Drozdov S.M., Brazhko V.N., Davletkildeev R.A., Fedorov D.S., Shemetov I.M.

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018_640799

Results of experimental investigation of stationary aerodynamic characteristics and heat flux distribution on the surface of DM-18 descent module of “ExoMars” project at hypersonic flow regimes are presented. The studies were initiated by a contract with FSUE “НПО им. С.А. Лавочкина” in framework of a collaboration program with the European Space Agency. To fulfill scientific goals of “ExoMars” project, delivery of DM-18 descent module with a payload on the surface of planet Mars is planned. The aim of this study was to determine aerodynamic characteristics and heat flux distribution on the surface of DM-18 descent module at hypersonic Mach numbers for calculating the module’s descent trajectory in the Martian atmosphere. To carry out the assigned tasks, a model of DM-18 module for balance tests and a model for heat transfer tests were manufactured at TsAGI and tested in T-117 wind tunnel at Mach numbers of М=[7.5, 10.5, 14]. Aerodynamic force and moment coefficients were determined at a range of angles of attack a=[0¸25°]. Interferometric visualization of the flow past the model was obtained. Simultaneously with balance tests, surface streamlines visualization on the model was performed. Distribution of heat flux was obtained by melting paint method and by surface thermocouples at angles of attack a=[0, 10°]. Comparative analysis of calculated and experimental data was also carried out, and aerodynamic characteristics of DM-18 module in full-scale flight conditions in the Martian atmosphere were estimated.

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In Categories: High-Speed Missions and Vehicles, HiSST 2018, Hypersonic Aerodynamics, Testing and Evaluation, Thermal and Energy Management Systems, Thermal Protection Systems
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