Projects
Modeling a Tri-Axial Gas Puff Valve for use in Pulsed-Power
Z-pinches
The stability of gas puff Z-pinch plasmas are highly dependent on the radius of the gas column used to generate them. However, stability can be significantly increased by using annular gas shells rather than a filled gas column and by carefully tuning the density of each shell's density. This project was preliminary work on the development of a computational model of the gas puff valve in the Cornell Beam Research Accelerator in order to characterize the density profiles better.
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This project stretched the limits of the CFD software ANSYS FLUENT by modeling high-pressure flow into a vacuum.
Velocity field of a gas puff from a 2D axisymmetric simulation of a Tri-Axial Gas Puff valve firing into a Vacuum Chamber
Venus Climate Orbiter and Autonomous Explorer
NASA's Planetary Sciences Decadal survey expressed the need for an investigation of Venus' climate to increase our understanding of climate change on Earth. This report is a comprehensive preliminary design review of a mission that addresses the goals of the Decadal survey by utilizing a semi-buoyant helicopter deployed to the Venusian atmosphere. The PDR outlines the size, weight, power, specific components, and rationale for key spacecraft subsystems. It also indicates the system requirements fulfilled by the design choices. The PDR also outlines the necessary work required before the mission concept could proceed to Critical Design Review. Linked below are the System Requirements, System Design Review and Preliminary Design Review
Thermal Protection System Models for Entry into Venus’
Atmosphere
This report is a specific analysis of the thermal protection system for the Venus Climate Explorer described in the project above. The mission uses an in-situ explorer that will use a semi-buoyant design in order to avoid the extreme temperatures and pressures on the surface of Venus. An investigation of the thermal protection system (TPS) requirements for this explorer to enter Venus' atmosphere was conducted using a number of NASA codes for simulating the thermal conductivity of porous materials as well as heat flux loading and recession during atmospheric entry.
Heating profile of a 2.75 cm thick Cork heatshield during Venus Atmospheric Entry measured at a variety of depths withing the heatshield
SPUN: Solar Propulsion to Uranus and Neptune
The SPUN (Solar Propulsion to Uranus and Neptune) spacecraft concept is a continuation of the Non-Nuclear Exploration of the Solar System Study developed through the Keck Institute of Space Studies (KISS). The goal is to develop a mission concept to reach outer solar system planets using electric propulsion, rather than conventional chemical rockets. This study examines Hall, Ion, and Field Emission thrusters for use as both primary and secondary propulsion for such a mission. It also examines the power system requirements and overall vehicle design for such a mission.
Rendering of relative size of solar panels compared to spacecraft bus, for proposed SPUN mission
High Velocity Interstellar and Deep Space Planet Reconnaissance: Hunting for Planet 9
The High-Velocity Interstellar Deep Space Planet Reconnaissance (VIDAR) spacecraft is designed to search for a presupposed 9th Planet on the solar system's edge. Using the New Horizons spacecraft model, this study lays out the mission requirements, including duration, spacecraft requirements, and scientific objectives. The study also determines this mission's optimal flight plan and launch vehicle. Finally, it investigates the pointing and attitude control requirements for such a mission to Planet 9.
Timeline of VIDAR Mission to Planet 9 including major mission milestones
FEA Analysis of a Space Plane Wing
In this study, the Space Shuttle profile is used as a starting point to design an optimized wing based on the results of finite element analysis (FEA) modeling of mechanical and thermal stresses during a typical reentry. The overall goal is to make the wing as lightweight as possible, as this would help reduce mission costs or increase payload capabilities. The thermal and structural modeling was conducted independently since the thermal protection system does not add structural support.
ANSYS Structural simulation of an aluminum space plane wing during maximum dynamic pressure