Design and implementation of the integrated thermal control system for Chang'E−5 lunar module. (November 2022)

• Record Type: Journal Article
• Authors: Xianwen, Ning; Yuying, Wang; Jing, Peng; Gao, Zhang; Fan, Jiang; Dong, Zhang
• Is Part Of: Acta astronautica. Volume 200(2022)
• Page Start: 188
• Page End: 195
• Publication Date: 2022-11
• Subjects: Spacecraft -- Thermal control -- Thermal bus -- Fluid loop -- Water sublimator; Astronautics -- Periodicals; Outer space -- Exploration -- Periodicals; Astronautics; Periodicals; 629.405
• DOI: 10.1016/j.actaastro.2022.08.005
• Languages: English
• ISSNs: 0094-5765

Abstract

Abstract: Aiming at the thermal control challenges of the Chang'E−5 lunar module, which is a complex of lunar lander and lunar ascent vehicle, a design method was proposed based on optimized management of energy. An integrated and autonomous thermal management system for robotic lunar spacecraft was designed including a single-phase fluid loop, water sublimator and high temperature thermal protection shield. The single-phase fluid loop driven by a miniature pump served as the thermal bus to collect heat. The water sublimator was applied as a supplementary heat sink of panel radiators to dissipate heat load on the lunar surface. The lightweight thermal protection shield was applied to protect the equipment in confined space from high temperature plume of big-powered engine during powered descent and ascending. The combination heat sink of fixed panel radiators and water sublimator was managed to meet different heat dissipation requirements of the Chang'E−5 lunar module. The flight data showed that the proposed thermal control system achieved excellent performance. The electronic equipment onboard the Chang'E−5 lunar module was kept between −7.7 °C to 39.6 °C during the mission profile. An optimized goal was achieved that there was zero thermal power compensation for the electronic equipment, while the ratio of thermal load peak-to-trough was as high as 7:1. At the same time, an inter-layer heat transfer model of the heat shield was verified with a temperature difference of less than 3 °C between the prediction result and flight data. Highlights: Thermal control challenges of the Chang'E−5 lunar module were described. Thermal management system for robotic lunar spacecraft was designed. Thermal control system was designed based on optimized management of energy. The thermal management system was verified by the operation on the lunar surface.