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Flight Performance of HALCA Satellite Thermal Control
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English
Abstract
The ISAS's space VLBI satellite HALCA was successfully launched in February 1997. The spacecraft HALCA consists of a box shaped main structure and a large deployable mesh antenna with 8 m effective diameter. The integrated spacecraft with the mesh structure antenna is so large and complex that the thermal design and tests had been performed separately for the main structure and the large antenna. No thermal vacuum test had been conducted in the fully integrated spacecraft configuration. The complex heat exchange between the antenna and the main structure had been taken into account in the numerical thermal analysis. Good correlation between in-orbit temperature and flight prediction has proved validity of the design and the verification method where no integrated spacecraft thermal vacuum test was performed.
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Citation
Ohnishi, A., Hirosawa, H., Okamoto, A., Nagashima, K. et al., "Flight Performance of HALCA Satellite Thermal Control," SAE Technical Paper 981545, 1998, https://doi.org/10.4271/981545.Also In
References
- Hirosawa H. Hirabayashi H. “Design and development of the Space VLBI Satellite for the VSOP (VLBI Space Observatory Program)” Space Technology 16 3 161 167 1996
- Ohnishi A. et al. “Thermal Design of the MUSES-B Spacecraft” SAE 951745 , 25 th ICES San Diego, California July 10 13 1995
- Futagi Y. et al. “Flight Performance of a Large Deplyable Antenna on the HALCA Satellite” SAE 981549, 28 th ICES Danver, Massachustts July 13 16 1998