Study of large multistage rockets for HEO missions
| Autor: | Marín Sotil, Elías |
|---|---|
| Přispěvatelé: | Lizandra Dalmases, José Oriol, Universitat Politècnica de Catalunya. Departament de Física |
| Jazyk: | angličtina |
| Rok vydání: | 2022 |
| Předmět: | |
| Zdroj: | UPCommons. Portal del coneixement obert de la UPC Universitat Politècnica de Catalunya (UPC) |
| Popis: | This thesis presents a study on super heavy two-stage rockets targeting high Earth orbit, focusing on geostationary and lunar transfer orbits. The work has been done under the supervision of UPC professor Josep Oriol Lizandra since December 2021 to June 2022. The first part, presents the most important theoretical concepts necessary to develop the study. This includes nozzle ideal theory, rocket 2D flight equations, as well as the most common ascent flight strategies. In addition, some essential rocket design guidelines such as the optimum number of stages and propellant types are introduced. This part also explains the different existing engine cycles in terms of turbopump arranging and propellant combinations. In the second part, first of all, the mission is defined and characterised by considering two particular destinations (GEO and the Moon) and setting a general ascent strategy. This strategy consists of using the gravity turn to reach a low circular parking orbit and then perform a second burn to reach HEO. Thereafter, rocket configuration is studied, thus the oxidiser and fuel are selected, the number of engines is set and the general vehicle shape is defined. Then, the engines are preliminary designed using a perfect gas model and based on the SpaceX Raptor engine. A MatLab code has been developed to simulate engine performance and rocket flight, allowing to set the most advantageous nozzle area ratio. The code has allowed to simulate rocket ascent and study the optimal trajectory using the gravity turn. For this purpose, the indicated magnitude of the pitching manoeuvre is sought, which allows gravity to begin to curve the trajectory and the parking orbit reached to be as circular as possible. Afterwards the code has been modified to optimise rocket characteristics. Most of the study is based on SpaceX Starship rocket, which has been taken as reference, nevertheless the thrust to weight ratio and the propellant ratio between the two stages have been varied. The analysis of these two parameters has allowed to see their affect in rocket dimensions and payload performance. Furthermore, it has allowed to define an optimal configuration to HEO and LEO (regarding cargo capability). Moreover, an interview with MIT professor Manuel Martínez-Sánchez has been conducted, which provides information about ideal flow models in nozzles, the role of super-heavy rockets in the space sector and the future of the different Earth orbits. |
| Databáze: | OpenAIRE |
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