Automated test bench for simulation of radiation electrification of spacecraft structural dielectrics

Detalles Bibliográficos
Parent link:IOP Conference Series: Materials Science and Engineering
Vol. 168 : Radiation-Thermal Effects and Processes in Inorganic Materials (RTEP2016).— 2017.— [012037, 6 p.]
Autor Corporativo: Национальный исследовательский Томский политехнический университет (ТПУ) Институт физики высоких технологий (ИФВТ) Кафедра сильноточной электроники (СЭ)
Outros autores: Vladimirov A. M. Aleksandr Mikhailovich, Bezhayev A. Yu., Zykov V. M. Vladimir Mikhailovich, Isaychenko V. I. Vadim Igorevich, Lukashchuk A. A. Andrei Aleksandrovich, Lukonin S. E. Stanislav Evgenievich
Summary:Title screen
The paper describes the test bench "Prognoz-2" designed in Testing Center, Institute of Non-Destructive Testing, Tomsk Polytechnic University, which can be used: for ground testing of individual samples of spacecraft structural materials (e.g. thermal control coatings or cover glasses for solar batteries) or ceramics of the plasma thruster discharge channel), and whole spacecraft units or instruments (e.g. instruments of solar and stellar orientation or correcting plasma thrusters) exposed to radiation electrification factors; to verify the calculation mathematical models of radiation electrification of structural dielectrics under the impact of space factors in different orbits.
Idioma:inglés
Publicado: 2017
Series:Physical and chemical phenomena in inorganic materials in radiation, electrical and thermal fields
Subjects:
Acceso en liña:http://dx.doi.org/10.1088/1757-899X/168/1/012037
http://earchive.tpu.ru/handle/11683/37754
Formato: Electrónico Capítulo de libro
KOHA link:https://koha.lib.tpu.ru/cgi-bin/koha/opac-detail.pl?biblionumber=653811
Descripción
Summary:Title screen
The paper describes the test bench "Prognoz-2" designed in Testing Center, Institute of Non-Destructive Testing, Tomsk Polytechnic University, which can be used: for ground testing of individual samples of spacecraft structural materials (e.g. thermal control coatings or cover glasses for solar batteries) or ceramics of the plasma thruster discharge channel), and whole spacecraft units or instruments (e.g. instruments of solar and stellar orientation or correcting plasma thrusters) exposed to radiation electrification factors; to verify the calculation mathematical models of radiation electrification of structural dielectrics under the impact of space factors in different orbits.
DOI:10.1088/1757-899X/168/1/012037