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An integrated solution to ACMM problem of spacecraft with inertia uncertainty
Author(s) -
Liu Ping,
Xue Wenchao,
Chen Sen,
Huang Yi,
Sun Zhendong
Publication year - 2018
Publication title -
international journal of robust and nonlinear control
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 1.361
H-Index - 106
eISSN - 1099-1239
pISSN - 1049-8923
DOI - 10.1002/rnc.4332
Subject(s) - control theory (sociology) , spacecraft , robustness (evolution) , inertia , linear quadratic regulator , quadratic equation , robust control , state observer , computer science , mathematics , control engineering , engineering , mathematical optimization , optimal control , control system , control (management) , nonlinear system , physics , aerospace engineering , artificial intelligence , biochemistry , chemistry , geometry , electrical engineering , classical mechanics , quantum mechanics , gene
Summary In this work, an integrated solution to the attitude control and momentum management problem is studied for the velocity‐free large spacecraft subject to both inertia uncertainty and strong disturbances. A multiple‐input–multiple‐output‐type linear extended state observer is constructed to estimate the uncertain information, and a novel disturbance compensator and a linear quadratic regulator controller are proposed. The stability of the proposed scheme is rigorously proved, and the quantitative relationship between the closed‐loop tracking error and the uncertainty size is thoroughly analyzed. Comparison studies are carried out to verify the effectiveness and robustness of the proposed approach.