We introduce a decentralized attitude control strategy that can dramatically reduce the usage of propellant, byudtaking full advantage of the physical coupling of the tether. Motivated by a controllability analysis, indicating that both array resizing and spin-up are fully controllable by the reaction wheels and the tether motor, we report the first propellant-free underactuated control results for tethered formation flying spacecraft. This paper also describes the hardware development and experimental validation of the proposed method using the Synchronized Position Hold, Engage, and Reorient Experimental Satellites test bed. In particular, a new relative sensing mechanism that uses sixderee-of-freedom force-torque sensors and rate gyroscopes is introduced and validated in the closed-loop control experiments.
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