Electric propulsion structure materials properties prediction

Material authority


Balashov V. V.1*, Volkov Y. F.2**, Demidov A. S.3***, Kashelkin V. V.4****, Pashutov A. V.5*****, Khartov S. A.3******

1. Research Institute of Applied Mechanics and Electrodynamics of Moscow Aviation Institute (RIAME MAI), Moscow, Russia
2. Federal State Unitary Establishment «Krasnaya Zvezda»,
3. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
4. Company «Red Star», 1а, Elektrolitny proezd, Moscow, 115230, Russia
5. Central research institute for special machinery, Zavodskay str., Khotkovo, Moscow region, 141371, Russia

*e-mail: riame@sokol.ru
**e-mail: volkov-yuri@yandex.ru
***e-mail: demidov@mai.ru
****e-mail: re.entry@g23.relcom.ru
*****e-mail: tsniism@tsniism.ru
******e-mail: skhartov@ya.ru


It is analyzed whether it is possible to estimate damage accumulation taking place in cantilever samples made of C-C composite material caused by vibration testing by means of observing how self-resonant frequency of the samples changes during test. References to previous results obtained for the samples made of stainless steel and other materials are given. The simplified variant for generating a strength surface for the composite material by using tensor-polynomial failure criterion is examined.


structure materials; ion thruster electrodes; C-C composite material; lifetime; fail; vibration tests; modal characteristics; cantilever samples; tensor-polynomial failure criterion; strength surface


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