Conceptual Design of a Lunar Landing Mission Using Korea Space Launch Vehicle 2

A lunar landing mission using a newly developing launch vehicle in Korea was conceptually designed. Korea planned to develop a new three-stage-to-orbit launch system, Korea Space Launch Vehicle 2. If KSLV-2 is successfully developed before 2018, Korea will examine the possibility of sending a lunar orbiter in 2020 and a lunar lander in 2025. In the present study, a 1200N H2O2/Kerosene bi-propellant thruster with the pressurized feed system was considered as the propulsion system of the upper stage which was used to translunar injection, and the lunar lander. Based on the proposed specifications of KSLV-2, the mass budgets of the upper stage and the lunar lander were estimated when the parking orbit was a circular low earth orbit an altitude of 300 km and inclination angle of 81°. Two translunar injection methods, direct transfer method and phasing loop method, were compared in determining masses. 3 degree-of-freedom orbit trajectory calculations were performed for the purpose using Satellite Tool Kit/Astrogator. The target landing site in both cases was the South Pole of the Moon. It was found that using KSLV-2, the possible dry mass of the lunar lander was about 170 kg. It was also found that 2.5 phasing loop is the optimal phasing loop method when lunar landing mission is conducted using KSLV-2, although the direct transfer method is easier to achieve the mission goal.