Based onphysical simulation experiment, an attitude control problem concerning the inplane motion of a tethered satellite system with short distance deployment is studied by means of dynamics similarity between the ground-based experiments and the onorbit system. Starting with nonlinear dynamic of the tethered satellite system with controllable arm, dynamics similarity conditions between the groundbased experiments and the onorbit system are obtained. using the proportion differential feedback control strategy, a numerical simulation is performed to the attitude motion of the controlled tethered satellite. Subsequently, the similar onorbit environment is realized by experimental platform. The groundbased test is conducted, the control of the attitude motion tethered satellite the tether swing is achieved only using single rigid arm. Finally, the comparison of experimental and numerical results demonstrate that the of rigid arm can effectively control the deployment of the tethered satellite.