Rotating tethers can be used for momentum transfer by releasing a payload from one end of the tether. The momentum transfer places the payload in a new orbit that can reach Geostationary Orbit (GEO), Lunar Transfer Orbit (LTO), or interplanetary trajectories from Low Earth Orbit (LEO). If the tether is to be reused, for electromagnetic propulsion or to place further payloads into orbit for example, then it is important that the tether not collapse from the stored spring energy of the tether. Analytical expressions are determined for a simplified tether system for the conditions under which collapse will occur in terms of end-body masses, tether properties, and rotation rate.
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