Lucia Squillari
Thermal Analysis of a Hybrid Rocket Motor's Aft-End.
Rel. Dario Giuseppe Pastrone. Politecnico di Torino, Corso di laurea magistrale in Ingegneria Aerospaziale, 2020
Abstract
In the next years, the space market forecasts un up-swell demand of small satellites which are traditionally delivered as piggyback payloads on rockets commissioned for larger spacecraft. For this kind of launch the primary payload takes priority imposing constraints on secondary payloads that have to be adapted to the launch schedule and orbit. In this scenario, private investors are now demanding for tailored services guaranteeing control over mission requirements, schedule reliability, and affordable launch opportunities to achieve a higher mission performance. Since new cost-effective and dedicated launchers have become mandatory, HyImpulse Technologies GmbH start-up has been founded to pursue the development of a hybrid rocket engine, in cooperation with the German Aerospace Center DLR in Lampoldshausen, in order to advance hybrid launcher technology.
The hybrid system is more reliable, safer to be produced and stored, and ecologically friendlier then its solid or liquid counterpart at a reasonable price if some technological measures are taken to alleviate the combustion inefficiencies and boost the performance
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