This paper addresses the challenge of stabilizing non-rigid satellites with uncertain dynamics, particularly those with flexible components like solar panels. The authors propose an adaptive detumbling method using two space tugs to stabilize a non-rigid satellite. The satellite is modeled as a two-link serial chain with unknown stiffness and damping, in contrast to previous models that treat satellites as rigid bodies. The method accounts for uncertainties in mass, inertia, and contact points, and uses proportional-derivative control with adaptive feedback linearization to drive the satellite to rest. The effectiveness of the method is demonstrated through simulations, showing that the satellite's angular and linear velocities converge to zero, and the Lyapunov-like function decreases over time, proving the system's stability. The paper also includes detailed analysis of the regressor matrix and proof of the positive definiteness of the mass matrix.This paper addresses the challenge of stabilizing non-rigid satellites with uncertain dynamics, particularly those with flexible components like solar panels. The authors propose an adaptive detumbling method using two space tugs to stabilize a non-rigid satellite. The satellite is modeled as a two-link serial chain with unknown stiffness and damping, in contrast to previous models that treat satellites as rigid bodies. The method accounts for uncertainties in mass, inertia, and contact points, and uses proportional-derivative control with adaptive feedback linearization to drive the satellite to rest. The effectiveness of the method is demonstrated through simulations, showing that the satellite's angular and linear velocities converge to zero, and the Lyapunov-like function decreases over time, proving the system's stability. The paper also includes detailed analysis of the regressor matrix and proof of the positive definiteness of the mass matrix.