Design and Testing of a Hovercraft with Electroaerodynamic Propulsion

Abstract

Electroaerodynamic (EAD) multistaged ducted (MSD) thrusters are a novel solid-state thruster architecture that has been shown to provide order-of-magnitude improvements in thrust density compared to single-stage EAD thrusters. This makes MSD thrusters well-suited for use in EAD hovercraft, where generating sufficient pressure is crucial for hovering. This study explored the feasibility of a wire-to-airfoil corona discharge MSD thruster powered hovercraft through a scaled-down prototype and final design. The hovercraft was tethered to a ground-based power supply and carried a payload mass to simulate having on-board power electronics to limit the scope of the project. The design of an EAD hovercraft involved applying the principles of hovercraft lift to a design optimization that implements the recently developed EAD MSD thruster model. A hovercraft prototype was designed and constructed to validate the models applied during the design phase and to test hovering capabilities without a payload. Using the manufacturing lessons and insights gathered in the prototype testing, a full-scale model was designed and built to hover while having an additional payload capacity that would be representative of a set of power electronics.