The increasing number of scientists and space technology designers pay great attention to developing of space crafts (SC) provided with Inflatable Braking Devices (IBD). These SC with IBD are very compact in a transport position and able to deploy additional braking surfaces just before aerobraking phase. In some cases such SC has got advantages over SC with aerodynamic shield of a rigid construction. For example, at present there is no alternative to the Landing Vehicle (LV) with inflatable aerodynamic shield used for landing phase of the Manned Martian Mission (MMM). A design technology of SC with IBD is named as Inflatable Re-Entry and Descent Technology (IRDT).rnIn the paper there are some results of estimation for LV IBD advantage in comparison with another LV variants for MMM landing phase. It's illustrated here the basic LV with IBD construction and the results of trajectory parameters calculation at aerobraking phase for LV of 70 tons mass in Martian atmosphere.rnThe main aim of the paper is to show the possibility to develop the flexible Thermal Protection System (TPS) to protect the gasproof LV IBD envelope able to be packed in a compact volume. Such TPS is to be manufactured from heat-resistant flexible and elastic materials, impregnated with sublimating substance.rnTo provide TPS construction parameters selection there have been calculated convective and radiation flows to the IBD surface at LV aerobraking phase, as well as construction warm-up and TPS mass loss.rnHere are also some suggestions and simplifications for aerothermodynamic calculations as well as recommendations for the furthest developing of the aerothermodynamics research directions at LV IBD TPS designing.
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