Compact Environmental Sensors for Batched Stratospheric and Orbital Launch

Abstract

The rapid growth of the commercial space sector, especially CubeSats, has made lowcost, compact sensor hardware an increasingly practical option for spacecraft applications, yet the gap between terrestrial development and space qualification remains a critical challenge. This thesis addresses that gap through the design, assembly, and testing of two experimental payloads developed with the MaxIQ Space program, in support of the Princeton TigerSats Laboratory’s development of a low-cost 1U CubeSat. The first payload targets a stratospheric flight aboard a NASA High-Altitude Balloon, validating commercial-off-the-shelf infrared horizon sensors to detect Earth’s horizon and compute spacecraft attitude estimates under near-space conditions. The second payload targets orbital deployment aboard the International Space Station, collecting in-situ environmental measurements to characterize the payload’s local operational conditions and validate the viability of commercial sensors in a true microgravity environment as well as their launch survivability. Across both experiments, design prioritized minimal volume, mass, and power consumption to adhere to the design requirements and constraints. Candidate sensors were evaluated through ground testing and iterative PCB design before delivery for launch, aiming to advance their Technology Readiness Level for future integration into the TigerSats CubeSat.