Mechanical and Aerospace Engineering, 1924-2026

This thesis presents the development and experimental validation of an emissivity-independent statistical pyrometry method for high-temperature diagnostics, with a focus on applications involving magnetoplasmadynamic (MPD) thruster cathodes. Conventional optical pyrometry techniques rely on assumed or known emissivity, which may introduce significant uncertainty in environments where emissivity is unknown or varies with wavelength and temperature. To address this issue, a multi-wavelength statistical model is proposed that reconstructs temperature by minimizing dispersion across pairwise wavelength combinations using Wien's approximation, while simultaneously estimating emissivity behavior.

The method is first validated using synthetic datasets with defined emissivity models, demonstrating accurate temperature reconstruction and robust recovery of spectral emissivity trends under controlled noise conditions. The approach is then applied to experimental data collected using a refurbished four-color pyrometer system and a spectrometer-based setup, both calibrated with a tungsten ribbon lamp over the temperature range $1300–2300\circ C$.

The results show that the statistical method consistently reconstructs temperature with greater stability than conventional approaches, particularly at higher temperatures, where Wien's approximation is most applicable. Although deviations are observed at shorter wavelengths due to increased noise sensitivity and exponential error amplification, the overall spectral trends in emissivity are preserved, supporting the use of simplified emissivity models. The study also identifies limitations, including restricted wavelength coverage and calibration biases, especially in discrete-filter pyrometry systems.

To summarize, this work demonstrates the feasibility of emissivity-independent temperature measurement using limited spectral data and establishes a validated framework for high-temperature diagnostics in plasma propulsion environments.

This project seeks to design one possible solution to the issue of accessibility on theatrical stages, as well as the issue of limited design configurations. This report goes through multiple iterations to discover the best materials from which to construct a functional automated platform for the stage. An emphasis is placed on ensuring that the platforms can tilt to form an ADA-accessible ramp from the ground to the stage. Safety factors are also emphasized, considering the machine must lift human payloads and therefore must be designed to these standards. The suggested technology, a linearly actuated Stewart Platform, is not currently used in the theater world, and this concept could open up many new possibilities for designers as well as accessibility.

The Princeton Space Physics Lab uses a commercial MCP detector to monitor the 2D flux of their ion beam. This type of detector uses Micro-Channel Plates to multiply a single incoming particle into an avalanche of electrons, which is detected by a resistive anode to determine the position of the original particle in 2D space. The detector's structural assembly provides support to the delicate MCPs and delivers voltage to the MCPs and resitive anode. In 2024, PSPL reverse engineered their commercial MCP detector with the goal of building their own set of detectors in-house, but the attempt was unsuccessful because certain crucial components had insufficient electrical contact between them. My senior thesis project aimed to improve the design of the reverse engineered detector, specifically by creating reliable electrical contact, and then manufacture a new, working detector. The beryllium copper components responsible for poor contact were eliminated: the spring plate was replaced with a stainless steel ring that compressed the MCP stack with a spring force and the anode holders were replaced with aluminum mounts that strapped down the anode with copper strips. All new parts were manufactured by me in the MAE/SEAS machine shop. During the design process, an error in the circuit of the MCP voltage dividing box was discovered, which may have also contributed to the issues with the reverse engineered detector. The new detector was cleaned, baked out, and then installed in the Main Chamber of PSPL. It did not produce any counts using the original box, but it began reading counts at 1975 volts with the new box. A gain curve was graphed going up to 2275 volts, which was determined to be the saturation point.

The purpose of this design project is to create a lightweight headset that holds 14 microphones. In multiple tests, 14 simultaneous pulses must be emitted from the microphones to train the Spatially Adaptive Neural Network (SANN), which generates the Personal Sound Zone (PSZ) with its data. Apart from the Head and Torso Simulator for testing, it needs to fit human heads of varying sizes as well. Lightweight materials were chosen, such as 3D-printed plastic and Velcro-One. The holders for the microphones were designed to be in a T-shape with 8 mm holes for each microphone and an earbud to hold them in place. The headset consists of 1 headpiece, 2 microphone holders, 3 feet of Velcro-One, an “X” clip to hold them in place, 4 threaded rods, 4 wing nuts, and 4 regular nuts. I completed the main design requirements, but many requirements still need many more iterations to be fulfilled. When evaluating the design, it proved to be comfortable for a human head, but no research can be done with it. While the headset was successfully proportioned for a human head, it could not fit the proportions of the sound dummy head. While the dimensions for human heads were available, the sound dummy’s technical drawings were impossible to find. Additionally, the supports used to hold the microphones and their holders are metallic and cause acoustical interference and reflections. In the end, my client considered the design a good prototype at its final iteration.

Designing robots capable of multimodal locomotion has been an area of interest and a big challenge in the field of robotics. It presents an interesting design problem, since any system that is created to operate in a certain medium will work less efficiently when forced to operate in a different medium. However, many creatures in the natural world move between different environments very efficiently, and perform excellently in each of these environments. One such creature is the flying fish, which is capable of achieving fast speeds in the water as well as gliding up to 400m meters in the air \cite{davenport1994}. The bio-inspired adaptive morphology (BAM) lab is investigating the flying fish through the use of a robotic model organism (RMO), which can be tested in a controlled environment, and provide greater insight into the extraordinary performance of the flying fish. This project focuses specifically on the transition between water and air. When swimming, flying fish fold their pectoral fins up close to their bodies and then expand them so that they can be used as wings to glide through the air. The current RMO has a rigid wing that is unable to fold back while the fish is swimming. The goal of this project is to adapt the flying fish RMO to include a deployable pectoral fin that stays folded in the water and deploys as it propels itself out of the water. This design was then evaluated by measuring the kinematics of fin deployment and then tested in the water channel to verify whether it could still reach minimum taxi height with the added weight of the mechanism. The mechanism was able to consistently and quickly deploy the fin, however the range of motion was limited slightly by the flexibility of the materials and the waterproofing method. Additionally, the added weight of the mechanism prevented the RMO from achieving minimum taxi height. Weight is the key limiting factor and the results show that if 80g were shed from the RMO, it would be able to achieve taxi height across a full change of frequencies.

Decarbonizing the aviation industry requires macro-scale modeling that can co-optimize for fleet, routing and infrastructure decisions. Extending on Sullivan Meyer ’24’s integrated model, and software improvements made by Maya Avida ’26, this work improves tractability and creates a case study to investigate the results of a model optimizing over realistic demand fluctuations using Plasmo-based Benders decomposition. The model is iteratively improved for tractability, and the base study is set up with the primary aim of creating a realistic a study as possible to prove that the model could be used functionally in a realistic situation. It was found that the model had a tractability ceiling of 12 airports, a large improvement from Meyer’s original formulation, with improvement both in tractability and realistic implications necessary before being considered ready to use in the industry.

The design process behind the development of a Low-Energy Modular Beam Analyzer (LEMBAS) is detailed. The device aims to address a need in the Space Physics Laboratory for low-energy beam characterization, focusing on high energy resolution. The LEMBAS device uses a Retarding Potential Analyzer (RPA) configuration and evaluates performance against requirements using ion simulations.

The goal of this thesis is to aid in the design of a Particle Image Velocimetry (PIV) system for the SuperTank, a high-pressure wind tunnel at Princeton University. Since most seeding systems use compressed air to produce droplets, they are inefficient for use in high-pressure systems. Another method, ultrasonic atomization, is investigated here. It consists of a vibrating piezoelectric element exciting a fluid boundary to produce droplets and is used commercially in the atomization of low viscosity fluids. Since certain high-viscosity fluids are preferred for PIV, experiments were done to establish a relationship between viscosity and the resulting distribution of droplet diameters made using a mesh atomizer. This distribution was bimodal, with a larger peak at smaller diameters and a smaller peak of larger particles. As the viscosity increased and the amplitude of the piezo vibrations decreased, the larger particles became more prevalent. Boundary curves were also made, delineating the minimum conditions at which atomization occurred. The data suggests a critical amplitude for the piezo to run at to produce droplets, which is based on the fluid parameters and the oscillation frequency. This, in turn, elicits a critical pressure difference across the piezo mesh independent of the static pressure. Future work would involve attempting to replicate this behavior for even higher viscosities, as well as in an increased pressure setting.

As transportation continues to develop and modernize, the evaluation of alternative and innovative systems will be essential to meet future mobility needs. Magnetic levitation (maglev) has been identified as a promising system for transportation, and its technology has been widely implemented in trains; applications of electromagnetic propulsion systems have been implemented in high-speed trains across Europe and Asia. This thesis provides a methodology for designing and building a magnetic train model. Using microcontrollers, transistors, and Time-of-Flight distance sensors, this model investigates how permanent magnets and electromagnetic coils can be coordinated to control the movement of a levitating train.

Two design iterations were evaluated to achieve stable levitation and propulsion. The first utilized coils wound with 30 AWG magnet wire mounted on electromagnetic supports to stabilize the train along the track. Lateral stabilization of the train requires sufficient support from the bottom permanent magnets. This gauge wire emitted too much heat and was unable to provide sufficient force on the train to achieve stable levitation. A second iteration using 20 AWG magnet wire eliminated heat-related failures but was unable to produce enough force to achieve a stabilized system.

Although a fully levitating prototype was not realized, the sensor and control system performed as intended; the Arduino reads the train's positional data and updates the electromagnet duty cycles in real time. These results highlight the primary limitations of electromagnets and validate the control approach. This report details the development of the train and track using CAD software, the design considerations involved in the construction of the physical and electrical systems of the model, and future work to achieve stable levitation.

Studying aquatic organisms requires close-range observation that minimizes disruption to natural behaviors. Bio-inspired robotic fish offer a promising low-impact platform for underwater exploration, but achieving depth control in such systems remains challenging. This thesis presents the design, development, and evaluation of a depth control mechanism for the BlueKoi, a bio-inspired robotic fish developed by the SSR Nagpal Lab at Princeton University. Previously lacking vertical maneuverability, the BlueKoi achieved forward swimming and turning through a tuna-inspired tail actuation system. After evaluating several depth control strategies, including a sliding weight, a buoyancy control unit, and upward-facing propulsion, actuated pectoral dive planes were selected given the BlueKoi’s existing size and mass constraints. The final design features three main components: a magnetic coupling “shaft” that transmits actuation from inside the body to an external dive plane through the intact body wall, achieving complete waterproofing; a modular internal bevel gear-servo assembly achieving a dive plane rotation range of -45 to +35°; and an external hydrofoil mounting interface enabling easy hydrofoil interchangeability. Eight hydrofoil variants based on NACA 0012, 0015, 0018, and 0021 profiles of varying span and chord lengths were evaluated in a water channel test at the BlueKoi's approximate minimum swimming speed (0.19 m/s). The system demonstrated reliable waterproofing across sixteen trials, and force measurements confirmed that negative angles of attack consistently produced negative lift, establishing the dive planes' capacity to initiate dives. The NACA 0018 profile with increased span performed best. A free-swim test further confirmed effective depth control, with the BlueKoi executing repeatable dives and ascents at multiple speeds. Depth changes appeared driven primarily by sustained lift forces rather than body pitch, indicating that continuous actuation is required. These results establish the feasibility of actuated dive planes as a depth control mechanism for the BlueKoi, and motivate future work on pitch characterization, actuation refinement, and complementary approaches such as dynamic buoyancy control.

Lunar orbits have become a topic of interest for future space mission architectures. However, pursuing long-term missions in low-altitude lunar orbit is particularly difficult due to the Moon's highly irregular gravitational field. Previous research identified candidate Lunar Frozen Orbits (LFOs) through analytical or numerical methods, but without a systematic understanding of where more frozen orbits may occur. This work attempts to fill this gap by using nonlinear analysis techniques to analyze the stability of current candidate Lunar Frozen Orbits through a Python computational framework which applies Lagrangian Coherent Structures (LCS) and the State Transition Matrix (STM). By mapping Lagrangian coherent structures for a grid of initial states, we were able to visualize local stretching and contracting, showing how small perturbations in nominal frozen orbits affect their long-term trajectories.

Experiments were conducted on candidate Lunar Frozen Orbits identified by Folta and Quinn (2006) and Miceli (2023), where 90×90 grids of initial conditions varying eccentricity and inclination were propagated for 1, 5, and 10 periods through NASA GMAT using the GRAIL gravity model at spherical harmonic order and degree 100×100. The STM for each grid point was reconstructed via central finite differencing, and its Singular Values (SVs) were plotted as contour fields to reveal the stretching and contracting manifolds of the local phase space. Results show highly organized, patterned singular value fields that evolve over time and reveal regions of differing sensitivity to initial conditions. A six-month long-term propagation of select representative points further validates that trajectories embedded within similar short-term Lagrangian coherent structure environments exhibit comparable long-term behavior, suggesting that LCS-based analysis may provide a more systematic and efficient method for identifying families of Lunar Frozen Orbits than existing large-scale numerical sampling approaches.

Future planetary robots designed for Mars-like environments must maintain mobility while enduring harsh conditions such as abrasive regolith, dust accumulation, and severe thermal fluctuations. This thesis presents the design, fabrication, and prototype evaluation of MARSKIN, a multilayer environmental skin developed for integration with OSCAR, a modular origami crawling robot. The primary objective is to enhance environmental survivability without compromising the flexibility, modularity, and sensing capabilities essential for confined-space robotic exploration.

The skin architecture comprises various materials, including TPU, EcoFlex silicone, aerogel, PETG-PTFE, aluminum, and a superhydrophobic outer coating. Each layer is strategically selected to fulfill specific structural or environmental functions such as thermal insulation, adhesion, mechanical support, partial shielding, and surface protection. A circular prototype was initially fabricated for subsystem-level validation, which was later adapted into a rectangular geometry tailored for OSCAR.

Incorporating a sensing subsystem featuring a TMP117 temperature sensor, an infrared temperature sensor, and a day/night livestream camera supported testing and future exploration tasks. Experimental evaluations were conducted under Mars-inspired laboratory conditions, employing heat-plate and heat-lamp testing, freezer exposure, repeated thermal cycling, and dust and abrasion assessments.

The results demonstrated that the full multilayer stack achieved superior thermal buffering performance, exhibiting significant through-thickness temperature differentials under both conductive and radiative heating, as well as delayed temperature equilibration during cold exposure. Notably, the thermal functionality remained consistent across repeated hot-cold cycles. Dust and abrasion tests revealed that the outer TPU and superhydrophobic coating effectively reduced dust adhesion and resisted abrasive contact, although localized dust accumulation occurred in exposed EcoFlex regions.

Overall, the findings indicate that a multilayer environmental skin can substantially enhance the environmental robustness of a small crawling robot while preserving its modular sensing potential and future Mars-inspired locomotion capabilities.

Future planetary robots designed for Mars-like environments must maintain mobility while enduring harsh conditions such as abrasive regolith, dust accumulation, and severe thermal fluctuations. This thesis presents the design, fabrication, and prototype evaluation of MARSKIN, a multilayer environmental skin developed for integration with OSCAR, a modular origami crawling robot. The primary objective is to enhance environmental survivability without compromising the flexibility, modularity, and sensing capabilities essential for confined-space robotic exploration.

The skin architecture comprises various materials, including TPU, EcoFlex silicone, aerogel, PETG-PTFE, aluminum, and a superhydrophobic outer coating. Each layer is strategically selected to fulfill specific structural or environmental functions such as thermal insulation, adhesion, mechanical support, partial shielding, and surface protection. A circular prototype was initially fabricated for subsystem-level validation, which was later adapted into a rectangular geometry tailored for OSCAR.

Incorporating a sensing subsystem featuring a TMP117 temperature sensor, an infrared temperature sensor, and a day/night livestream camera supported testing and future exploration tasks. Experimental evaluations were conducted under Mars-inspired laboratory conditions, employing heat-plate and heat-lamp testing, freezer exposure, repeated thermal cycling, and dust and abrasion assessments.

The results demonstrated that the full multilayer stack achieved superior thermal buffering performance, exhibiting significant through-thickness temperature differentials under both conductive and radiative heating, as well as delayed temperature equilibration during cold exposure. Notably, the thermal functionality remained consistent across repeated hot-cold cycles. Dust and abrasion tests revealed that the outer TPU and superhydrophobic coating effectively reduced dust adhesion and resisted abrasive contact, although localized dust accumulation occurred in exposed EcoFlex regions.

Overall, the findings indicate that a multilayer environmental skin can substantially enhance the environmental robustness of a small crawling robot while preserving its modular sensing potential and future Mars-inspired locomotion capabilities.

Bubble management in microgravity presents a critical challenge for spacecraft fluid systems, where the absence of buoyancy allows bubbles to remain suspended within liquids, threatening systems such as life support and water purification. Microfluidic channels offer a promising passive approach to bubble manipulation through geometry-based control. The Complex Fluids Group at Princeton University has been investigating the behavior of bubbles in curved microchannels with the goal of understanding how to efficiently focus them using curvature. Their ground-based experiments determined that curves heavily influence bubble dynamics, causing the bubbles to deform and migrate toward the inner wall of the channel. They hypothesize that taller channels, where gravitational forces are no longer negligible, in microgravity should have the same effect on bubble behavior as shorter channels on Earth. This thesis documents the design, fabrication, and ground-based validation of a flight-ready, semi-autonomous experimental setup which will allow the Complex Fluids Group to test their hypothesis on a parabolic microgravity flight. Developed within the TigerSats Lab, the design consists of a rolling cart as the primary structure, a gas system to inject nitrogen into the experimental channels, a liquid system where fluid injection is routed to specific channels via a motorized rotary valve, and an imaging system that precisely positions a high-speed camera. The platform utilizes a Raspberry Pi-based control system with a keypad interface where a single input seamlessly synchronizes the rotary valve's fluid injection with a linear stage, rapidly aligning the high-speed camera to the targeted channel. The system also continuously logs inertial measurement unit (IMU) acceleration data. Ground testing validated this automated integration and demonstrated an average sample-switching time of 11.78 seconds. Ultimately, this setup will allow for efficient data collection that can inform the design of novel, passive degassing methods in space.

Ammonia is one of the most promising carbon-free energy carriers, but its slow reaction kinetics, long ignition delay time, and narrow flammability range make direct detonation initiation difficult and limit its use in pressure-gain combustion systems. Reactive co-fuels offer a possible way to overcome these challenges. However, the deflagration-to-detonation transition (DDT) behavior of ammonia-dimethyl ether (NH₃/DME) mixtures has not yet been experimentally investigated, despite DME’s well-established role as a strong low-temperature ignition promoter. This thesis addresses that gap through a combined computational and experimental study of NH₃/DME/O₂/Ar mixtures in a microchannel. NASA CEA and Cantera are first used together to evaluate different fuel compositions based on detonability, ignitability, and equilibrium emissions, narrowing a broad design space into a practical experimental matrix. To support reliable diagnostics across multiple observation windows, an automated traversal system was developed to maintain optical alignment during imaging. Flame propagation and wave-structure evolution were then captured using synchronized high-speed imaging and shadowgraphy. Results at ϕ = 1.0 show repeatable DDT in the 90/10 and 80/20 DME/NH₃ blends, while the 75/25 composition marks the practical ignition limit of the current experimental configuration. Compositions exceeding approximately 25% ammonia failed to ignite under the tested conditions. Across all ignitable blends, increasing ammonia content progressively delays both first-stage ignition and DDT onset, while also lowering peak flame-tip velocity. Despite this reduction in reactivity, successful transition is still consistently achieved in the ignitable cases. This demonstrates that ammonia can reliably undergo the full DDT process when mixed with DME. These results show that DME acts as an effective enabling co-fuel, offsetting ammonia’s reactivity limitations and bringing meaningful NH₃ fractions into the detonable regime. Extending this work to fuel-rich NH₃/DME mixtures, where computational analysis predicts higher detonation velocities and potentially earlier DDT onset, is a promising next step for accessing stronger detonation regimes and even higher NH₃ fractions. Overall , this thesis establishes NH₃/DME blends as a promising mixture for detonation-based combustion and supports ammonia’s role as a practical carbon-free fuel for pressure-gain propulsion and power systems.

As energy systems across the world push towards decarbonization, hydropower will play an increasingly prominent role as a flexibility-provider to offset the variability of renewable energy resources. Despite its importance, most capacity expansion models overly simplify the formulation of hydropower’s network, operational, and environmental constraints, aggregating individual units into large energy-equivalent resources. This aggregate approach can misrepresent the true dynamics of hydropower, obscuring its value and flexibility in macro energy systems. Recognizing the growing need for multi-sector decarbonization analysis, this study extends the base formulation of MacroEnergy.jl, implementing streamflow linkages, and disaggregating operational limits to the reservoir-level. A test case of the Brazilian power sector is proposed to understand the impact of the proposed model on system costs, hydropower dispatch, and broader capacity expansion decisions. An Aggregated and a Streamflow model are thus presented and tested on two scenarios, using 2019 as the reference weather-year: 1) one year of operations without expansion or retirement and 2) a 10-year capacity expansion period with a 15% increase in system demand. The study finds that disaggregating hydropower into cascading reservoirs and run-of-river units yields higher costs, with more generation during the wet season but restricted output during the dry spell relative to the aggregated representation. The second scenario further finds that disaggregated hydropower leads to prioritizing firm capacity, while aggregated representations over-invest in renewable energy.

Euclidean projections onto intersections of polyhedral sets are essential operations in constrained optimisation. Dykstra's algorithm provides an efficient iterative method for computing these projections; however, its practical utility is limited by a stalling phenomenon that can result in arbitrarily long execution cycles. The primary theoretical contribution of this thesis is the formalisation of the stalling condition and the derivation of its duration in closed form. Building on this mathematical resolution, a fast-forward modification is introduced that detects stalling and advances the internal memory variables beyond the stalling cycle in a single computational step. This modification eliminates the algorithm's unpredictable execution time while preserving its asymptotic convergence guarantees.

An accelerated version of the stall-averse solver is integrated within a large-scale, inexact projected gradient descent framework to address density estimation tasks via optimal transport. Specifically, we approximate Knothe-Rosenblatt triangular maps parameterised by a probabilist's Hermite polynomial basis. Empirical estimation of these maps necessitates enforcing monotonicity over a discrete sample ensemble, resulting in an ill-conditioned polyhedral feasible set. The modified Dykstra algorithm is consequently employed to compute the required Euclidean projections onto this geometric structure.

The combined architecture is evaluated across two nonlinear tracking domains. In astrodynamics, the framework is applied to non-Gaussian uncertainty propagation through orbital dynamics, reconstructing physical ground-truth shears of satellite state distributions where classical filters are inadequate. In geophysical data assimilation, the engine is used with the Lorenz 1963 system to approximate continuous mappings of chaotic probability densities. These results collectively demonstrate the robustness and scalability of the framework for mapping uncertainty distributions.

Electrostatic analyzers (ESAs) are charged-particle instruments central to space plasma physics, providing energy-per-charge resolved measurements of particle populations in the solar wind, planetary magnetospheres, and heliospheric boundaries. Conventional ESA fabrication relies on CNC machining, which can be costly, time-intensive, and poorly suited to rapid design iteration. This thesis investigates the use of Direct Metal Laser Sintering (DMLS), a metal additive manufacturing technique, as an alternative fabrication pathway for top-hat ESA prototyping. A top-hat ESA was designed from first principles, with geometric parameters selected to target an analyzer constant of approximately 4.5 and an energy resolution below 20% for 5 keV incident particles, incorporating constraints arising from DMLS manufacturing including minimum wall thickness requirements, high-voltage isolation, and ultra-high vacuum (UHV) compatibility. Electrostatic performance was predicted using SIMION particle trajectory simulations, yielding values for analyzer constant, energy resolution, geometric factor, and angular field of view. The fabricated analyzer underwent vacuum compatibility testing, high-voltage conditioning, and performance characterization using a 5 keV ion beam and a microchannel plate (MCP) detector. The measured analyzer constant of K ≈ 4.31 showed good agreement with both the theoretical value of 4.5 and the simulated value of approximately 4.0, while the experimental energy resolution of 15.7% was slightly wider than the simulated value of 12.6%, with the discrepancy attributed to particle scattering, surface roughness, and alignment uncertainties. DMLS-fabricated components demonstrated stable high-voltage operation and full UHV compatibility following standard cleaning and bakeout procedures. These results establish that additive metal manufacturing is a viable approach for ESA prototyping, offering geometric flexibility and rapid iteration while achieving performance comparable to conventionally machined instruments.

As CO2 levels in the atmosphere rise, promising new methods of carbon sequestration in the form of chemical synthesis are emerging. Plasma has been proven to lower reaction energy of fuel reduction, a concept that could be employed for CO2 graphene synthesis with an Alkali metal catalyst. This paper explores the design and manufacture of a Dielectric Barrier Discharge (DBD) cell to produce plasma at conditions conducive for the graphene synthesis reaction. Experimentation found that plasma was able to be produced at the proper conditions (200 torr, 100 ◦C, in the presence of CO2), and that increasing Ar concentration imparts beneficial effects on the plasma quality and ease of formation. Additionally, the higher temperature also proved to increase plasma volume and may increase the dissociation of species in the CO2 gas. Finally, the cell design was able to accomplish other goals, including low pressure maintenance and heat resistance. This experimentation provides the basis for future high temperature CO2 plasma research, as well as validates the ability of plasma to form in conditions necessary for graphene synthesis. In the future, experimentation with alkali metals placed in the plasma field with CO2 can be attempted to validate the theory of a plasma-induced graphene synthesis reaction.

Aircraft engines operating in particle-laden environments are frequently at risk of internal damage and performance degradation due to the ingestion of foreign object debris (FOD). This research project focuses on the design of an axisymmetric inertial particle separator (IPS) to protect small turbojet engines, employing physical testing to evaluate performance. The primary objectives of this study are to design a functional IPS prototype and to enable rapid experimental evaluation of a variety of IPS geometries. Through iterative processes, a final IPS device and physical experiments for pressure drop, separation efficiency, and flow visualization are developed to meet all design requirements. The device’s modular architecture allows for individual components of the IPS to be swapped to test a variety of geometries in quick succession. The experimentation focuses on rapid iteration and comparative analysis of IPS performance indicators, informing the selection of the final design. Key results include that the presented IPS device achieves an air-particle separation efficiency of 90.83%, demonstrates a pressure drop of 1.03% for 100,mph flight, and displays successful debris rejection in flow visualization tests. Of the geometries tested, the baseline device is supported by the most convincing experimental evidence and is therefore selected as the final IPS design. This research presents a modular, axisymmetric inertial particle separator design for minimizing FOD ingestion in small turbojet engines, enabling rapid comparison of multiple geometries via separation efficiency, pressure loss, and flow visualization experiments.