TRAJECTORY DESIGN FOR THE KOREA PATHFINDER LUNAR ORBITER (KPLO)

Abstract

The Korea Pathfinder Lunar Orbiter (KPLO) will be the first spacecraft for the Korean lunar exploration program. KPLO will fly in a low 100 km mean altitude lunar polar orbit. KPLO will utilize a 3.5 phasing loop transfer trajectory. This paper will describe several trade-off studies of critical parameters to minimize the Delta-V such as phasing loop option, trans-lunar inclination, 1st apogee altitude, SEM (Satellite-Earth-Moon) angle and periselene altitude for lunar orbit insertion. After lunar orbit insertion, KPLO will be placed into a mission orbit. These parameters were studied over a month-long launch period in December 2020 and the results are given. As a result, 3.5 loops with first apogee altitude of a 320,000 km provides minimum Delta-V. Low initial inclination, low SEM angle and low captured periselene altitude of LOI1 shows better performance.