A great amount of research is going on in the field of aerospace vehicles for improved access to space for higher altitude operations as well as high speed aircraft. The current mantra in the field of rocket propulsion is “THE FUTURE IS GREEN”. Liquid oxygen and methane are often regarded as new promising green propellant components. As we know from BE-4 engines for future launchers is going to be a replacement of RD-180 Russian engine. In the past decade the use of vehicles (including commercial aircrafts) has increased to a substantial extent. Due to such a large scale use of combustion engines, pollution related concerns are escalating. Many countries have started putting rigorous restrictions on emission related regulations. Therefore a need for an accurate prediction of liquid spray penetration and vapor evolution has arised because the efficiency of the combustion is directly affected by the fuel atomization quality and fuel-air mixing. Therefore, this work is a literature review of papers which tends to the fate of flight test for the American space program. This thesis aims to do a comparative analysis of methane, kerosene, and hydrogen as rocket fuel combined with liquid oxygen using NASA CEA code. Therefore, this work is a literature review of papers which tends to the fate of flight test for the American space program. We considered papers which in details discuss mixed propulsion cycles. Based on this background, this study focuses on the tradeoff of kerosene and methane as booster propellants. The evaluation is thereby made on the launch-vehicle system level. Calculations are based on an Ariane 5 model case; the results are however of general nature and can be applied to other launcher configurations.
È in corso una grande quantità di ricerca nel campo dei veicoli aerospaziali per migliorare l'accesso allo spazio per operazioni ad alta quota e velivoli ad alta velocità. Il mantra attuale nel campo della propulsione a razzo è "IL FUTURO È VERDE". L'ossigeno liquido e il metano sono spesso considerati nuovi promettenti componenti del propellente verde. Come sappiamo dai motori BE-4 per i futuri lanciatori, sostituiranno il motore russo RD-180. Nell'ultimo decennio l'uso dei veicoli (compresi gli aerei commerciali) è aumentato in misura sostanziale. A causa di un uso su larga scala di motori a combustione, le preoccupazioni relative all'inquinamento stanno aumentando. Molti paesi hanno iniziato a imporre rigorose restrizioni alle normative relative alle emissioni. Pertanto è emersa la necessità di una previsione accurata della penetrazione del liquido nebulizzato e dell'evoluzione del vapore poiché l'efficienza della combustione è direttamente influenzata dalla qualità dell'atomizzazione del combustibile e dalla miscelazione aria-combustibile. Pertanto, questo lavoro è una revisione della letteratura di documenti propedeutica al test di volo per il programma spaziale americano. La tesi mira a fare un'analisi comparativa di metano, cherosene e idrogeno come combustibile per missili combinato con ossigeno liquido utilizzando il codice CEA della NASA. Sono presi in considerazione articoli che trattano in dettaglio i cicli di propulsione mista. Sulla base di questo background, lo studio si concentra sul compromesso tra cherosene e metano come propellenti per i booster. La valutazione viene quindi effettuata a livello di sistema del veicolo di lancio. I calcoli condotti si basano su un caso di riferimento, identificato nel lanciatore europeo Ariane 5; i risultati sono comunque di carattere generale e possono essere applicati ad altre configurazioni di lanciatore.
A Methan engine for an improved access to space
JONNALAGADDA, ABHINAV KUMAR
2021/2022
Abstract
A great amount of research is going on in the field of aerospace vehicles for improved access to space for higher altitude operations as well as high speed aircraft. The current mantra in the field of rocket propulsion is “THE FUTURE IS GREEN”. Liquid oxygen and methane are often regarded as new promising green propellant components. As we know from BE-4 engines for future launchers is going to be a replacement of RD-180 Russian engine. In the past decade the use of vehicles (including commercial aircrafts) has increased to a substantial extent. Due to such a large scale use of combustion engines, pollution related concerns are escalating. Many countries have started putting rigorous restrictions on emission related regulations. Therefore a need for an accurate prediction of liquid spray penetration and vapor evolution has arised because the efficiency of the combustion is directly affected by the fuel atomization quality and fuel-air mixing. Therefore, this work is a literature review of papers which tends to the fate of flight test for the American space program. This thesis aims to do a comparative analysis of methane, kerosene, and hydrogen as rocket fuel combined with liquid oxygen using NASA CEA code. Therefore, this work is a literature review of papers which tends to the fate of flight test for the American space program. We considered papers which in details discuss mixed propulsion cycles. Based on this background, this study focuses on the tradeoff of kerosene and methane as booster propellants. The evaluation is thereby made on the launch-vehicle system level. Calculations are based on an Ariane 5 model case; the results are however of general nature and can be applied to other launcher configurations.| File | Dimensione | Formato | |
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https://hdl.handle.net/10589/201757