The physical aspects of gas dynamic and thermal physics processes mathematical modelling of descent spacecraft’s
The article discusses the physical aspects and assumptions in the formulation of the gas dynamics and thermal physics models in conditions of “Luna - Resource” spacecraft landing on the Moon surface. It was proposed to divide the problem into two stages: calculation of the gas phase and det...
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VINCA Institute of Nuclear Sciences
2019-01-01
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| Series: | Thermal Science |
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| Online Access: | http://www.doiserbia.nb.rs/img/doi/0354-9836/2019/0354-983619513V .pdf |
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doaj-512585234d714d198f70879ed6ed94be2021-01-02T13:26:49ZengVINCA Institute of Nuclear SciencesThermal Science0354-98362019-01-0123Suppl. 251351810.2298/TSCI19S2513V0354-983619513VThe physical aspects of gas dynamic and thermal physics processes mathematical modelling of descent spacecraft’sVasenin Igor0Glazunov Anatoliy1Shuvarikov Vladimir2Eremin Ivan3Kagenov Anuar4Kostyushin Kirill5Tomsk State University, Tomsk, RussiaTomsk State University, Tomsk, RussiaTomsk State University, Tomsk, RussiaTomsk State University, Tomsk, RussiaTomsk State University, Tomsk, RussiaTomsk State University, Tomsk, RussiaThe article discusses the physical aspects and assumptions in the formulation of the gas dynamics and thermal physics models in conditions of “Luna - Resource” spacecraft landing on the Moon surface. It was proposed to divide the problem into two stages: calculation of the gas phase and determination of trajectories and heating of particles of lunar dust. The use of the continuum equations and not taking into account the reverse effect of particles on gas was substantiated. The calculation results of parameters impingement exhaust jet of spacecraft propulsion system with Moon surface are given. It was obtained that a reverse external force is added to the streamlined surfaces equal to 196 N, the gas temperature at the bottom of the cargo compartment reaches 2000 K, and the calculated heat flux was 400 kW. The trajectories of the particles of lunar dust was determined and it was found that with a size of 1 μm the distance of their flight range was 3.5 km.http://www.doiserbia.nb.rs/img/doi/0354-9836/2019/0354-983619513V .pdfspacecraftvacuum environmentcontinuous mediumsoft landing enginesmoon surfaceparticles of lunar dust |
| collection |
DOAJ |
| language |
English |
| format |
Article |
| sources |
DOAJ |
| author |
Vasenin Igor Glazunov Anatoliy Shuvarikov Vladimir Eremin Ivan Kagenov Anuar Kostyushin Kirill |
| spellingShingle |
Vasenin Igor Glazunov Anatoliy Shuvarikov Vladimir Eremin Ivan Kagenov Anuar Kostyushin Kirill The physical aspects of gas dynamic and thermal physics processes mathematical modelling of descent spacecraft’s Thermal Science spacecraft vacuum environment continuous medium soft landing engines moon surface particles of lunar dust |
| author_facet |
Vasenin Igor Glazunov Anatoliy Shuvarikov Vladimir Eremin Ivan Kagenov Anuar Kostyushin Kirill |
| author_sort |
Vasenin Igor |
| title |
The physical aspects of gas dynamic and thermal physics processes mathematical modelling of descent spacecraft’s |
| title_short |
The physical aspects of gas dynamic and thermal physics processes mathematical modelling of descent spacecraft’s |
| title_full |
The physical aspects of gas dynamic and thermal physics processes mathematical modelling of descent spacecraft’s |
| title_fullStr |
The physical aspects of gas dynamic and thermal physics processes mathematical modelling of descent spacecraft’s |
| title_full_unstemmed |
The physical aspects of gas dynamic and thermal physics processes mathematical modelling of descent spacecraft’s |
| title_sort |
physical aspects of gas dynamic and thermal physics processes mathematical modelling of descent spacecraft’s |
| publisher |
VINCA Institute of Nuclear Sciences |
| series |
Thermal Science |
| issn |
0354-9836 |
| publishDate |
2019-01-01 |
| description |
The article discusses the physical aspects and assumptions in the formulation
of the gas dynamics and thermal physics models in conditions of “Luna -
Resource” spacecraft landing on the Moon surface. It was proposed to divide
the problem into two stages: calculation of the gas phase and determination
of trajectories and heating of particles of lunar dust. The use of the
continuum equations and not taking into account the reverse effect of
particles on gas was substantiated. The calculation results of parameters
impingement exhaust jet of spacecraft propulsion system with Moon surface
are given. It was obtained that a reverse external force is added to the
streamlined surfaces equal to 196 N, the gas temperature at the bottom of
the cargo compartment reaches 2000 K, and the calculated heat flux was 400
kW. The trajectories of the particles of lunar dust was determined and it
was found that with a size of 1 μm the distance of their flight range was
3.5 km. |
| topic |
spacecraft vacuum environment continuous medium soft landing engines moon surface particles of lunar dust |
| url |
http://www.doiserbia.nb.rs/img/doi/0354-9836/2019/0354-983619513V .pdf |
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