小型月着陸実証機SLIM の着陸降下軌道最適化

抄録

Thanks to recent lunar exploration missions, high-resolution lunar surface observation data was obtained. In future lunar exploration, it is requested to land at a specific point in which scientific interest is higher than other areas. SLIM project is demonstrating pinpoint landing technology, which is achieved, by combination of "autonomous image-based high-precision navigation technology" and "autonomous guidance technology aims to generate fuel optimum landing trajectory". This paper presents powered descending trajectory design in terms of trajectory optimization. As usually considered in general space mission development, an optimal solution in terms of minimum fuel consumption is the basis of investigation. This study addresses trajectory optimization considering specific objective functions derived from practical constraints regarding mission design, e.g., altitude, length of downrange, and visibility from ground stations. In this paper, nominal trajectory design considering minimum fuel consumption is presented, followed by parametric studies to identify sensitivity to change of initial conditions with which powered descending starts. Finally, trajectory optimization results with various type of objective function are presented.