Study of unusable liquid propellant residues evaporation processes parameters in the tanks of launch vehicle worked-off stage in microgravity
A method is proposed for studying the evaporation process of unusable rocket propellant residues in worked-off stage under weightless conditions. Two options are considered as boundary conditions for liquid rocket propellant residues: a) liquid drop distribution in N identical drops, which surface...
Saved in:
| Main Authors: | , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
Omsk State Technical University, Federal State Autonomous Educational Institution of Higher Education
2019-06-01
|
| 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/2019/%D0%A2.%203,%20%E2%84%96%202%20(%D0%90%D0%A0%D0%B8%D0%AD%D0%9C)/103-114%20%D0%A2%D1%80%D1%83%D1%88%D0%BB%D1%8F%D0%BA%D0%BE%D0%B2%20%D0%92.%20%D0%98.,%20%D0%A3%D1%80%D0%B1%D0%B0%D0%BD%D1%81%D0%BA%D0%B8%D0%B9%20%D0%92.%20%D0%90..pdf |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| _version_ | 1832572081103962112 |
|---|---|
| author | V. I. Trushlyakov V. A. Urbansky |
| author_facet | V. I. Trushlyakov V. A. Urbansky |
| author_sort | V. I. Trushlyakov |
| collection | DOAJ |
| description | A method is proposed for studying the evaporation process of unusable rocket propellant residues in
worked-off stage under weightless conditions. Two options are considered as boundary conditions for
liquid rocket propellant residues: a) liquid drop distribution in N identical drops, which surface decreases
during evaporation and b) the liquid location in the lower tank bottom and the mirror presence, which
area decreases during evaporation. A high-temperature stream of hydrogen peroxide decomposition
products is used as a heat carrier fed to the fuel tank. The physical and mathematical model of the
liquid evaporation process is based on the first thermodynamics law. Based on the analysis of the Frud
and Grashof criteria, the assumption that there is no convection movement inside the drop (Rayleigh
number is less than critical) for both boundary conditions variants, the heat transfer coefficient of the
gas-vapor mixture produced in the tank is determined based on the regression dependence obtained in
ground conditions as a function of from the Nusselt, Reynolds, Prandtl numbers. Comparisons of the gasvapor mixture parameters for the considered boundary conditions variants and the proposed physical
mathematical model with the results, obtained earlier, for the boundary conditions variant of uniform
fluid distribution over the inner tank wall (third boundary conditions variant) and using the boundary
layer theory based on integral impulses, energy and diffusion ratios are given. The thermophysical gas-vapor mixture parameters and the gas-vapor mixture exhaust velocity for oxygen, kerosene for two
boundary conditions types are given, using the example of Soyuz-2.1.v type fuel tanks. The total rocket
propellant residues evaporation system design mass is less than 1,3% of the total «dry» worked-off
stage design mass |
| format | Article |
| id | doaj-art-893f5905faf9470694cb60e2a41866ec |
| institution | Kabale University |
| issn | 2588-0373 2587-764X |
| language | English |
| publishDate | 2019-06-01 |
| publisher | Omsk State Technical University, Federal State Autonomous Educational Institution of Higher Education |
| record_format | Article |
| series | Омский научный вестник: Серия "Авиационно-ракетное и энергетическое машиностроение" |
| spelling | doaj-art-893f5905faf9470694cb60e2a41866ec2025-02-02T11:56:31ZengOmsk State Technical University, Federal State Autonomous Educational Institution of Higher EducationОмский научный вестник: Серия "Авиационно-ракетное и энергетическое машиностроение"2588-03732587-764X2019-06-013210311410.25206/2588-0373-2019-3-2-103-114Study of unusable liquid propellant residues evaporation processes parameters in the tanks of launch vehicle worked-off stage in microgravityV. I. Trushlyakov0V. A. Urbansky1Omsk State Technical UniversityOmsk State Technical UniversityA method is proposed for studying the evaporation process of unusable rocket propellant residues in worked-off stage under weightless conditions. Two options are considered as boundary conditions for liquid rocket propellant residues: a) liquid drop distribution in N identical drops, which surface decreases during evaporation and b) the liquid location in the lower tank bottom and the mirror presence, which area decreases during evaporation. A high-temperature stream of hydrogen peroxide decomposition products is used as a heat carrier fed to the fuel tank. The physical and mathematical model of the liquid evaporation process is based on the first thermodynamics law. Based on the analysis of the Frud and Grashof criteria, the assumption that there is no convection movement inside the drop (Rayleigh number is less than critical) for both boundary conditions variants, the heat transfer coefficient of the gas-vapor mixture produced in the tank is determined based on the regression dependence obtained in ground conditions as a function of from the Nusselt, Reynolds, Prandtl numbers. Comparisons of the gasvapor mixture parameters for the considered boundary conditions variants and the proposed physical mathematical model with the results, obtained earlier, for the boundary conditions variant of uniform fluid distribution over the inner tank wall (third boundary conditions variant) and using the boundary layer theory based on integral impulses, energy and diffusion ratios are given. The thermophysical gas-vapor mixture parameters and the gas-vapor mixture exhaust velocity for oxygen, kerosene for two boundary conditions types are given, using the example of Soyuz-2.1.v type fuel tanks. The total rocket propellant residues evaporation system design mass is less than 1,3% of the total «dry» worked-off stage design masshttps://www.omgtu.ru/general_information/media_omgtu/journal_of_omsk_research_journal/files/arhiv/2019/%D0%A2.%203,%20%E2%84%96%202%20(%D0%90%D0%A0%D0%B8%D0%AD%D0%9C)/103-114%20%D0%A2%D1%80%D1%83%D1%88%D0%BB%D1%8F%D0%BA%D0%BE%D0%B2%20%D0%92.%20%D0%98.,%20%D0%A3%D1%80%D0%B1%D0%B0%D0%BD%D1%81%D0%BA%D0%B8%D0%B9%20%D0%92.%20%D0%90..pdfworked-off rocket stageliquid propellant residueshydrogen peroxideheat carrierevaporation |
| spellingShingle | V. I. Trushlyakov V. A. Urbansky Study of unusable liquid propellant residues evaporation processes parameters in the tanks of launch vehicle worked-off stage in microgravity Омский научный вестник: Серия "Авиационно-ракетное и энергетическое машиностроение" worked-off rocket stage liquid propellant residues hydrogen peroxide heat carrier evaporation |
| title | Study of unusable liquid propellant residues evaporation processes parameters in the tanks of launch vehicle worked-off stage in microgravity |
| title_full | Study of unusable liquid propellant residues evaporation processes parameters in the tanks of launch vehicle worked-off stage in microgravity |
| title_fullStr | Study of unusable liquid propellant residues evaporation processes parameters in the tanks of launch vehicle worked-off stage in microgravity |
| title_full_unstemmed | Study of unusable liquid propellant residues evaporation processes parameters in the tanks of launch vehicle worked-off stage in microgravity |
| title_short | Study of unusable liquid propellant residues evaporation processes parameters in the tanks of launch vehicle worked-off stage in microgravity |
| title_sort | study of unusable liquid propellant residues evaporation processes parameters in the tanks of launch vehicle worked off stage in microgravity |
| topic | worked-off rocket stage liquid propellant residues hydrogen peroxide heat carrier evaporation |
| url | https://www.omgtu.ru/general_information/media_omgtu/journal_of_omsk_research_journal/files/arhiv/2019/%D0%A2.%203,%20%E2%84%96%202%20(%D0%90%D0%A0%D0%B8%D0%AD%D0%9C)/103-114%20%D0%A2%D1%80%D1%83%D1%88%D0%BB%D1%8F%D0%BA%D0%BE%D0%B2%20%D0%92.%20%D0%98.,%20%D0%A3%D1%80%D0%B1%D0%B0%D0%BD%D1%81%D0%BA%D0%B8%D0%B9%20%D0%92.%20%D0%90..pdf |
| work_keys_str_mv | AT vitrushlyakov studyofunusableliquidpropellantresiduesevaporationprocessesparametersinthetanksoflaunchvehicleworkedoffstageinmicrogravity AT vaurbansky studyofunusableliquidpropellantresiduesevaporationprocessesparametersinthetanksoflaunchvehicleworkedoffstageinmicrogravity |