PORTO @ 
Archivio Istituzionale della Ricerca
IRIS è la soluzione IT che facilita la raccolta e la gestione dei dati relativi alle attività e ai prodotti della ricerca. Fornisce a ricercatori, amministratori e valutatori gli strumenti per monitorare i risultati della ricerca, aumentarne la visibilità e allocare in modo efficace le risorse disponibili.
EnglishA nested direct/indirect method is used to find the optimal design of a microgravity platform which consists of a hybrid sounding rocket that uses a self-pressurizing oxidizer, namely, nitrous oxide. The direct optimization of the parameters that affect the engine design is coupled with the trajectory indirect optimization to maximize a given mission performance index. Different models can be used to describe the self-pressurizing behavior of the oxidizer in the tank. The simplest model assumes liquid/vapor equilibrium. A two-phase model is also proposed: saturated vapor and superheated liquid are considered and the liquid/vapor mass transfer is evaluated making reference to the liquid spinodal line. Results show that the different models have a limited impact in the optimal engine characteristics. The performance are slightly modified due to the different mass of the residual oxidizer. A performance comparison with different propellant combinations is also shown.
Optimal design of hybrid rockets with self-pressurising oxidizer / Casalino, L.; Pastrone, D.. - 3:(2006), pp. 1923-1932. ((Intervento presentato al convegno AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference tenutosi a Sacramento, CA, usa nel 2006.
| Titolo: | Optimal design of hybrid rockets with self-pressurising oxidizer | |
| Autori: | ||
| Data di pubblicazione: | 2006 | |
| Abstract: | A nested direct/indirect method is used to find the optimal design of a microgravity platform whi...ch consists of a hybrid sounding rocket that uses a self-pressurizing oxidizer, namely, nitrous oxide. The direct optimization of the parameters that affect the engine design is coupled with the trajectory indirect optimization to maximize a given mission performance index. Different models can be used to describe the self-pressurizing behavior of the oxidizer in the tank. The simplest model assumes liquid/vapor equilibrium. A two-phase model is also proposed: saturated vapor and superheated liquid are considered and the liquid/vapor mass transfer is evaluated making reference to the liquid spinodal line. Results show that the different models have a limited impact in the optimal engine characteristics. The performance are slightly modified due to the different mass of the residual oxidizer. A performance comparison with different propellant combinations is also shown. | |
| Appare nelle tipologie: | 4.1 Contributo in Atti di convegno |
File in questo prodotto:
http://hdl.handle.net/11583/2922432
Copyright © 2022