2017 SURE Program Abstract Book
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Abstract Book Summer Undergraduate Research in Engineering Program Summer 2017 College of Engineering, University of Michigan Table of Contents Aerospace Engineering……………………………………………………6-15 Climate and Space Sciences and Engineering………………………16-18 Biomedical Engineering………………………………………………….19-23 Civil and Environmental Engineering………………………………….24-31 Chemical Engineering…………………………………………………….32-37 Electrical Engineering and Computer Science………………………38-57 Engineering Education Research………………………….……………….58 Industrial and Operations Engineering……………………….…….…59-65 Macromolecular Science and Engineering……………………….………66 Mechanical Engineering………………………………………………….67-77 Materials Science and Engineering………………………………….…78-80 Nuclear Engineering and Radiological Sciences…………...……….81-85 Robotics…………………………………………………………………………86 Overview The Summer Undergraduate Research in Engineering Program (SURE) offers summer research internships to outstanding undergraduate students who have completed their sophomore or junior year by the start of the summer. Participants conduct 10-12 weeks of full-time summer research with some of the country’s leading faculty in a wide range of engineering disciplines. The program provides opportunities for students to assess their interests and potential in pursuing research at the master's or Ph.D. level in graduate school. SURE students receive guidance by a faculty advisor in a College of Engineering research facility and have produced an abstract booklet which highlights their summer research project and/or experience. Validation of an Air Force Research Laboratory Retarding Potential Analyzer Veronika Bayer1, Marcel Georgin2, Grant Miars3, Dr. Benjamin Jorns4 1Aerospace Engineering, University of Michigan, Ann Arbor, Michigan 2Ph.D. Candidate, Applied Physics, University of Michigan, Ann Arbor, Michigan 3Ph.D. Candidate, Electrical and Computer Engineering, University of Michigan, Ann Arbor, Michigan 4Assistant Professor, Aerospace Engineering, University of Michigan, Ann Arbor, Michigan A Retarding Potential Analyzer (RPA), is a plasma diagnostic tool that collects ion current and uses repelling grids to determine the ion energy distribution function (IEDF). An Air-Force designed RPA is calibrated against an ion source, a device that produces an ion beam of known energy. To extract the ion beam energy and ion temperature, the IEDFs of the ion source are analyzed using curve-fitting. These measurements are compared to expectations from the discharge parameters of the ion source. A range of 0-200 volts is investigated and the measured ion energies are within expected uncertainty. The plasma potential is within 5V of the previous measurements, and the distributions of both IEDFs fit a similar function. This RPA allows accurate measurements to be taken from new plasma sources. 6 Plasma SparkJet Design and Analysis Matthew Cosby1 1Aerospace Engineering, University of Michigan, Ann Arbor, MI Ignition of high velocity flows in aircraft engine combustors is often a complex process. A spark is generally created in the combustor via a capacitively discharging spark plug. With very high velocity flows, it can be beneficial to remove these obstructions from the flow path to reduce the risk of damaging shocks and instabilities. I was tasked with designing a device that would create a spark inside of a small cavity filled with an injected gas to ideally induce heating in the gas and cause high energy plasma to be ejected from a small orifice into an oncoming flow. Multiple designs were examined via the reading of papers containing similar designs generally used for flow control rather than ignition. A device was designed and constructed featuring cavities of various volume drilled from machinable ceramic with small gas injection ports in each, a copper sheet serving as an anode with circular orifices of varying diameter, and a movable tungsten cathode inserted to vary electrode gap spacing. Test matrices involving combinations of cavity volume, orifice diameter, electrode gap spacing, gas injected, sparking frequency, and flow rate were populated and schlieren imaging at 5 kHz was taken to view the individual pulses and qualitatively analyze the results. This testing is still in the process of being completed and will be used to further improve the design as a whole. 7 Ray Tracing in Laser Diagnostics of Combustion Alex Feleo1 1Aerospace Engineering, University of Michigan, Ann Arbor, Michigan Laser-based diagnostics are used to measure temperature, pressure, and velocity in combustion and fluid flow applications. The absorbance of a gas species depends on its temperature, pressure, and concentration. The velocity of the gas is found from the shift of the absorption line center position due to the Doppler effect. The typical setup for laser diagnostics requires a laser producing a beam of light with a tunable wavelength and a receiving sensor. The laser beam is typically manipulated through prisms, lens, and mirrors. Therefore, having a way to simulate the path of the light rays is often needed to design the optical arrangement used in the experiments. Ray tracing is the process of mapping the path of the light as it goes through the optical system. Part of my responsibilities was to create a generic code for ray tracing analysis of optical elements (lenses, prisms, etc.). The codes include a 2D representation, as well as a full 3D solver. The user can choose the type of light source, any number of optical elements, input the information about all the elements, and then run a ray tracing analysis on the configuration. This generic code was then modified and specialized for specific situations, such as specific geometric arrangements of prims and sensors. The code was then used to evaluate the tolerance of the sensor positions in orientation and position of the incident light. The study then found when the light beam properly passes through the arrangement into the receiving sensor. 8 Operation and Control of an Inverted Pendulum Thrust Stand Christopher Naughton1, Joshua Woods1, Scott Hall1, Benjamin Jorns1 1Aerospace Engineering Department, University of Michigan, Ann Arbor, MI, 48109, USA Thrust measurements of electric propulsion (EP) devices are difficult to obtain, but necessary for the proper characterization of electric thrusters. The force output by electric thrusters is small enough to be significantly obscured by a number of sources. Any change in thruster orientation during testing will add or subtract a portion of the device’s weight to the thrust measurement. EP devices have a very low thrust to weight ratio, so this can drastically change thrust values. It is therefore imperative for EP thrust measurement setups to have precise control systems designed to prevent these errors from impacting the data. A control system for two inverted pendulum style thrust stands was designed and built to provide accurate and reliable thrust measurements. In an inverted pendulum thrust stand the electric thruster is secured to a mounting system, which rotates about a pivot located below the thruster. Gravity acts as a disturbing force in this configuration, making the system very sensitive to thruster output at the cost of stability. The control system therefore was designed to measure the movement of the thruster and provide a counteracting “null” force to maintain a zero displacement. A fiber optic displacement sensor was installed to measure the movement, a control board was built to send electrical current through coils and provide the null force, and an analog PID controller was used to regulate the system. The thrust stand was tested using calibration weights to provide a mock thrust load. The acquired data formed a linear calibration curve, which demonstrated that the control system can provide consistent and accurate thrust measurements over the tested load range. 9 Aerodynamic Shape Optimization of Wind Turbine Blades Using a Reynolds-Averaged Navier-Stokes Model and an Adjoint Method Yue Shen1 1Aerospace Engineering, University of Michigan, Ann Arbor, MI This project aims to obtain optimization results for IEA Task 37 Case Study: Aerodynamic Shape Optimization of DTU 10MW Reference Wind Turbine Blades. The entire work is conducted in Multidisciplinary Design Optimization Lab directed by Professor Martins. Prior to running this case with current code in MDO Lab, it is worthwhile reproducing the optimization results from a previous paper in MDO Lab by Tristan Dhert. Tristan’s paper presents a similar aerodynamic shape optimization problem of NREL VI wind turbine blades but his code is no longer compatible with latest Adflow. After running Tristan’s case with Adflow and comparing results, I gained confident in optimizing aerodynamic shape of wind turbine blades and started to work on IEA wind turbine case. I used pyGeo and ICEM to generate the geometry of a Reference Wind Turbine blade and surface mesh on this blade. Then pyHyp was applied to extrude the surface mesh and rotate the single blade 120o to get three blades at different orientations. The future work for this project is to finish overset mesh and run aerodynamic analysis and optimization. 10 Experimental Setup and Modeling of Aircraft with Hybrid Power System Guankun Su1 1Aerospace Engineering, University of Michigan, Ann Arbor, MI This project aims to set up a lab environment for testing controllers on power management of a hybrid air vehicle in Prof. Girard and Kolmanovsky’s Vehicle Optimization, Dynamics, Control and Autonomy Lab. The project can be divided