The University of Washington High Enthalpy Flow Laboratory (HEFL) has constructed a purpose built laboratory for experimental research on Rotating Detonation Engines (RDE). This refit included the rebuilding of the lab apparatus, the assembly of the RDE and supporting equipment such as downstream piping, vacuum system, gas handling plumbing, and the redevelopment of the experimental instrumentation. The assembly of the lab apparatus consisted of the construction and mounting of fuel, oxygen, and nitrogen lines for the RDE, and the assembly of back pressure controlled exhaust tubes leading to a dump tank and an optical imaging port. A stand for the engine apparatus itself as well as much of the plumbing support equipment was also constructed. The assembly of the RDE consisted of the assembly of the various engine parts, followed by the connection of the various instruments such as pressure sensors, temperature sensors, ion probes to the engine itself. The hardware and software components of the instrumentation systems were also redeveloped to allow for very high instrument density for pressure and temperature sensors on the RDE. The software component of the instrumentation involved developing MATLAB scripts for valve actuation, data acquisition, and sensor calibration. The hardware aspect of the instrumentation involved selecting the sensors to be used on the engine based on their signal conditioning, as well as designing and building power supply and signal processing circuits to connect the sensors to a rebuilt data acquisition computer system.

This research involves the design of a system for an unmanned aerial system (UAS) to operate and navigate in an environment devoid of a Global Navigation Satellite System (GNSS) such as the Global Positioning System (GPS). The system operates by interrogating an aviation transponder (either mode C or S) that is carried by the UAS and measuring the time elapsed for the response to multiple, ground-based antennas and using triangulation (multilateration) to locate the transponder and by association, the UAS. The ground-based system then routes this position information back to the UAS via the UAS’s data telemetry link. The autopilot then utilizes this position information for navigation in much the same way it would utilize a GPS-based position report. Our research focused on the system architecture to enable a UAS to operate in a GPS-denied environment. Flight test results are presented utilizing a customized version of the popular Pixhawk/ArduPlane avionics platform and demonstrate that the system is capable of guiding a UAS through a series of waypoints in the absence of GPS signals. Furthermore, the customized controller that was designed to consume this alternate source of position information performed well in highly unfavorable environmental conditions. This success illustrates the feasibility of the system as a practical alternative to GPS.

HIT-SI, also know as steady-inductive helicity-injected torus experiment, uses three coplanar inductive helicity injectors to form and sustain a spheromak equilibrium. Spheromak is a configuration of the plasma that forms  into a shape of smoke ring and it is a promising approach to nuclear fusion energy based on its long confinement time and the confinment achieved by the self-induced current. This project is centered around data analysis from a new tomography diagnostic system to assess the symmetry of spheromak plasma density while varying the key current drive parameters of the HIT-SI3 plasma physics and fusion energy.  The tomography diagnostic system consists of four toroidal chord fans and three sets of three poloidal fans that provide 3D plasma emission information. Each fan expands from 130 degree wide angle lenses coupled to bundles of fiber optics. The light collected by the fiber optics is split, filtered at 668 nm and 728 nm, and imaged by a high-speed camera. Since the ratio of the 668/728 nm emission has a strong plasma density dependence within the range of typical HIT-SI3 plasma parameters, the 3D emissivity profile constructed by inverting line-averaged emissivity along chords can be related to the plasma density profile. The objective of this project is to find the correlations between parameters affecting wall conditioning and the plasma density profile, then use the results from the analysis to maximize the performance of the plasma toward the goal of improving confinement. The initial analysis will include all available data covering a variety of experimental plasma conditions. After the correlation is established from the initial analysis, a series of carefully controlled experiments will be conducted to test and improve the certainty of the initial results. In the controlled experiments, plasma discharges will be taken under more specific settings so the effects of different conditions on the plasma profile can be isolated and better understood.

Fiber-reinforced composites are advanced materials that combine polymeric matrices with fibers to achieve low densities along with high strengths and moduli. These properties make composites invaluable to industries that rely on materials with high strength-to-weight ratios, such as aviation and aerospace. This contribution discusses the structural design of the Hyperloop Prototype built by the University of Washington’s team competing in the SpaceX Hyperloop Competition. As the Structures’ team lead, my work has centered around designing a reinforced sandwich panel c-channel design, for the upcoming fourth competition, to optimize the total structural weight to 16lbs respect to the third competition design’s weight of 60lbs. I then analyzed and optimized this design using 1D beam analysis scripts written in MATLAB as well as 2D composite shell analysis in Femap and Hypersizer software to validate SpaceX’s structural stiffness and strength requirements. The structures team conducted an extensive testing campaign to capture flexural properties and identify limit loads of the design. This campaign included three-point-bend tests to capture sandwich panel properties and insert hardpoint testing to validate performance of the mechanical joints between the primary structure and propulsion, stability and braking modules. Finally, with the support of Boeing composite production advisors, the team manufactured prototype composite structures making use of advanced industry procedures including use of FlexCore, carbon puck hardpoints and autoclave cure cycles. This work serves as a critical example of composite material technology application to student-lead design projects as well as the engineering knowledge that can be developed outside of the traditional classroom setting through research and independent studies.