On the guidance for the Lunar return skip reentry considering the earth rotation
WANG Ze-guo
MENG Bin
ZHAO Yun-bo
Abstract：We address the guidance problem for the Lunar return spacecraft skip reentry. Taking the Earth rotation into consideration, we perform an observer-based approximate feedback linearization guidance law design for the uncertain and nonlinear dynamics of the Lunar return spacecraft. Firstly, the peak phenomenon of observer-based controllers is considered. The air density approximates to zero when the initial reentry, so the initial observation error of drag is also zero approximately. Considering this feature, a simplified design for peak-free phenomenon is given for the observer-based controllers. Then, the guidance design problems are considered. It is first proved that the internal dynamics is bounded-input-bounded-state, which constructs the basis for the design of guidance law. The closed-loop properties are proved that the guidance errors are uniformly ultimately bounded, and tend to zero with the diminish of initial observed errors. Combining that the initial observation errors approximate to zero, the guidance errors are also zero approximately. Finally, simulation on Apollo Command Module illustrates the effectiveness of the proposed theoretical method. This paper has laid the foundations for the research on Mars reentry and the Lunar reentry etc.
Keywords：the Lunar return spacecraftskip reentrythe Earth rotationthe observer-based approximate feedback linearization guidance lawinternal dynamics propertiesclosed-loop properties
Publication Date：2018-01-01
Online Publishing Date：2025-08-15(First online date of this platform, not the publication date of the document)
Pages：9( 732-740 )