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Zenodo
2026
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| Online Access: | https://doi.org/10.5281/zenodo.19425182 |
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| _version_ | 1866901182211948544 |
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| author | Fernandez, Adrian G. |
| author_facet | Fernandez, Adrian G. |
| contents | <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> |
| format | Recurso digital |
| id | zenodo_https___doi_org_10_5281_zenodo_19425182 |
| institution | Zenodo |
| language | |
| publishDate | 2026 |
| publisher | Zenodo |
| record_format | zenodo |
| spellingShingle | Predicted Orbital Deviation in the Artemis II Mission Under the Cosmological Thermosynthesis Theory v3.2 Fernandez, Adrian G. <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> |
| title | Predicted Orbital Deviation in the Artemis II Mission Under the Cosmological Thermosynthesis Theory v3.2 |
| url | https://doi.org/10.5281/zenodo.19425182 |