Comprehensive modeling and characterization of the General-Purpose Heat Source Radioisotope Thermoelectric Generator for solar system missions

• Published in: Applied thermal engineering Vol. 248; p. 123278
• Main Authors: Tailin, Li, Youhong, Liu, Yingzeng, Zhang, Haodong, Chen, Qingpei, Xiang
• Format: Journal Article
• Language: English
• Published: Elsevier Ltd 01.07.2024
• Subjects: GPHS-RTG; Modeling analysis; Radioisotope thermoelectric generator; Solar system mission; Thermoelectric conversion; Solar system mission; Thermoelectric conversion; Radioisotope thermoelectric generator; Modeling analysis; GPHS-RTG
• ISSN: 1359-4311
• DOI: 10.1016/j.applthermaleng.2024.123278

[Display omitted] •A comprehensive modeling and simulation of the GPHS-RTG in space is realized.•The simulation results are validated by reports with error less than 1.6 %.•The conservative application range of the GPHS-RTG in the solar system is revealed.•Several methods to expend the application range of the GPHS-RTG are summarized.•The GPHS-RTG’s axial and circumferential thermal distributions in space are analyzed. The radioisotope thermoelectric generator relies solely on radioactive decay for its energy and generates power through the thermoelectric effect. The General-Purpose Heat Source Radioisotope Thermoelectric Generator (GPHS-RTG) represents the RTG with the largest power and highest conversion efficiency ever built, and its energy supply supported four daring interplanetary missions (Galileo, Ulysses, Cassini, New Horizons). To explore the use potential of the GPHS-RTG in the solar system, its conservative application range and performance should be determined. In this work, a comprehensive model of the GPHS-RTG was developed, and its calculated results agreed well with Lockheed Martin’s test report (temperature relative error < 1 %). The study demonstrates that within the Earth orbit, the distance of the mission area from the sun and the angle of incidence sunlight significantly affect the thermoelectric performance and hot-junctions’ temperature. Moreover, conservative application ranges and their extending methods (changing coating material, thermal loading, and operational voltage) for GPHS-RTG at different attitudes in the solar system were determined for the first time by comparing the proportion of the hot-junction over-temperature area. The temperature distribution and its cause of formation in the axial and circumferential directions of the GPHS-RTG during solar system missions were revealed in the end. This work is valuable for future RTG design and mission planning.