Aerospace, Physics and Space Sciences

Project Summary

Utilizing propeller propulsion, M.A.R.S. is creating a proof of concept Martian driving/flying rover that can take off and fly over obstacles or into areas of interest. Such technology saves mission time, extending the capabilities of the mission. This vehicle will also be capable of exploring the Martian terrain, similar to previous research vehicles already implemented on Mars. Our goal with this project is to design and fly a proof-of-concept rover inside a simulated Martian environment. This bimodal approach to surface mobility will positively impact the future colonization of Mars. A vehicle capable of multiple forms of transportation allows a colony to scout future landing sites or habitation zones and provide transportation for in-situ resource utilization.

Other Information

In addition to flying our vehicle in a vacuum chamber, the team worked hard to get faculty support to revigorate the vacuum chamber on campus which had been left dormant for roughly 10 years. The team created our own passthrough to send power to our vehicle as well as implemented a gantry system to simulate Martian gravity inside the chamber. Additionally, the propellers used on the vehicle were designed by our team to maximize lift in a less dense atmosphere. This is no small feat.

Project Summary

Due to their prevalence in the modern market, it is essential that students develop a strong understanding of the principles and practice of liquid bipropellant rocket design. This project was conceived as an effort to provide that practical experience and to improve upon previous attempts at developing a liquid bipropellant rocket at the Florida Institute of Technology. Should the design prove successful, it will be the first rocket of its kind to be designed, tested, launched, and recovered in the school’s history. The BiProp team is designing their liquid bipropellant rocket to compete in the FAR-OUT Competition on June 5-11, 2024, in the Mojave Desert. This Senior Capstone project builds off lessons learned from the 2022-2023 capstone project. The team is challenged with launching and recovering a liquid bipropellant rocket that must reach an altitude band of 5,000ft to 15,000ft and carry a payload above 1kg. This will be achieved by building a propulsion system that uses a propellant combination of Nitrous Oxide and Ethane, which provides a thrust-to-weight of 10:1 and a burn time of around 2 seconds. To accomplish this, the team has been divided into four technical subsystems: Grounds, Structures, Budget/Safety, and Avionics/Recovery. The team aims to complete a variety of tests before mid-May 2024: hydrostatic pressure tests of both tanks, an avionics test, and a static test fire. These tests are designed to validate the design, manufacturing, and construction of the final product to allow for revisions as necessary before the competition.

Manufacturing Design Methods

Many components and subsystems are being built in-house using the L3Harris Student Design Center (HSDC) and machine shop and in consultation with their leadership. Many parts have been machined in person using manual and CNC machinery (i.e.: lathe, mills, welding) in both locations. While official testing and operation of the rocket will be in an acceptable outdoor environment, assembly and installation of the rocket subsystems can be conducted at the reserved bench for the BiProp team in the HSDC.

Analysis

The team has used accepted industry methods (hand calculations, simulation tools, custom simulation code, etc.) to compare design approaches and to satisfy the project requirements. Design solutions for the rocket and each subsystem have been chosen based on their safety to personnel and equipment, feasibility, and cost. A full series of tests has been developed and is in progress to ensure the safe operation of the rocket.

Future Works

Future work and research opportunities include design revisions based on lessons learned, mass optimization with different materials, alternative fuel and oxidizer combinations, and further exploration of simulation & analysis software for predicting performance.

Manufacturing Design Methods

Many components and subsystems are being built in-house using the L3Harris Student Design Center (HSDC) and machine shop and in consultation with their leadership. Many parts have been machined in person using manual and CNC machinery (i.e.: lathe, mills, welding) in both locations. While official testing and operation of the rocket will be in an acceptable outdoor environment, assembly and installation of the rocket subsystems can be conducted at the reserved bench for the BiProp team in the HSDC.

Project Summary

The M2M team analyzed, constructed, and tested a small-scale lunar habitat. The habitat must provide a safe place for four astronauts to live and work in deep space for 90 days, have robust life support systems (appropriate radiation safety, fire safety, etc.), and reduce the need for resupply missions through in-situ advancement.

Project Objective

The engineering system designed for the M2M lunar habitat project is an autonomously deployed hybrid inflatable structure designed to support and protect human life from lunar environmental conditions. We developed a small-scale model of this structure to demonstrate the functionality of our design without the need for extensive funding and to readily test the system's efficacy in lunar conditions.

Manufacturing Design Methods

The system's structure consists of the center column, arm assembly, and baseplates. The center column upholds the structural integrity throughout the habitat while housing our primary deployment system and other essential components. Comprised of three integral parts: Top cap: serves as an anchor point for the arms. Center pole: houses the electronics and hardware for the habitat. Bottom cap: acts as the anchor and connection point for the base plates to the center column. As the major component in primary deployment, the arms are responsible for lowering the baseplates and providing structural rigidity to the system. Double shear joints enable the assembly to fold onto itself, allowing the arm segments to sit parallel to each other before deployment. T-slot aluminum extrusions provide a modular, compatible solution for the arm assembly, offering structural rigidity compared to other options. The base plates' main function is to provide the habitat with equidistant flooring around the center column to ensure stability on uneven lunar terrain. Our baseplates were designed in a semi-triangular shape, which has multiple components to enable foldability for practicality and size reduction. Additionally, our system includes a deployment system consisting of motor and tension cables, as well as a membrane inflation system.

Analysis

Analysis was performed using Ansys Workbench software. Static structural analysis was applied on base plates to test the stress, deformation, factor of safety, and failure points. Results meet our standard requirements. 

Future Works

In the future, the membrane will be custom-made to fit the dome shape.

Manufacturing Design Methods

The system's structure consists of the center column, arm assembly, and baseplates. The center column upholds the structural integrity throughout the habitat while housing our primary deployment system and other essential components. Comprised of three integral parts: Top cap: serves as an anchor point for the arms. Center pole: houses the electronics and hardware for the habitat. Bottom cap: acts as the anchor and connection point for the base plates to the center column. As the major component in primary deployment, the arms are responsible for lowering the baseplates and providing structural rigidity to the system. Double shear joints enable the assembly to fold onto itself, allowing the arm segments to sit parallel to each other before deployment. T-slot aluminum extrusions provide a modular, compatible solution for the arm assembly, offering structural rigidity compared to other options. The base plates' main function is to provide the habitat with equidistant flooring around the center column to ensure stability on uneven lunar terrain. Our baseplates were designed in a semi-triangular shape, which has multiple components to enable foldability for practicality and size reduction. Additionally, our system includes a deployment system consisting of motor and tension cables, as well as a membrane inflation system.

Project Summary

The primary objective of this document is to conduct a systems requirements review for Air Delivery, a 2023-2024 capstone project undertaken by the Aerospace Engineering and Mechanical Engineering senior design team at Florida Tech. It encompasses essential variables, from project necessities to task allocation and execution, aimed at achieving the established objectives. The project involves the development of a lighter-than-air delivery system, with key components including buoyancy mechanism, gas pressurization, delivery pathing, and efficient propulsion and power systems. The team aims to deliver a demonstrator vehicle to validate the concept. The blimp system comprises four subsystems: structure & payload, electrical, navigation, and safety & operations, delineating construction and testing specifics. Compliance with FAA regulations dictates a maximum loaded weight of 25 kilograms (55 pounds). The structure must achieve near-neutral buoyancy without payload. Helium gas bags strategically placed throughout the structure provide buoyancy. Propulsion must ensure positional stability and attitude control, with a minimum endurance of 3 hours and a thrust-to-weight ratio of one for effective package delivery. Ground communication with the PX6C will be facilitated through Qground, while safety protocols mandate ascent to 400 feet and precise navigation within designated test areas. Permissions from Florida Institute of Technology safety department and KMLB are required for test operations.

Project Objective

The Air Delivery System or ADS team intends to work towards the solution with an automated lighter than air demonstrator vehicle capable of performing multiple deliveries of sensitive medical goods an endurance of more than 3 hours, and a minimum of 0.9 kg total payload capacity.

Project Summary

This lab is focused on creating an experience for potential Florida Tech students to have an opportunity to learn how satellite ground stations interact with a satellite to perform maneuvers, solve problems, and analyze data. The lab is designed to have a permanent set-up in the Aerospace Lab building to create a space environment for the ESAT with an external ground station. The system will consist of a dark environment enclosing the ESAT to minimize error in attitude measurement. The lab will provide missions of varying difficulty to include educational objectives, set-up, procedures, operations, and data analysis. There are few opportunities in the astronautics concentration of the Aerospace Engineering major to operate a satellite hands-on in a realistic environment. In a true ground station, the satellite is not visible, and the user will need to use data analysis to determine what the satellite is doing before sending any commands. In terms of key requirements, the system shall be portable to the point that it can be presented at the Northrup Grumman Showcase, transporting the environmental container and the ESAT system. The system shall provide education to perform and analyze satellite simulation in a ground station environment. Each mission developed will be documented in an operator’s PowerPoint to instruct the user of the goals of the mission. Communication with the ESAT shall be wireless, and the system shall store telemetry data for future analysis. The system will integrate with external sensors, such as cameras, to perform the mission operations. There will be 2 missions, the first going over general satellite controls such as charging solar panels, detumbling, and attitude control. The second mission will use a computer vision program that recognizes and follows a target using the ESAT’s Raspberry pi camera, which is placed on top acting as the payload.

Project Objective

OBJ – 01. The SAL team shall design an interactive and intuitive code, including the satellite systems that it will interact with. • Rationale: Students will need to input adjustment commands to adjust the respective satellite in each condition when using the ESAL. OBJ – 02. The program shall determine the attitude of the satellite via wireless communication with the ESAT hardware. • Rationale: To adjust the attitude of the satellite, the program must know the attitude prior to adjustment commands and without the intervention of the satellite’s hardware. OBJ – 03. The code shall be documented and described in an operator’s manual. • Rationale: The code will be used by future groups and in future laboratories, so instructions on inputting data are required. OBJ – 04. The SAL system should be designed to maintain stability within the laboratory setting while still being durable and portable for Showcase. • Rationale: The SAL design will prioritize its stability for use within the laboratory for most of its lifetime while also considering its potential portability when required. OBJ – 05. The team will develop laboratory exercises in an operations document, designed for undergraduate students and potential students to gain experience in satellite operations. • Rationale: To develop appropriate lab exercises, the team will consider the capabilities of the system and design these to offer beneficial learning opportunities in data collection, analysis, and other areas.

Manufacturing Design Methods

Purchased a ULINE wooden crate and cut holes for the sun simulator connection piece, a window, and cables. Box is wrapped in flocking fabric both on inside and outside and has handles attached on the outside for easy storage.

Specification

ULINE crate is 32" x 24" x 24" and ESAT is cube of 10 cm x 10 cm x 10 cm.

Analysis

Mission codes were ran and tested thoroughly to ensure proper operation. Problems were analyzed and researched to fix any problems found.

Future Works

Future groups may tune the PID controller on the ESAT to allow the reaction wheel to work properly. Future groups may also create more complex missions.

Manufacturing Design Methods

Purchased a ULINE wooden crate and cut holes for the sun simulator connection piece, a window, and cables. Box is wrapped in flocking fabric both on inside and outside and has handles attached on the outside for easy storage.

Project Summary

The Seaplane Hydrofoil aims to enhance seaplane performance and safety in challenging environments by integrating hydrofoils within the aircraft's floats. The addition of hydrofoils allows the seaplane to lift off faster and shorten takeoff distances by raising the floats out of the water, reducing drag. A sub-scale prototype was developed to test novel active pitch control and hydrofoil retraction methods. These hydrofoils are designed with passive stability features and are constructed using Tow-Based Discontinuous Composites to minimize weight. The project will validate these enhancements through a rigorous flight test campaign, setting the stage for potential full-scale production using traditional manufacturing techniques.

Project Objective

OBJ-01. The team shall design, build, and test a hydrofoil attachment for a seaplane. OBJ-02. The team shall design a hydrofoil that interfaces with any floatplanes. OBJ-03. The team shall design a hydrofoil that decreases takeoff distance. OBJ-04. The team shall design a hydrofoil that improves rough-water performance by decreasing the airspeed loss per swell. OBJ-05. The team shall test the hydrofoil-equipped model plane. OBJ-06. The team shall deliver flight test performance data to prove the device's functionality.

Manufacturing Design Methods

Carbon Fiber FDM 3D printing, PLA 3D printing, Tow-Based Discontinuous Composites utilizing 1-inch carbon fiber tows, Autodesk Fusion 360, Ansys Fluent.

Specification

NACA 4412, 2 in chord, 3 in span, 8 deg AoA, located at CG with 30 deg cant angle.

Analysis

The team utilized Computational fluid dynamics (CFD) to analyze the pressure and velocity distribution around the hydrofoil and the stress/strain induced. This enabled cavitation and flutter analysis before the final structural design to ensure the hydrofoil and its rod would not suffer plastic deformation. An extensive CAD was created in Fusion 360 to model the seaplane hydrofoil prototype and its housing. This allowed the manufacturing team to make molds for the hydrofoils. The control systems were analyzed to verify proper flapevon (flap + elevator + aileron) mixer outputs and retraction. The structural integrity of the hydrofoil was analyzed by performing a three-point bending flexure test on different samples. The aircraft was configured in three ways and tested in a water strip to determine takeoff distance. A drone hovered above the test aircraft and recorded video footage. The video footage was analyzed to measure takeoff distance.

Future Works

We will explore the possibility of incorporating new technologies and materials to further enhance the hydrofoil’s housing within the floats. Furthermore, we intend to increase the capabilities of the hydrofoil to allow active pitch stabilization through an autopilot control system. Scalability feasibility has been analyzed in the team's scaling report. The RC plane poses unique challenges because ancillary actuators add significant weight relative to the aircraft's gross weight. On a larger seaplane, this would be a small fraction. Furthermore, manufacturing on a small scale requires novel techniques, as evidenced by the team's approach with tow-based discontinuous composites. The team would like to make a full-scale model in the future to analyze these concerns. The full-scale analysis would involve materials research, vibration and flutter analysis, and advanced foil shapes designed for turbulent and super cavitating conditions induced by cavitation.

Manufacturing Design Methods

Carbon Fiber FDM 3D printing, PLA 3D printing, Tow-Based Discontinuous Composites utilizing 1-inch carbon fiber tows, Autodesk Fusion 360, Ansys Fluent.

Project Summary

The Solid Propellant Adaptive and Responsive Combustion Control (SPARCC) project, led by a multidisciplinary team of engineers from the Florida Institute of Technology, aims to develop an alternative propulsion system for small satellites. Building upon previous research, SPARCC seeks to address the limitations of existing propulsion systems by utilizing solid propellant in a controlled manner. The project's objectives encompass several key components, including the development of a loading mechanism capable of securely transporting propellant grains into the combustion chamber, optimization of propellant choice and sizing to achieve desired thrust output and chamber pressure, design of a combustion chamber capable of withstanding high pressures generated during operation, and implementation of electrical components and controls to regulate propellant ignition and thrust generation. The loading mechanism is meticulously designed to ensure proper sealing and reliable operation, while the propellant choice and sizing involve adjustments to optimize performance and efficiency. The chamber sizing and design incorporate material selection and thickness considerations to withstand the intense pressures encountered during combustion. Additionally, the electrical components and controls utilize a microcontroller-based system to manage propellant ignition, thrust generation, and monitoring of system conditions. Future work will focus on optimizing mass, power, and volume considerations to align with the requirements of small satellite missions, enhancing propellant storage to improve system efficiency and versatility, improving operation time and ignition methods for rapid response and reliability, and exploring alternative materials and components to streamline the system and reduce complexity. In conclusion, the SPARCC project represents a significant advancement in the development of alternative propulsion systems for small satellites, offering potential benefits in simplicity, cost-effectiveness, and maneuverability for future space missions.

Project Objective

The project objective is to develop a proof-of-concept system that can convert the chemical energy stored by solid propellants into a controllable, on-demand thrust output for small spacecraft, thereby increasing their maneuverability.

Manufacturing Design Methods

The loading mechanism design incorporates a combination of 3D printing for non-critical components like the magazine and back plate, purchased components such as the linear actuator and aluminum extrusion, and machined parts such as the piston cap and sealing rings. All machined parts were designed by the team and created in the Harris Student Design Center (HSDC) or Machine shop using a variety of different machines: mill, lathe, waterjet, laser cutter, bandsaw, drill press, sandblaster, and belt sander. Propellant choice and sizing involve laboratory testing and analysis to determine the optimal mixture and dimensions of propellant grains, ensuring efficient and reliable performance. Chamber sizing and design are conducted through structural analysis and material selection, typically employing robust materials like steel to withstand high pressures encountered during combustion. The entire combustion chamber structure was designed and made at Florida Tech facilities by the team. Additionally, electrical components and controls are integrated, combining off-the-shelf and custom-made electronic components to regulate system operation effectively.

Specification

Propellant Choice: Utilizes a mixture of Hydroxyl-terminated Polybutadiene (HTPB) as fuel and Ammonium Perchlorate (NH4ClO4) as the oxidizer. Chamber Volume: Approximately 150 cm^3 to accommodate pressurization and thrust generation. Thrust Output: Targeting around 20 Newtons to provide sufficient maneuverability for small spacecraft. Nozzle Geometry: Utilizes a provided nozzle with exit and throat diameters of 5.88 mm and 3.04 mm, respectively. Material: Employed 1045 steel for the combustion chamber, chosen for its strength and durability under high-pressure conditions. Control System: Incorporates an ESP32 microcontroller, linear actuator, L298N Motor Drive Controller, solenoid valve, and glow plug. Power Supply: Operates at 12V with a lab bench power supply, utilizing step-up and step-down converters to adapt components to the required voltage.

Analysis

The latest sealing tests revealed that approximately 270 psi was generated within the chamber before the temperature was conducted through the chamber, reducing the pressure rapidly. The metal seal rings provide a sufficient seal given the limitations and scope of the project, thus the test was considered a success.

Future Works

As mentioned previously, SPARCC is a proof-of-concept system. Moving forward, previously omitted budgets such as mass, power, and volume, would be reimplemented to further tailor the model as a feasible propulsion system for small spacecraft. SPARCC was also initially conceptualized to have multiple valves connected to a single chamber to provide thrust along all axes. Furthermore, the system operation time needs to be optimized to reduce the minimum time to produce thrust. The propellant storage can also be improved to hold more propellant and to be replaceable to allow for reloading of the propellant bank. Finally, the system currently requires that all of the combustion gases are expelled before it can reload another propellant grain. Ideally, the system should be able to add propellant to a pressurized chamber if more thrust is required.

Manufacturing Design Methods

The loading mechanism design incorporates a combination of 3D printing for non-critical components like the magazine and back plate, purchased components such as the linear actuator and aluminum extrusion, and machined parts such as the piston cap and sealing rings. All machined parts were designed by the team and created in the Harris Student Design Center (HSDC) or Machine shop using a variety of different machines: mill, lathe, waterjet, laser cutter, bandsaw, drill press, sandblaster, and belt sander. Propellant choice and sizing involve laboratory testing and analysis to determine the optimal mixture and dimensions of propellant grains, ensuring efficient and reliable performance. Chamber sizing and design are conducted through structural analysis and material selection, typically employing robust materials like steel to withstand high pressures encountered during combustion. The entire combustion chamber structure was designed and made at Florida Tech facilities by the team. Additionally, electrical components and controls are integrated, combining off-the-shelf and custom-made electronic components to regulate system operation effectively.

Project Summary

The AIAA - Design, Build, Fly (DBF) competition team aims to design a remote-controlled aircraft that complies with 2024 AIAA - DBF competition rules centered around Urban Air Mobility applications. The project focuses on designing, fabricating, and testing a scale aircraft that meets competition requirements while incorporating innovative design principles. The team employed a method of rapid prototyping, designing for immediate on-site repair capability and mission adaptability. The competition requirements led the team to design a high payload capacity, high endurance aircraft with a detachable wing mechanism to optimize spatial efficiency while in a parking configuration. The result was a dual-motor, high wing aircraft with a large payload capacity. The choice of tricycle landing gear was driven by the competition’s short takeoff and landing (STOL) requirements.

Manufacturing Design Methods

PLA 3D Printing, Laser Cutting, Hotwire CNC, CNC Routing, Monokoting Wing/Tail, XFLR5, Autodesk Inventor

Specification

Aerodynamics: Main Wing: MH112, Wingspan: 5 ft, Aspect Ratio: 5.71, Tail: NACA 0012, CL = 1.585​, CL/CD = 7.029 Electronics: Two 4s LiPo Batteries, Maximum Thrust: 12.5 lbf, Flight Duration: 9 minutes, Propellor Size: 13” x 6.5” Structures: Empty Weight: 8.1 lbs, Carbon Fiber Fuselage Stringers, Laser Cut Wood Frame, Hotwire CNC Cut Foam Wing, 3D Printed Mounts

Analysis

A number of methods and software were used to generate a thorough, clear aircraft analysis. XFLR5 was used to simulate airflow over the wing and tail surfaces, determining the aerodynamic properties of the generated models. The team was dedicated to rapid prototyping, allowing dynamic responses to design changes and varying test circumstances. Structural, electrical, and aerodynamics testing was done on both prototypes and final designs to ensure both the components and system meet requirements.

Future Works

AIAA - DBF is a competition team slated to be continued in following years. We aim to aid upcoming teams in navigating the rapid-paced development process of the AIAA - DBF competition.

Manufacturing Design Methods

PLA 3D Printing, Laser Cutting, Hotwire CNC, CNC Routing, Monokoting Wing/Tail, XFLR5, Autodesk Inventor

Project Summary

The processes through which the solar wind turbulence dissipates its energy has been a highly research area of space science for the last 25 years. This project utilizes a numerical approach to resolve the dynamic alignment angle between velocity and magnetic field flux for balanced solar wind turbulence in a 512^3 box.

Project Objective

To produce contour plots that depict the variation of the cosine of alignment angle in space for three different spatial scales. To analyze the relationship between spatial scale and local imbalances in otherwise balanced turbulence.

Future Works

We aim to determine the proportionality of the dynamic alignment angle with spatial scale. This relationship's correlation with the turbulence spectra will then be investigated.

Project Summary

In particle physics, many processes (collisions, decays, etc.) are studied using simulations before getting recreated in laboratories. These simulations, however, need to consider the resolution effects of the detectors to be used. There is a software called GEANT4 that takes care of this quite thoroughly. However, this software takes a lot of time and computing power to process any meaningful amount of data. Our goal is to accelerate the data production process using Neural Networks. Particularly, we will be implementing instances of Mixture Density Networks that will output various models for the resolution of the detectors. These will be sampled to generate new simulated data, which should (overall) match the statistics of the GEANT4 data. So far, good results have been observed for the simulation of electrons and muons. Further fine-tuning is being performed to enhance the results for very high-energy events. In the future, other particles shall be incorporated into the pipeline. Additionally, we are looking into forms of optimizing our sampling methods.

Project Summary

This was an observational study conducted in Indianapolis, Indiana, aimed at documenting the April 8th 2024 solar eclipse, with a special focus on photographing the solar corona.

Project Objective

• To capture high-resolution images of the sun prior to a solar eclipse. • To capture high-resolution images of the solar corona during a total solar eclipse. • To investigate variations in the corona’s morphology.

Manufacturing Design Methods

• Images of the solar eclipse were taken using a Canon Rebel T7 model camera attached to a Sky-Watcher EvoStar 72mm refractor telescope, with a reducer/field flattener. • During the partial phases of the eclipse, an AstroZap solar filter was attached to block out the light from the Sun. • During totality, when the Moon was completely obstructing the light from the Sun, the solar filter was removed. • A composite image was then created by overlaying multiple images on top of each other, compiling them into one image.

Manufacturing Design Methods

• Images of the solar eclipse were taken using a Canon Rebel T7 model camera attached to a Sky-Watcher EvoStar 72mm refractor telescope, with a reducer/field flattener. • During the partial phases of the eclipse, an AstroZap solar filter was attached to block out the light from the Sun. • During totality, when the Moon was completely obstructing the light from the Sun, the solar filter was removed. • A composite image was then created by overlaying multiple images on top of each other, compiling them into one image.

Project Summary

Top quarks are exceedingly rare fundamental particles only produced in high-energy collisions. This project explores a new machine learning-based method to reconstruct the momentum of top quarks produced in the Large Hadron Collider (LHC), with the specific aim of characterizing quantum entanglement in top quarks. Top quarks are extremely short-lived with a mean lifetime of less than 10^-24 seconds. This short lifespan means that when entangled top quarks decay, characteristics of their entanglement become encoded in the kinematics of their decay products: b quarks, leptons, and neutrinos. All of these particles are observable in the LHC's Compact Muon Solenoid (CMS) detector, except for neutrinos, which can travel through the entire planet undetected. The uncertainty resulting from these neutrinos' lost momentum propagates into our measurement of top quark entanglement, making it noisy. We address this issue by training a neural network to minimize residuals in the relevant top entanglement variable (the angle between daughter leptons Lorentz-boosted by top momenta). With this method, we are able to reduce residuals by a factor of two, and significantly decrease the amount of very poorly-reconstructed events. This ultimately provides us with a significantly more precise measurement of top quark entanglement.

Specification

Our analysis runs on Monte-Carlo generated data (with detector effects simulated). Our training set contains 1.2×10^6 simulated electron-positron events. The network structure is very simple, with just two ReLU-activated hidden layers with 12 and 8 nodes. We use an 8:1:1 training:test:validation split. Data is processed in Python using sklearn, keras, vector, and custom utility & math modules built for this project.

Future Works

Soon, this reconstruction technique will be applied to real data from the LHC's CMS experiment. Additionally, we posit that similar noise-shaping neural networks (paired with analysis-specific loss functions) could be used to improve analyses in other areas of particle physics.

Project Summary

This project aimed to write python scripts that would perform high voltage quality control tests for new Gaseous Electron Multiplier detectors (GEMS) at the Compact Muon Solenoid (CMS) detector at the Large Hadron Collider (LHC). Before new GEMs can be built and installed designs must undergo a series of quality control tests. One of these, quality control number 6 (QC6) tests how the detector responds to high voltage. Multiple sub tests make up QC6 many of which are typically ran with LabView scripts. Python scripts intended to replace this LabView scripts were created and tested to perform four out of the five QC6 tests.

Project Objective

To create python scripts to replace the current high voltage quality control tests written in LabView.

Manufacturing Design Methods

In to apply HV to the various parts of the detector a CAEN SY5527 HV Power Supply with an A1515 board is hooked up to the detector. LabView code is written with diagrams word and pictures of the detector being tested. Instead of attempting to convert existing LabView code into Python, programs were written from scratch in Python to perform the necessary functions of the various QC6.

Specification

QC6 is meant to ensure the foils of each detector are without imperfections and to ensure the foils are not only able to withstand HV, but also demonstrate stability when at HV.

Analysis

Plots of a 'Stress Test', an 'IV Scan', and a 'Short Short Stability Test' are shown.

Future Works

Quality control tests based in Python as opposed to LabView provides a more streamlined approach and resolves the bugs found in the LabView code. Each of the Python scripts load in information from the CAEN via a .TOML configuration file. Storing information into a configuration files allows the QC6 tests to potentially apply to detectors beyond just GEM detectors. In addition to applications beyond GEM detectors, Python scripts can written to replace the rest of the Quality Control tests that are currently written in LabView.

Manufacturing Design Methods

In to apply HV to the various parts of the detector a CAEN SY5527 HV Power Supply with an A1515 board is hooked up to the detector. LabView code is written with diagrams word and pictures of the detector being tested. Instead of attempting to convert existing LabView code into Python, programs were written from scratch in Python to perform the necessary functions of the various QC6.

Project Summary

Theoretical developments in particle physics suggest the existence of a fourth generation of quarks that may be producible at the Large Hadron Collider (LHC) via pair production of Top partners, T Tbar. This project is part of the first ever effort to search for T Tbar into the t-gluon t-photon decay routes, focused on selecting particle collision events with the necessary physics objects.

Analysis

The searched final state has a number of physics objects, namely several particle jets, a photon, and a single lepton, which must have minimum momentum thresholds and other physical properties to be T Tbar decay products, the common particle physics c++ library ROOT is specifically designed to work with this style of data and was used with python bindings with existing Florida Tech HEP computational resources to search for these physics objects.

Future Works

Selecting candidate events from data is only the first step in finding a new particle. Additional work is being done or will be done in: Verifying background agreement in signal free region, Estimating backgrounds for the analysis Reconstructing the masses of decayed particles and many other potential further analysis.

Project Summary

I present a novel approach for detecting rogue nuclear material at country borders, addressing the current lack of reliable and economical mechanisms for this purpose. My proposed methodology utilizes Cherenkov radiation emitted by cosmic muons to reconstruct the particle's trajectory using a single detector. By analyzing the eccentricity of the projected ellipse formed when the Cherenkov cone intersects the detector plane, one can determine the angle a muon makes with the detector. This innovative technique effectively doubles the efficiency of the detection system by halving the number of required detectors while simultaneously increasing the resolution of the measurements taken. To validate the feasibility and accuracy of the proposed method, I conducted Geant4 simulations. The results demonstrated a strong correlation between the true angles of the particles and the reconstructed angles using my new model, with a 96.8% correlation achieved in a sample of 200 simulated events. These findings highlight the potential of this novel technique to significantly improve the detection of dense nuclear matter at borders, thereby enhancing nuclear terrorism prevention efforts. The successful implementation of this methodology could provide a more efficient and accurate means of identifying and intercepting rogue nuclear materials, ultimately strengthening national and international security measures.

Project Objective

The objective of this project is to develop a novel technique for detecting rogue nuclear materials at country borders using Cherenkov radiation emitted by cosmic muons. By utilizing a single detector to reconstruct the muon's trajectory, this method aims to improve the efficiency and accuracy of nuclear material detection, ultimately enhancing global security and preventing nuclear terrorism.

Future Works

In future works, I plan to further refine and optimize the proposed methodology by conducting more extensive simulations and developing a prototype detector system for real-world experiments. Collaborations with border security agencies and nuclear physics experts will be crucial in identifying potential challenges and ensuring the successful implementation of this novel approach in real-world scenarios.

Project Summary

The gravitational potential field for a galaxy is a field indicating the intensity of the gravitational pull at any point in a galaxy. To overcome a host galaxy's gravitational influence, an object must exceed the gravitational potential energy at its region in the galaxy in order to successful send itself on an escape trajectory. Utilizing this gravitational potential field, the escape velocity map can easily be resolved and applied to objects of various masses and sizes. The escape velocity map then can be used as a threshold for stellar dynamics, predicting their trajectory within or outside the host galaxy

Project Objective

Create a gravitational potential field map of a galaxy with comparable parameters to the Milky Way using density profiles to simulate the distribution of matter throughout the disk and bulge. Once obtained, use the field to determine the escape velocity throughout the galaxy.

Manufacturing Design Methods

This simulation was ran in Python utilizing various integration techniques and density profiles to resolve the gravitational potential of the disk and bulge components prior to superimposing them to create a comprehensive model.

Analysis

From the maps generated by the simulation, it can be inferred that an object must move anywhere from thousands to tens of thousands of kilometers per second to escape the gravitational influence of its host galaxy depending on its location in the galaxy.

Future Works

The next steps would be to apply a dark matter density profile to the simulation to provide a more accurate representation of the escape velocity required for an object to leave the host galaxy's gravitational influence. Information gathered from this simulation will also be helpful to the Galactic Astrodynamics Research Group in their endeavors.

Manufacturing Design Methods

This simulation was ran in Python utilizing various integration techniques and density profiles to resolve the gravitational potential of the disk and bulge components prior to superimposing them to create a comprehensive model.

Project Summary

Orbital dynamics play a crucial role in determining the habitability of exoplanets, and many models have been developed to study the dynamical evolution of broader planetary system structure. To further investigate the implications this has regarding planetary habitability, this project simulated the evolution of the Solar System with an additional planet orbiting in place of the Asteroid Belt using the Gravitational Rigid-body InTegrator (GRIT) package. 21 total simulations were run for 100,000 years with varying values for the extra planet’s mass (from 0.01 to 10 Earth masses) and orbital parameters (based on the 4 most massive asteroids in the Asteroid Belt). The habitability of the Earth’s resulting orbital parameters was then analyzed. All of the final Earth orbits were stable, but the percentage of time spent within the atmosphere-free habitable distance from the Sun varied both higher and lower than the control. These results indicate that many potentially habitable configurations of the Solar System with an additional terrestrial planet exist, and further work is needed to incorporate atmospheric effects on Earth’s climate and habitability under these conditions.

Project Summary

In this project, a 3-D region of stars, centered at the point where the Sagittarius Stream crosses the Galactic disk, is explicitly defined. The stars in this region belong to two different stellar populations, and the goal of this research is to determine what parameter (e.g. proper motions, radial velocity, etc.) can be used to discriminate between the stellar populations of merging galaxies. Because stellar streams retain the dynamical properties of their progenitors, they are the optimal candidates for tracing the formation and evolution history of the Milky Way.

Project Objective

The aim of this project is to identify the Sgr dSph’s role in contributing to disequilibrium in the Milky Way. More specifically, this research seeks to answer the following questions: i) What can debris from accretion events tell us about their dwarf galaxy progenitors? ii) What parameters can be used to distinguish between stellar populations of merging galaxies and satellites?

Specification

Data was extracted from the Gaia Archive via advanced queries implementing ADQL.

Future Works

Future work involves using Sgr dSph as framework to establish a method of tracing galactic evolution. In doing so, the applications can be extended beyond the Milky Way and applied to any suspected merger.

Project Summary

Our target object is HD15745, an F2V star with an extended scattered light disk. 27 Images were taken by the Hubble Space Telescope's (HST) Imaging Spectrograph (STIS) and its coronagraph, which helps to reveal faint structures while suppressing the star's glare. The images were captured using Angular Differential Imaging (ADI) by changing the roll angles of HST. Using Affinity Photo 2 software, the images were masked, and Python was used to perform Point Spread Function (PSF) subtraction and Principal Component (PCA) on the data. This analysis provides us with insight on the most important structures and features in the disk surrounding HD15745.

Project Objective

Can new ways of digital masking help to find important features in our data, and reconstruct the data blocked by the coronagraph during Angular Differential Imaging? What insight can Point Spread Function (PSF) Subtraction and Principal Component Analysis (PCA) give us on our newly masked images?

Specification

Digital masking was performed using Affinity Photo 2, a professional photo editing software. Array multiplication for the masking of the science images was applied using Python. Python was also used to perform Point Spread Function (PSF) subtraction and Principal Component Analysis (PCA) on our images to allow us to determine the structures and patterns in our masked data.

Future Works

Further analysis involves comparisons of standard deviations of PSF subtractions to extract patterns. Additional work on refining masking techniques could increase our ability to detect faint features in HD15745's scattered light disk.

Project Summary

We propose a new method to measure supermassive black hole (SMBH) spin using Active Galactic Nuclei (AGN) quasi-periodic oscillations (QPOs). Black holes can be characterized by three parameters: mass, charge, and spin. This makes knowledge of the black hole spin essential for many empirical issues, such as gamma-ray bursts, jets, and other outflows. We report the discovery of ~242 day and ~33.2 day QPOs found using archival 3C 273 data observed by RXTE. The upper QPO frequency is Keplerian orbital frequency, while the lower QPO frequency is the Lense-Thirring precession period. Using the recent mass estimate of 3C 273 and discovered QPOs, it is possible to estimate the spin of the SMBH.

Project Objective

First objective was to find QPOs in the RXTE archival data and determine their period. Second objective was to use the recent estimates of the mass of 3C 273 and QPOs to determine the spin of the SMBH.

Project Summary

The initial degree of gas turbulence required for stars to form is largely unconstrained with current models, especially for high-mass star formation. This is due to observational limitations towards very dense, optically thick regions of gas in the Interstellar medium where high-mass stars typically form. By observing molecular tracers of these regions, such as ammonia (NH3(1,1)), we can determine the initial degree of turbulence around denser clumps of gas, which are a critical stage in star formation. Identifying these regions can be tedious and difficult in large data surveys; therefore, unsupervised machine learning was used to find denser clumps of gas using clustering algorithms. It was found that many of these clumps form in regions of significantly low turbulence, around 0.6 km/s, often approaching the expected value in local thermodynamic equilibrium. This suggests that the formation of gas clumps is turbulence-dominated and turbulence plays an important role in the formation of massive stars.

Project Objective

In this project, I will identify dense clumps of Ammonia (NH3(1,1)) gas from the Radio-Ammonia Mid-Plane Survey (RAMPS) using machine learning and measure the turbulence and density at each of these clumps.

Manufacturing Design Methods

I implement K-Means clustering, an unsupervised machine learning algorithm that spatially clusters data into regions of higher density, where K is the number of clumps found in the data. I determined the best K value by using a silhouette analysis, which minimizes the within-cluster separation of data and provides a metric for measuring the clustering efficiency. Using the clumps identified, I measured the kinematics, temperature, turbulence, and density of each clump and plotted the distribution of these regions to visualize where NH3(1,1) typically clusters the most in these regions.

Analysis

In the plot of turbulence vs density for each of the clumps, we can see that most of the clumps form at very low turbulence, around 0.6 km/s, and typically have a higher density as well. We can also see that most of the clumps are approaching local thermodynamic equilibrium (LTE), which shows that the gas is turbulence-dominated in these regions and star formation heavily depends on the initial gas clump turbulence.

Future Works

By measuring the distances using a combination of known parallax values and utilizing a Monte Carlo sampled kinematic distance method, we can measure the distances to each of these clumps. Knowing the distance to these sources will allow measurements of the mass fraction of ammonia in each clump, which we can compare to the virial mass to determine whether these regions are undergoing gravitational collapse. In addition, plotting a galactic map of these clumps that shows where collapse is occurring may provide support for the competitive accretion model of high-mass star formation.

Manufacturing Design Methods

I implement K-Means clustering, an unsupervised machine learning algorithm that spatially clusters data into regions of higher density, where K is the number of clumps found in the data. I determined the best K value by using a silhouette analysis, which minimizes the within-cluster separation of data and provides a metric for measuring the clustering efficiency. Using the clumps identified, I measured the kinematics, temperature, turbulence, and density of each clump and plotted the distribution of these regions to visualize where NH3(1,1) typically clusters the most in these regions.

Project Summary

Our project investigates the spatial distribution of carbon monosulfide (CS) emissions relative to young stellar objects (YSOs) and molecular cloud boundaries. Utilizing observational data from Dr. M.O. Lewis, we analyze CS emission patterns using spatial analysis tools like Aladin, mapping them against astronomical survey backgrounds. Our hypothesis is that CS emissions predominantly occur at the edges of molecular clouds, indicating specific environmental conditions conducive to emission. Our findings confirm a concentration of CS-only emissions along the outer edges of molecular clouds, supporting our hypothesis. These insights shed light on the spatial dynamics of CS emissions around YSOs, enhancing our understanding of star formation processes within molecular clouds.

Project Objective

Our project aims to analyze the spatial distribution of carbon monosulfide (CS) emissions in correlation with young stellar objects (YSOs) and molecular cloud boundaries. Utilizing observational data provided by Dr. M.O. Lewis and employing spatial analysis tools like Aladin, our goal was to validate our hypothesis that CS emissions predominantly occur at the edges of molecular clouds, indicating specific environmental conditions that support these emissions. By clarifying these spatial dynamics, our objective is to deepen our understanding of star formation processes within molecular clouds.

Manufacturing Design Methods

This research utilized advanced spatial analysis using the Aladin software tool, integrating data from different astronomical surveys (2MASS, allWISE, DSS2) to perform comparative spatial mapping and detailed visibility enhancement of CS emissions across multiple wavelengths.

Analysis

The analysis identified a notable concentration of CS-only emissions along the outer edges of molecular clouds, supporting the hypothesis that these boundary regions host specific conditions conducive to CS emissions. This was demonstrated across multiple figures and using different wavelengths, confirming a consistent spatial trend across the study area.

Future Works

The next stage involves detailed spectral analysis using CASA to further investigate the correlation between emission locations and observed spatial patterns. This will help in uncovering the underlying reasons for the observed trends and refining the understanding of processes at molecular cloud boundaries.

Manufacturing Design Methods

This research utilized advanced spatial analysis using the Aladin software tool, integrating data from different astronomical surveys (2MASS, allWISE, DSS2) to perform comparative spatial mapping and detailed visibility enhancement of CS emissions across multiple wavelengths.

Project Summary

JetCurry is a program designed to attempt to construct 3D models of relativistic jets from 2D data. We find the flux maxima of the jet centroids and from there use them as inputs to build the jet. The program uses MCMC solvers to find geometric parameters and converts them to Cartesian coordinates. From there, a 3D visualization is developed that one can use to visualize a jet better. Jetcurry currently assumes that the jets are non-relativistic. The program has been tested on the M87 jet, particularly the knot D region and the core of M87. Future work will include running the entire M87 jet through jetcurry and updating jetcurry to account for relativistic effects. This work is important as we cannot assume any symmetry with a relativistic jet, since it does not have a general shape, only a general direction of propagation, unlike other objects like stars and certain galaxies. Jets contribute the moving material to the interstellar medium and other galaxies, so they are an important contributing factor to the evolution of their host galaxies and the surrounding galaxies.

Project Objective

The objective of this project is to build a program to visualize these jets from multiple angles

Manufacturing Design Methods

Jetcurry uses Python as a basis for running. It will take an image of a jet and its flux maxima as an input, from there it will take some geometric parameters, and use Monte Carlo Markov Chain solvers to solve for the other parameters. These are then converted to cartesian coordinates that are used to visualize the jet.

Specification

Jetcurry currently assumes the relativistic jets are non-relativistic.

Analysis

Jetcurry successfully developed three dimensional coordinates and their two dimensional projection of the points lined up with the flux maxima showing a successful visualization of the M87 Core and Knot D of the jet

Future Works

Future work includes developing a three-dimensional visualization of the M87 core and running jetcurry through the entire M87 jet. Once we have confirmed it works on the whole jet then relativistic effects will be accounted for

Manufacturing Design Methods

Jetcurry uses Python as a basis for running. It will take an image of a jet and its flux maxima as an input, from there it will take some geometric parameters, and use Monte Carlo Markov Chain solvers to solve for the other parameters. These are then converted to cartesian coordinates that are used to visualize the jet.

Project Summary

In pursuing sustainable human colonies beyond Earth, using extraterrestrial environments for agriculture has become a significant area of research. Among all other planets, Mars stands out as a potential candidate for human habitation; however, the challenges of cultivating crops in its unique environment require creative solutions. The methodology involves analyzing a range of experiments on various crops and their responses to varying light and temperature conditions. These findings offer insights into creating an optimal growth environment for crops on Mars. Additionally, energy resources to supplement the lower solar irradiance on Mars, including nuclear power, wind turbines, or solar panels, are considered. These findings could contribute to the design of advanced Mars habitats, sustainable agricultural systems, and cost-effective missions. Furthermore, the research holds potential applications on Earth, promoting controlled environment agriculture and sustainable crop production.

Project Objective

This project aims to answer the following questions: How do varying light and temperature levels impact the growth and development of different crops? Are there effects between specific light and temperature combinations that enhance crop yield and nutritional value?

Project Summary

A hypervelocity star occurs when it is traveling at thousands of kilometers per second, while stars normally travel at only hundreds of kilometers per second. One theory of how this happens is a binary star system, meaning two stars are in orbit around each other. It is thought that when one of the stars explodes into a supernova, the remaining star then gains the energy to travel at thousands of kilometers per second. In addition to this uncertainty, binary star system supernovae are rarely modeled to visualize the code and what is physically occurring.

Project Objective

The purpose of this project was to write a code tackling these two issues; hypervelocity stars and the lack of visualizing code for supernova explosions.

Manufacturing Design Methods

In Jupyter Notebook, a mix of Python and VPython was used to create a simulation of a binary star system, where one star goes supernova.

Analysis

When modeling the star system, the initial mass of the stars and the initial distance between each star have a bigger effect on the system’s outcome compared to the initial radius of the star.

Future Works

More trials need to be done by making specific comparisons relating different orbit shapes as well as adding more stars into the system.

Manufacturing Design Methods

In Jupyter Notebook, a mix of Python and VPython was used to create a simulation of a binary star system, where one star goes supernova.

Project Summary

To facilitate the production a modular, autonomous meteor observation system, our team has worked to develop a 3D printed mounting structure to contain the system’s various off-the-shelf components. This system has undergone several iterations but has finally landed on a finalized design that is versatile enough to accommodate various boxes meant to house the observation system. This project details this structure’s design and manufacturing.

Project Objective

Our goal was to create a meteor observation system that could be assembled quickly and inexpensively for large scale distribution and observation across the country.

Manufacturing Design Methods

The creation of this observation system’s mounting structure was accomplished using additive manufacturing with a carbon fiber-nylon filament produced by MarkForged. This filament enables usage in higher temperature environments over longer timescales.

Future Works

With the printing and assembly of 10 new observation nodes nearly complete, our team will soon switch its focus to deploying these systems and processing the data that they gather.

Manufacturing Design Methods

The creation of this observation system’s mounting structure was accomplished using additive manufacturing with a carbon fiber-nylon filament produced by MarkForged. This filament enables usage in higher temperature environments over longer timescales.

Project Summary

My project is about using the all sky monitor attached to the satellite SWIFT in order to take observations of various AGN. Using this data to try and calculate the QPO's (Quasi-Periodic Oscillations) of these AGN. Once we find the periods for these AGN we are hoping to, in the future, compare this data to that of other satellites and attempt to find the true period and what it can tell us about the various objects we are looking at.

Project Summary

Earth is unique for being the only planet known to be currently habitable, making it essential for study when it comes to searching for life elsewhere in the universe. In the new and growing field of astrobiology, many unknowns and uncertainties remain with regards to the emergence of life on Earth. Urability, in contrast to habitability, describes the ability of a world to host abiogeneiss, the process through which organisms arise from non-biological materials. Various habitats found on Earth have been suggested as potential urable sites, including but not limited to deep sea hydrothermal vents, semiarid intermountain valleys, atmospheric aerosols, lakes and ponds, beaches and lagoons, nuclear geysers, impact craters, and hydrogels. These sites have been identified as providing the basic criteria assumed to be required by life as we know it. These criteria, although still undefined and contestable, tend to include the following: a solvent (liquid water) and sources of free energy and organic compounds as well as mechanisms for concentration and for amplifying reactions. Here, we are concerned with estimating the number of abiogenesis events on a given world despite the limited information available (the only instance being that of the emergence of life at least once on Earth) by generating the Probability Distribution Function (PDF) and, subsequently, the Cumulative Distribution Function (CDF) of the probability of a given site i hosting a successful abiogenesis event, which is denoted here as p_L. By looking at three extreme scenarios (the optimistic, pessimistic, and agnostic cases, with p_L ~ 1, p_L ~ 0, and the “uninformative” log-uniform prior, respectively) for the abundance of abiogensis, insight can be gained into the potential PDFs for different values of p_L.

Project Summary

Radiation protection is a crucial consideration in space exploration and settlement. Among the various types is ultraviolet radiation (UVR) which can have significantly deleterious effects on biological organisms. Prior to the formation of the ozone layer, Earth was affected by these rays, along with the different bacterial species that were present significantly impacting the distribution and nature of life across Earth. Members of the phylum Cyanophyta (Cyanobacteria), among the oldest living organisms, evolved to grow under such heavily irradiated conditions. One common strategy among members of this phylum is the production of dense ‘biomats’ which can protect the bacteria from radiation while also providing a nutrient rich environment. Such biomats are crucial to the pioneering role members of this genus play in regenerating ecosystems and could be of significant benefit to space agriculture efforts. We hypothesize that the cyanobacteria Anabaena cylindrica has natural resistance and recovery systems to withstand UV radiation and still form biomats which could be used to support plant growth in regolith-based agriculture. While A. cylindrica resistance to UV-A and B radiation is well documented, less is known about the resistance to UV-C. We hypothesize that following exposure to UV-C, A. cylindrica retains its capacity to produce these biomats in the present study we provide preliminary data on UV-C resistance and recovery via. If A. cylindrica can withstand these UV-C rays, it is a promising species for future space colonies which could use it to fertilize regolith found on different planets.

Project Summary

In the eukaryotic algae Chlamydomonas reinhardtii, when the cell density is high enough, an unknown molecule, known as the CSSF (Chlamydomonas Swimming Speed Factor) causes an acceleration in the swimming speed of the algae. This is the product of quorum sensing (QS), a phenomenon that couples phenotypic switching to population density. Understanding the QS process in C. reinhardtii has significant implications to our understanding of microbial ecology as well as the distribution of the QS phenomenon more broadly in the microbial world. This work is focused on the isolation and identification of the CSSF. Here we will attempt to resolve important structural questions as to the nature of the signal molecule. This will include the use of HPLC (High Pressure Liquid Chromatography) to isolate fractions containing the CSSF, as well as enzymatic treatments to inform on its identity.

Project Objective

This work is focused on the isolation and identification of the CSSF. Here we will attempt to resolve important structural questions as to the nature of the signal molecule.

Manufacturing Design Methods

Low-cell density cultures of Chlamydomonas reinhardtii are grown in three flasks, and one milliliter of culture is added to microcentrifuge tubes. Three tubes are labeled control and contain only the low-cell density cultures, while 10 microliters of acidified high-cell density extract is added to the others, after this, an activity assay is employed.

Analysis

Extract testing supports that the HCD 124 extract contained the CSSF, and the average swimming speeds for the treated samples was about double that of the controls.​ The acidified extract had very similar speeds to that of the normal extract test, suggesting that the CSSF is not pH sensitive.​ Additional tests need to be employed to further identify the structural composition of this signal molecule​

Future Works

I plan to continue enzymatic tests on the positive extracts to attempt to solve structural composition questions on the CSSF.​ I also plan to work closely with fractions from the positive extracts to identify the molecule through HPLC testing.​

Manufacturing Design Methods

Low-cell density cultures of Chlamydomonas reinhardtii are grown in three flasks, and one milliliter of culture is added to microcentrifuge tubes. Three tubes are labeled control and contain only the low-cell density cultures, while 10 microliters of acidified high-cell density extract is added to the others, after this, an activity assay is employed.

Project Summary

Martian and lunar settlements will require sustainable practices to support human habitation due to cargo constraints. In-situ resource utilization (ISRU) maximizes available resources on extraterrestrial bodies, limiting the materials imported via spaceflight. Crop production will be an integral part of supporting these settlements. Upper layers of Martian and lunar regolith can be modified into viable plant growth substrate with the application of microbial life. Atmospheric resources available on Mars for plant growth include carbon dioxide and a small amount of nitrogen. Observation of species on Earth which utilize these resources lead to solutions for extraterrestrial crop production. Using the nitrogen and carbon dioxide present in the Martian atmosphere, cyanobacteria can produce nitrate and sugars which aid plant growth. I hypothesize that these pioneering species can be used to fertilize Martian and lunar regolith. In this study, the quick-growing cyanobacteria Anabaena cylindrica is grown and its biomass is introduced to Martian and lunar regolith simulants. Cell density and nitrate production are measured to determine photosynthetic and nitrogen fixing activities. Growth methods are explored, including growth in regolith simulants, as a liquid culture, and in a bioreactor built for the project. The effects of various methods of supplementation including growth with regolith, application of liquid culture, and concentration of cells are then tested on seeds planted in the substrate. These findings will impact understanding of how Earthly biochemical processes can be leveraged on extraterrestrial bodies to support settlement and extend the locale of human life.

Project Objective

Remediation of Martian and lunar regolith will give astronauts agency to use the most widely available resource to support their habitation on each of these bodies.

Manufacturing Design Methods

A sterile bioreactor is built using a five gallon water jug, an air input with HEPA filter, a Lowry disk for gas collection, a pressure gauge, and a sterile pressure relief component. The bioreactor is filled with low-nitrogen liquid media to promote the nitrogen fixation capabilities of the microbe. Arabidopsis thaliana (GA-1) is utilized as a model plant species to test the realistic application of the cyanobacterial fertilizer.

Analysis

Analysis of photosynthetic and nitrogen fixing activities is performed using chlorophyll extraction and ion chromatography. Interactions between microbes and regolith simulant viewed using Scanning Electron Microscope.

Future Works

Plant growth trials for concentrated cyanobacteria application to regolith simulant are still underway. Cation chromatography will reveal the biomining capabilites of the microbe in the presence of regolith simulants.

Other Information

Image of bioreactor located in attached file.

Manufacturing Design Methods

A sterile bioreactor is built using a five gallon water jug, an air input with HEPA filter, a Lowry disk for gas collection, a pressure gauge, and a sterile pressure relief component. The bioreactor is filled with low-nitrogen liquid media to promote the nitrogen fixation capabilities of the microbe. Arabidopsis thaliana (GA-1) is utilized as a model plant species to test the realistic application of the cyanobacterial fertilizer.

Project Summary

Establishing a bioregenerative life support (BRLS) system with supplemental food production is key to the sustainable settlement of sites too remote for easy resupply from Earth. Decomposers are organisms capable of breaking down organic material making nutrients available for reuse by other organisms. We propose that involving edible decomposers into BRLS systems is an efficient method of recycling valuable organic plant waste for a settlement’s ecosystem. Specifically, in conditioning lunar or Martian regolith to support further plant growth, while also introducing a supplemental nutrient source for settlers. Pleurotus ostreatus (Pearl Oyster mushroom), is a model fungus for exploring this option due to its simplicity in growth, nutritional value, and abundance in nature. We hypothesize that the ratio of organic matter to regolith in substrates for P. ostreatus growth is correlated with both the yield of edible biomass as well as the enhancement of soil parameters associated with improved plant growth relative to unconditioned regolith. In the present investigation, we aim to optimize the ratio of regolith to organic material that will support viable fungi growth as a preliminary step in this process. Our findings contribute to our understanding of food security, BRLS, and in situ resource utilization for future Martian settlements.

Project Summary

The Moon’s gravitational force and the Sun’s gravitational force on the Earth cause ocean tides, which is theorized why life first began on Earth. This relationship extends to the Moon, where a hypothetical moon with oceans could also have tides. This creates the question: Are there exomoons of specific sizes and distances from the host planet with tidal modulations conducive to waves? Tidal modulations and the habitability of exoplanetary systems. This expands to studying the habitability of the exomoon itself and whether tidal modulations large enough can create waves on the planet if liquid exists. This paper focuses on a Python model that creates regions of validity of the mass of the moon-to-planet ratio (x-axis) and the distance to planet AU (y-axis). Theoretical variables will be expanded to real planets to prove the model. Certain exomoons will have this tidal modulation with specific masses of planets. Some will be too small or far from the planet to create this tidal modulation. The contribution to field/theory relates to JWST & other telescopes, which can be implemented to study specifically for exomoons that orbit planets of specific sizes to find these exomoons.

Project Summary

Active galactic nuclei (AGN) are caused when a galaxy’s supermassive black hole accretes large amounts of mass, in the process emitting copious amounts of light. We aim to predict the effect of an AGN on the habitability of nearby terrestrial exoplanets, as well as the distance to which this effect is significant. This project is the second in a series to study this phenomenon. The first was published by Ambrifi et al, 2022, in MNRAS. Where Ambrifi et al. Studied this phenomenon under the constraints of the the Milky Way galaxy, we aim to expand upon Ambrifi et al.’s work by extending the scope to galaxies outside of the Milky Way.

Project Objective

1. Observe and measure the effects of black hole mass, radiative efficiency, and outflow velocity on habitability (Changing the black hole mass and efficiency changes the luminosity.) 2. Observe and Measure multiple variables which impact habitability. 3. Use these data to draw conclusions about potentially habitable areas in other galaxies.

Analysis

1. Adjusting the black hole mass increased the distance at which the galaxy was inhabitable. 2. Adjusting the black hole mass resulted in primarily linear relations. 3. The outflow velocity was found to have minimal effect on habitability. 4. The radiative efficiency provided the greatest effect on the measured variables. Rather than our expected linear trend, we found a series of power laws.

Future Works

1. Increase parameters to include momentum driven outflow. 2. Increase parameters to include hydrogen based atmospheres.

Project Summary

As space exploration expands exponentially, it is necessary to focus on the effects of spaceflight on human health. Radiation, in long-term encounters, is known to damage cellular structure mechanisms, leading to mutations and later to cancer. In space, astronauts face increased ionizing radiation due to not having a protective barrier, which may trigger a carcinogenic effect. The Low Earth Orbit (LEO) is protected by Earth’s atmosphere and the magnetosphere, but it can still be affected by increased solar radiation during solar particle events. The LEO is estimated to be 0.33-0.44 mGy per day, while a human on Earth absorbs about 1 mGy compared to outer space dosimeter readings that showed a 1-1.8 mGy per day. The National Cancer Institute made a model called Radiation Risk Assessment Tool (RadRAT) to calculate the lifetime cancer risk from ionizing radiation, which calculates with a 90% uncertainty the probability of getting induced cancer by high-energy radiation. The dose can be acute or chronic, simulating a long-term exposure or a particular event. We used this tool to calculate and compare the lifetime risk of getting induced cancer in different situations.

Project Summary

Food security is a prominent concern in harsh environments, even on Earth. When humans begin to travel off world, where traditional soil is scarce or not availablefood will continue to be a prominent concern. As conditions change, methods must as well, and this may necessitate farming in Martian regolith. In the interest of conserving crew time in these hostile environments, automated farming may play an important role in ensuring food security. Farmbot is a robot designed to automate farming and allow this work to be controlled remotely. While initially created for Earth, this project will continue previous work to assess its ability to farm in regolith. Finer particles of regolith simulants present a challenge for this system, as the more delicate components will cease to function if they are exposed to too much dust, and the regolith has the potential to build up in the wiring connections and accumulate on tools with frequent contact with the regolith. The present study will expand on prior studies by expanding functionality of the robot to include an automated watering system and soil moisture sensor. A self-cleaning feature to eliminate regolith dust will also be explored. The objective is to have the robot fully able to perform the task of growing viable plants in regolith without human intervention to the point where they may be harvested, while self-cleaning, evaluate its performance, and assess if the robot is a worthy investment based on the crew time required to maintain the robot versus performing comparable tasks manually.

Project Objective

Have the Farmbot in working condition to evaluate it's capability to grow edible plants in regolith simulant.

Manufacturing Design Methods

The robot was equipped with a new Arduino after evaluation revealed that the connector pins on the old version were too damaged to have the watering system function in tandem with the soil moisture sensor tool, and prevent the addition of other tools that could improve function within regolith.

Analysis

The upgraded system is now in line with FarmBot's current standards and has a better system that could be further expanded on and customized for regolith research.

Future Works

The future of this project will entail having the robot compete against a human farmer and compare the results of their harvests and if the robot's difficulties are correctable.

Manufacturing Design Methods

The robot was equipped with a new Arduino after evaluation revealed that the connector pins on the old version were too damaged to have the watering system function in tandem with the soil moisture sensor tool, and prevent the addition of other tools that could improve function within regolith.