Abstract
The research aimed at investigating the possibility of obtaining thin intermetallic films, which can be used as thermal control coatings for spacecraft. The coating films build the passive part of the overall thermal control system of a spacecraft, thus they must provide strong adhesion with the carrier material and have high functional characteristics, optical ones in particular. The study concerned issues of synthesis of stable intermetallic phase of Al4Cu9, Al2Cu, Cu5Zn8 on aluminum and copper carriers by magnetron layer-wise sputtering of reagents. They have looked into patterns of emergence of intermetallic coating applying modes of "rapid" and "slow" sputtering of reagents, applying various thicknesses of sputtered layers of reagents, temperature of the carrier, heat treatment of sprayed coatings. Incomplete and complete modes of synthesis of intermetallic coverage have been discovered. Obtained cross-sectional images of coatings, outcomes of microanalyzer scanning of reagent distribution through the thickness of sputtered coatings, microhardness values, optical absorption and emission ratios, unit of electric resistances, adhesion to the carrier. Obtained prototypes of intermetallic thermostatic coatings could be used in "solar reflectors" and "solar absorbers" classes. The results of measurements of optical and strength characteristics revealed that the intermetallic films can be used not only as thermostatic coatings for space technology, but also in general mechanical engineering, due to high-end mechanical properties.
Highlights
When in Earth orbit, a spacecraft (SC) is exposed to strong thermal radiation of the Sun leading to some individual surfaces heating up to +150 °C
Required temperature is provided by thermal regulation system of SC, which protects electronics from overheating by solar radiation and heats colder parts of the working area
An important part of any thermal regulation system consists of thermostatic coatings (TSC) of a SC external surfaces [1]
Summary
When in Earth orbit, a spacecraft (SC) is exposed to strong thermal radiation of the Sun leading to some individual surfaces heating up to +150 °C. Connection (1) demonstrates that minimizing temperature of SC heating by solar radiation is achieved by minimization of coefficient ratios of AS/ε TSC, meaning the less AS and the more ε is, 82 A Study on the Possibilities of Obtaining Intermetallic Coating of Al-Cu and Cu-Zn Systems Deposited the less the body temperature becomes. TSC class "Solar absorbers" is designed for maximum absorption of solar energy, which further is transported inside the SC to provide thermal energy to individual units. Experts believe that new TSC classes, "Solar reflectors"class with stable thermal radioactive properties at long-term service when applied to SC in space, are one of the most important priorities in the space industry of the 21 century [4]. This technique is known as the method of coating flexible surfaces with strengthening intermetallic coatings [7], the possibility of using such coatings as TSC has not been investigated
Sign-in/Register to view highlights & summary 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 callDisclaimer: 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.
