Degree thesis work carried out during six months spent in Siberia in collaboration with the Omsk State Technical University, in the aerospace department. The thesis report describes the preliminary draft of a propulsion system capable of putting into orbit a satellite and, after the completion of the mission, reach a decay orbit of 25 years lifetime, as required by NASA regulations, relating to the program of reduction of space debris orbiting in LEO band. Two Russian companies have applied for designing the propulsion system for their satellites, for a total of four missions. Launch of a microsatellite and a nanosatellites from the last stage of the Soyuz space launcher, the launch of two other nanosatellites from the third stage of the same. Satellites used for telecommunications and scientific research, to be injected on sun-synchronous orbits, radius of 700-850 km. It was decided to chemical propulsion systems, in particular, hydrogen peroxide monopropellant engines, at high concentration, for the nanosatellites while a hybrid rocket of new concept, developed by the Surrey Space Centre, for the microsatellite. The hybrid engine in question, Vortex Flow Pancake Hybrid Engine, has a new geometry of the combustion chamber, consisting of two disks of solid fuel separated by a small gap in which the oxidizer is injected tangentially. This involves the creation of a vortex combustion, that has shown to provide very efficient combustion, close to 100\%. This project has assessed the feasibility of using solid fuel made from HTPB with nanoaluminum powder and hydrogen peroxide as oxidizer and, through a study of the thermochemical variables in the combustion chamber and nozzle, carried out by the CEA software, provided by NASA, were obtained theoretical values of specific impulse around 317s and thrust up to 187 N. While for the monopropellant engines, specific impulse of between 126 s and 172 s, depending on the type of mission to be fulfilled.
Lavoro di tesi di laurea specialistica eseguito durante sei mesi trascorsi in Siberia in collaborazione con l'università Tecnica Statale di Omsk, presso il dipartimento aerospaziale. La relazione di tesi descrive il progetto preliminare di un sistema propulsivo in grado di effettuare la messa in orbita di un satellite e, conclusa la missione, l'uscita dalla stessa tramite raggiungimento di un orbita di decadimento di 25 anni di vita, come prescritto dalle normative NASA, relative al programma di riduzione dei detriti spaziali orbitanti nella fascia LEO. Due aziende russe hanno richiesto la progettazione di tale sistema propulsivo per i loro satelliti, per un totale di quattro missioni. Lancio di un microsatellite e di un nanosatellite dall'ultimo stadio del lanciatore spaziale Soyuz, lancio di altri due nanosatelliti dal terzo stadio dello stesso. Satelliti adibiti a ricerca scientifica e telecomunicazioni, da iniettare su orbite sun-synchronous, raggi di 700-850 km. Scelta di sistemi a propulsione chimica, motori monopropellente liquido a perossido di idrogeno, a elevata concentrazione, per i nanosatelliti mentre un motore ibrido di nuova concezione, sviluppato dal Surrey Space Centre, per il microsatellite. Il motore ibrido in questione, Vortex Flow Pancake Hybrid Engine, presenta una nuova geometria della camera di combustione, costituita da due dischi di combustibile solido separati da un piccolo spazio in cui l'ossidante viene iniettato tangenzialmente. Questo comporta la nascita di un vortice di combustione che ha dimostrato fornire un'efficienza molto prossima al 100\%. Questo progetto ha valutato la possibilità di utilizzare combustibile solido a base di HTPB alluminizzato con nano alluminio e perossido di idrogeno come ossidante e, attraverso uno studio delle variabili termochimiche in camera di combustione e ugello, effettuate tramite il software CEA, fornito dalla NASA, sono stati ottenuti valori teorici di impulso specifico intorno a 317 s e spinte fino a 187 N. Mentre per i motori monopropellente, impulsi specifici compresi tra i 126 e i 172 s, in relazione al tipo di missione che devono soddisfare.
Preliminary design of rocket engines for nanosatellites and microsatellites launched by Soyuz space vector
TADINI, PIETRO
2009/2010
Abstract
Degree thesis work carried out during six months spent in Siberia in collaboration with the Omsk State Technical University, in the aerospace department. The thesis report describes the preliminary draft of a propulsion system capable of putting into orbit a satellite and, after the completion of the mission, reach a decay orbit of 25 years lifetime, as required by NASA regulations, relating to the program of reduction of space debris orbiting in LEO band. Two Russian companies have applied for designing the propulsion system for their satellites, for a total of four missions. Launch of a microsatellite and a nanosatellites from the last stage of the Soyuz space launcher, the launch of two other nanosatellites from the third stage of the same. Satellites used for telecommunications and scientific research, to be injected on sun-synchronous orbits, radius of 700-850 km. It was decided to chemical propulsion systems, in particular, hydrogen peroxide monopropellant engines, at high concentration, for the nanosatellites while a hybrid rocket of new concept, developed by the Surrey Space Centre, for the microsatellite. The hybrid engine in question, Vortex Flow Pancake Hybrid Engine, has a new geometry of the combustion chamber, consisting of two disks of solid fuel separated by a small gap in which the oxidizer is injected tangentially. This involves the creation of a vortex combustion, that has shown to provide very efficient combustion, close to 100\%. This project has assessed the feasibility of using solid fuel made from HTPB with nanoaluminum powder and hydrogen peroxide as oxidizer and, through a study of the thermochemical variables in the combustion chamber and nozzle, carried out by the CEA software, provided by NASA, were obtained theoretical values of specific impulse around 317s and thrust up to 187 N. While for the monopropellant engines, specific impulse of between 126 s and 172 s, depending on the type of mission to be fulfilled.| File | Dimensione | Formato | |
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2010_12_Tadini.pdf
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Descrizione: Testo della tesi
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https://hdl.handle.net/10589/8961