From top to bottom, the rocket was designed to be simple, lightweight, cost-effective, and optimized not to the final degree, but rather to a degree that balanced integration and design ease, with raw performance.  The nose tip, forward closure, and an adapter piece from a G10 laminate avionics sled to the nose tip, were all machined out of 6061-T6 aluminum.  The avionics bay featured a single GPS tracket and barometric altimeter/recovery deployment computer, responsible for transmitting location, as well as ensuring safe recovery of the rocket.  The parachute and shock cord were packed inside of the nose cone and forward closure/coupler piece, an approach more volume-efficient than most conventional designs.  This coupler was responsible for sealing combustion gases at the top of the motor, anchoring the recovery system, and providing a sturdy nose cone coupling point.  The propellant was designed in a stepped-BATES geometry, to strike a balance of manufacturing ease and a relatively flat thrust curve.  The fins were composed of 3D-printed AlSi10Mg, and designed by Julien Denat for use on his Gas Gas Gas project, being repurposed later on for this project.

All CAD was done in Autodesk Fusion 360, and the rocket design softwares OpenMotor and Openrocket were used.