Volatiles including water on the Moon has been one of the most interesting scientific objects for decades. In this study, we systematically introduced a concept for China's Chang'E- 7 (CE-7) lunar polar exploration mission which consists of five elements, the orbiter, lander, rover, and leaper, and one relay satellite. The orbiter will provide a high-resolution image preparing for landing site selection. We also proposed three phases for in-situ investigation after landing. (1) The rover and leaper will jointly investigate the sunlit area; (2) the leaper will explore cold traps; and (3) the leaper will fly back to the sunlit area and continue an extended exploration mission. An experimental penetrator launched by the lander will penetrate permanently shadowed crater walls for water ice detection. Data will be transmitted to Earth through the relay satellite due to the limited Earth visibility. We also calculated the illumination rate within a 15 x 15 km area that partially covers the Shackleton crater at a high spatial resolution of 20 m/pixel during lunar southern summer. Specifically, we compared two potential landing sites with accumulated illumination at different altitude levels, slopes, and distances to the target. We found that one part of the Shackleton crater rim can be a primary landing site for CE-7's both sunlit areas and cold trap explorations.

The LVS-PIE Phase A project successfully investigated the feasibility of using the Lunar Volatiles Scout instrument on the ispace Polar Ice Explorer rover to search for possible cold-trapped water ice deposits at the lunar poles. The suitability of the two systems for a joint mission was studied based on identified conflicts between both initial systems, such as the envelope for integration or the power budget. The interfaces were made compatible, mechanical structure and mechanisms were updated to enable system integration and thermal simulations were performed to refine the thermal design for safe operation within the thermal limits under lunar conditions. Thermal extraction simulations for the instrument constrained the power requirement during the instrument's heating phase. Real drilling down forces and reaction torques were determined with representative experiments for both rover and instrument revealing stable conditions during the envisioned drilling process. In the developed mission scenario, operational feasibility of the LVS-PIE mission concept was demonstrated using a notional traverse, remote sensing data and investigation of technical budgets. The mission can reach sites of high scientific interest at the lunar poles and perform relevant measurements with the instrument. A joined mission consisting of an instrument package for drilling and gas analysis on a rover below 20 kg total mass is found to be technically feasible and scientifically valuable.