A CubeSat for RFI detection and tethered interferometer experiment

Abstract

CubeSats are tiny space exploration vessels with a lower cost than most satellites in history. Studies on this technology are flourishing, as evidenced by the doubling of published research between initial exploration and final projects. These versatile mini- satellites fulfill diverse missions while adhering to a standardized, compact design. Inspired by Phase I & II of the Space Electric and Magnetic Sensor (SEAMS) mission, which is aimed at performing an RFI survey and testing out interferometric principles respectively, we propose a mission wherein we will try to observe an RFI scenario and perform an interferometer using a tethered system in this work. With this mission, we can get an insight into what other factors may affect the interferometer experiment of SEAMS phase II. The proposed tethered CubeSat system will comprise a 2U and 1U CubeSat and will be launched as a combined 3U payload into Low Earth Orbit (LEO). Upon reaching LEO, the 1U CubeSat will autonomously deploy from the 3U CubeSat. The primary objective of this study is to validate the electronic functionality and effectiveness of a tethered CubeSat system for performing astronomical observations using radio interferometry. In this study, I present FEA analysis of the CubeSat structure, Two-Element interferometer configuration, designing of the backend, and processing to observe interferometric fringes.