Abstract: The problem of tracking the longitudinal skip reentry trajectory is considered for the lunar return vehicle with the rotation of the Earth. First, the influence of the Earth rotation on the guidance is given via the detailed analysis of guidance dynamics. Considering this problem, the guidance for lunar return vehicle is studied based on feedback linearization method with the consideration of the Earth rotation. The reentry dynamics equations are very complicated with the Earth rotation. If the guidance is designed using the exact feedback linearization method, too many states should be measured, and the guidance would be too complex to implement. A simplified guidance is designed in the paper, and the design principle is analyzed. It is concluded that with some uncertainties the proposed guidance has higher precision by comparison with shuttle entry guidance.

Key words: lunar return, skip reentry, guidance, the rotation of the Earth, feedback linearization