An innovate re-entry power system is proposed for development which collects the re-entry energy for a vehicle/module entering the atmosphere for LEO using an MHD power generator that is configured on the exterior surface of the vehicle nose to utilize the heated air sheath as the plasma for promoting the MHD power process. The MHD power produced is collect in an internal energy storage system that will dispense the energy to a deployable pod for a subsequent lower atmosphere tactical flight mission. Phase I will assess and qualify the MHD power system which has been pre-defined from earlier work for this specific re-entry tactical mission application. Phase I will also perform engineering and trade studies on energy storage technologies to down select a single technology or multiple technologies in combination which best suits the tactical mission requirements of minimum size and weight and high specific energy. Phase I will conclude a preliminary overall power system concept inclusive of defining its integration into a standard re-entry vehicle fairing. The results of Phase I will be assembled to provide direction for a Phase II follow-on focused at research and development of the overall power system including definition of need system laboratory demonstrations.
Keywords: Magnetohydrodynamics, Air Plasmas, Mhd Power Systems, Re-Entry, Energy Storage Systems, Space
