Comparison of Solar Radiation Torque and Power Generation of Deployable Solar Panel Configurations on Nanosatellites

Abstract

Nanosatellites, like CubeSat, have begun completing advanced missions that require high power that can be obtained using deployable solar panels. However, a larger solar array area facing the Sun increases the solar radiation torque on the satellite. In this study, we investigated solar radiation torque characteristics resulting from the increased area of solar panels on board the CubeSats. Three common deployable solar panel configurations that are commercially available were introduced and their reference missions were established for the purpose of comparison. The software algorithms used to simulate a variety of orbit scenarios are described in detail and some concerns are highlighted based on the results obtained. The solar power generation of the respective configurations is provided. The findings are useful for nanosatellite developers in predicting the characteristics of solar radiation torques and solar power generation that will be encountered when using various deployable solar panels, thus helping with the selection of a suitable configuration for their design.

Modeling and simulation of the kinematic behavior of the deployment mechanism of solar array for a 1‐U CubeSat

“…The BM types have the panels mounted (fixed) on the side frames of the satellites. On the other hand, DSA have in addition to the fixed panels, deployable ones that give them more surface area to optimize power generation 8 . The payload operations of BM CubeSats were limited to basic low power image coverage due to inadequate power in earlier systems like the CUTE‐I 1 U/BM for Armature Radio with 1.5 W launched in 2003 9 and CanX‐2 3 U/BM as technology demonstrator for formation flying launched in 2008 10 .…”

“…On the other hand, DSA have in addition to the fixed panels, deployable ones that give them more surface area to optimize power generation. 8 The payload operations of BM CubeSats were limited to basic low power image coverage due to inadequate power in earlier systems like the CUTE-I 1 U/BM for Armature Radio with 1.5 W launched in 2003 9 and CanX-2 3 U/BM as technology demonstrator for formation flying launched in 2008. 10 On the other hand, the use of DSA in the recent systems provides more power to achieve high precision images and other sophisticated operations as obtained in FLOCK-1 3 U/DSA with 20 W launched in 2014 as earth observer, 11 and Mars Cube One (MarCO) 6 U/DSA launched in 2018 for Telecom technology, 12 producing 8 to 12 times more power.…”