Xanadu Rocket
2025
Xanadu Rocket Abstract
The objective of this project was to design and validate a 30-inch G-class rocket as part of Project Daedalus at the Rocket Propulsion Laboratory. The rocket features NACA 0012 fins modeled in SolidWorks, optimized CG/CP stability margins, and a recovery system engineered to cap descent at 15 ft/s. Iterative configuration testing in OpenRocket and structural design refinements maintained stability throughout the flight profile.
Design Process
The design process began with extensive research into rocket aerodynamics and stability analysis. Using OpenRocket simulation software, we iterated through multiple fin configurations to optimize the center of gravity and center of pressure relationship. The NACA 0012 airfoil was selected for its proven aerodynamic efficiency and ease of manufacturing.
Recovery System Analysis
The recovery parachute was sized via drag-force equilibrium calculations with a drag coefficient (Cd) of 0.9. Through iterative calculations balancing gravitational force and drag force, we determined that a 30-inch canopy diameter would cap descent velocity at the target 15 ft/s, ensuring safe recovery of the rocket body and avionics.
Technical Documentation
Comprehensive technical design documentation was authored and presented at the Critical Design Review (CDR). The presentation incorporated cross-team feedback into the final configuration, addressing concerns about structural integrity, recovery deployment timing, and flight stability margins.