Thermal Design of the MUSES-B Spacecraft

Paper #:
  • 951745

Published:
  • 1995-07-01
Citation:
Ohnishi, A., Hirosawa, H., Okamoto, A., and Uchihori, H., "Thermal Design of the MUSES-B Spacecraft," SAE Technical Paper 951745, 1995, https://doi.org/10.4271/951745.
Pages:
7
Abstract:
The MUSES-B spacecraft will be launched in 1996 by the Institute of Space and Astronautical Science (ISAS). Its primary mission is experiments on space Very Long Baseline Interferometry (VLBI) for radio astronomy using a large deployable antenna.A challenging thermal design must be compatible with a wide range of sun angle and an 86 minute eclipse. The thermal design and verification has been performed separately for the major modules of the spacecraft; a main structure, a deployable antenna and Reaction Control System (RCS). Special attention is paid to the exposed RCS whose solar input varies significantly depending on the sun angle.This paper describes the thermal design concept for MUSES-B and verification results of its thermal model test focusing on the main structure and the RCS.
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