Three-Axis Attitude Determination of a Nanosatellite Using Optimized TRIAD Algorithms

This paper aims to develop a comprehensive approach for determining the attitude of a nanosatellite. Accurate determination of these parameters is essential for the proper operation of the nanosatellite and its successful mission completion. To achieve this goal, a detailed simulation of the magnetometer and sun sensor measurements in the body and orbital frame of the nanosatellite is conducted. These measurements are critical for determining the attitude of the nanosatellite and ensuring that it is pointing in the right direction. The attitude determination process is carried out using the Three-Axis Attitude Determination (TRIAD) algorithm, which is a popular and effective approach for estimating the attitude of a nanosatellite. The optimization of TRIAD with three different approaches is analyzed to ensure high accuracy and efficiency in determining the attitude of the nanosatellite. A covariance analysis is performed to evaluate the accuracy and reliability of the attitude determination process. The analysis provides valuable insights into the error sources and uncertainties associated with the measurements and estimation process. This information is used to improve the performance of the system and enhance the accuracy of the results. Overall, the results of this paper are expected to contribute significantly to the development of efficient and accurate methods for determining the attitude of a nanosatellite.