Heat and mass exchange on a permeable surface of the system of the thermal protection of the descent vehicle of the spacecraft small form

Аuthors

Fedorchenko E. А., Nikitin P. V.^*

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: petrunecha@gmail.com

Abstract

. Results of the analysis of heat and mass destruction in the surface layer of thermal protection of reentry spacecraft small form committing ballistic descent to Earth. The calculation of trajectory parameters and heat transfer on the surface of the landing of the spacecraft at hypersonic flight segment. According to the calculation results, a series of experiments on high-temperature gas-dynamic stand to determine the thermal protective performance TRV series. Selected material surface layer of a heat of the thermal protection of spacecraft. The estimation of the thickness of the destruction of the layer.

Keywords:

Heat and Mass Transfer, hypersonic speed, thermal protection, orbital parameters, the enthalpy of inhibition, orbital flight, ballistic descent, gas-dynamic stand

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