Abstract
High requirements are imposed on the mass and dimensional stability of reflectors of onboard mirror space antennas in promising communication satellites. To meet these requirements, new design and layout schemes for reflectors using composite materials are being developed. The use of flat reinforced carbon fabric composites in these designs is of particular interest. A technique is developed for the experimental determination of mechanical and thermophysical characteristics of the carbon fiber used in a thin-walled shell (0.6 mm) of the onboard space antenna reflector. Data are obtained on the elastic modulus of the carbon fiber based on Aspro-A80 carbon fabric and Huntsman Araldite LY8615 US/XB 5173 Hardener epoxy compound in two directions. The thermal conductivity of the material in the plane of reinforcement is determined.
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: Proceedings of Higher Educational Institutions. Маchine Building
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.
