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The Lagrange method was used to establish the kinematic and dynamic models of the spacecraft. The translation and rotation of the spacecraft, vibrations of solar panels, and imbalance caused by the rotating appendages, which cause a complex control problem, were considered. To address the complex control problem, a novel, fast nonsingular integral sliding mode control method is proposed to perform the attitude tracking function of spacecraft. A sliding mode control law was established for the high\u2010inertia appendages to maintain an appropriate angular velocity during rotation. Finally, the effectiveness of the proposed attitude control law was verified by numerical simulations for a spacecraft with high\u2010inertia rotating appendages and symmetrical flexible solar panels.<\/jats:p>","DOI":"10.1155\/2021\/8812187","type":"journal-article","created":{"date-parts":[[2021,2,17]],"date-time":"2021-02-17T09:38:38Z","timestamp":1613554718000},"update-policy":"https:\/\/doi.org\/10.1002\/crossmark_policy","source":"Crossref","is-referenced-by-count":4,"title":["Nonsingular Integral Sliding Mode Attitude Control for Rigid\u2010Flexible Coupled Spacecraft with High\u2010Inertia Rotating Appendages"],"prefix":"10.1155","volume":"2021","author":[{"given":"Gaowang","family":"Zhang","sequence":"first","affiliation":[]},{"ORCID":"https:\/\/orcid.org\/0000-0002-5087-8415","authenticated-orcid":false,"given":"Xueqin","family":"Chen","sequence":"additional","affiliation":[]},{"given":"Ruichen","family":"Xi","sequence":"additional","affiliation":[]},{"given":"Huayi","family":"Li","sequence":"additional","affiliation":[]}],"member":"311","published-online":{"date-parts":[[2021,2,16]]},"reference":[{"key":"e_1_2_10_1_2","doi-asserted-by":"publisher","DOI":"10.1109\/TAES.2017.2740078"},{"key":"e_1_2_10_2_2","doi-asserted-by":"publisher","DOI":"10.1016\/j.ast.2017.11.036"},{"key":"e_1_2_10_3_2","doi-asserted-by":"publisher","DOI":"10.1109\/jas.2019.1911858"},{"key":"e_1_2_10_4_2","doi-asserted-by":"publisher","DOI":"10.1360\/SSI-2019-0105"},{"key":"e_1_2_10_5_2","doi-asserted-by":"publisher","DOI":"10.1109\/tfuzz.2018.2868898"},{"key":"e_1_2_10_6_2","doi-asserted-by":"publisher","DOI":"10.1109\/tcyb.2020.2977175"},{"key":"e_1_2_10_7_2","doi-asserted-by":"publisher","DOI":"10.1016\/j.automatica.2019.03.008"},{"key":"e_1_2_10_8_2","doi-asserted-by":"publisher","DOI":"10.1109\/TSMC.2019.2896614"},{"key":"e_1_2_10_9_2","doi-asserted-by":"publisher","DOI":"10.1109\/tgrs.2012.2197826"},{"key":"e_1_2_10_10_2","volume-title":"The Technique for Estimating and Compensating the Uncertainties: Active Disturbance Rejection Control Technique","author":"Han J.","year":"2008"},{"key":"e_1_2_10_11_2","doi-asserted-by":"publisher","DOI":"10.1109\/tnnls.2017.2756993"},{"key":"e_1_2_10_12_2","doi-asserted-by":"publisher","DOI":"10.1109\/TSMC.2019.2932225"},{"key":"e_1_2_10_13_2","doi-asserted-by":"publisher","DOI":"10.1109\/tac.2018.2794826"},{"key":"e_1_2_10_14_2","doi-asserted-by":"publisher","DOI":"10.1016\/j.automatica.2005.07.001"},{"key":"e_1_2_10_15_2","doi-asserted-by":"publisher","DOI":"10.1002\/rnc.4586"},{"key":"e_1_2_10_16_2","doi-asserted-by":"publisher","DOI":"10.1016\/j.cja.2018.03.003"},{"key":"e_1_2_10_17_2","doi-asserted-by":"publisher","DOI":"10.1177\/0142331219889172"},{"key":"e_1_2_10_18_2","doi-asserted-by":"publisher","DOI":"10.1109\/TFUZZ.2020.2996387"},{"key":"e_1_2_10_19_2","doi-asserted-by":"publisher","DOI":"10.1016\/j.jfranklin.2011.07.019"},{"key":"e_1_2_10_20_2","doi-asserted-by":"publisher","DOI":"10.1140\/epjst\/e2019-900041-4"},{"key":"e_1_2_10_21_2","doi-asserted-by":"crossref","unstructured":"LvS. 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