Investigation of supersonic jets shock-wave structure

Zapryagaev, V. I.; Gubanov, D. A.; Kavun, I. N.; Kiselev, N. A.; Kundasev, S. G.; Пивоваров, А. А.

doi:10.1063/1.5007516

Cited by 6 publications

(2 citation statements)

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“…To solve the first problem, 3-D viscous gas equations were integrated [5][6][7][8][9][10]. The second problem was solved by integrating the 3-D equations of motion and heat exchange of particles [11][12][13].…”

Section: Resultsmentioning

confidence: 99%

“…When moving away from the landing site of the spacecraft such particles move only under the influence of gravity. Therefore, the flight range was calculated according to the known formula: (8) where g moon is the acceleration of gravity on the Moon, u 0the initial speed, y 0the departure point height, and αthe particle departure angle. When u 0 = 80 m/s and α = 30 the range calculated L s , by the eq.…”

Section: Resultsmentioning

confidence: 99%

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The physical aspects of gas dynamic and thermal physics processes mathematical modelling of descent spacecraft’s

et al. 2019

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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.

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