An integrated solution to ACMM problem of spacecraft with inertia uncertainty

Abstract

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.