contribute to thrust, maintaining uninterrupted useful action. This continuity maximizes the conversion of electrical power to mechanical thrust over time.
3Force
If ducted multi-stage configuration is used, then thrust density improves, but device complexity increases
Solution Approach 1:
The patent merges multiple functional elements into an integrated ducted structure. The duct itself serves as both a structural component and a flow confinement mechanism, while ion sources and collectors are combined in repeating stage units. This merging reduces the number of separate components and simplifies the overall system architecture despite the multi-stage configuration.
Solution Approach 2:
Each stage within the duct serves multiple functions: ion generation, ion acceleration, and thrust contribution. The duct structure itself provides both mechanical support and aerodynamic flow management. This multi-functionality reduces the need for separate dedicated components for each function, thereby managing complexity.
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
Ducted and multi-stage electroaerodynamic devices provide improved thrust density and thrust-to-power ratio, making them more efficient and quieter than conventional alternatives, suitable for aircraft propulsion.
Implementation Method 1
The most successful EAD propulsion devices thus far have used a direct current (DC) corona discharge to produce ions and the same DC field to accelerate those ions to produce a thrust.
Implementation Method 2
the same DC field to accelerate those ions to produce a thrust
Implementation Method 3
enhances thrust density and thrust-to-power ratio by optimizing fluid flow and reducing turbulence
Data Source
AI summary
Electroaerodynamic devices and their methods of operation are disclosed. In one embodiment, ions are formed by dielectric barrier discharge using a time-varying voltage differential applied between a first electrode and a second electrode. The ions are then accelerated in a downstream direction using a second voltage differential applied between a third electrode and the first and/or second electrodes, where the third electrode is located downstream from the first and second electrodes. The ions may then collide with naturally charged molecules and/or atoms within a fluid to accelerate the fluid in the downstream to create an ionic wind and an associated thrust.