Abstract
In the present paper, the Iranian spacecraft is considered, and is studied from an aero thermo dynamic viewpoint to design the proper thermal protection system, for its first mission: the suborbital flight. The design procedure is based on the decoupling of the aerodynamic heating phenomena and the solid phase heating process. Due to the sub-orbital mission of this spacecraft as a first flight, an elastomeric material is used as an unconventional heat shield to protect the blunt body reentry vehicle. The full Navier-Stokes equations are used for heat-flux estimation during flight, and the one-dimensional equations for an ablative materials are used to design the thermal protection system, according to the structural criteria.
Published Version
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