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The orientation of a satellite that contains a passive, internal mass damper about a stationary point is studied. The satellite is moving in a resistive medium and influenced by gyrostatic torque (GT). The nonlinear governing equations of motion (EOMs) for such a case are derived. The parameterized feedback control torques are applied to the satellite to achieve rapid stabilization. Using the angular momentum law and the energy integral with the initial conditions of the motion made it easy to approach a solution for the nutation angle and the angular velocities. The Runge-Kutta fourth-order method (RK4) is applied to get a graphical simulation for the influence of some parameters on the solutions. Based on this simulation, the stability of motion is examined. By striking a balance between active gyrostatic control and passive damping, satellite systems can achieve strong rotation stability in resistive mediums. The proposed strategy demonstrates a balance between active control and passive damping, suggesting potential benefits for energy efficiency and operational lifespan compared to traditional thrusters in specific scenarios. Applications extend to next-generation satellites requiring agile reorientation in dynamic environments, such as debris-dense orbits or missions involving deployable payloads, where precise angular velocity regulation is a determinant of success.
Elneklawy et al. (Wed,) studied this question.