As the previous semester concluded, the team successfully conducted a torch igniter hotfire campaign, executing eight static fires at Purdue’s Zucrow Labs. A notable achievement included four hotfires within twelve hours and two hotfires within a span of just four minutes.

The culmination of efforts resulted in the full assembly of the TADPOLE engine, integrating steel, copper, and a novel aluminum alloy utilized by NASA. Beyond the technical advancements, the injector, chamber, and throttle valves were not the only elements experiencing flow during testing— the team members’ eyes were also experiencing tears of joy.

To further support GNC, efforts have transitioned toward an upgraded ASTRA electric lander design. This iteration features a carbon fiber structure and a refined propulsion system, with a fully custom flight computer ensuring precise navigation and operational efficiency.

The team initially designed and constructed a proof-of-concept 3-degree-of-freedom (DOF) robotic arm capable of grasping a tennis-ball-sized object. Subsequently, material enhancements were implemented to improve durability, ensuring suitability for testing, integration, and onboarding purposes.

A YOLOv8 model is under development and training for target identification and tracking using both real and synthetic data. Additionally, disparity and thermal maps are being generated to facilitate depth analysis and enhance environmental awareness.

Efforts are underway to refine inverse kinematics for robust arm movement in Move-It, alongside reinforcement learning applications aimed at developing control methodologies for both computer vision and simulation models within ROS2 and Gazebo.

System design work has commenced for a space-grade 7-DOF inch-worm robotic arm, complemented by the development of a 4-DOF arm for future integration. This arm features an attachment mechanism capable of data and power transfer, tool operation, and sensor feedback for autonomous functionality.

Custom radiation-hardened electronics are being developed to ensure operational reliability in LEO.

A modal aeroelastic analysis code was developed utilizing a one-dimensional finite element rocket model to predict potential failures due to dynamic instability.

A cycler orbit between Earth and an asteroid within Jupiter’s Trojan asteroid family was modeled to explore the feasibility of employing cycler orbits for asteroid mining operations.

A Systems Tool Kit (STK) workshop was conducted, modeling the Apollo 11 mission from launch to lunar landing. This included implementing a differential corrector method to determine the optimal maneuver for lunar transfer.

A real-time capable optimal control algorithm was developed to simulate the landing of a rocket-powered lander. Utilizing model predictive control, the algorithm optimizes fuel consumption while maintaining safety parameters. The lander’s dynamics were modeled in MATLAB Simulink, incorporating factors such as wind, delays, and mismodeling errors to assess the controller’s robustness in realistic conditions.

In Spring 2024, High Altitude successfully launched the first student-mixed and cast solid propellant in team history, marking a significant milestone. Plans are now in place to conduct static fire tests in the upcoming semester. The team also launched Skyshot twice. The first successfully flew to about 13,000 ft. The rocket suffered a structural failure on takeoff during the second launch, however, the biological payload and the avionics survived, and the research collaborators gained plenty of interesting and useful data from the flight.

In Fall 2024, High Altitude achieved another milestone by launching the first two-stage rocket built by an undergraduate team in Purdue history.

During the same semester, the design of the Event Horizon rocket was finalized, culminating in a successful Critical Design Review. Event Horizon is currently under construction and is set to compete in the Argonia Cup in March 2025, with a targeted altitude of 25,000 feet.

A test stand was also completed to facilitate static fires of custom propellant. Grain geometry experiments are planned to enhance understanding of propellant behavior.

Since Fall 2023, the Hybrids team has finalized the design of Spectre, a hybrid rocket utilizing hydroxyl-terminated polybutadiene (HTPB) as fuel and nitrous oxide as an oxidizer.

The Critical Design Review (CDR) for Spectre was successfully presented, receiving evaluation and feedback from facility advisors and alumni.

With the CDR completed, the current focus has shifted toward procurement, manufacturing, and testing of the propulsion system.

Several cold-flow tests have been conducted on the CraterMaker Special rocket in preparation for its scheduled flight in April.

Design efforts have commenced on PSP-Liquids’ newest project, Copperhead, which aims to pioneer the use of electric propellant pumps at the collegiate level.

The final design phase for PSP’s Condor Test Cell at Zucrow Labs is nearing completion, with infrastructure development underway to support advanced liquid rocket engine testing.

In August, PSP Sats team members Nathan Drzadinski and Griffin Hentzen presented their research at the 39th Annual Small Satellite Conference in Logan, Utah. Their work emphasized the impact of the Boiler Bus program and the satellite-as-a-service (SataaS) model on the evolution of collegiate satellite institutions, reinforcing Purdue Space Program’s role in advancing space innovation.

In November, PSP Sats hosted the first Systems Design Review, showcasing three semesters of progress to industry professionals, academic advisors, and alumni. Insights gained from this milestone are being incorporated into the upcoming Delta System Design Review to refine key design aspects based on expert feedback.

The team began characterization of a student-formulated solid propellant, ensuring the consistency and performance of in-house fuel compositions.

A filament winder has been designed and constructed, enabling the production of custom body tubes for future rockets.

Two iterations of a custom flight computer have been developed, enhancing avionics capabilities for upcoming missions.

Participation in the 2024 Intercollegiate Rocket Engineering Competition (IREC) resulted in a 13th place finish among 121 global teams, marking a strong showing on the international stage.

The team successfully authored the Proposal, Preliminary Design Review (PDR), and Critical Design Review (CDR), each serving as key technical milestones. The Proposal encompassed over 70 pages, while both the PDR and CDR spanned approximately 250 pages. The upcoming focus is on completing the Launch Readiness Review (LRR) and Post-Launch Assessment Review (PLAR).

A 60% scale version of the launch vehicle intended for the Huntsville competition was successfully flown. This vehicle achieved an average thrust of approximately 85 pounds, reaching an altitude of 1,851 feet before deploying its parachute safely.

Additionally, 38 members participated in Purdue Space Day, an outreach initiative designed to educate third to eighth graders on STEM concepts and rocketry through interactive activities. A significant portion of PSP-SL members facilitated a hands-on water bottle rocket activity.