Attitude Determination and Control System Simulation for Low Earth Orbit CubeSats

Abstract

This paper presents the development of a high-fidelity, configurable Attitude Determination and Control System (ADCS) simulator designed to address the challenges of ground testing and validation for CubeSat missions. The simulator employs quaternion-based kinematics and rigid body dynamics, which are validated against in-orbit telemetry data.

The system supports multiple reference frames and attitude targeting modes, including Nadir, Earth Surface Tracking, and Inertial Pointing. Regarding control strategies, the work details the implementation of a PD controller for safe-mode Sun pointing and a nonlinear Sliding Mode Controller for rough pointing maneuvers.

Furthermore, the paper describes a robust data management workflow utilizing HDF5 to integrate a user-friendly interface with MATLAB/Simulink. Simulation results demonstrate the effectiveness of the control algorithms and the simulator's capability to facilitate personalized mission analysis in an academic environment.