{"status":"ok","message-type":"work","message-version":"1.0.0","message":{"indexed":{"date-parts":[[2026,6,3]],"date-time":"2026-06-03T18:26:21Z","timestamp":1780511181690,"version":"3.54.1"},"reference-count":48,"publisher":"MDPI AG","issue":"1","license":[{"start":{"date-parts":[[2023,1,6]],"date-time":"2023-01-06T00:00:00Z","timestamp":1672963200000},"content-version":"vor","delay-in-days":0,"URL":"https:\/\/creativecommons.org\/licenses\/by\/4.0\/"}],"funder":[{"DOI":"10.13039\/501100006769","name":"Russian Science Foundation","doi-asserted-by":"publisher","award":["22-19-00160"],"award-info":[{"award-number":["22-19-00160"]}],"id":[{"id":"10.13039\/501100006769","id-type":"DOI","asserted-by":"publisher"}]}],"content-domain":{"domain":[],"crossmark-restriction":false},"short-container-title":["Symmetry"],"abstract":"<jats:p>The paper considers the problem of a small-spacecraft elastic elements\u2019 temperature shock that occurs when the spacecraft immerses into the Earth\u2019s shadow or comes out of it. A small spacecraft with two elastic elements is simulated. In the first approximation, such a problem is considered to be a symmetric problem. Estimations of disturbing factors from the temperature shock in a symmetric formulation are obtained. The differences from the results for a small spacecraft with a single elastic element are analyzed. The results of the work can be used for promising small technological spacecraft development, as well as for solving problems of space debris removal and remote sensing of the Earth.<\/jats:p>","DOI":"10.3390\/sym15010172","type":"journal-article","created":{"date-parts":[[2023,1,9]],"date-time":"2023-01-09T02:31:30Z","timestamp":1673231490000},"page":"172","update-policy":"https:\/\/doi.org\/10.3390\/mdpi_crossmark_policy","source":"Crossref","is-referenced-by-count":12,"title":["The Symmetric Formulation of the Temperature Shock Problem for a Small Spacecraft with Two Elastic Elements"],"prefix":"10.3390","volume":"15","author":[{"ORCID":"https:\/\/orcid.org\/0000-0003-2698-1348","authenticated-orcid":false,"given":"Andrey","family":"Sedelnikov","sequence":"first","affiliation":[{"name":"Institute of Aerospace Engineering of Samara National Research University, 34 Moskovskoye Shosse, 443086 Samara, Russia"}],"role":[{"vocabulary":"crossref","role":"author"}]},{"ORCID":"https:\/\/orcid.org\/0000-0002-6750-1307","authenticated-orcid":false,"given":"Denis","family":"Orlov","sequence":"additional","affiliation":[{"name":"Institute of Aerospace Engineering of Samara National Research University, 34 Moskovskoye Shosse, 443086 Samara, Russia"}],"role":[{"vocabulary":"crossref","role":"author"}]},{"given":"Valeria","family":"Serdakova","sequence":"additional","affiliation":[{"name":"Institute of Aerospace Engineering of Samara National Research University, 34 Moskovskoye Shosse, 443086 Samara, Russia"}],"role":[{"vocabulary":"crossref","role":"author"}]},{"given":"Alexandra","family":"Nikolaeva","sequence":"additional","affiliation":[{"name":"Institute of Aerospace Engineering of Samara National Research University, 34 Moskovskoye Shosse, 443086 Samara, Russia"}],"role":[{"vocabulary":"crossref","role":"author"}]}],"member":"1968","published-online":{"date-parts":[[2023,1,6]]},"reference":[{"key":"ref_1","doi-asserted-by":"crossref","first-page":"1503","DOI":"10.2514\/1.A33116","article-title":"Thermally Induced Dynamics of a Spinning Spacecraft with an Axial Flexible Boom","volume":"52","author":"Shen","year":"2015","journal-title":"J. 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