Hybrid propulsion for rocket applications shows a large number of advantages with respect to traditional thermochemical propulsion systems, which are: thrust modulation, inherent safety, low cost and environmental friendliness. In order to achieve full exploitation of these beneficial aspects, it is necessary to overcome the main disadvantage of hybrid propulsion: low regression rate. This thesis work has the objective to measure, through an extensive experimental campaign, the average regression rate of innovative fuel formulations for hybrid propulsion. The fuel formulations tested are HTPB and paraffin waxes filled with magnesium hydride. The comparison of such formulations in terms of ballistic performance allows to quantify the relative importance, in terms of specifically propulsive performances, of the main chemical and physical phenomena characterizing the combustion processes of the most advanced fuel formulations (e.g. metal hydrides filling; entrainment effect). An extensive and specific experimental campaign is realized, in order to obtain useful data for analysis and final discussion.
La propulsione aerospaziale di tipo ibrido offre numerosi vantaggi rispetto a sistemi di propulsione termochimica più tradizionale, tra i quali: modulabilità della spinta, sicurezza intrinseca, riduzione dei costi e basso impatto ambientale. Al fine di poter sfruttare appieno questi numerosi aspetti positivi, è necessario superare il principale limite della propulsione ibrida: la bassa velocità di regressione. Il presente lavoro si pone l’obiettivo di misurare, attraverso un’estesa campagna sperimentale, la velocità di regressione media di formulazioni innovative di combustibili per la propusione ibrida. Le formulazioni indagate sono HTPB e cere paraffiniche additivate con idruro di magnesio. Il confronto delle prestazioni balistiche di tali combustibili permette di quantificare il peso relativo, in termini di prestazioni propulsive, di alcuni tra i principali fenomeni chimico/fisici caratterizzanti la combustione delle formulazioni più innovative (additivazione con idruri metallici; effetto dell’entrainment) A tal fine è in atto una specifica ed estesa indagine sperimentale volta a fornire i dati per l’elaborazione ed il confronto critico conclusivo.
Indagine teorica e sperimentale dei processi di combustione eterogenea in endoreattore ibrido
MAZZETTI, ALESSANDRO
2009/2010
Abstract
Hybrid propulsion for rocket applications shows a large number of advantages with respect to traditional thermochemical propulsion systems, which are: thrust modulation, inherent safety, low cost and environmental friendliness. In order to achieve full exploitation of these beneficial aspects, it is necessary to overcome the main disadvantage of hybrid propulsion: low regression rate. This thesis work has the objective to measure, through an extensive experimental campaign, the average regression rate of innovative fuel formulations for hybrid propulsion. The fuel formulations tested are HTPB and paraffin waxes filled with magnesium hydride. The comparison of such formulations in terms of ballistic performance allows to quantify the relative importance, in terms of specifically propulsive performances, of the main chemical and physical phenomena characterizing the combustion processes of the most advanced fuel formulations (e.g. metal hydrides filling; entrainment effect). An extensive and specific experimental campaign is realized, in order to obtain useful data for analysis and final discussion.File | Dimensione | Formato | |
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https://hdl.handle.net/10589/4764