Embry-Riddle Aeronautical University
PRESENTATION DATE DECEMBER 5, 2025
FALL 2025
SENIOR CAPSTONE ABSTRACTS
COLLEGE OF ENGINEERING AEROSPACE ENGINEERING MECHANICAL ENGINEERING
CONTENTS
2
AE 420: Aircraft Preliminary Design
4
AE 421: Aircraft Detail Design
5
AE 427: Spacecraft Preliminary Design
11
AE 445: Spacecraft Detail Design
13
M E 407: Preliminary Design for Robotics Systems
15
ME 429: Propulsion System Preliminary Design
19
ME 435: Energy Engineering Preliminary Design
AE 420: AIRCRAFT PRELIMINARY DESIGN
DOLPHIN Student Lead: André Leppert Student Team Members: Sydney Akana, Brandon Barkey, Gregory Covello, William Hays, Donald Higgs, Lucas Knoth, André Leppert, Jason Marsan, Michael Perales, Harpreet Saroya, Erik Skibsrud, Antonio Tosco, Barry Uchima Faculty: Dr. Johann Dorfling and Dr. Richard Mangum Project DOLPHIN is designing, fabricating, and testing an eVTOL aircraft to participate in the Design Build Vertical Fly (DBVF) competition in Maryland on April 7 – 10, 2026. The competition context is autonomous wildfire fighting. The aircraft will complete one ground mission and then three flight missions consecutively within a 10-minute flight window. The team is required to fly a 500-foot flight path and drop payload from the aircraft onto simulated fires. Sandbags filled with at least 0.5 pounds of sand represent the payload and will be dropped from an altitude of 30 feet AGL. Throughout the flight missions, the team will retrieve more sandbags from different waypoints to drop onto two target zones (fires) both manually and autonomously. To complete the flight missions, the team is building three separate aircraft throughout the design process to compete in the competition. The team is verifying the aerodynamic model with hand calculation methods and aerodynamic simulations. Autonomous flight and control is being verified with an off-the-shelf quadcopter. Payload delivery and retrieval tests are used to prove the system design, and static thrust tests are being performed to verify propulsion system selection.
2
SENIOR CAPSTONE PROJECTS
F. I .S.H. Student Lead: Richard Thompson, Haakon Evers
Student Team Members: Isabella Bartels, Joey Dorsten, Haakon Evers, Rhys Hendershot, Jackson Householder, Oscar Jan, Ambroise Juston, Dakota Krock, Francisco Laso Iglesias, Alex Lopez, Angeline Masongsong, Stephen Nelson, Louis Opie, Joseph Peavy, McKenna Possehl, Cade Quinlan, Jeremy Randermann, Alexia Richmond, Matthew Salisbury, Samuel Salita, Trey Talko, Richard Thompson, Keenan Williams, Julian Zon Faculty: Dr. Brian Roth and Dr. Richard Mangum Aerial recovery provides a unique capability allowing for rapid retrieval of small unmanned aircraft systems (SUAS) to provide a force multiplier and extend mission endurance for unmanned aircraft. The Flying Intercept SUAS Hook (F.I.S.H.) team has been tasked to design and manufacture an SUAS to support General Atomics Aeronautical Systems’ Aerial Recovery program. This program will develop an unmanned aircraft system capable of performing mid-air capture of a 50 ft towline and hoist system being trailed behind a host aircraft. The SUAS, named Remora, will serve as a surrogate test bed for proof-of-concept flight testing of in-flight aerial recovery via towline capture. Remora will integrate an external capture mechanism capable of intercepting the towline. Upon intercept, the towline will feed through towline until a spherical end feature is reached. Then the towline will be pulled taut, and the capture mechanism will release the end feature before the line tension exceeds 10 pounds. After release, Remora will return to normal flight and will be recovered via conventional landing. Successful proof of concept testing of aerial recovery will advance General Atomics’ mission of developing an aerial recovery system to improve the overall mission effectiveness of unmanned aircraft systems. MAGNUM Student Lead: Thomas Carlson Student Team Members: Enzo Arvizu, Alec Bessonny, Samuel Black, Thomas Carlson, Ryan Corpuz, Braeden Crowl, Luke Edwards, Jacob Heitmann, Trenton Navarro, Joshua Nugent, Micah Oliver, Aidan Prouty, Nicco Wolter Faculty: Dr. Johann Dorfling and Dr. Richard Mangum Project MAGNUM is developing a fixed-wing, remotely operated aircraft to compete in the 2026 Society of Automotive Engineers (SAE) Aero Design West Regular Class competition. This international event challenges collegiate teams to design and build an aircraft capable of lifting the maximum payload while adhering to strict performance and dimensional constraints. Competition requirements include a maximum takeoff distance of 100 feet, a landing distance of 400 feet, total aircraft weight not exceeding 55 pounds, and a wingspan between 72 and 120 inches. To meet these challenges, our multidisciplinary team of thirteen Aerospace and Mechanical Engineering students is designing an electric multi-motor aircraft featuring an independently powered propulsion and receiver system. Using the competition prescribed 14.8V 2200mAh LiPo battery for propulsion, we will optimize aerodynamic efficiency, structural integrity and stability through iterative computer-aided design (CAD) modeling, computational fluid dynamics (CFD) simulations and prototype testing. Throughout the fall 2025 and spring 2026 semesters, our team will progress from conceptual design to manufacturing and flight testing. Our goal is to deliver a high- performance, competition-ready aircraft that meets all mission requirements while demonstrating the technical excellence of Embry-Riddle’s Aerospace Engineering program and preparing us for future careers in the aerospace industry.
3
COLLEGE OF ENGINEERING
AE 421: AIRCRAFT DETAIL DESIGN
AEROCARE Student Lead: Kelsey Martin Student Team Members: Joseph Baskette, Archer Coates, Michael DiNisco, Benjamin Eben, Allison Eastman, Cody Hall, Marcus Ile, Aidan Ivers, Kelsey Martin, Tomas Schweitzer Faculty: Professor Joseph Smith and Dr. Matthew Haslam Access to critical medical supplies in remote regions remains limited due to the inefficiency of conventional ground transportation. Aerial delivery systems have demonstrated the ability to drastically reduce transport times and improve response capability in emergency situations. To address this challenge, AeroCare has developed an unmanned aerial vehicle (UAV) designed for rapid, mid-flight medical payload deployment. The system is engineered to complete missions of at least 100 miles in under one hour while carrying a 4 lb payload. The baseline mission profile includes a short takeoff under 56 ft, a climb rate of 1,000 ft/min to a cruise altitude of 1,000 ft AGL, descent to 400 ft AGL for payload release, and autonomous return to base. Following trade studies and preliminary analyses, a high-wing, conventional-tail configuration was selected for optimal stability, aerodynamic efficiency and manufacturability. Propulsion is provided by a two-stroke gasoline engine, chosen for its high energy density, favorable power-to-weight ratio and cost-effectiveness relative to electric alternatives. At the Critical Design Review stage, all major subsystems, including outer mold line, propulsion, avionics and payload release mechanisms, have been refined to meet mission requirements and manufacturing constraints. The AeroCare UAV demonstrates the feasibility of a reliable, rapid-response aerial delivery platform, advancing the use of UAV technology to enhance access to life-saving medical resources in remote environments. GLIDR Student Lead: Bruce Willey Student Team Members: Jason Davis, Cody Hawes, Josiah Lincoln, Kaylee Mason, Jasmyn McBeth, Luke Pierce, Jameson Shockley, Thomas Sly, Bruce Willey Faculty: Professor Joseph Smith and Dr. Matthew Haslam NASA’s Wallops Facility requires a guided, high-altitude return vehicle to deliver data from their Super Pressure Weather Balloons. To address this issue, NASA launched a competition for collegiate submissions. This Critical Design Review (CDR) presents the development of the Guided Landing Instrument for Descent and Recovery (GLIDR). This autonomous return vehicle is deployed from a high-altitude balloon, designed to land a data vault precisely at a specified location designated by the end user. GLIDR is a unique solution that incorporates airbrakes for attitude control at high altitudes, a paraglider for covering long ranges and navigating to specific locations, and a 3D-printed ballistic Crumple Zone designed to reduce the impact felt by the data vault significantly. The design focuses on full six-degree-of-freedom (6-DOF) analysis, empirical ballistics tests for landing behavior and the integration of a flight computer with on-board sensors to ensure accurate descent guidance. Key design considerations include aerodynamic stability, control algorithms and impact mitigation, evaluated through computational modeling and hardware-in-the-loop testing. Preliminary results from simulations and tests provide insights into trajectory accuracy, environmental robustness, aerodynamic and ballistic performance, as well as potential risks that affect landing precision.
4
SENIOR CAPSTONE PROJECTS
PROJECT EMBER Student Lead: Christopher Sorensen Student Team Members: Pramendra Bairagi, Julie Bengoa, Fred Benton, Emily Clark, Drew Dudek, David Gergeis, David Macphee, Kaija Martin, Cameron Meier, Christopher Sorensen Faculty: Professor Joseph Smith and Dr. Matthew Haslam Fire-mapping, the process of creating maps depicting the size, location, and rate of spread of a forest fire, has traditionally been done using manned aircraft. However, there are three notable challenges with manned aircraft: environmental hazards, cost and infrastructure requirements. These three challenges establish the need for an inexpensive UAV to perform this task. Ember is a small UAV designed to provide rapid deployment to the scene of developing fires to provide fire-mapping capabilities that allow first responders to better understand the fire, increasing the safety of everyone involved. Ember’s cost-conscious design ensures that it can provide IR mapping capabilities in the face of an ever-increasing demand that outpaces the current supply of IR mapping aircraft. The four keys to Ember’s success are its thermal camera, integration with ground software to generate maps, 2-hour endurance, and its ability to be transported in U.S. Forest Service trucks. Ember is a gas-powered UAV with a 6-foot, detachable wing and has the capability of being rail-launched. When Ember has completed testing and manufacturing, it will be capable of utilization for more than two hours in the field and will have no more than a 15-minute reset time between runs. These qualities make it a project with strong potential for use in the field after development.
AE 427: SPACECRAFT PRELIMINARY DESIGN
ARIES Student Lead: Sierra Gerard Student Team Members: Alima Bagdat, Grayson Bryant, Sierra Gerard, Morgan Lih, Jesse Lyszczarz, William McHugh, Christian Perez, Nicholas Verhelle Faculty: Dr. Mark Benton and Dr. Richard Mangum The Asteroid Reconnaissance and Imaging Exploration System (ARIES) is designed to advance the feasibility of asteroid mining and colonization through early classification of potential resources. Modeled after a 12U CubeSat, ARIES will validate the effectiveness of its design by constructing a small satellite body capable of maneuvering, enduring launch vibrations of a Falcon 9 rocket, and identifying an asteroid type. The ARIES test article will map asteroid topography and analyze surface composition using a LiDAR sensor, red-green-blue (RGB) imaging, and near-infrared (NIR) sensors. ARIES will contain an onboard propulsion system to demonstrate translational movement using cold gas. ARIES will be equipped with an ADCS to demonstrate rotational movement. To reduce costs, ARIES will test the compositional and topographical sensors independently from the maneuvering systems. Rotational control will be demonstrated on a dynamic suspension mount, while translational control will be demonstrated using a frictionless rail. The ARIES sensor package will be tested on a sample made of materials found in asteroids. Various ARIES components will undergo survivability testing using the vibration table on campus. The development of ARIES is critical for future space exploration missions that seek to utilize asteroid resources.
5
COLLEGE OF ENGINEERING
DAEDALUS Student Lead: Alexis Rohrke Student Team Members: Mansour Almansoori, Camden Balch, Amanda Ditton, Hunter Higginson, Katie Kinney, Brady Lawrence, Eli Martin, Alexis Rohrke Faculty: Dr. Mark Benton and Dr. Richard Mangum The ability to determine and control attitude is imperative for spacecraft operations to ensure mission success. An attitude determination and control (ADC) system allows for a satellite to be stabilized, pointed, and rotated into a desired orientation regardless of external or internal disturbance torques acting upon the satellite. Daedalus aims to design and build a low-cost attitude determination and control system for CubeSat spacecraft as an alternative to commercially available systems that exceed student teams’ and small companies’ budgets. The system will focus on achieving 2-3 axis control through a combination of reaction wheels and an inertial measurement unit (IMU). By narrowing the scope down to control and determination, Daedalus seeks to demonstrate that precise spacecraft control can be achieved with the allotted budget and available resources at Embry-Riddle Aeronautical University. This project will involve designing, prototyping, and testing our attitude determination and control system by developing a reaction wheel and testbed to verify system performance under simulated space conditions, including vacuum pressure and free rotation testing. FORGE Student Lead: Jessica Martineau Student Team Members: Luka Arozqueta, Ethan Cerniglia, Garrett Greve, Jacob Hart, Jessica Martineau, Nicholia Moody, Ryan Raglin Faculty: Dr. Siwei Fan and Dr. Matthew Haslam FORGE is a lunar based mission set to melt lunar regolith in order to provide refined materials and oxygen in the support of establishing lunar infrastructure. FORGE will combine the processes of an induction furnace, and the recent NASA project, Molten Regolith Electrolysis (MRE), to accomplish this. The induction furnace will melt the regolith up to the melting temperature of titania, during this process oxygen trapped within the regolith is extracted and dispersed. FORGE will detect the current temperature of the regolith within the crucible by sonic vibrations and sensing the output. The output should be “louder” when the material is solid, whereas the output should be “muffled” when the regolith is molten. Once the set temperature has been met, the furnace will wait until all the titania has melted sufficiently, in which case FORGE will begin to cool down until the regolith inside the crucible has completely cooled. The refined materials inside are now ready for use.
6
SENIOR CAPSTONE PROJECTS
GLADOS Student Lead: Conner Odom Student Team Members: Zoe Acedo, Kobie DeLeonard, Anika Labuschagne, Benjamin Mickelson, Conner Odom, Andreas Olafsrud, Ryan Yoder, Feiran Zhang Faculty: Dr. Mark Benton and Dr. Richard Mangum Despite the rapid evolution of space technologies, the methods used for detailed spacecraft inspection have remained largely unchanged. In current practice, extra vehicular activities, or EVAs, have been primarily used for detailed inspection tests for over 50 years. Though effective, EVAs require extensive time and money while also exposing astronauts to significant safety hazards, such as extreme temperatures, suit limitations, fatigue, and navigation issues. The Gas Leak and Damage Observation System, or GLADOS, aims to resolve these issues by reducing the need for EVAs by creating an efficient and low-cost alternative for detailed inspections. GLADOS will be a remote-operated deployable free-flyer designed to inspect spacecraft exteriors for surface damage and leaks. Given the scope of this project, GLADOS will be equipped with thrusters to allow for translational movement, along with an infrared sensor for thermal sensing, and a visual camera to relay live footage to an operator. In an ideal implementation, GLADOS would deploy from a docking bay, the system would scan the exterior surface, and the collected data would be relayed to an operator for real-time analysis. Upon completion, the collected data could be reviewed to determine if further action is needed. Overall, by minimizing the need for EVAs, GLADOS could significantly decrease mission cost, and improve safety and operational efficiency for detailed spacecraft inspections. HOPR Student Lead: Tyrol Ponder Student Team Members: Tejas Dhilip, Luke Hyde, Jesse Kaphing, Kaden Menard, Michael Mercer, Tyrol Ponder, Kyle Young Faculty: Dr. Siwei Fan and Dr. Matthew Haslam The Hopping Observation Platform for Reconnaissance (HOPR) is a lunar jumping robot developed to investigate permanently shadowed regions and collect imagery of potential ice deposits near the Moon’s poles. Lunar ice represents a vital in-situ resource for future missions, offering potential sources of water, oxygen, and propellant. HOPR’s primary objective is to capture high-resolution images and terrain data to support future exploration and resource utilization HOPR utilizes a compact, spring-powered hopping mechanism that enables mobility across uneven terrain in low gravity. Its lightweight structure, efficient power system, and elastic energy storage system allow it to operate effectively within hazardous environments traditional rovers cannot reach. By combining a jumping mobility approach with an on-board data collection system, HOPR demonstrates a practical approach to reconnaissance in extreme conditions. The platform serves as a proof of concept for small, agile robotic explorers capable of enhancing lunar surface studies and supporting the development of sustainable exploration infrastructure.
7
COLLEGE OF ENGINEERING
MOCA Student Lead: Manan Patel Student Team Members: Keven Duong, Ben Grieger, Cordelia Kohuth, Daniel Mount, Ela Ozatay, Manan Patel, Abigail Storey Faculty: Dr. Kaela Martin and Dr. Dawn Armfield Manufacturing Of Cold-Welded Assemblies (MOCA) will join aluminum members using a cold-welding process with the goal of proving a new manufacturing technique for use in space. The welding process will be carried out inside a vacuum chamber and includes alignment of the metal members, removal the oxide layer from the metal surface, and pressing the two members together until they bond at the molecular level. MOCA is designed to integrate with Arkisys’ Bosuns Locker Max as part of the C3 COSMIC Capstone Challenge track 1 for in space manufacturing and assembly. The benefit of cold welding is the low energy requirement compared to fusion welding, the lack of added heat, and no need for additional materials. Once proven, MOCA’s joining process can be used to build structures in space whose size and shape are constrained only by the continued supply of raw material.
MOSS Student Lead: Bruce Noble Student Team Members: Paytn Barnette, Paul Brich, Connor Hall, Brendan King, Bruce Noble, Parker Scribner, Lawrence Tolentino Faculty: Dr. Siwei Fan and Dr. Matthew Haslam The Mission for Orbital Service and Support (MOSS) is designing an on-orbit propellant transfer mechanism for satellites in Geostationary Earth Orbit (GEO). Satellites require propellant to perform orbital corrections, orientation, and eventually disposal. When satellites in GEO run low on propellant, satellites must use the last of their propellant to be disposed of and deactivated in a special graveyard orbit. MOSS is working to extend the life of satellites in GEO by transferring propellant to the satellites, allowing them to continue making orbital corrections. MOSS will restore life to these satellites by flowing propellant backwards through the satellite’s engines.
8
SENIOR CAPSTONE PROJECTS
ORCA Student Lead: Aiden Dunlop Student Team Members: Simon Cura, Kailea Danielson, Aiden Dunlop, Kayleigh Fischer, Madison Jacobs, Sydney Luttrell, Nhi Nguyen, Liv Ordoñez Faculty: Dr. Kaela Martin and Dr. Dawn Armfield The Orbital Retrieval and Containment Apparatus (ORCA) project addresses the growing issue of orbital debris in low Earth orbit (LEO). With over 12,000 small satellites currently in orbit and projections exceeding 60,000 by 2030, inactive CubeSats pose an increasing threat to active missions and future launches. ORCA is designed as a cost-effective, deployable system capable of remotely capturing defunct CubeSats ranging in size from 1U to 6U. The system employs a robotic arm capture mechanism that secures the target satellite for containment. ORCA’s design emphasizes reusability of external power sources and low-cost commercial components for an Earth-based prototype. By focusing on CubeSat-sized debris, ORCA provides a practical and scalable solution that complements ongoing international efforts in debris mitigation. ORCA contributes to safer orbital operations, reduces the likelihood of fragmentation events, and supports the long-term sustainability of space for commercial, governmental and scientific missions.
PIGASUS Student Lead: Kyle Lake Student Team Members: Ken Bee, Stephanie Hannis, Kadin Hume, Benjamin Knoell, Kyle Lake, Nathan Viser, Rex Weber Faculty: Dr. Kaela Martin and Dr. Dawn Armfield Project PIGASUS (Propellant Interface for Gaseous Assistance of Small Under-fueled Spacecraft) is developing a standardized docking and refueling interface to extend the operational lifespan of small spacecraft. Many satellites in constellations depend on gaseous or sublimating solid fuels, such as xenon or iodine, yet lack practical methods for in-orbit refueling. PIGASUS addresses this problem by providing a modular docking system through a secure mechanical coupling, fluid transfer, and data exchange. The system architecture consists of three integrated subsystems: Structures, Avionics and Fluidics. The Structures subsystem ensures stable docking with tolerance for misalignment and operational safety margins. The Avionics subsystem enables communication, docking state detection and thermal regulation for reliable performance. The Fluidic subsystem provides controlled propellant transfer, leak prevention and heated lines to accommodate sublimating fuels. Collectively, these features enable the PIGASUS system to perform repeatable docking cycles, maintain secure connections, and transfer propellant within defined pressure and flow ranges. By promoting compatibility across satellites from different organizations, PIGASUS aims to advance the standardization of in-space servicing to reduce satellite replacement frequency, lower operational costs and support more sustainable space operations, ultimately contributing to long-term viability of satellite constellations.
9
COLLEGE OF ENGINEERING
PRISM Student Lead: Ryan Coder Student Team Members: Charles Allen, Ryan Coder, Chanel Davis, Isaiah Gale, Owen Glascoe, Zachary McKissor, Tanner Whitney Faculty: Dr. Siwei Fan and Dr. Matthew Haslam The Proximity and Rendezvous Integrated Simulation Model (PRISM) project is developing a frictionless planar testbed and modular mock-satellite system for testing autonomous spacecraft control algorithms. PRISM enables safe, repeatable evaluation of guidance, navigation, and control (GNC) logic in an emulated orbital environment. The system consists of two main components: an air table and a mock-satellite (MockSat). The air table provides a low-friction surface using pressurized air to simulate two-dimensional microgravity motion, while the MockSat integrates propulsion, sensors, and onboard processing for real-time control. Equipped with propellers for attitude and translational control, an inertial measurement unit for rate sensing, and Bluetooth-enabled telemetry, the MockSat supports multiple operational modes including manual, assisted, and autonomous. A built-in data logger records vehicle states and command histories for post-test analysis. Together, the air table and MockSat form a scalable platform for validating estimation filters, trajectory planning, and disturbance rejection in proximity operations. The PRISM system will serve as a long-term educational and research asset for spacecraft dynamics and control, bridging theoretical coursework with applied experimentation in autonomous rendezvous and docking technologies. SNAPUR Student Lead: Naomi Borg Student Team Members: Aiden Angoco, Jasmine Aranda, Naomi Borg, Jaxon Danner, Jacob Haney, Natalie Kauffman, Ethan Murphy, James Orcutt Faculty: Dr. Kaela Martin and Dr. Dawn Armfield Space Non-Actuating Portable Utility Receptacle (SNAPUR) is an Extravehicular Activity (EVA) tool receiver and receptacle that is composed of two parts. One part is bolted to the astronaut’s suit’s swingarms and the other part is bolted to the tools. SNAPUR will improve astronauts’ ease of access to necessary tools during EVA repairs. EVA excursions can last up to eight hours, during which astronauts traverse outside of the ISS carrying multiple tools. The current method of storing tools utilizes the Mini Workstation (MWS) which requires two hands and dedicated actuation to detach and reattach tools to the swingarm. Two-handed dedicated actuation becomes cumbersome quickly because astronauts often find themselves unable to use both hands or in unusual body positions. SNAPUR will reduce usage to one-handed installation and remove the need for dedicated actuation to reduce EVA time. SNAPUR will also save costs during EVA’s and improve astronaut safety while preventing tool loss. In accordance with the Micro-g NExT Challenge and our expected outcomes, SNAPUR will enable one- handed tool installation with minimum actuations, while maintaining single-fault tolerance and ergonomics. Should SNAPUR be selected by NASA, it will be tested in Johnson Space Center’s Neutral Buoyancy Lab.
10
SENIOR CAPSTONE PROJECTS
AE 445: SPACECRAFT DETAIL DESIGN
L .E.A.P. Student Lead: Lacy Pyle Student Team Members: Natalie Carroll, Braden Hass, Lacy Pyle, Roee Shemesh, Hamim Vali, Jimi Wadnola Faculty: Dr. Karl Siebold and Dr. Matthew Haslam Sustained lunar exploration requires a reliable energy system capable of operating through extreme conditions, including prolonged periods of darkness. The Lunar Energy Access Program (L.E.A.P.) investigates a regenerative power solution that integrates solar energy, water electrolysis, and a hydrogen fuel cell to enable continuous power generation. A scaled-down prototype demonstrates this concept in a controlled, Earth-based environment. During simulated daylight, solar panels supply power to a battery and drive an electrolysis system that produces hydrogen and oxygen from provided distilled water. Generated oxygen is immediately vented to the atmosphere and hydrogen is temporarily stored in a custom-built tank. To simulate nighttime power generation, a proton exchange membrane (PEM) fuel cell, operating on the generated hydrogen and ambient air, generates electricity to sustain continuous power output. A manual switch transitions the system between power sources, allowing real-time validation of energy flow. Two light bulbs serve as the primary load, providing a clear visual representation of power availability and system functionality. By constructing and refining both the electrolysis and fuel cell systems, this project provides hands-on validation of key energy conversion principles. The results contribute to the development of regenerative power architectures for space applications, supporting the feasibility of long-duration lunar infrastructure. ODIN Student Lead: Shea Schmidt Student Team Members: John Anderson, Cole Brunson, Elliot Chubon, Adrien Hobelman, Andrew Reynolds Faculty: Dr. Karl Siebold and Dr. Matthew Haslam The Orbital Debris Identification Network (ODIN) addresses the escalating challenge of orbital debris that jeopardizes critical space infrastructure and human spaceflight . ODIN is a scalable, space-based platform that leverages advanced control moment gyroscopes and multi-sensor technology to detect and track debris smaller than 10 cm in Low Earth Orbit (LEO). This system provides near real-time, precise orbital data to mitigate collision risks and support space situational awareness. By bridging current gaps in tracking capabilities, ODIN aims to safeguard orbital environments, reduce LEO satellite collisions, and extend satellite lifespans. The mission design emphasizes reliability, scalability, and affordability by integrating commercially available technologies and robust control algorithms. ODIN’s contributions will advance sustainable space operations, ensuring the viability of LEO for continuing scientific, commercial, and defense applications. ODIN is an advanced satellite testbed designed to control its attitude using control moment gyroscopes (CMGs) in a microgravity-simulated environment. It employs onboard sensors to detect, track, and point at moving objects, determining their relative position and velocity. ODIN actively manages its center of gravity with linear actuators and estimates its mass moment of inertia. Operations begin with a calibration sequence, followed by scanning the surroundings using a wide-field sensor system. Upon identifying a target, ODIN adjusts its orientation to point directly at it. A narrow-field sensor suite then refines depth measurements and gathers critical data. By integrating position, depth, and time, ODIN calculates the object’s state, simulating in-flight orbital determination.
11
COLLEGE OF ENGINEERING
PISCES Student Lead: Vincent Adams Student Team Members: Vincent Adams, Levi Campbell, Jack Hamrick, Clyde Miller, Saul Samiljan, Nathaniel Stringer, Canon Swain, Lance Yearick Faculty: Dr. Karl Siebold and Dr. Matthew Haslam Scans of Jupiter’s moon Europa have discovered a saltwater ocean under sheets of ice. These oceans could support life but lack explicit evidence. Currently NASA’s Clipper mission is enroute to make further scans. The successor mission would be to explore the oceans themselves. The PISCES (Probe Investigating Subsurface Cold Europan Seas) capstone project has developed and tested a remotely operated underwater vehicle (ROUV) designed to explore a simulated Europan ocean in search of a habitable environment. The ROUV measures pH, salinity, pressure, and temperature, to scan for signs of life. Fitting within a small payload, the ROUV is 40cm long, 25.8cm wide, and 12cm tall. The ROUV has high underwater maneuverability, able to move in five free degrees of freedom up to 15cm/s. The ROUV relays data back to the data storage device via a tether. All sensors and materials withstand a temperature of -3°C. RED HAVEN Student Lead: Aidan Maney Student Team Members: Shahan Ahmed, Aidan Maney, Skye Mayo, Karim Hernandez, Devin Trujillo, Kevin Zamora Faculty: Dr. Karl Siebold and Dr. Matthew Haslam Red Haven is a Mars analog habitat concept designed to support long-duration surface missions through a compact, modular, and semi-autonomous system. The project seeks to advance the development of controlled life support systems by integrating essential regulation technologies within a deployable structure suitable for extraterrestrial applications. This habitat emphasizes structural and semi-autonomous monitoring reliability, ensuring safe and resilient operation during prolonged crew isolation, harsh environmental exposure, and limited maintenance capability inherent to Martian surface missions. The design approach is grounded in system-level integration and resilience under resource- constrained conditions analogous to Mars. Material selection, structural form, and power redundancy were chosen to simulate challenges posed by low-pressure, variable thermal loads, and limited energy availability. A distributed sensing and control architecture has been implemented to ensure real-time monitoring and semi-autonomous actuation, both critical for sustaining life and reducing crew workload. Red Haven explores pathways for future modular expansion, field testing, and eventual adaptation into full-scale Martian or lunar systems. By addressing both the technical requirements and operational challenges of off- world habitation, Red Haven contributes to a scalable framework for sustainable human presence in space.
12
SENIOR CAPSTONE PROJECTS
RIFT Student Lead: Hailey Choi Student Team Members: Hailey Choi, Nohora Diaz, Jack Hanna, Carter Maciejewski, Adam Stanley, Tiaron Starrine Faculty: Dr. Karl Siebold and Dr. Matthew Haslam This project seeks to explore a new method for collecting geologically representative samples from metallic (M-type) asteroids using laser-based excavation. These asteroids are believed to be the exposed cores of early planets and contain high concentrations of iron, nickel, and platinum-group metals, yet their true composition remains unverified because no mission has returned a physical sample. Metallic asteroids are expected to have solid, metal-rich surfaces rather than loose regolith, making conventional drilling or coring techniques ineffective in microgravity where anchoring and reaction forces pose major challenges. The proposed technique uses a focused laser to cut converging layers that isolate a large, intact section of subsurface material while minimizing debris generation. To ensure meaningful scientific value, the targeted sample dimensions align with ASTM standards for geological representativeness, capturing material less affected by surface alteration. Two laboratory systems were developed to validate this method. The Positioning Test Stand demonstrates semi- autonomous, layered laser cutting sequences using a three-axis gantry and precision control software. The Displacement Test Stand, which evaluates gas-driven displacement of molten material into porous asteroid analog geometry to address concerns related to slag (molten metal) accumulation and re-solidification. Together, these experiments provide early physical evidence that controlled laser excavation can produce representative subsurface samples and inform future metallic asteroid sample-return missions.
ME 407: PRELIMINARY DESIGN FOR ROBOTIC SYSTEMS
AEROFILL AUTOMATION Student Lead: Noah Temperendola Student Team Members: Owen Dyer, Anika Ginger, Alexis Hall, Dutch Lely, Aliya Takano, Noah Temperendola Faculty: Dr. Mehran Andalibi and Dr. Richard Mangum AeroFill Automation is a senior design project sponsored by IronTree Solutions, a company that develops agricultural equipment. The project focuses on automating the refilling of a crop dusting helicopter on a mobile landing platform to improve safety and efficiency in agricultural operations. Helicopters play a vital role in agriculture by applying fertilizers, pesticides and frost protectants across large fields. They can refuel and refill chemicals on mobile platforms such as trucks or trailers that can travel between job sites. While effective, this process still requires operators to climb ladders, handle heavy hoses and manually connect fuel and chemical lines—tasks that are physically demanding, time-consuming and potentially hazardous. Hazards can include risks such as falling, entrapment under the heavy hoses and rotor wash. Safety and operational efficiency are the core priorities driving this project. The AeroFill system integrates with IronTree Solutions’ mobile refilling trailer and the Bell UH-1H helicopter to perform autonomous fuel and chemical transfers at the pilot’s command. AeroFill aims to make the refilling process safer, faster and less expensive.
13
COLLEGE OF ENGINEERING
ARM Student Lead: William Hector Lindauer II Student Team Members: Leilani Alvarado, Joshua Butler, Dakota Jacobs, William Lindauer, Lauren Otto, Hunter Smith Faculty: Dr. Mehran Andalibi and Dr. Richard Mangum Embry-Riddle’s Robotics Lab is requesting the creation of a low-cost robotic arm that can interface with a robotic base and uses computer vision AI for object detection. The arm will be used as a learning tool helping students understand how to integrate two robotic systems along with how implementing AI in robotics can benefit the system. The robotic arm being developed will be able to grab objects using programmable inverse and forward kinematic operations and object detection powered by an AI assisting the robot with grabbing objects in a changing environment. The camera used will also have depth sensing allowing it to move and adjust on its own to pick up an object. Object detection will allow the robotic arm to interact with a large variety of objects, showing the versatility of AI. This robotic arm will be able to operate attached to a robotic base being developed by ODD (Octagon Differential Drive) Robot where it will be powered and able to access ODD Robot’s depth-sensing camera for additional information. In tandem with the robotic arm, a base is also being created to allow the robotic arm to be attached to the lab bench where students can continue to learn and utilize all the robotic arm’s capabilities.
ART Student Lead: Bryce Thirtyacre Student Team Members: Nicole Evenson, Emma McBride, Payton Mickelsen, Jagan Sandhu, Siddharth Shah, Bryce Thirtyacre, Madeleine Wallace Faculty: Dr. Mehran Andalibi and Dr. Richard Mangum The COE Automation Lab has commissioned ART to develop an autonomous robotic system that integrates with its existing Programmable Logic Controller (PLC) conveyor belt system. The PLC system employs an induction sensor and pneumatic actuator to sort metallic and non-metallic objects. The new system must demonstrate artificial intelligence through Computer Vision (CV) and support Python programming to align with the COE curriculum’s shift toward that language. To operate the PLC conveyor belt, the robotic system must manipulate a control panel featuring six color-coded buttons, a toggle switch, and a rotary knob without causing damage. The gripper must be capable of pressing buttons, toggling the switch between on/off positions, twisting the knob, and using a stylus to interact with the Human Machine Interface (HMI). The CV module must interpret status indicators, voltage meter readings, knob positions, and HMI screen text. It must also identify and classify objects by shape and color before grasping and placing them on the conveyor belt for material-based sorting.
14 SENIOR CAPSTONE PROJECTS | COLLEGE OF BUSINESS, SECURITY AND INTELLIGENCE
ODD Student Lead: Darcie Hughes Student Team Members: Gabriel Allred, Bianca Fernandez, Darcie Hughes, Wrin Monger, Austin Palahnuk, Jack Seigworth Faculty: Dr. Mehran Andalibi and Dr. Richard Mangum The Octagon Differential Drive (ODD) Robot is an educational robotics platform developed to provide a cost-effective and capable system for teaching key concepts in mobility, sensing, and artificial intelligence (AI). Designed for user control and experimentation, ODD Robot employs a differential drive system that enables forward, reverse, and rotational motion, with wheel encoders supplying feedback for odometry and motion analysis. Its onboard RGB-D camera captures both color and depth information, which the system processes to execute computer vision models. The robot also integrates with an attachable Articulated Removable Manipulator (ARM), expanding its capabilities to include manipulation and interaction tasks. Powered by rechargeable batteries and programmed in Python, ODD Robot provides an accessible platform for developing algorithms in motion control, perception, and data processing. By combining performance, flexibility, and affordability, ODD Robot serves as a versatile educational tool that bridges the gap between classroom learning and practical robotics experience, offering advanced features comparable to commercial systems at a fraction of the cost.
ME 429: PROPULSION SYSTEM PRELIMINARY DESIGN
AERO Student Lead: Ross Leek Student Team Members: Nathan Hernandez, Ryan Husom, Ross Leek, Aiden Sorrells, Jag Wray Faculty: Dr. Ambady Suresh, Dr. Matthew Haslam, Professor Andy Gerrick
In recent years, there has been an effort to convert the transportation sector from fossil fuels to renewables in order to decrease net carbon emissions; however, the aviation sector has proven more difficult to convert due to considerations of weight and size as well as compatibility with existing aircraft. Some benefits of this conversion are that it may lead to net- zero carbon emissions and reduced fuel prices as hydrogen, the renewable fuel most likely to replace jet fuel, production scales. This project aims to develop an economical storage solution for a more environmentally friendly fuel that maximizes the energy density while not requiring significant modifications to existing aircraft. Liquid hydrogen has been identified as the alternative fuel most capable of replacing jet fuel due to its high gravimetric energy density, its reasonable compatibility with existing aircraft, the low cost of hydrogen, and its clean-burning capability. Due to the cryogenic temperatures of liquid hydrogen, the tank will need to be made of 6061-T6 Aluminum due to its capability of resisting embrittlement under these extreme temperatures. Additionally, the tank will be insulated using an air gap to maintain these cryogenic temperatures cheaply and efficiently and decrease the extent of hydrogen boil-off.
15
COLLEGE OF ENGINEERING
ARC Student Lead: Benjamin Weimer Student Team Members: Evan Cordoba, Aidan Hermens, Luke Hurst, William Prater, Benjamin Weimer Faculty: Dr. Ambady Suresh, Dr. Matthew Haslam, Professor Andy Gerrick ARC Thermal Systems is engineering a next generation spacecraft radiator array, implementing modern developments in materials science and manufacturing, to serve the developing range of demanding performance requirements for future spacecraft. Future spacecraft, such as a SpaceX Starship outfitted for interplanetary travel, will require megawatts of power to serve onboard systems needs and electric propulsion units. Carrying the proposed 100 people and associated cargo between Earth and the red planet demands it. Needing to solve a specific, well-defined problem, we selected the NASA JIMO spacecraft as a case study in high-power spacecraft within which we can build out a design for a modern radiator array at the 100kW+ scale). Quality research regarding the development and optimization of this integral piece of thermal hardware unlocks spacecraft power level scaling beyond anything offered on the market today and therefore opens up untouched mission profiles like exoplanetary mining, space tourism, and much more. Our top-level requirements are: • Reject heat from a closed-loop fluid NaK system. • Mass of less than 864 kg (current NASA JIMO Spacecraft radiator array mass). • NaK fluid loop: m ̇ =1.28 kg/s ; T_in=556K; T_out=399K • Prevent single-point system failure (redundancy). The primary focus of the group will be on reducing the nominal weight of a proposed radiator array for a specified power level class. The methods used to do so will apply broadly to support future designs of the kind of craft mentioned above. BEAR Student Lead: Joseph Lucchese Student Team Members: Jamie Black, Benjamin Freeman, Natalie Lang, Joseph Lucchese, Gracie Miller, Omar Monreal, Anise Romo Faculty: Professor Gary Cosentino and Dr. Shannon Lodoen Foil bearings enable oil-free, high-speed operation in turbomachinery and are critical for next-generation, fuel-efficient turbine engines. Their air-film lubrication allows operation in high-temperature environments where conventional bearings fail. However, foil bearing reliability is limited by multiple wear mechanisms, many of which are not fully understood. In particular, wear caused by sediment ingestion accelerates coating degradation and shortens operational lifespan. Limited experimental data on this process hinders accurate life-prediction modeling, which slows the incorporation of these bearings into broader aerospace applications. Bearing Endurance and Analysis Rig (BEAR) focuses on the design and construction of a foil bearing test rig capable of simulating a turbine engine environment at representative conditions. The rig will facilitate investigation into how particulate ingestion influences coating wear. Integrated instrumentation and environmental controls will enable precise measurement of: operating conditions, particulate delivery, and wear progression over time. This project lays the groundwork for systematic investigation of foil bearing degradation. The resulting data will support the development of predictive foil bearing life models, guide improvements in materials and coatings technologies, and ultimately contribute to the advancement of reliable, high-performance turbomachinery systems.
16
SENIOR CAPSTONE PROJECTS
FLOW GOOD INC. Student Lead: Joss Mikeal Picardal Student Team Members: Derrick Drango, Samuel Drown, Elliott He, Liam Keily, Joss Mikeal Picardal Faculty: Dr. Ambady Suresh, Dr. Matthew Haslam, Professor Andy Gerrick
The current Liquid rocket test cell used by the Rocket Development Lab has technical limitations that prevent the testing of more powerful rocket engines. To take this leap forward, the current test cell will require greater propellant capacity, lower pressure drop, accurate measurement instrumentation, and less system transients. By implementing an additional set of tanks to hold propellant, longer burns can be sustained which can be used to profile longer burning rocket engine designs. By replacing the current cavitating venturis we can reduce pressure loss through the system resulting in lower tank feed pressures for the same mass flow rate allowing for more efficient use of pressurization gas. To ensure accurate measurements the implementation of turbine flow meters which will replace the current venturi flow meters will reduce pressure loss while making higher resolution and accurate measurements. Transients in the system makes it hard to precisely control the pressure and therefore the mass flowrate due to large spikes and dips in pressure through the current “bang bang” regulation system. These pressure transients can be reduced by replacing or enhancing the current regulation system design allowing for precise mass flow control.
HUSH Student Lead: Narayan Bal Student Team Members: Narayan Bal, Daniel Lavy, Aidan Ota, James Roman, Alex Tejeda Faculty: Dr. Ambady Suresh, Dr. Matthew Haslam, Professor Andy Gerrick
The HUSH Capstone team wishes to design a quiet drone propeller that is commercially available to drone users worldwide. Traditional drone propellers generate significant noise, which limits their use in noise-sensitive environments such as wildlife monitoring, urban mobility, and cinematography. Additionally, the noise of drone blades can cause adverse health effects such as increased anxiety as well as hearing loss. Team HUSH aims to make drones more usable by diminishing drone noise. The primary objective of this project is to design quiet propeller blades by optimizing blade count, pitch angle, taper ratio and blade features, while ensuring compatibility with a consumer grade drone’s existing motor and aerodynamic profile. Computational Fluid Dynamics simulation and acoustic simulation will be utilized to evaluate design iterations, followed by prototyping and real-world testing using sound level meters and flight performance metrics. To ensure the success of this objective, several design requirements and constraints must be carefully considered throughout the development process. For example, the propellers in flight must not produce a noise at volumes greater than the ambient noise of the environment. Other requirements like the flight speed must not decrease by more than 20%, and the propellers must endure a minimum of 300 flights must be met. Ultimately, this project aims to deliver a refined propeller design that achieves significant noise reduction while preserving the performance, efficiency, and weight limitations required for seamless integration with consumer grade drones.
17
COLLEGE OF ENGINEERING
QUEEN PROPULSION Student Lead: Riley Lambert Student Team Members: Kendall Allen, Valerie Arana, Riley Lambert, Catherine Nguyen, Julia Payne, Dane Soaper Faculty: Professor Gary Cosentino and Dr. Shannon Lodoen Hydrogen combustion propulsion systems are emerging as a new clean-energy alternative within the aerospace industry. This alternative fuel source aims to reduce fossil fuel emissions and increase propulsion efficiency. Despite these advantages, this emerging technology faces two main obstacles. First, hydrogen does not conform to standardized safety regulations, as it is highly flammable and risks spontaneous combustion or flame back. Second, materials exposed to hydrogen display decreased ductility and are more likely to fail (material embrittlement). This has been identified as being especially a problem for the fuel line material carrying the hydrogen to the combustion chamber. Currently, Embry-Riddle’s Propulsion Laboratory lacks the means to investigate hydrogen combustion and embrittlement research under realistic environmental conditions. To address these challenges, Queen Propulsion, sponsored by Honeywell, is designing a hydrogen combustion test rig. Our design expands upon Mamba Propulsion’s initial combustor design to achieve ignition with hydrogen fuel and test hydrogen embrittlement within the fuel lines. Throughout this academic school year, Queen Propulsion will develop a standard testing rig for hydrogen combustion, achieve hydrogen ignition, and set the stage to advance research on hydrogen embrittlement. In doing so, we can propel Embry-Riddle to the forefront of alternative energy research and aid in the advancement of hydrogen propulsion technologies across the aerospace industry. VULCAN PROPULSION Student Lead: Kaitlyn E. Smith Student Team Members: Christopher Finnegan, Miles Holt, Kaitlyn E. Smith, William Temple, Ryan Toughill Faculty: Dr. Ambady Suresh, Dr. Matthew Haslam, Professor Andy Gerrick The Embry‑Riddle Aeronautical University, Prescott Liquid Rocket Program’s goal is to develop, launch to the Karman Line, and recover a reusable liquid‑propellant rocket. By means of various vehicle iterations such as Altair, Deneb, and Deneb 2, the program made advancements in propulsion testing by achieving a collegiate altitude record. However, ongoing technical problems restricted performance and reusability. Altair suffered an ignition‑caused explosion and valve/fitting failures. Deneb performed successful ignition and sustained flight but had shortcomings in engine efficiency, sensing of ignition, mass control, aerodynamics, and recovery. Deneb 2 was a repeat of subpar performance with the added feature of chamber ablation, and injector warping. These failures define three primary technology gaps: engine efficiency, robust ignition with abort/re‑start capability, and long-duration test chamber with thermal and mechanical degradation resistance. This capstone project will focus on the proposed engine which will be comprised of injector and chamber designs focused on increasing efficiency, a fluid-cooled chamber jacket permitting flight-like burn durations, and a torch ignitor for reliable and repeatable engine ignition. Achieving these objectives will improve program duration and provide a solid base for Embry-Riddle liquid propulsion teaching and research. Outcomes will inform future flight‑capable engines.
18
SENIOR CAPSTONE PROJECTS
Page 1 Page 2 Page 3 Page 4 Page 5 Page 6 Page 7 Page 8 Page 9 Page 10 Page 11 Page 12 Page 13 Page 14 Page 15 Page 16 Page 17 Page 18 Page 19 Page 20Made with FlippingBook - professional solution for displaying marketing and sales documents online