Design, Implementation, and Flight Validation Strategy of AkSat U2 and ViskanSat Sub-Orbital Picosatellite Platforms aboard the Rhumi-1 Sounding Rocket

Abstract

This study presents the design rationale, subsystem implementation, and comparative evaluation of two sub-orbital picosatellite demonstrators, AkSat U2 and ViskanSat, developed as ultra-compact, low-cost platforms for near-space technology validation aboard the Space Zone Aerospace’s Rhumi-1 sounding rocket. Both systems employ an identical mechanical form factor, avionics architecture, and power subsystem to enable controlled performance comparison under the same flight conditions. Each demonstrator integrates a 3D-printed structural enclosure, an ESP32-based microcontroller, a high-resolution MS5611 barometric pressure sensor, and an MPU6050 inertial measurement unit to support autonomous data logging of altitude, inertial dynamics, and thermal variations during ascent, coast, and descent. The Rhumi-1 sub-orbital trajectory, reaching altitudes of approximately 30–75 km, provides a relevant test environment for evaluating sensor fidelity, structural robustness, and low-power operational strategies under rapidly changing atmospheric and dynamic conditions. Pre-flight characterization and comparative analysis indicate strong performance consistency between the two platforms, demonstrating manufacturing repeatability and subsystem reliability. The results reinforce the effectiveness of low-cost picosatellite demonstrators as scalable technology-readiness tools for future balloon-borne, aerial, and femtosatellite orbital missions.