Abstract
Thermal design verification of large deployable reflectors was estimated by using flight data. The temperatures were recorded from ETS-VI, which was launched on August 28, 1994 using H-II vehicle. The reflector surfaces were coated with white paint which had low absorptivity 0.23 at begin of life (BOL) as well as high emissivity 0.87 at BOL. The back structure of the surface was covered with multi-layer insulation (MLI) blankets to shield the solar energy to the trusses. The maximum and minimum temperatures of the large reflectors were fell within the allowable temperature range. The analysis results obtained by a mathematical model agreed well with the flight data. The maximum temperature difference in the surface of the reflector using the analysis model was also evaluated within the allowable temperature.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callMore From: Journal of the Japan Society for Aeronautical and Space Sciences
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
