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- Article name
- Experimental-analytical methodology used to define parameters of sandy-grained roughness on burned surfaces of composite thermal-protective materials
- Authors
- DEGTYAR V. G., , src@makeyev.ru, Open Joint Stock Company"State Rocket Centre named after academician V. P. Makeyev", Miass, Chelyabinsk Region, Russia
KALASHNIKOV S. T., , src@makeyev.ru, Department of Fundamental Aerospace Technologies Problems of the Chelyabinsk Research Centre of the RAS Urals Branch, Miass, Chelyabinskaya oblast, Russia
KOSTIN G. F., , kostgf@yandex.ru, Senior Researcher of Chelyabinsk Scientific Centre of the RAS Urals Branch, Miass, Chelyabinsk region, Russia
TYUMENTSEV V. A., , vatyum@csu.ru, Federal State Budget Educational Institution of Higher Professional Education «CSU», Chelyabinsk, Russia
SHVALEVA R. K., , src@makeyev.ru, Joint Stock Company "Academician V. P. Makeyev State Rocket Center"; South Ural Scientific Centre, Miass, Chelyabinsk Region, Russia
SAVELIEV V. N., , src@makeyev.ru, Joint Stock Company "Academician V. P. Makeyev State Rocket Center", Miass, Chelyabinsk Region, Russia
KHLYBOV V. I., , src@makeyev.ru, Joint Stock Company "Academician V. P. Makeyev State Rocket Center"; South Ural Scientific Centre, Miass, Chelyabinsk Region, Russia
- Keywords
- flight vehicles / C-C composites / surface roughness / electron microscopic study / distribution of voids / ablation of materials
- Year
- 2018 Issue 3 Pages 29 - 39
- Code EDN
- Code DOI
- Abstract
- The paper presents an experimental-analytical methodology to define parameters of sandy-grained roughness equivalent in the influence on laminar/turbulent transition in the boundary layer and heat exchange to the real physical roughness that is formed on surfaces of thermal-protective composite coatings in burning along trajectories of Flight Vehicles (FV). The methodology includes electron microscopic study, X-ray diffraction of materials, tomographic measurements of a density distribution by volume with the assessment of large-scale roughness (formed by structures and geometry of composite frames (fillers)), finely grained roughness (formed by outcropping of voids, shells, micro-cracks in burning) and a factor of the influence of a graphitation degree on the ablation of material using these records. The corresponding parameters of roughness and the graphitation degree are used in the analysis of heat exchange and varying FV shapes in burning of the thermal protection system along the flight trajectory.
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