Thermal design of «AIST» small spacecraft
Thermal design is a prerequisite essential to design a satellite. In space environment, it makes it possible for the satellite to survive in extreme hot and cold conditions. In recent years small satellite missions have been developed for many kinds of purposes. The paper describes thermal design fo...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
Samara National Research University
2016-04-01
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| Series: | Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение |
| Subjects: | |
| Online Access: | https://journals.ssau.ru/vestnik/article/viewFile/3022/2973 |
| _version_ | 1818914644975157248 |
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| author | D. S. Kulikov Ja. N. Erilkin |
| author_facet | D. S. Kulikov Ja. N. Erilkin |
| author_sort | D. S. Kulikov |
| collection | DOAJ |
| description | Thermal design is a prerequisite essential to design a satellite. In space environment, it makes it possible for the satellite to survive in extreme hot and cold conditions. In recent years small satellite missions have been developed for many kinds of purposes. The paper describes thermal design for the AIST small spacecraft mission. To calculate thermal environment a detailed thermal mathematical model has been developed using the finite element method and Siemens NX 10.0 software with the integrated module NX Space Systems Thermal Simulation. The analysis carried out with the help of mathematical simulation showed the sufficiency of the passive thermal control system of the AIST small spacecraft. In order to improve thermal radiation couplings between panels a coating with a high emissivity factor was applied on all the inner surfaces. The outer surfaces (except the areas occupied with photovoltaic converters) were coated with aluminum foil. The graphs of changes in temperatures of onboard equipment in the orbital flight phase show that all the parameters meet the requirements of the thermal control system specifications. |
| first_indexed | 2024-12-19T23:49:40Z |
| format | Article |
| id | doaj.art-d41d1c143c6b47df95a520ab63a56c68 |
| institution | Directory Open Access Journal |
| issn | 2542-0453 2541-7533 |
| language | English |
| last_indexed | 2024-12-19T23:49:40Z |
| publishDate | 2016-04-01 |
| publisher | Samara National Research University |
| record_format | Article |
| series | Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение |
| spelling | doaj.art-d41d1c143c6b47df95a520ab63a56c682022-12-21T20:01:12ZengSamara National Research UniversityВестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение2542-04532541-75332016-04-01151818810.18287/2412-7329-2016-15-1-81-882855Thermal design of «AIST» small spacecraftD. S. Kulikov0Ja. N. Erilkin1Space Rocket Center «Progress», SamaraSpace Rocket Center «Progress», SamaraThermal design is a prerequisite essential to design a satellite. In space environment, it makes it possible for the satellite to survive in extreme hot and cold conditions. In recent years small satellite missions have been developed for many kinds of purposes. The paper describes thermal design for the AIST small spacecraft mission. To calculate thermal environment a detailed thermal mathematical model has been developed using the finite element method and Siemens NX 10.0 software with the integrated module NX Space Systems Thermal Simulation. The analysis carried out with the help of mathematical simulation showed the sufficiency of the passive thermal control system of the AIST small spacecraft. In order to improve thermal radiation couplings between panels a coating with a high emissivity factor was applied on all the inner surfaces. The outer surfaces (except the areas occupied with photovoltaic converters) were coated with aluminum foil. The graphs of changes in temperatures of onboard equipment in the orbital flight phase show that all the parameters meet the requirements of the thermal control system specifications.https://journals.ssau.ru/vestnik/article/viewFile/3022/2973thermal control systemthermal loadsheat conductionradiationtemperature rangeorbital flight |
| spellingShingle | D. S. Kulikov Ja. N. Erilkin Thermal design of «AIST» small spacecraft Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение thermal control system thermal loads heat conduction radiation temperature range orbital flight |
| title | Thermal design of «AIST» small spacecraft |
| title_full | Thermal design of «AIST» small spacecraft |
| title_fullStr | Thermal design of «AIST» small spacecraft |
| title_full_unstemmed | Thermal design of «AIST» small spacecraft |
| title_short | Thermal design of «AIST» small spacecraft |
| title_sort | thermal design of aist small spacecraft |
| topic | thermal control system thermal loads heat conduction radiation temperature range orbital flight |
| url | https://journals.ssau.ru/vestnik/article/viewFile/3022/2973 |
| work_keys_str_mv | AT dskulikov thermaldesignofaistsmallspacecraft AT janerilkin thermaldesignofaistsmallspacecraft |