Rapid Attitude Reorientation for Defunct Spacecraft Deorbit Manoeuvre based on Robust Piece-wise Affine MPC

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Rapid Attitude Reorientation for Defunct Spacecraft Deorbit Manoeuvre based on Robust Piece-wise Affine MPC | Research Square window.SnipcartSettings = { analytics: { enabled: false } }; (function() { var accessVector = localStorage.getItem('access_vector') || ''; window.dataLayer = window.dataLayer || []; if (accessVector) { window.dataLayer.push({ user: { profile: { profileInfo: { snid: accessVector } } } }); } })(); (function(w,d,s,l,i){w[l]=w[l]||[];w[l].push({'gtm.start':new Date().getTime(),event:'gtm.js'});var f=d.getElementsByTagName(s)[0],j=d.createElement(s),dl=l!='dataLayer'?'&l='+l:'';j.async=true;j.src='https://www.googletagmanager.com/gtm.js?id='+i+dl;f.parentNode.insertBefore(j,f);})(window,document,'script','dataLayer','GTM-K279D39R'); Browse Preprints In Review Journals COVID-19 Preprints AJE Video Bytes Research Tools Research Promotion AJE Professional Editing AJE Rubriq About Preprint Platform In Review Editorial Policies Our Team Advisory Board Help Center Sign In Submit a Preprint Cite Share Download PDF Research Article Rapid Attitude Reorientation for Defunct Spacecraft Deorbit Manoeuvre based on Robust Piece-wise Affine MPC Xiaohua Zhang, Shu Yang, Wee Seng Lim This is a preprint; it has not been peer reviewed by a journal. https://doi.org/ 10.21203/rs.3.rs-8558308/v1 This work is licensed under a CC BY 4.0 License Status: Under Review Version 1 posted 9 You are reading this latest preprint version Abstract As spacecraft reach the end of their operational life, they pose a significant threat to active spacecrafts in orbit. This paper presents an approach for rapid deorbit attitude reorientation of defunct spacecraft using Robust Piece-wise Affine Model Predictive Control (RPWA MPC) for attitude control. An innovative method where multiple solid fuel micro thrusters with brief operational duration are employed for rapid attitude reorientation. A theoretical attitude characteristic analysis for defunct spacecraft is conducted, and simulations assess the impact of environmental disturbances. Based on the analysis, this study introduces a unique single-axis attitude control strategy focused on the pitch axis to achieve the desired deorbit attitude. Given the need for the spacecraft to attain this deorbit attitude within a fixed number of control periods, a RPWA MPC controller is designed. Due to high non-linearities arising from environmental disturbance torques, the PWA model breaks down the MPC into multiple computationally feasible discrete models to reduce computational complexity. A disturbance observer is designed to provide real-time estimation of the disturbance torques in the PWA model, enhancing the robustness of the system. Numerical simulations demonstrate that only thirty micro thrusters are needed to achieve the required attitude reorientation, enabling the spacecraft to reach deorbit attitude efficiently before igniting the deorbit thrusters. Deorbit attitude reorientation Model Predictive Control Robust Piece-wise affine model Defunct spacecraft Full Text Additional Declarations No competing interests reported. Cite Share Download PDF Status: Under Review Version 1 posted Reviews received at journal 15 May, 2026 Reviewers agreed at journal 14 Apr, 2026 Reviews received at journal 07 Apr, 2026 Reviewers agreed at journal 01 Apr, 2026 Reviewers agreed at journal 21 Jan, 2026 Reviewers invited by journal 19 Jan, 2026 Editor assigned by journal 14 Jan, 2026 Submission checks completed at journal 12 Jan, 2026 First submitted to journal 09 Jan, 2026 You are reading this latest preprint version Research Square lets you share your work early, gain feedback from the community, and start making changes to your manuscript prior to peer review in a journal. As a division of Research Square Company, we’re committed to making research communication faster, fairer, and more useful. We do this by developing innovative software and high quality services for the global research community. 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last seen: 2026-05-20T01:45:00.602351+00:00