Abstract:

Few studies have sought to integrate the strengths of advanced control technologies with classical control approaches to address the stringent requirements of hyper-agile satellites for both ultra-high precision and ultra-fast maneuverability. The present work addresses this issue by combining active disturbance rejection control (ADRC) and proportional-integral-derivative (PID) control, with a focus on the use of reaction flywheels as control actuators in hyper-agile satellites. The ADRC algorithm enables the rapid correction of significant control errors and avoids excessive control torque by adopting a transition process in a tracking differentiator. In contrast, the PID algorithm applies direct error feedback to achieve ultra-high steady-state precision tracking. The results of numerical simulations demonstrate that the proposed integrated control method not only achieves ultra-fast maneuverability, with an angular displacement of 25° within 10 s, but also delivers ultra-high precision steady-state tracking with an angular error of 1×10⁻⁶° and an angular velocity variability of 2×10⁻⁸ °/s without the reaction flywheel actuator control errors. However, the reaction flywheel output torque errors reduce the velocity control stability by four orders of magnitude and the attitude control accuracy by a factor of two.

Key words: hyper-agile satellite, ultra-high precision, ultra-fast maneuverability, active disturbance rejection control (ADRC), proportional-integral-derivative (PID) control