System Analysis and Pre-Flight Evaluation of Deployable Solar Panels for 3U CubeSat HOKUSHIN-1

TL;DR

This paper presents the system design, structural and thermal analysis, and vibration test results of deployable solar panels for a 3U CubeSat, supporting future lunar exploration missions.

Contribution

It introduces a comprehensive design methodology and evaluation process for deployable solar panels on CubeSats, including structural, thermal, and vibration analyses.

Findings

Successful structural and thermal analysis validation

Vibration test results confirm panel durability

Design supports lunar exploration mission requirements

Abstract

This paper describes the system design methodology derived from the development and evaluation tests of deployable solar panels to be mounted on a 3U CubeSat. The study mainly includes structural analysis, thermal analysis, and a review of vibration test results. Hokkaido University is developing the 3U CubeSat HOKUSHIN-1 in collaboration with Tohoku University and Muroran Institute of Technology. Deployable solar panels are a key technology for future planned lunar exploration missions, as they enable power-intensive communication and propulsion required for orbit control. The satellite also demonstrates a newly developed compact and efficient propulsion system. The satellite has dimensions of approximately 10x10x34 cm, a mass of 3.99 kg, and will be deployed into a circular orbit at an altitude of about 400 km with an orbital inclination of 51.6 degrees from the International Space Station.