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| Format: | Recurso digital |
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Zenodo
2026
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| Accès en ligne: | https://doi.org/10.5281/zenodo.19425182 |
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- <p>This work presents a rigorous mathematical prediction of orbital deviation in the Artemis II mission trajectory under the Cosmological Thermosynthesis Theory v3.2 (TTC v3.2). The theory posits that spacetime behaves as a topological superfluid etherionic medium, inducing a weak cumulative radial perturbation on macroscopic trajectories near massive bodies. We derive the etherionic drag term from first principles of TTC v3.2, implement a high-precision three-body numerical integration (Earth–Moon–Sun) with the additional perturbation, and quantify the expected deviation in lunar flyby distance and re-entry velocity. Results predict a systematic deviation of +18 to +50 km in the minimum lunar approach distance (nominal<br>NASA value: 6513 km). Given the Orion spacecraft’s navigation accuracy (±3 to ±8 km), this signal is detectable at 3.75–10σ significance. The effect on re-entry velocity (∼ −0.12 m/s) is negligible for mission safety. These predictions provide a falsifiable, observationally testable consequence of TTC v3.2 using data from the April 2026 Artemis II mission.</p>