초소형 위성의 자체 폐기 기동 및 재진입 궤적 분석을 위한 JINJUSat-2 부탑재체 설계 및 열 해석

초록

The proliferation of CubeSats in Low-Earth Orbit (LEO) demands both responsible end-of-life disposal and late-phase re-entry (h < 200 km) flight-data acquisition. This study assesses a 0.5U re-entry capsule (JREM) aboard the 6U JINJUSat-2, protected only by a 5mm carbon-phenolic TPS. Aerothermal loads computed with DRAMA 3.0/SARA were applied to a Thermal Desktop/SINDA model from the de-orbit release altitude of 94 km to ground impact. The capsule endures 11min 12s of re-entry, encountering a peak heat flux of 21.9kW·m⁻² and a TPS surface temperature of 1,600°C, while the internal battery remains below 45°C (design limit 60 °C). Imposing a conservative +30% load margin to bound ablation and air-ingress uncertainties raises the battery maximum to 58°C, still within its discharge limit but indicating the need for additional shell-to-battery insulation. These results demonstrate, for the first time, that continuous trajectory and thermal data can be captured from late-phase re-entry to ground without a full-area TPS, positioning JREM as a practical in-orbit demonstrator for small-satellite disposal and re-entry model validation.

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