{"title":"Adaptive Backstepping Terminal Sliding Mode Attitude stabilization control for Moving Mass Rocket-propelled CubeSat","authors":"Qian Pengjun, Lu Zhengliang","doi":"10.1109/icmeas54189.2021.00014","DOIUrl":null,"url":null,"abstract":"This article addresses the attitude stabilization control problem of the moving mass rocket-propelled CubeSat in orbit maneuver. Considering the propellant combustion and the motion of two moving masses, the attitude dynamic model of the satellite is established by Newton multi-rigid system with variable mass dynamic. Subsequently, based on the simplified control model of pitch and yaw channel, backstepping technique is utilized to design the controller and the dynamic surface control is employed to avoid the computer explosion. An adaptive law is proposed to estimate the upper boundaries of uncertainties. Lyapunov function is used to prove the stability of the closed-loop system. Finally, numerical simulation results indicate the effectiveness of the designed control method.","PeriodicalId":374943,"journal":{"name":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","volume":"14 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"2021-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"2021 7th International Conference on Mechanical Engineering and Automation Science (ICMEAS)","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1109/icmeas54189.2021.00014","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
引用次数: 0
Abstract
This article addresses the attitude stabilization control problem of the moving mass rocket-propelled CubeSat in orbit maneuver. Considering the propellant combustion and the motion of two moving masses, the attitude dynamic model of the satellite is established by Newton multi-rigid system with variable mass dynamic. Subsequently, based on the simplified control model of pitch and yaw channel, backstepping technique is utilized to design the controller and the dynamic surface control is employed to avoid the computer explosion. An adaptive law is proposed to estimate the upper boundaries of uncertainties. Lyapunov function is used to prove the stability of the closed-loop system. Finally, numerical simulation results indicate the effectiveness of the designed control method.
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