Design and verification of thermal control system for Chang’E-3 probe

Abstract

ChangE-3 probe is the first Chinese spacecraft landed on the lunar surface and survived for lunar day/night cycles. The ChangE-3 thermal control system developed new elements such as closed two-phase thermosyphons, variable conductance heat pipes (VCHP), high-temperature adiabatic shield and radioisotope heater units (RHU) to deal with the harsh environment. Ground test methods for simulating the effect of lunar gravity and descent engine were established as well. Thermal control system worked well in orbit and on the lunar surface, and maintained the probe components and structure within the required range of temperatures throughout the mission. First-hand data of the lunar surface probe, which is useful for the future mission, was obtained during the flight test. This paper introduces the primary requirements, chief factors and the characteristics of the thermal control system design. The final scheme, key elements and flight performance of thermal control system are also described.