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The research program aims at analyzing the applicability of hybrid rocket system to mini-satellite-launcher-vehicles. The main objective is to verify the possibility of achieving a substantial cost reduction thanks to the intrinsic capabilities of these propulsion systems. The research program will develop through the following phases: (i) Literature review, (ii)Analysis of combustion stability issues, (iii) analysis of pressurization concepts, (iv) analysis of structural problem of the propellant grain, (v)subscale testing, (vi) Phase A design.
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Engineering - Aerospace engineering
comparative assessment and interview
comparative assessment of qualifications, scientific and professional curriculum, scientific productivity and interview
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