A coupled convective and radiative heat transfer of single-nozzle and four-nozzle liquid launch vehicles is presented. Three-dimensional multicomponent Navier–Stokes equations, radiative transfer equations, and realizable turbulence model are used to establish the rocket supersonic plumes flow model with freestream in high altitude. By using the discrete ordinates method and the second-order total variation diminishing upwind scheme and multigrid method, the flow field and the heat flux of the liquid launch vehicle in different typical altitudes are calculated. The accuracy and effectiveness of this established model are verified by comparing with experimental data, and the results show that the radiation heat flux of afterbody becomes smaller with an increase in altitude. The convection heat flux of afterbody increased first and then decreased, and the peak of convection heat flux occurs at 20 and 35 km for single-nozzle and four-nozzle rockets, respectively. The study results provide theoretical significance and engineering guidance for designing the thermal protection system of the afterbody of liquid launch vehicle.
Investigations of Base Thermal Environment on Four-Nozzle Liquid Launch Vehicle at High Altitude
Journal of Spacecraft and Rockets ; 57 , 1 ; 49-57
2019-08-30
9 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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