| _version_ | 1866901971764510720 |
|---|---|
| author | İzgi, Burak |
| author_facet | İzgi, Burak |
| contents | <p>Thermal control is a critical design driver for microsatellite reliability. Optimization of Phase Change Materials (PCM) as a passive thermal management solution in microsatellites is usually based on a single, nominal operational point in time and a fixed heat load. This study goes one step beyond this common approach and investigates how robust optimized PCM-filler configurations remain in the face of a wide range of different operational scenarios. To this end, we conducted a parametric study using an established analytical model, systematically varying heat loads (15W, 25W, 35W) and pulse durations (20, 40, 60 min). Our main objective was to determine the minimum system mass and volume required to maintain the maximum component temperature at 50 °C for each scenario. The results conclusively demonstrate that the “best” material choice is not a fixed truth, but rather strongly dependent on the mission profile. Mapping the operational space showed that Glycerol-based configurations are ideal for a wide range of medium-to-hard scenarios. However, under the most challenging, high-energy conditions, we observed that the optimally balanced design shifts towards PlusICE-based systems, indicating a critical material selection transition based on mission demands. This study provides satellite designers with a quantitative framework to go beyond a single design point and select truly robust and reliable thermal solutions for the entire operational envelope of a mission.</p> |
| format | Recurso digital |
| id | zenodo_https___doi_org_10_5281_zenodo_18626173 |
| institution | Zenodo |
| language | |
| publishDate | 2026 |
| publisher | Zenodo |
| record_format | zenodo |
| spellingShingle | Mission Profile Robustness of PCM Thermal Management for Microsatellites İzgi, Burak microsatellite thermal control, Phase Change Material (PCM), robustness analysis, parametric study, mission profile <p>Thermal control is a critical design driver for microsatellite reliability. Optimization of Phase Change Materials (PCM) as a passive thermal management solution in microsatellites is usually based on a single, nominal operational point in time and a fixed heat load. This study goes one step beyond this common approach and investigates how robust optimized PCM-filler configurations remain in the face of a wide range of different operational scenarios. To this end, we conducted a parametric study using an established analytical model, systematically varying heat loads (15W, 25W, 35W) and pulse durations (20, 40, 60 min). Our main objective was to determine the minimum system mass and volume required to maintain the maximum component temperature at 50 °C for each scenario. The results conclusively demonstrate that the “best” material choice is not a fixed truth, but rather strongly dependent on the mission profile. Mapping the operational space showed that Glycerol-based configurations are ideal for a wide range of medium-to-hard scenarios. However, under the most challenging, high-energy conditions, we observed that the optimally balanced design shifts towards PlusICE-based systems, indicating a critical material selection transition based on mission demands. This study provides satellite designers with a quantitative framework to go beyond a single design point and select truly robust and reliable thermal solutions for the entire operational envelope of a mission.</p> |
| title | Mission Profile Robustness of PCM Thermal Management for Microsatellites |
| topic | microsatellite thermal control, Phase Change Material (PCM), robustness analysis, parametric study, mission profile |
| url | https://doi.org/10.5281/zenodo.18626173 |