Thermal Design of the MUSES-B Spacecraft

951745

07/01/1995

Event
International Conference on Environmental Systems
Authors Abstract
Content
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.
Meta TagsDetails
DOI
https://doi.org/10.4271/951745
Pages
7
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.
Additional Details
Publisher
Published
Jul 1, 1995
Product Code
951745
Content Type
Technical Paper
Language
English