This paper is devoted to the dynamics of a multi-tethered tetrahedral satellite formation. The proposed formation consists of a spinning tethered triangle and a free-flying spacecraft orbiting at LEO. It is shown that a proper choice of the spin rate of the tethered triangle causes it to change its orientation due to gravity-gradient torque and track the free-flying satellite that changes its periodic inertial position because of the argument of perigee drift. Furthermore, the design of J2-invariant relative orbits is utilized to minimize any undesired drift. The proposed passive control strategy results in producing high-quality tetrahedra. The proposed formation is suitable for scientific missions where three-dimensional multi-point measurements are required.