Development of a Sun Vector Determination Algorithm for CubeSat-class Spacecraft

The limited power, mass, and volume allotted for attitude determination systems on nanosatellites require that less accurate sensors be used when compared to those found on larger spacecraft. The addition of multiple sensors allows for improved accuracy, and the solar arrays that are found on most spacecraft can act as coarse sun sensors. By utilizing the current data from the arrays, an independent attitude vector can be established without any additional non-computational resources. The sun-sensing algorithms that interpret the current data influence the accuracy of this sun vector. This thesis investigates six different sun-sensing algorithms for use with CubeSat-class spacecraft and evaluates their performances through comprehensive simulations, with the objective of determining the most suitable algorithm for use onboard the YuSEND-1 spacecraft.