Simulation of Satellite Attitude Control System Utilizing Flywheel Actuators

The simulation system implements a satellite attitude control framework where flywheels serve as the primary actuators. This architecture employs mathematical models of satellite dynamics coupled with flywheel control logic to replicate real-world scenarios. The system's core algorithm typically involves momentum exchange principles, where flywheel rotational speed adjustments generate control torques to stabilize the satellite's orientation. Key functional components include: 1) Kinematic and dynamic modeling of spacecraft motion using quaternion or Euler angle representations 2) Flywheel torque calculation modules implementing PID or modern control algorithms 3) Real-time sensor data processing for attitude determination 4) Momentum management systems to prevent flywheel saturation. The simulation enables engineers to validate control algorithms through code implementations that mimic orbital disturbances and spacecraft parameters. Advanced features incorporate sensor noise modeling and actuator delay simulations, providing critical insights for optimizing attitude determination and control system (ADCS) performance. This virtual testing environment proves indispensable for verifying satellite stability margins and control authority before orbital deployment.