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Articles 1 - 8 of 8
Full-Text Articles in Aeronautical Vehicles
Characteristics Of Patterned Surface Dielectric Barrier Discharge Devices For Ionic Wind Propulsion, Ethan J. Graef
Characteristics Of Patterned Surface Dielectric Barrier Discharge Devices For Ionic Wind Propulsion, Ethan J. Graef
Mechanical Engineering Undergraduate Honors Theses
Electroaerodynamic (EAD) or ionic wind propulsion is a growing area of research for small noiseless low speed aircraft. Previous flight demonstrations and experimentation have revealed that traditional methods of EAD propulsion utilizing corona discharge incur a large drag penalty due to their collector and emitter geometries. Recent publications detail flexible and geometrically conformable surface dielectric barrier discharge devices (SDBD) that could increase thrust and decrease drag as an ion source for an EAD propulsion system. This thesis explores the effects of different electrode sizes and geometries on total SDBD power consumption. SDBDs of a hexagonal, triangular, and square electrode geometry …
Simulating Dielectric Barrier Plasma Actuators With Varying Geometries, Cass Wiederkehr
Simulating Dielectric Barrier Plasma Actuators With Varying Geometries, Cass Wiederkehr
Mechanical Engineering Undergraduate Honors Theses
The idea of Ionic Wind Propulsion has long been a topic of research for whether or not it can be used as a practical power source for flight. MIT researchers proved in 2018 that a plane with zero moving parts powered by Ionic Wind Propulsion was possible, and sustained flight could work with an internal power supply. However, due to the thin wire electrodes required to generate the ion cloud that made such propulsion possible, large amounts of drag rendered the plane extremely inefficient and impractical. Dielectric Barrier Discharge Devices (DBDs) are being investigated as to whether they can serve …
Monte-Carlo-Based Analysis Of Traffic Flow For Urban Air Mobility Vehicles, Sara Ghayouraneh
Monte-Carlo-Based Analysis Of Traffic Flow For Urban Air Mobility Vehicles, Sara Ghayouraneh
Graduate Theses and Dissertations
The research conducted in this dissertation is focused on developing a simulation tool that can predict the traffic flow patterns of the Urban Air Mobility vehicles to alleviate some of the challenges related to their traffic management. First, an introduction to the concept of Urban Air Mobility is given, the usage of Automatic Dependent Surveillance-Broadcast systems for Urban Air Mobility vehicles is suggested and dynamic addressing concept is introduced as an answer to a part of air traffic management and address scarcity challenge for Urban air Mobility vehicles. Next, in order to simulate the traffic flow patterns of the Urban …
Improving The Performance Of An Ead Aircraft By Use Of A Retractable Electrode System, Michael Alexander Fredricks
Improving The Performance Of An Ead Aircraft By Use Of A Retractable Electrode System, Michael Alexander Fredricks
Mechanical Engineering Undergraduate Honors Theses
Electroaerodynamic (EAD) propulsion is a growing area of research for small, low powered aircraft. Recent tests of EAD aircraft have demonstrated low performance in unpowered, gliding flight. The purpose of this paper is to investigate the effect of a retractable electrode system on the flight performance of an EAD aircraft. An analysis of electrode drag contribution on the MIT ionic wind plane’s performance predicts a maximum lift to drag ratio of 22, with the addition of a retractable electrode system, for a similarly sized and modeled EAD aircraft. An experiment is developed using a prototype aircraft, launcher, and retraction system …
Development Of High-Density Propulsion System Technologies For Interplanetary Small Satellites And Cubesats, Morgan Andrew Roddy
Development Of High-Density Propulsion System Technologies For Interplanetary Small Satellites And Cubesats, Morgan Andrew Roddy
Graduate Theses and Dissertations
The goal of this research was to support the development of a novel propulsion system for small satellites (<180 kg) and CubeSats. This was pursued by conducting a collection of studies that were designed to provide engineering data that would be critical in designing a functional prototype. The novel propulsion system was conceived by the author to provide best-in-class performance for the small satellite and CubeSat families of spacecraft. This context presents specific design requirements that the presented technology attempts to satisfy. The most critical among these is high density; the propellant was designed to be stored with high density and the thruster was designed to be as compact as possible. The propulsion system is composed of two primary elements, a propellant generator and a thruster. The propellant generator works by sublimating a solid crystal into vapor and then using this vapor to etch a dense metal. The resulting gaseous byproducts of this reaction are the propellant. This dissertation used xenon difluoride (XeF2) vapor to etch tungsten (W) which react to form xenon gas (Xe) and tungsten hexafluoride (WF6). This approach gave a theoretical propellant storage density 5.40 g/cm3; and 5.17 g/cm3 was demonstrated. The sublimation dynamics of the XeF2 were studied as a function of surface area and temperature and it was found to be suitable for the intended application due to its high effluence rate; that is, it sublimates fast enough to be useful. The sublimation rates are on the order of 10’s of µg/s. The etch rate of XeF2 on W was also studied and found to be suitably fast to provide useful amounts of reactants for use as a propellant, again on the order of 1’s of µg/s. The thruster is an electrostatic radio frequency (RF) ion thruster design and is manufactured with Low Temperature Co-Fired Ceramic (LTCC) materials system and manufacturing technology. Manufacturing samples of the thruster were built at the University of Arkansas in July 2015 and tested at NASA’s Marshall Space Flight Center in May 2018. Testing validated the viability of the LTCC thruster and provided valuable information on how to improve the thruster’s design.
Task 1: Silver-Based Microbial Check Valve For Spacecraft Potable Water Systems, Eric Beitle
Task 1: Silver-Based Microbial Check Valve For Spacecraft Potable Water Systems, Eric Beitle
Chemical Engineering Undergraduate Honors Theses
As human space exploration increases, the development of a more efficient potable water treatment system suited for spacecraft becomes crucial. This Waste-management Education Research Consortium (WERC) challenge was designed to explore the viability of microbial control through the utilization of silver ions as a biocide for possible integration into the Tranquility Node 3 water purification system aboard the International Space Station (ISS). Current systems using iodine risk causing hyperthyroidism from overexposure; however, silver can be safely ingested without this side effect. After researching silver delivery methods including electrochemical ion production, controlled release, or a combination of the two, our team …
Active Permanent Magnet Attitude Control For Cubesats Using Mu-Metal Shielding, Maxwell Martin
Active Permanent Magnet Attitude Control For Cubesats Using Mu-Metal Shielding, Maxwell Martin
Mechanical Engineering Undergraduate Honors Theses
Cube-Satellites (CubeSats) are nanosatellites composed of cube shaped units, each nominally 10cm to a side and around 1kg in mass. Due to their inherent size and weight limitations, it is often impractical to use conventional attitude, or rotational, control methods such as thrusters on these small satellites. Several methods, including magnetorquer rods and small reaction wheels, are often used instead of traditional methods to work around the size and weight limitations. As a new alternative to these methods, a permanent magnet mounted on a rotatable shaft could be used to achieve attitude control. In much the same way that a …
Flexible Circuits For Aerospace Applications With Special Emphasis On Rf Connectors, Abhishek Nareshraj Singh
Flexible Circuits For Aerospace Applications With Special Emphasis On Rf Connectors, Abhishek Nareshraj Singh
Graduate Theses and Dissertations
The current work focused on the study of flexible electronic circuits for use in aerospace applications with emphasis on RF Connectors. The electrical and mechanical performance of the flexible circuits was studied and compared to a standard coaxial cable for feasibility study in avionics space. Also, Anisotropic Conductive Films (ACF) are studied for connecting the flexible RF connectors and their performance studied for electrical and mechanical behavior with change in bonding parameters.