Thermal loading of spent rocket stage structure during ballistic descent
The results of a numerical calculation of the aerodynamic heating of a spent rocket stage structural elements during its controlled descent along a ballistic trajectory are presented. The influence of the initial trajectory parameters on the specific convective and radiant heat fluxes is determine...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Omsk State Technical University, Federal State Autonomous Educational Institution of Higher Education
2022-03-01
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| Series: | Омский научный вестник: Серия "Авиационно-ракетное и энергетическое машиностроение" |
| Subjects: | |
| Online Access: | https://www.omgtu.ru/general_information/media_omgtu/journal_of_omsk_research_journal/files/arhiv/2022/%D0%A2.%206,%20%E2%84%961%20(%D0%90%D0%A0%D0%B8%D0%AD%D0%9C)/101-108%20%D0%9A%D1%83%D0%B4%D0%B5%D0%BD%D1%86%D0%BE%D0%B2%20%D0%92.%20%D0%AE.,%20%D0%9A%D1%83%D0%B4%D0%B5%D0%BD%D1%86%D0%BE%D0%B2%20%D0%90.%20%D0%92.,%20%D0%9A%D1%83%D0%B7%D0%B8%D0%BD%D0%B0%20%D0%9D.%20%D0%90.,%20%D0%91%D0%B8%D0%BC%D0%B0%D1%82%D0%BE%D0%B2%20%D0%92.%D0%98..pdf |
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| Summary: | The results of a numerical calculation of the aerodynamic heating of a spent rocket stage structural
elements during its controlled descent along a ballistic trajectory are presented. The influence of the
initial trajectory parameters on the specific convective and radiant heat fluxes is determined. To assess
the thermal loading of the spent rocket stage structure, the parameter of the total specific energy flux
is introduced. It has been established that in the range of initial speeds of the spent rocket stage from
1800 m/s to 2600 m/s, an increase in the initial speed by 200 m/s leads to an increase in the specific
convective flow by an average of 11 % for the tail compartment and the fuel tank and by 5 % for the
oxidizer tank. The share of the specific radiant energy flux withdrawn from the surface in relation to the
specific convective energy flux is from 0,15 to 0,19 for the tail compartment, from 0,12 to 0,15 for the
fuel tank and not more than 0,009 for the oxidizer tank. Empirical dependencies are proposed for the
preliminary stage of assessing the temperature state of the spent rocket stage structure when moving
on a ballistic trajectory. The error of the calculation results according to the proposed dependencies
does not exceed 12 %. |
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| ISSN: | 2588-0373 2587-764X |