Aerospace, Physics and Space Sciences

Project Summary

The use of unmanned aerial vehicles (UAVs) has proven to greatly enhance search and rescue operations by reaching inaccessible areas quickly and safely. The ability of drones to cover vast areas while providing real-time feedback is crucial in search and rescue missions. Nonetheless, the drone’s limitations become apparent due to its quickly deteriorating battery life while in flight. The primary objective of Project DROVER is to design, build, and fly a drone-rover hybrid prototype designed to enhance search and rescue operations capable of aerial and terrestrial navigation to locate and assist people in distress. This prototype will demonstrate the unique capability to take flight when traversal via driving is not possible due to obstacles such as steep inclines and impassable debris. This hybrid vehicle holds the potential to revolutionize search and rescue operations by harnessing the energy efficiency of a rover combined with the agile air mobility of a drone.

Project Objective

Objective 1: The team shall design, build, and test a drone-rover hybrid that can drive, fly, and turn in a search-and-rescue environment. Objective 2: The DROVER shall be able to establish communication with identified targets in support of mission operations.

Manufacturing Design Methods

The Rocker-bogie components include the legs, the attachments, the assembly of these parts, as well as the wheels and motors. The legs were made out of carbon fiber tubes that were cut using a Kobalt Wet Tile Saw to the desired length. The attachments were printed using the 3D printers located in the HSDC and were printed using an onyx filament. Once these components were manufactured and verified, they were assembled and attached to the rest of the structure. The motors have specially made mounts that were made from PLA and attached to the inside of the legs, and then there was special adapter made from polycarbonate for the wheels to fit on the shaft of the motors. The attachments as well as the motor mounts were attached to the carbon fiber tubes using an epoxy found in the HSDC. The drone structure includes the drone plate, the drone arms, as well as the mounting of the drone motors. The drone plate and drone arms were made out of carbon fiber plates cut with the PROTOMAX waterjet in the HSDC. The full structure was assembled using epoxy and fasteners.

Specification

Drone Motors: T-Motor V3120 700KV Drone Props: Master Airscrew 11x5.5-3 blade propellers Flight Controller and software: Pixhawk 6x with Ardupilot software Hobby Wing Xrotor 4-in-1 esc Remote Control: Radio Master TX16S FrSky R-XSR Receiver Driving system microcontroller: Arduino Nano Driving Motors: 20mm Metal Gear Motor Model NFP-GM20-180 ReadyToSky GPS FPV Camera Reaper Nano 25-350MW VTX FPV Monitor IR Camera Microphone & Speaker Microcontroller for IR camera and speaker system: Raspberry Pi

Analysis

-Tested live video feed of FPV camera and IR camera during operations. -Established 2-way verbal communication. -Tested flying and driving capabilities of the prototype independently and combined. -Completed obstacle course with 600g payload, featuring 20° inclines and diverse terrains. -Implemented automatic landing failsafe in case of controller signal lost and low system battery. -Conducted endurance test resulting in a 15-minute hover time.

Future Works

All objectives are complete in DROVER’s prototype design; however, it is not an industry-ready product. To enable use in industry, some future work includes: -Protective electronic casing. -Improved two-way communication. -Consolidate major electronic components. -Improvement of battery technology. -Retractable flight system. -Drive system improvements.

Acknowledgement

Project DROVER wants to thank their faculty advisors, GSA Steven Holmberg, Zac Schardt, and other HSDC staff for their guidance.

Project Summary

Project Vulcan aims to advance propulsion technology by developing a proof-of-concept metal 3D-printed clustered aerospike engine featuring an integrated Liquid-Injected Thrust Vector Control (LITVC) system. Aerospike engines, known for their unique altitude compensation properties, offer theoretical efficiency across varying altitudes, potentially outperforming traditional bell nozzles. The addition of an LITVC system promises enhanced control, making this a significant contribution to propulsion technology. Project Vulcan is developed in partnership with Vaya Space, aligning with their small launch vehicle, Dauntless, designed for cost-effective space access. Vaya Space focuses on sustainable and affordable launch solutions, particularly in the small satellite market. This collaboration provides Project Vulcan with practical relevance, placing it within the context of industry developments and directly supporting applications in commercial and research satellite launches. Through this effort, we aim to gain insights into the feasibility, performance, and optimization of the LITVC system, enhancing future designs and implementation strategies. Our objectives include designing, constructing, and validating an aerospike engine through static fire testing with solid rocket motors. The project will use iterative additive manufacturing, a custom-built test stand, an altitude-simulating shroud, and a tunable Ansys model to optimize performance, streamline virtual testing, and reduce the need for physical prototypes. Safety is prioritized in alignment with Vaya Space’s protocols, ensuring risk mitigation during testing. By the end of the academic year, Project Vulcan will deliver a validated prototype with comprehensive data, contributing valuable insights to next-generation propulsion systems.

Project Objective

The objectives of Project Vulcan center on validating the performance, manufacturability, and control capabilities of a clustered aerospike engine with integrated LITVC. The aerospike shall withstand a 3-second static fire test using solid rocket motors to simulate real-world flow conditions, ensuring aerodynamic efficiency and structural durability under operational stress. It shall be fabricated using additive manufacturing technologies to take advantage of intricate design fidelity, rapid prototyping, and optimized structural performance. The aerospike must be fully compatible with the custom-designed test stand to streamline integration and minimize the need for adjustments during testing. Additionally, an altitude-simulating shroud shall be designed and fabricated to interface with the aerospike system, enabling accurate performance assessment across a range of atmospheric conditions. Finally, the aerospike shall incorporate a Liquid-Injected Thrust Vector Control (LITVC) system, allowing precise thrust vectoring through liquid injection into the exhaust flow and expanding control authority over the engine’s performance envelope.

Manufacturing Design Methods

Due to the complexity of the aerospike geometry, advanced manufacturing methods needed to be applied to account for the interior cooling lines. To enable this, laser-powder bed fusion (LPBF) was selected as the optimal manufacturing method. LPBF is a metal printing technique that uses lasers to melt layers of microscopically thin material. To ensure that the aerospike design could be manufactured successfully, certain requirements were set in place. This included having a minimum 45º angle to reduce the need for support structures, a teardrop shape for any interior cooling lines that were originally circular, once again to minimize the need for support structures. The final requirement was ensuring a minimum 2 mm thickness throughout the geometry. This is to ensure proper metal fusion and reduce the chances of warping with each added layer. To prepare the aerospike geometry for the high-stress thermal environments, both thermally and in the context of the expected high pressure, a heat treatment was done to set the internal crystal structure to the right specifications. The material of choice was AlSi10Mg. This was chosen due to its high thermal conductivity as well as its price. The selected manufacturer was MIMO Technik, a 3D metal printing company that specialized in LPBF.

Specification

Metal 3D-Printed Aerospike: The metal 3D-printed radial aerospike engine represents a complex integration of advanced manufacturing, fluid dynamics, structural resilience, and data acquisition, culminating in a system designed for high-temperature, high-pressure static fire testing. The system-level components have been carefully developed to ensure a seamless and controlled testing environment at the Vaya Space facilities. Test Stand: The custom-built test stand replicates a Stewart Platform and serves as the structural foundation for the aerospike engine, securing it against thrust forces up to 1.5 kN. The stand incorporates two steel plates, clevis brackets, spherical brackets, and load cells, ensuring accurate force measurement and stability. Two rings of M12 and M10 bolts are used to secure the model flange to the test stand for maximum structural integrity. The base is then bolted to the concrete floor at the Vaya Space test site during firings to ensure secure stabilization. The test stand was specifically designed to take measurements in 6 degrees of freedom (DOF). This is done to avoid constructing two different test stands for thrust and LITVC. Altitude Simulation Shroud: An altitude-simulating shroud compatible with the aerospike design will be placed around the nozzle. This shroud will create controlled localized pressure drop, simulating ambient atmospheric conditions experienced at various altitudes during a rocket launch. Thrust and pressure data will be recorded to validate the performance of the shroud and to evaluate how the aerospike performs under reduced ambient pressure, assessing its altitude-compensating efficiency.

Analysis

The team utilized engineering tools and methods to validate the propulsion system and ensure the desired performance and survivability of the system. Computational Fluid Dynamics (CFD) simulations in ANSYS Fluent were employed to analyze flow behavior and predict pressure and thermal loads on the nozzle. Thermal survivability of the structure was verified using a combination of heat transfer data extracted from custom field functions written in Fluent and MATLAB-based heat transfer coefficient calculations. These coefficients were then applied in ANSYS Structural for a comprehensive thermal analysis. Subsequent structural simulations incorporated both thermal and pressure boundary conditions to confirm the system's integrity under expected operating conditions. The cooling system, critical to the survivability of the aerospike, was analyzed through a combination of MATLAB and CFD in Fluent to determine pressure losses and the required flow rate necessary to sustain effective heat removal. The altitude-simulating shroud design incorporated pressure analyses using two methods: MATLAB-based calculations and Fluent CFD simulations. MATLAB employed simplified isentropic flow equations, combining nozzle throats into a single equivalent throat and predicting an internal pressure of approximately 6,334 Pa. In contrast, Fluent CFD simulations realistically modeled the geometry, capturing complex flow behaviors and interactions between individual nozzles, resulting in a higher internal pressure prediction of about 10,000 Pa. The 44.9% discrepancy between MATLAB and Fluent primarily arose from MATLAB's assumptions of ideal, frictionless, and isentropic conditions, and its simplification of multiple nozzles into one. Consequently, Fluent's higher predicted pressure was adopted as the simulated altitude condition.

Future Works

With more time and resources, we’d implement a hybrid system akin to Vaya Space to better mimic their system to fortify LITVC performance at a smaller scale in their architecture.

Other Information

LinkedIn Page: linkedin.com/in/projectvulcan Instagram Page: https://www.instagram.com/project_vulcan_floridatech?igsh=MTB0NWVlMnNieG96aw==

Acknowledgement

We would like to acknowledge the generous support of our sponsors: Educate the Children Foundation, MIMO Technik, Panther Works, Solideon, and Vaya Space. We extend our sincere thanks to our capstone coaches—Brooks Kimmel, Kineo Wallace, and Carson Zide—for their guidance throughout the project. We also wish to recognize the invaluable contributions of Florida Tech faculty members Felix Gabriel, Niall Harris, Dr. Firat Irmak, Dr. Daniel Kirk, Dr. Ilya Mingareev, Dr. Hamidreza Najafi, and Dr. Eric Swenson for their expertise and continued support.

Project Summary

Achieving sustained presence in orbit and enabling space missions to more distant destinations will require advancements in on-orbit servicing technologies with cryogenic propellants. Without gravity settling, fluid distribution becomes very difficult to manage inside propellant tanks, and possible vapor ingestion could lead to full system failure. Mission tailored Propellant Management Devices (PMDs) are flight-proven, passive devices positioned over a tank outlet to ensure vapor free propellant delivery to the system, while also meeting flow rate demands. Project SLOSH explores relevant fluid management theory directed towards the challenges microgravity would pose in making these advancements a reality.

Project Objective

Project SLOSH aims to design and conduct quantitative tests to evaluate performance characteristics of a PMD optimized for handling cryogenic oxidizer. The team also aims to design two testing apparatuses in order to simulate operating conditions for experiments.

Acknowledgement

The team would like to thank the project advisor Dr. Daniel Kirk for his invaluable technical guidance and generosity, as well as Dr. Firat Irmak and Dr. Eric Swenson for their support during the Senior Design capstone process.

Project Summary

Supersonic Shock Tube aims to build and test a shock tube to be utilized in the Aerospace Experimentation Laboratory at Florida Tech. A shock tube is a device that is used to create shock waves in a safe, low-cost setting as opposed to utilizing high-speed vehicles for experimentation. Our shock tube will feature a test section with two windows and a modular bottom. The windows can accommodate a Schlieren imaging set up to capture the shock waves and the modular bottom can be swapped and used to insert various test specimen. This project will give students hands-on experience with supersonic flows, experimentation and data analysis, and shock wave visualization techniques.

Specification

1ft Driver Section, 3ft Driven Section, 1ft Test Section

Project Summary

The main motivation for this design project is to satisfy a desire from the USSF to possess the capability to deliver global payloads in less time than required by conventional means (i.e., cargo planes). The importance of this project lies in the aerospace industry's trend towards reusable, propulsive-landing rocketry. The project's main objective is to demonstrate a targeted, propulsive landing before the 2025 Senior Design Showcase. To reach this goal, three subsystems have been created: Controls, Propulsion, and Structures. The team has completed many incremental objectives, including static fire tests, abort system tests, ascent tests, and attitude control tests. These tests have informed the final design so that it meets the requirements set forth.

Project Objective

The primary goal of the DART project is to demonstrate the feasibility of autonomous, propulsive landing in a reusable model rocket. The vehicle must carry a payload representing at least five percent of its total mass, operate without human input during flight, and complete a point-to-point delivery within a defined landing zone, all while remaining compliant with Class 1 amateur rocketry regulations.

Specification

The rocket was limited to a total mass of 1500 grams, ensuring compliance with Class 1 amateur rocketry rules. It was required to achieve a minimum altitude of 75 meters and a lateral displacement of at least 50 meters. The vehicle was also designed to land within a 5-meter radius target zone and to remain upright for five seconds after landing. At least 80 percent of the rocket’s mass was required to be reusable, and the system had to carry a payload equal to or exceeding 5 percent of its total weight.

Analysis

A comprehensive analysis was conducted across all subsystems to validate the rocket’s performance and safety. Structural and thermal analyses were performed using ANSYS to ensure the critical components could withstand the mechanical stress and heat loads experienced during launch and descent. Finite Element Analysis (FEA) was used to evaluate the strength and deflection of the airframe, mounting structures, and landing legs under both static and dynamic loads. Thermal simulations assessed the exposure of components, particularly near the ascent and descent motors, to high temperatures, confirming material choices and ensuring electronics were shielded appropriately. Aerodynamic behavior was analyzed using Computational Fluid Dynamics (CFD) simulations conducted in ANSYS Fluent. These simulations characterized the pressure distribution, flow separation, and aerodynamic stability of the rocket during various flight phases. The team also used RocketPy and MATLAB to develop trajectory simulations and verify system-level requirements such as altitude, lateral displacement, and landing zones. Monte Carlo simulations assessed the sensitivity of the flight path to initial conditions and wind variations. To manage descent, a Proportional-Integral-Derivative (PID) controller was implemented to control the thrust vectoring system. Finally, a flight envelope was generated to define safe flight corridors, enabling the autonomous abort logic to detect off-nominal behavior and trigger a parachute recovery when necessary.

Future Works

DART serves as a testbed for precision landing techniques in small-scale, reusable rockets. It enables future research in TVC, GNC, and rapid-response delivery systems. The project expands Florida Tech’s capabilities in autonomous rocketry and experimental controls. Future work includes advanced controller development and precision guidance capabilities.

Acknowledgement

The team thanks our faculty advisors, Dr. Firat Irmak and Dr. Darshan Yadav, our graduate student assistant, Steven Holmberg, and the Florida Tech HSDC staff for their support with this endeavor. Special thanks also go to Spaceport Rocketry Association (SRA) and Regional Orlando Applied Rocketry (ROAR), two sections of the National Association of Rocketry that facilitated flight tests for the team and shared invaluable rocketry expertise.

Project Summary

SPARCC (Solid Propellant Adaptive Responsive Controlled Combustion) 3.0 aims to demonstrate the use of solid propellant in a propulsion system by blending the shelf life and energy density of solid propulsion and the reusability of liquid propulsion into one solution. This prototype was designed with strict technical budgets, expanding on concepts from previous project iterations. SPARCC 3.0’s concept is designed to enable a broader range of CubeSat missions.

Project Objective

The objectives listed below are the goals set by the team to define the success of the SPARCC 3.0 project. These goals stem mainly from two sources: creating a functional system and building on prior teams' progress. Objective 1: The team shall build a propulsion system that uses solid propellant Objective 2: The team shall design a system that will produce variable thrust Objective 3: The team shall design a propulsion system that meets constraints for a small spacecraft.

Manufacturing Design Methods

The SPARCC 3.0 team followed an iterative design methodology to design, build, and test their system. Prototypes were made at each step of the process to ensure dimensions and tolerances were as expected. 3D printing and water jet cutting were used for rapid prototyping, and both water jet cutting and machining on lathes, mills, and presses were used to create the finished product. Integration testing was done after each component was manufactured to identify any errors so they could be corrected in a timely manner.

Specification

Technical budgets: Mass: 6 [kg] Power: 16 [W] Volume: 2U (20x10x10) [cm] Propellant Specs: Ammonium Perchlorate and HTPB propellant was used Standard sizing to be within 5%: Length: ± 0.65 mm Mass: ± 0.093 g Materials: Combustion Chamber: Cold Rolled 1045 Carbon Steel Propellant Loader: Cold Rolled 1045 Carbon Steel Support Brackets: Aluminum 5052 Thermal Coating: Cerakote 7700

Future Works

The first area of improvement is in the valve of the system. The first valve the team wanted to use was a solenoid valve, which fit the technical budgets very well, but had the issue of not actuating at the high pressure the system would experience. Instead, the team chose a ball valve design that could handle the high pressures, but it overlaps with the volume budget by approximately 0.5 cm. An ideal component would likely be a custom-fit valve that would fit the system’s volume, mass, and power requirements and could withstand the high pressures of the chamber. The second area of improvement is the ignition subassembly. The original design used a glow plug, similar to prior teams. However, this solution violated the volume and power limits of the system. Instead, the team aimed to develop its own solution using a capacitor bank, a charging circuit, and a coil of thin wire to heat propellant. This design had some issues, namely complications with the design of the circuit and integration into the loader, which meant it failed often. If this project were to be continued in the future, further design iterations could develop a more robust and reusable design, focusing on the reusability of the heating element.

Acknowledgement

Dr. Eric Swenson – L3Harris – Technical Mentor Ms. Jennifer Geehan – Relativity Space – Industry Mentor Dr. Jonathan Sasson – Airbus – Thermal Mentor Mr. Steven Holmberg – Graduate Student Assistant – Overall Mentor/Prior Team Member

Project Summary

The AIAA-Design, Build, Fly competition is designed for undergraduate and graduate students to create new and innovative ways to make remote-controlled aircraft, while meeting the various requirements given each year. The team aims to design, build, and fly a remote-controlled plane capable of completing multiple missions, including transporting payloads and accurately dropping an X-1 vehicle at a designated target location. The team chose an easy design to separate, attach, and repair to adhere to the competition rules. The design for the plane is a boom and box fuselage, fixed-high wing, and a conventional tail, and consists of a tail dragger landing gear.

Manufacturing Design Methods

The box-and-boom fuselage, high wing, and conventional tail comprise a laser-cut birch ply. The team used a carbon fiber rod for the boom section. Laser cutting is used for the wooden spars and ribs, and carbon fiber rods are also used to reinforce the spars for added strength. 3D printing, CNC machines, and foam cutters are employed to create the small X-1 test vehicle. The front main landing gear is made of carbon fiber cut and shaped via CNC. The rear section of the tail dragger is 3D printed using PLA carbon.

Analysis

CFD analysis utilizing ANSYS software was conducted to evaluate the aircraft’s aerodynamic performance. Stability calculations and XFLR5 analysis were used to estimate the conditions required for stable flight. Structural analysis was performed in ANSYS to ensure the aircraft can withstand the expected payload and aerodynamic forces encountered during flight.

Future Works

The AIAA-Design, Build, Fly competition is an annual competition in which Florida Tech students participate. The team aims to help upcoming teams qualify for the competition.

Project Summary

The Attitude Determination And Precision Tracking (ADAPT) project, led by the 2024–2025 Capstone Design Team at the Florida Institute of Technology and advised by Dr. Riano-Rios, is focused on developing a low-cost, high-performance Attitude Determination and Control Subsystem (ADCS) for a satellite simulator. The project aims to support both educational and research objectives, strengthening FIT’s role in aerospace innovation. The ADCS will incorporate an Inertial Measurement Unit (IMU), reaction wheels, magnetorquers, and sun sensors to provide accurate three-axis attitude estimation and control. A key innovation is the use of air-core magnetorquers, which minimize residual magnetic dipoles and avoid magnetic saturation, offering improved reliability and performance over traditional ferrous core designs. These magnetorquers are integrated into the structural frame, reducing system complexity, weight, and cost. Working within a limited budget of $1,750, the team is relying on commercially available, non-space-grade components to demonstrate that advanced satellite systems can be developed affordably in academic environments. This approach reflects the industry’s shift toward smaller, cost-effective satellites for applications such as research, Earth observation, and communication. The ADAPT system will utilize the IMU for real-time data (via ROS2) to assist in attitude determination, reaction wheels for precise control via changes in angular momentum, magnetorquers for detumbling and desaturation, and sun sensors to assist in determining orientation relative to the Sun. A custom algorithm will integrate these inputs to enable stable and responsive attitude control. Beyond the technical innovations, ADAPT serves as an educational platform, providing students with hands-on experience in system engineering, control algorithms, and aerospace software tools. The project helps students build critical problem-solving and project management skills, better preparing them for careers in the aerospace industry. It also offers a replicable model for other academic institutions interested in developing affordable satellite systems. Ultimately, the ADAPT project enhances FIT’s standing in aerospace education while contributing to the broader space technology community by showcasing how universities can lead in the development of scalable, accessible spacecraft subsystems.

Project Objective

The project's objectives are as follows: OBJ.01 – The ADCS shall estimate its attitude about all axes (X, Y, and Z) using a gyroscope and magnetometer via the IMU, along with a sun sensor. OBJ.02 – The ADCS shall provide 3-axis attitude control using four reaction wheels and five magnetorquers. OBJ.03 – The ADCS shall be built from commercially available, non-space-grade, low-cost hardware and software wherever possible. OBJ.04 – The project budget shall not exceed $1,750. OBJ.05 – The ADCS shall be designed with modular components and documented interfaces to support the integration of new hardware in the future.

Manufacturing Design Methods

Fabricated components and subsystems were made in-house at the L3Harris Student Design Center (HSDC) and the campus machine shop. Various parts have been manufactured using both manual and CNC equipment, including mills, drills, taps, band saws, soldering irons, and PLA 3D printing, across both facilities.

Specification

The 6061 aluminum testbed is 24x24x1.27-centimeters. The inside platform is made from PLA and is 20x20x7.5-centimeters. The five magnetorquers are also made of 3D printed PLA plastic and wrapped 60 times with 18 AWG magnetic copper wire, outer dimensions are 20x20x2-centimeters. The four 6061 aluminum reaction wheel arms are comprised of two pieces of 8x14x1-cm and 8x4x1-cm and boast a 70-degree angle from the horizontal.

Analysis

The team has applied standard industry practices—including hand calculations, simulation software (Ansys), and custom simulation code (MATLAB, Simulink, Python)—to evaluate design options and meet project requirements. Final design choices for the ADCS and its subsystems were made based on performance, weight, feasibility, and cost-effectiveness. Comprehensive testing plans have been created and are currently underway to verify the safe and reliable performance of the ADCS.

Future Works

All objectives for the ADCS project have been successfully met, with the exception of OBJ-02, which is fully expected to comply pending additional full system testing. Subsystem integration testing confirmed that each component operates reliably and integrates seamlessly with others, validating the design and control strategy. Developed under the guidance of Dr. Riano-Rios, this ADCS now serves as the foundation for his continued research and instructional development. Following the ADAPT team’s completion of the project, Dr. Riano-Rios will continue development, using the team’s work as a baseline for his prototype. The system’s modular architecture allows for future upgrades aligned with his academic goals, including autonomous finely-tuned mass balancing, a payload platform, flywheels for improved motor control, and more. With a strong and expandable foundation, this system is positioned to evolve into a versatile educational and experimental tool.

Acknowledgement

Faculty Advisor - Dr. Eric Swenson Electronic Support - Royce Jacobs Industry Mentor - Dr. Michael Polites

Project Summary

Conventional fixed-wing aircraft require long runways to take off and land. However, these vehicles are effective at transporting heavy loads quickly across vast distances. Likewise, helicopters and rotorcraft require significantly less takeoff and landing space, given their VTOL capabilities. However, these vehicles struggle to carry large loads quickly over long distances. The Heli-Plane prototype is a unique vertical takeoff and landing (VTOL) concept that balances the mobility and speed of fixed-wing aircraft with the accessibility advantages of VTOL. Its quadcopter, tandem wing design utilizes a unique stop-rotor approach to improve upon the mechanically complex tilt-rotor mechanism currently used by the V-22 Osprey. The project has included designing, fabricating, and testing a small-scale RC model of this stop-rotor concept. The lessons learned from this project serve to guide the future implementation of the stop-rotor approach into larger, full-scale flight vehicles.

Project Objective

Design, build, and test a prototype RC stop-rotor aircraft capable of in-air transition between vertical and forward flight.

Manufacturing Design Methods

The main structural framework of Heli-Plane is based on a carbon fiber rod design. Complex geometric structures such as bulkheads, control surfaces, motor mounts, and tail fairing were 3D printed using PETG. The lifting surfaces were primarily constructed by laser cutting basswood ribs and applying an outer layer of Monokote to ensure a smooth, aerodynamic outer surface.

Specification

Various specifications include: NACA 23016 wing airfoil, NACA 0018 tail airfoil, 15 lbf total weight, 45 mph cruise speed at 5° AoA, 21% static margin at cruise, 25 mph stall speed, 0.25 maximum capable thrust-to-weight ratio, maximum time in vertical flight: 6.6 min, maximum time in forward flight: 110 min.

Analysis

Various analysis software was used during all phases of the project to ensure compliance with the project requirements. The aerodynamics team performed computational fluid dynamic (CFD) analyses using Ansys Fluent to guide design choices such as wing step location. XFLR 5 was also utilized to assess the stability of the aircraft and explore parameters such as cruise velocity and angle of attack. The structures team performed finite element analyses using Ansys Mechanical to ensure that critical aircraft components were designed with a 1.5 factor of safety given aerodynamic loading during both vertical and forward flight.

Future Works

Future work on the Heli-Plane project includes the implementation of an enhanced rotor design that can pitch during forward flight. Introducing such capabilities would reduce the aerodynamic drag generated by the rotors during forward flight. More importantly, the pitching ability itself can serve as a replacement for the current aileron design. Additional future work also includes structural design optimization to improve the weight distribution of the aircraft for stability purposes.

Acknowledgement

Dr. Jason A. Russell (Technical Advisor), Dr. Eric D. Swenson (Project Facilitator)

Project Summary

In 2023, 56,580 wildfires destroyed 2.7 million acres of land in the United States, causing extensive economic and environmental damage. RangerEye is a fully autonomous drone designed for continuous, hands‑off wildfire surveillance in remote environments. Its primary objective is to detect wildfires at the earliest possible stage and fully automate aerial patrols, covering flight, detection, docking, and recharging without human intervention in harsh, inaccessible landscapes. This capability accelerates response times and reduces risk to firefighting personnel.  The drone combines vertical takeoff and landing with an efficient fixed‑wing cruise using a quad‑rotor lift system and a rear pusher propeller. A high‑resolution thermal camera enables real‑time hotspot detection, while onboard autonomy powered by ArduPilot and custom DroneKit Python scripts dynamically adjust flight paths in response to emerging threats.  Upon mission completion, RangerEye autonomously returns to its weatherproof, solar‑powered ground station, docks via an elevator mechanism, recharges via conductive plates, and shares telemetry and alert data over a secure satellite link. Global connectivity enables operators to monitor system status and update mission parameters from any location. RangerEye equips emergency responders with critical real‑time intelligence to contain wildfires before they spread by autonomously patrolling vast landscapes and delivering hotspot alerts. 

Project Objective

The team shall (1) design, build, and test a fully autonomous drone-based wildfire detection system; (2) deliver a functional RangerEye prototype by the Senior Design Showcase; and (3) integrate onboard thermal detection capable of identifying fire-prone areas and detecting hotspots above configurable thresholds.

Manufacturing Design Methods

RangerEye’s airframe was produced through iterative 3D printing using Aero ASA, PETG, PLA, and LW-PLA with 3D printers. Print settings including density, layer height, and wall thickness were optimized through testing to balance weight and structural strength. Carbon-fiber rods were integrated into the wing spars and booms to enhance stiffness, with brass heat-set inserts providing reliable fastening points. Internal wing structures featured ribbing and gyroid infill patterns to minimize mass. The ground station, constructed from T-slot aluminum framing, integrates an elevator docking system and spring-loaded charging plate.

Specification

RangerEye weighs 6.5 kg and sustains 100 minutes of flight at 18 m/s (≈108 km range). Propulsion includes four VTOL motors with 17×5.8″ props and one pusher motor with a 13×8″ prop, achieving a max speed of 22 m/s and a climb rate of 2.5 m/s. Operational ceiling is 380 ft. Aerodynamics are driven by a NACA 4412 main wing airfoil and NACA 0012/0008 tail airfoils for lift and control stability. Flight control is managed by a Matek F405-VTOL running ArduPilot, paired with a Raspberry Pi Zero companion computer executing DroneKit Python scripts for adaptive routing. Communication between the UAV and ground station uses ExpressLRS 900 MHz for control, with LTE/Starlink handling command relay. RTK GNSS enables precision landings within 10 cm, while the thermal payload captures 640×512 px imagery at 30 Hz. Recharge time at the ground station is 3 hours.

Analysis

Various engineering tools were used to ensure that RangerEye met all performance and FAA requirements. CFD simulations in ANSYS Fluent optimized the NACA 4412 wing and tail airfoils, achieving target lift and drag coefficients at an 18 m/s cruise speed while ensuring stability under turbulent conditions. XFLR5 analyses confirmed the static margin, stall behavior, and cruise angle of attack. Structural integrity was validated via finite‑element analysis in ANSYS by applying aerodynamic and payload loads to the carbon‑fiber–reinforced frame, maintaining a minimum safety factor of 1.5 across all critical components. Thrust‑stand testing verified that the propulsion system’s performance aligned with CFD predictions, while material testing of 3D‑printed components ensured optimal strength. Autonomy was validated using developer quadcopters running ArduPilot and custom DroneKit Python scripts to verify waypoint mission execution and terrain‑optimized search patterns.

Future Works

With additional time and resources, RangerEye will incorporate Li-ion batteries and a full composite airframe to enhance performance. The team will conduct field trials alongside the Forest Service and rescue teams in active wildfire zones to validate real-world operation.

Other Information

Project Website: www.rangereye.org

Acknowledgement

We thank Dr. Firat Irmak, Melbourne Fire Department, Felix Gabriel, Niall Harris, Zac Schardt and HSDC staff for guidance.

Project Summary

White dwarfs can be thought of as the “fossils” of the Milky Way Galaxy. They are the remnants of low- to medium-mass stars and help scientists understand stellar and Galactic evolution. Although they are found throughout the Milky Way, their spatial distribution with respect to the Galaxy’s spiral arms is not well understood. The purpose of this project is to analyze the correlation between the location of white dwarfs and the Milky Way's spiral arm structure. This correlation was determined by modeling the Galaxy's structure and the location of white dwarfs in a 3D plot, using up-to-date data from the Gaia mission.

Project Objective

To determine if there is a significant relationship between the location of white dwarfs and the Milky Way's Spiral arms.

Acknowledgement

Special thanks to Dr. Luis H. Quiroga-Nuñez for guidance. Data provided by the Gaia Archive (ESA) and Reid et al. (2019) on spiral arm modeling.

Project Summary

This project has been highly researched upon over the last 20 years or so. This deals with the disturbances caused in the plasmasphere by the solar winds particularly the origins of these waves.

Project Objective

This project intends on finding the origination of low frequency waves caused in the plasmasphere and the differences between day-side and night-side waves.

Future Works

Although we have some conclusive evidence but using better distribution analysis we can better the understanding of the results.

Project Summary

With the production of new hardware for the Compact Muon Solenoid experiment at CERN underway, a series of tests must be conducted and recorded to ensure the quality of these new silicon detector chip batches are within acceptable thresholds to be placed on the CMS experiment. The process of conducting and recording a scaled IV curve test will be detailed in this project to show off the process and the current stage of development for the quality grading system.

Project Summary

This project investigates the structural evolution and asymmetry of the Tycho Supernova Remnant (SNR) using X-ray data from the Chandra Space Telescope. By analyzing images from 2003 and 2021, the team measured the remnant's expansion—about 0.04 pc (8200 AU)—and conducted Principal Component Analysis (PCA) across 12 energy bands to isolate key fluid discontinuities: the blast wave, reverse shock, and contact discontinuity. These features were mapped radially to assess the remnant’s asymmetry, providing insights into the explosion mechanics and fluid dynamics of SN 1572. The project reinforces the SNR's role in nucleosynthesis, stellar evolution, and cosmic structure formation.

Project Summary

We studied X-ray observations of black holes at the centers of galaxies in the process of devouring stars. These black holes are called active galactic nuclei (AGN). Within the process, the stars getting devoured form a ring around the black hole. The ring is called an accretion disc, and the X-ray observations come from the light emitted by the disc. Looking at the light from the disc, we can see there are sometimes fluctuations in the brightness. We analyzed these fluctuations in brightness by comparing them in two energy bands. In comparing these energy bands, we can see how they vary through time, and depending on which band leads the other, we can see how the black hole emission processes evolve. My project is of years-long research that I participated in and looks at X-ray observations from AGN accretion discs at different energy bands. From the AGN we found, I will be presenting our most interesting results.

Project Summary

The galactic habitable zone, analogous to the solar "Goldilocks Zone," is the region around a galaxy suitable for sustaining human life, particularly around Active Galactic Nuclei (AGN) with active supermassive black holes (SMBHs). These AGN emit powerful jets, winds, and Ultra Fast Outflows (UFOs) capable of stripping planetary atmospheres. This study examines UFOs' impact on five atmospheric characteristics—heating, particle velocity, mass loss, ozone depletion in a Salpeter time, and time until 90% ozone depletion—to determine the "kill zone" radius around a SMBH. The kill zone indicates where life cannot be sustained, varying by the SMBH's mass and distance away. This provides insight into where carbon-based life can exist in galaxies like the Milky Way, which could activate its dormant SMBH at any moment.

Project Objective

Determining how the kill zone changes with the mass of the SMBH and the radius around it. Assessing where the Earth is in relation to the SMBH at the center of the Milky Way and whether we would be in danger if Sagittarius A* became active. Establishing the same zone for any type of AGN, considering the potential for space travel.

Future Works

Another study will be conducted with the same concept, except the kill zones will be determined based on the velocity of the UFO, rather than the mass of the SMBH. Additionally, the efficiency term for the UFO can be evaluated, and another set of habitable zones determined. A combination of all three studies provides a comprehensive view of the kill zones around any type of AGN.

Project Summary

The escape velocity from the Milky Way depends on the gravitational potential of the galaxy. We identified the propulsion methods that could be used to send a probe outside of the galaxy. The depth of the gravitational well determines which methods are required to escape. To model the gravitational potential of the Milky Way, the contributions from the disk, bulge, and halo must be considered. A probe sent against the rotation of the galaxy requires a greater change in velocity to escape. Traveling in the same direction as the rotation requires less change in velocity. We assume a Δv equal to three times the exhaust velocity, using a mass ratio of 20. The propulsion methods required to escape the Milky Way include DHD, VASIMR, and Hall Thrusters. When launching away from the galaxy against the rotation curve, only DFD and VASIMR are plausible. While launching with the rotation, the plausible methods are DFD, VASIMR, and Hall Thrusters.

Project Summary

Escaping the solar system from Earth’s position requires a Δ

Project Summary

This research aims at learning more about how our Solar System formed the way it did, and how it could have formed under different circumstances. The Solar System was simulated in MATLAB to see how the Sun's mass changing would affect the planets, their orbits, and the habitability of the Solar System. From these simulations, it was determined that the Solar System as we know it now is somewhat unique, in that changing the Sun's mass slightly could result in significant changes. For example, the Earth was only habitable during the simulation of our current Solar System, while Mars could potentially become habitable if the Sun's mass increased by around 20%. In addition to this, interesting results were also found, such as some of planets being more likely to "lose" some of their current moons as the mass of the Sun increases, or how the length of Solar Days will change rather insignificantly as the Sun's mass changes.

Project Objective

Our Solar System has often been used as a reference when studying other planetary systems, to answer questions such as “How could that planet have formed there?” But it is less often that our own Solar System is examined through that same scope. This research hopes to shed some light on that question by examining how the Solar System would be affected by the Sun’s mass – and therefore stellar classification – changing.

Manufacturing Design Methods

MATLAB was used to simulate how stable the Solar System would be if the Sun had a different mass - and therefore, stellar classification. For each of the different masses, two different types of simulations were done to try and obtain stable orbits: one where the planets' initial average velocity was kept the same as it is now, and another where its initial average distance was kept the same. The data from these simulations were then analyzed to determine any noticeable patterns across the simulations, and what affects the different solar masses had on the Solar System overall.

Analysis

Overall, the results show that it is highly unlikely that any two planetary systems will form and end up looking the same. For example, the habitable zone around a star can change drastically with its mass. Increasing the Sun's mass around 20% to make it a F-Type star now makes it so that only Mars is in the habitable zone, while decreasing the mass around 40% to a K-Type makes it so only Mercury and Venus are in the zone, and only partially. Despite this, there were some interesting results found, such as how the length of Solar Days will barely change for the planets, unless they are really close to the Sun like Mercury and Venus.

Future Works

This research could be further improved in various ways. For example, using better hardware, the time span of the simulations could be greatly increased to get a better understanding of how the stability of the Solar System could change farther in the future, or the time steps could be decreased, to get more more accurate data - especially for the inner planets - and smoother orbital plots. The Sun itself could also be changed to answer questions like "How would the Solar System change if it had more than one star?"

Project Summary

This project sees the processing and stacking of all images of M87 taken by the Chandra X-ray telescope between the years of 2000-2022. Each image was processed using the astropy library in python such that they all show data in photon counts per second. Otherwise, the images would be much more difficult to directly compare, as they have wildly different exposure times. Using each image as a frame, a movie was constructed that shows the changes and fluctuations that occurred over this time frame, particularly in objects near the galactic nucleus, such as HST-1. It was observed that the luminosity continually rose until peaking in a bright flare in 2005, before making several smaller peaks thereafter, such as one in 2007.

Project Summary

Solar wind does not cool adiabatically as theory would suggest, implying the existence of a heating mechanism in the plasma. One proposed heating mechanism is stochastic heating, in which Alfvén wave dissipation causes turbulent fluctuations in the solar wind, leading to heating of the plasma.

Project Objective

Use Parker Solar Probe measurements of solar winds to analyze the stochastic heating model to see if the model fits the observed empirical heating phenomena at distances ranging between 0.1 and 0.8 AU from the sun.

Future Works

In the future, the project will look to analyze the stochastic heating at smaller intervals over longer time periods to refine the results.

Project Summary

As the number of exoplanets detected via the transit method increases, so does the need to have accurate predictions for the physical and chemical characteristics of an exoplanet, called an atmosphere retrieval. The rise of machine learning and neural networks provides an excellent opportunity to improve the methods of atmosphere retrieval. This project investigates the accuracy of specific neural network models in performing atmosphere retrievals using the transmission spectra of exoplanets. This project develops a long short-term memory (LSTM) model and a graph neural network (GNN) model and compares both of them with a convolutional neural network (CNN) model and a Bayesian retrieval model. These models try to predict an exoplanet's surface temperature, radius, surface gravity, and atmospheric composition (abundance of water, carbon dioxide, carbon monoxide, ammonia, and methane). The data for this project comes from NASA's Planetary Spectrum Generator, an online and downloadable API that generates synthetic transmission spectra from known orbital and atmospheric parameters. The results of the LSTM and GNN models show potential for future use but require further work to increase their prediction accuracy.

Future Works

Future work on this project would focus on improving the prediction accuracy of the LSTM and GNN models. This could be done in several ways, including refining the architecture of the models, improving the data source for the transmission spectra, and increasing the number of transmission spectra used for training data.

Project Summary

The intricate biogeochemistry of our planet has been studied quite thoroughly, especially in the Phanerozoic Eon. Despite the established importance of biogeochemical cycling on Earth, almost no studies have attempted to gauge how this feedback process affects the habitability and atmospheric biosignatures of Earth-analogs; hence, this is the chief objective of our analysis. We approach this goal by considering volcanism as a key influencing factor. Several studies have identified the contribution of volcanic outputs to elemental cycles on our planet: volcanic emissions directly impact measurable entities such as oxygen and carbon dioxide levels and contribute to sulfur and phosphorus cycles via quiescent and eruptive degassing. Here, we examine the role of volcanic influences by implementing a continuous and time-integrated biogeochemical model (known as SCION) to simulate Earth-like exoplanets. A systematic parametric exploration was conducted on three variables that are primarily impacted by volcanic outputs. These parameters were sequentially modified and were consequently demonstrated to exert striking changes on the molecular oxygen and carbon dioxide levels, as well as the nitrogen and phosphorus nutrient fluxes. Our work underscores: (1) the role of coupled biogeochemical cycles in modulating the planet’s habitability and future prospects for empirical characterization by telescopes; (2) the importance of volcanism in regulating molecular oxygen levels (a vital requirement for atmospheric biosignatures and possibly complex life); (3) the necessity of biogeochemical modeling to interpret data from future observations; and (4) the need for caution when using Earth as a template to make predictions about “Earth-like” worlds.

Project Summary

This research seeks to provide the foundational layer for the new interfaces of interacting with astronomical data from the advancement of decentralized app technologies and the blockchain. The blockchain delivers several key benefits that are already becoming prominent in key industries like finance because of the advantages provided over traditional information systems. Consequently, access to scientific data has become more centralized, which brings considerable disadvantages to institutional and independent researchers, such as the availability of data and the inability to research with live, linked data. Traditional knowledge graphics are growing, and have shown to be beneficial in providing real-time access to live data, but they still lack redundant availability of data and are unable to serve as an application interface for astronomical data due to the size of astronomical data repositories. The significance of this research will deliver several key benefits to organizations, institutions, and individual researchers, including a high degree of data redundancy, ensuring data availability regardless of the state of central repositories. Furthermore, this research will allow for more interoperability of astronomical data for future decentralized applications and the benefits provided by the blockchain, which are growing rapidly.

Project Objective

The primary objective of this research is to develop and validate a decentralized front-end and backend system for astronomical data management. (i) Developing the system. (ii) Programming(and deploying) the ERC20 L2 smart contracts. (iii). Empirically evaluate the performance of data manipulation methods for FITS files.

Future Works

1. Support compatibility for different file formats and structures. 2. Add smart contracts to Github, for further iteration, security, and contribution.

Acknowledgement

We gratefully acknowledge Dr. Khald Slhoub for his advisement in this research. Furthermore, Dr. Luis Quiroga-Nunez for his feedback and guidance.

Project Summary

In my project, I ran simulations to see how altering stellar metallicity affected surrounding planets. I used the software suite 'MESA' to run them, and tracked how the radius changed over the timescale of the simulations.

Project Summary

The spaceflight environment, with increased radiation exposure and microgravity, presents various stressors to successful plant growth. Yet, plant growth for psychological benefits, supplemental life support, and fresh food is an important consideration for long-term space exploration. Plants on Earth utilize interactions with plant growth-promoting bacterial organisms to thrive and improve yields, and it is hypothesized that plant-growth promoting bacterial organisms can be similarly utilized in a microgravity environment. However, current procedures aboard the International Space Station (ISS) focus on the elimination of microbial species. Despite these procedures, these microorganisms persist aboard the ISS and have been shown to include several strains of bacteria with plant growth promoting phenotypes (PGP). This presents the possibility of using these populations to improve plant growth aboard the ISS given these strains already have spaceflight history. Benefits of these interactions could be better maximized by combining multiple strains. The present study takes microorganisms isolated from plants grown on the International Space Station that have been screened for plant growth-promoting properties to evaluate their capacity for co-culture both in the presence and absence of plant species relevant to space agriculture.

Project Summary

Further exploration of the solar system, particularly the Moon and Mars, will require the establishment of food production systems that are reliable and self-sustaining. Regolith-based agriculture presents a potential method for ensuring food security by incorporating In Situ Resource Utilization (ISRU) and Bioregenerative Life Support Systems (BLSS) methods for functioning. However, these regoliths will require conditioning prior to agricultural use due to the presence of heavy metals that can accumulate in crops and pose health hazards to both plant and astronaut health. Using plants with phytoremediating capabilities to convert the regolith into soil by removing toxins while incorporating biological material offers a partial remedy to the regolith challenges. Carnivorous plants, such as Utricularia vulgaris may act as a remediator organism for its abilities to survive in low nutrient environments and to accumulate several heavy metals that are present in both lunar and Martian environments in hazardous amounts. We hypothesize that several Utricularia species and their associated microbiomes will be able to successfully capture heavy metals from lunar regolith and provide ‘remediating’ services that condition the regolith into a more soil-like substrate. In the present study, we further characterize the phytoremediation potential of U. vulgaris and establish growth protocols and baselines for U. subulata, a terrestrial variant.

Future Works

Compare growth of the plants in and out of regolith using the methods developed here to observe plant stress and the efficacy of remediation efforts.

Project Summary

Space Crop Production has been deemed mission-critical for the success and safety of extraterrestrial missions. To limit resupply missions, regolith-based agriculture is a potentially cost-effective method but proposes physical and chemical challenges to plant growth. Peanut shells are a highly lignocellulosic inedible waste product of peanut plants, making them difficult to quickly decompose. This project aims to utilize a lignocellulosic recycling technique to mitigate several plant growth challenges. To do this, peanuts have been proven to grow and reproduce in regolith, and mixtures of peanut shells and regolith have been characterized as a soil for plant growth.

Project Objective

Here we aim to improve plant growth through a novel regolith amendment strategy utilizing peanuts. This strategy specifically aims to mitigate the dense compaction, high drainage, and alkaline pH presented by extraterrestrial regolith simulants.

Manufacturing Design Methods

Task 1: Grow peanuts in a regolith simulant to prove feasibility and quantitatively compare against soil growth. Task 2: Create peanut shell-regolith mixtures for plant growth. Task 3: Characterize the sterilized mixtures for plant growth, water holding capacity, pH, and density.

Analysis

Peanuts can viably grow in Martian Mojave Simulant with little amendment insisting they are a viable candidate for regolith-based agriculture. Peanut shells mitigate the densely compactible, alkaline, high drainage LHS-1 to create a more favorable substrate for plant growth. Increases in plant size and amount justifies peanut shell-amended regolith as a plant-growth substrate.

Future Works

Expansion of regolith types, optimization of growth, growth trials repetition.

Project Summary

Further advancements towards a visit to the red planet require a lot of precise planning and sustainable methods for the astronauts survival. A sustainable space agriculture system for an on site Martian encampment is vital for any long term mission. The cost of transporting payloads of soil repeatedly is unreasonable and unsustainable, thus we must look to the Martian soil in-situ. Martian soil is very claylike in feel and composition and thus doesn't take well to growing plants. Here on Earth the use of Plant Growth Promoting Bacteria (PGPB) is one method we use to increase crop yields. In this project PGPB with space flight history will be tested in different concentrations with seedlings to determine their effect on growth in Martian regolith. The seeds underwent the germination process while inoculated with the bacteria selected, C. flaccumfaciens and P. agglomerans. The results show that C. flaccumfaciens had a statistically significant effect on germination of L. sativa seeds in Martian regolith. This is a step in the right direction for sustainable space agriculture on our neighboring red planet.

Project Summary

Heavy metals accumulate in soil by way of natural processes and human activities. While some metals are beneficial to life in the soil others can be a great detriment to those organisms. Even beneficial metals may be harmful to plant growth at elevated concentrations. Common naturally occurring heavy metals in soil include but are not limited to chromium (Cr), aluminum(Al), barium (Ba), cobalt (Co), manganese (Mn), selenium (Se), zinc (Zn), mercury (Hg), Cadmium (Cd), lead (Pb), copper (Cu), Nickel (Ni), and Arsenic (As). Lead, aluminum, mercury, copper, arsenic, and copper are well-established as being toxic to plant growth. When present, these metals interfere with essential metabolic processes of plants. Some plants are able to hyperaccumulate and sequester heavy metals in their roots and shoots. Phytomining is the process by which hyperaccumulating plants are used to extract these heavy metals from soil. Phytomining can be utilized as a method for remediation of polluted or degraded soil or even as a more environmentally friendly approach to acquiring important metals. Furthermore, phytomining could be utilized in the bioremediation of Martian and lunar regolith to sustain plant growth systems. Helianthus annuus is a known a hyperaccumulator of several heavy metals including Pb, As, and Cr. In this experiment the use of a hyperacculamtor as a method for bioremediation of Martian and lunar regolith as well as metal extraction by evaluating the growth and accumulation of heavy metals in Helianthus annuus as well as the efficiency of hyperaccumulator plants as a means of phytoremediation of Martian and lunar regolith were evaluated.