Study of a nuclear thermal thruster for interplanetary manned missions
This study delves into the development and analysis of nuclear space propulsion systems for future missions, drawing valuable insights from past experiences and the historical context of these systems. Nuclear Thermal Propulsion (NTP) emerges as a promising option, offering several advantages over a...
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| Tipo de recurso: | tesis de maestría |
| Fecha de publicación: | 2023 |
| País: | España |
| Institución: | Universitat Politècnica de Catalunya (UPC) |
| Repositorio: | UPCommons. Portal del coneixement obert de la UPC |
| Idioma: | inglés |
| OAI Identifier: | oai:upcommons.upc.edu:2117/398133 |
| Acceso en línea: | https://hdl.handle.net/2117/398133 |
| Access Level: | acceso abierto |
| Palabra clave: | Propulsió nuclear Space vehicles--Propulsion systems Manned space flight Vehicles espacials--Sistemes de propulsió Vol espacial tripulat Àrees temàtiques de la UPC::Aeronàutica i espai::Sistemes de propulsió |
| Sumario: | This study delves into the development and analysis of nuclear space propulsion systems for future missions, drawing valuable insights from past experiences and the historical context of these systems. Nuclear Thermal Propulsion (NTP) emerges as a promising option, offering several advantages over alternative propulsion systems, such as reduced propellant mass per payload and the potential for shorter travel times to Mars and near-Earth objects. The extensive research conducted demonstrates that NTP engines possess key attributes, including energy efficiency, high specific impulse, and extended operational capabilities, making them particularly well-suited for Mars missions. Furthermore, the study places emphasis on the meticulous selection of materials for the primary components of the NTP system. Factors such as high-temperature strength, corrosion resistance, and pressure resistance are carefully considered in this analysis, ensuring the optimal performance and reliability of the system. Besides, in order to compute the maneuver and the mission to Mars, it is necessary compute the specific impulse ��� of the engine. Therefore, to ascertain the most accurate approach for calculating specific impulse (���), two methodologies, Chemical Equilibrium and Frozen Composition, are compared using the CEARUN software. The results highlight the distinct characteristics of each method, with Chemical Equilibrium assuming certain properties and Frozen Composition incorporating various factors, leading to variations in the calculated ���. Once the ��� is selected, the mission to Mars is carefully modelled and analyzed utilizing computational tools such as MATLAB. This comprehensive analysis encompasses diverse propulsion maneuvers and trajectory optimization, shedding light on the potential benefits and considerations associated with the implementation of NTP systems in space missions. In conclusion, NTP systems have the inherent capacity to significantly reduce travel durations in space missions owing to their augmented thrust capability and high specific impulse, ultimately resulting in a more efficient utilization of propellant. However, it is important to underscore that fully harnessing the benefits of NTP systems in future space missions necessitates further research and optimization efforts. By continuously exploring and refining these systems, it is possible unlock their full potential and propel humanity towards new frontiers in space exploration. |
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