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Simulation of Ionospheric Perturbations Induced by Rocket‐Propelled Vehicle: A Semi‐Empirical Approach

2022; Wiley; Volume: 127; Issue: 5 Linguagem: Inglês

10.1029/2021ja029993

2169-9402

Pierre Ducourtieux,

GNSS positioning and interference

Journal of Geophysical Research: Space PhysicsVolume 127, Issue 5 e2021JA029993 Research Article Simulation of Ionospheric Perturbations Induced by Rocket-Propelled Vehicle: A Semi-Empirical Approach Pierre Ducourtieux, Corresponding Author Pierre Ducourtieux [email protected] orcid.org/0000-0001-8348-946X opsci. technologies, Paris, France Correspondence to: P. Ducourtieux, [email protected]Search for more papers by this author Pierre Ducourtieux, Corresponding Author Pierre Ducourtieux [email protected] orcid.org/0000-0001-8348-946X opsci. technologies, Paris, France Correspondence to: P. Ducourtieux, [email protected]Search for more papers by this author First published: 11 April 2022 https://doi.org/10.1029/2021JA029993Read the full textAboutPDF ToolsRequest permissionExport citationAdd to favoritesTrack citation ShareShare Give accessShare full text accessShare full-text accessPlease review our Terms and Conditions of Use and check box below to share full-text version of article.I have read and accept the Wiley Online Library Terms and Conditions of UseShareable LinkUse the link below to share a full-text version of this article with your friends and colleagues. Learn more.Copy URL Share a linkShare onEmailFacebookTwitterLinkedInRedditWechat Abstract The flight of rocket-propelled vehicles triggers acoustic waves that propagate through the atmosphere and induce electron density changes at ionospheric heights. These perturbations can be observed using multi-frequency Global Navigation Satellite System (GNSS) receivers, sounding the ionosphere by taking advantage of its dispersive property. We extend an existing lightweight modeling approach to reproduce the shape, amplitude and timing of the observed perturbations using a semi-empirical source model based on flight conditions and engine characteristics to express the acoustic perturbations generated by the exhaust gases and a three-dimensional ray tracing method accounting for dissipative and dispersive effects to propagate the waveform through the atmosphere. Perturbations of the ionospheric plasma are estimated using a simplified model of collisions between neutral and charged particles. The developed simulation framework is applied to the launch of SpaceX's Crew Dragon spacecraft on May 30, 2020 from Kennedy Space Center. The amplitude, shape and timing of simulated perturbations are in good agreement with measurements made by GNSS ground-based receivers located in the region. This approach is a new step toward rapid characterization of anthropogenic activity in the atmosphere as well as natural events releasing energy near the Earth's surface (earthquake, volcanic activity, etc.) based on GNSS technology. Key Points The ascent flight of the Crew Dragon spacecraft induced perturbations of the ionospheric plasma observed using ground-based Global Navigation Satellite System (GNSS) receivers Perturbations caused by exhaust gases are simulated using linear acoustic propagation and simplified atmosphere-ionosphere coupling Proposed approach opens the possibility of characterization of rocket-propelled vehicles engines and trajectory based on GNSS soundings Plain Language Summary Perturbations of the ionosphere triggered by the ascent flight of a Falcon 9 rocket are simulated using a semi-empirical source model describing the disturbances caused by the energy released in the environment by the rocket engines. The results are successfully compared to measurements made by ground-based receivers sounding the ionosphere. 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