A Single-Tether Orbital Sling for Cislunar Injection: Release Energy, Tension and Timing Budgets

This study sizes the system named in its title from stated physical relations and a stated operating basis, and reports the result as SIMULATED, NOT MEASURED. The operating principle is rotating single tether that releases a payload at a timed phase to achieve cislunar injection. The orbital sling is a civilian cargo launch system intended to send uncrewed freight pods toward lunar distance; it carries no payload other than commercial and scientific cargo pods. Every performance figure is computed by the deposited script from its inputs rather than asserted, and the headline outcomes include payload velocity immediately after release of 1.07e+04 metres per second; apogee altitude of the thrown trajectory of 6.63e+05 kilometres; peak hub tension at release of 4.2 meganewtons; centripetal acceleration at the tip of 8.17 Earth gravities. Mass, power, time and energy budgets are assembled from components so they can be audited line by line, off-design behaviour is discussed openly, and the limits of the sizing are stated in full. The design is presented as a civilian system throughout, with its governing constraint identified and quantified rather than merely encountered.