Over the past three decades, a variety of concepts have been proposed for space exploration using Tethered Satellite Systems (TSS), and numerous missions have already been launched to verify the tethered system concept for space applications [1-10]. The advantage of using tethers stems from its lightness and structural as well as dynamical versatility. A triangular system, for example, provides a particularly convenient basis for stereoscopic observation. In this study we consider an equilateral tether system connecting three rigid satellites. We derive the equations of attitude motion of this spinning system in a circular orbit around a planet and give their numerical solutions and discuss the stability of attitude motion.