{"title":"基于预定性能的刚性航天器有限时间姿态跟踪控制","authors":"Yanning Guo, Pengyu Wang, G. Ma, Chuanjiang Li","doi":"10.1109/ICIST.2018.8426177","DOIUrl":null,"url":null,"abstract":"This paper investigates the attitude tracking control problem for rigid spacecraft with bounded external disturbance. By combing the terminal sliding-mode technique and the prescribed performance concept, a finite-time control scheme with sliding-mode surface constraint is proposed, whose structure is simpler than the conventional transformed error constraint methods. Then, a saturation function is introduced to the control scheme to eliminate singularity, and the system performance in both the reaching phase and the ideal sliding-mode are studied. Stability analysis shows that the proposed control scheme can make the spacecraft tracking a time-varying desired signal with a finite-time convergence. The effectiveness of the attitude tracking control scheme is evaluated by numerical simulations.","PeriodicalId":331555,"journal":{"name":"2018 Eighth International Conference on Information Science and Technology (ICIST)","volume":null,"pages":null},"PeriodicalIF":0.0000,"publicationDate":"2018-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"3","resultStr":"{\"title\":\"Prescribed Performance Based Finite-Time Attitude Tracking Control for Rigid Spacecraft\",\"authors\":\"Yanning Guo, Pengyu Wang, G. Ma, Chuanjiang Li\",\"doi\":\"10.1109/ICIST.2018.8426177\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"This paper investigates the attitude tracking control problem for rigid spacecraft with bounded external disturbance. By combing the terminal sliding-mode technique and the prescribed performance concept, a finite-time control scheme with sliding-mode surface constraint is proposed, whose structure is simpler than the conventional transformed error constraint methods. Then, a saturation function is introduced to the control scheme to eliminate singularity, and the system performance in both the reaching phase and the ideal sliding-mode are studied. Stability analysis shows that the proposed control scheme can make the spacecraft tracking a time-varying desired signal with a finite-time convergence. The effectiveness of the attitude tracking control scheme is evaluated by numerical simulations.\",\"PeriodicalId\":331555,\"journal\":{\"name\":\"2018 Eighth International Conference on Information Science and Technology (ICIST)\",\"volume\":null,\"pages\":null},\"PeriodicalIF\":0.0000,\"publicationDate\":\"2018-06-01\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"3\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"2018 Eighth International Conference on Information Science and Technology (ICIST)\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.1109/ICIST.2018.8426177\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"2018 Eighth International Conference on Information Science and Technology (ICIST)","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1109/ICIST.2018.8426177","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
Prescribed Performance Based Finite-Time Attitude Tracking Control for Rigid Spacecraft
This paper investigates the attitude tracking control problem for rigid spacecraft with bounded external disturbance. By combing the terminal sliding-mode technique and the prescribed performance concept, a finite-time control scheme with sliding-mode surface constraint is proposed, whose structure is simpler than the conventional transformed error constraint methods. Then, a saturation function is introduced to the control scheme to eliminate singularity, and the system performance in both the reaching phase and the ideal sliding-mode are studied. Stability analysis shows that the proposed control scheme can make the spacecraft tracking a time-varying desired signal with a finite-time convergence. The effectiveness of the attitude tracking control scheme is evaluated by numerical simulations.