Study of the viability of a nuclear thermal thruster as a space propulsion system for interplanetary missions
In this thesis, a comprehensive technical analysis and viability assessment of nuclear space propulsion technologies as transformative solutions for advancing solar system exploration is presented. Beginning with an examination of the fundamental limitations of chemical propulsion and the physical p...
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| Tipo de recurso: | tesis de maestría |
| Fecha de publicación: | 2025 |
| 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:2117/455104 |
| Acceso en línea: | https://hdl.handle.net/2117/455104 |
| Access Level: | acceso abierto |
| Palabra clave: | Space vehicles--Propulsion systems Nuclear propulsion Interplanetary voyages Nuclear thermal propulsion Interplanetary propulsion systems Specific impulse Mars mission propulsion NERVA Radiation shielding Thrust-to-weight ratio Vehicles espacials--Sistemes de propulsió Propulsió nuclear Viatges interplanetaris Àrees temàtiques de la UPC::Aeronàutica i espai::Sistemes de propulsió |
| Sumario: | In this thesis, a comprehensive technical analysis and viability assessment of nuclear space propulsion technologies as transformative solutions for advancing solar system exploration is presented. Beginning with an examination of the fundamental limitations of chemical propulsion and the physical principles underlying the application of nuclear energy in space, the theoretical performance boundaries and historical development trajectory of nuclear propulsion systems are established. Nuclear thermal propulsion architectures are systematically evaluated, including solid-core reactors, particle bed designs, innovative CERMET and MITEE fuels, gas core concepts, and Rubbia’s accelerator-driven engine. For each system, performance parameters, material constraints, and engineering challenges are quantified. A parallel investigation of nuclear electric propulsion is also conducted, encompassing arcjet systems, electrostatic ion thrusters, magnetoplasmadynamic (MPD) devices, VASIMR technology, and hybrid thermal-electric configurations, with particular attention given to plasma dynamics and power conversion efficiencies. Through comparative analysis, it is demonstrated that specific impulse values of 850–1,200 seconds with thrust-to-weight ratios of 3:1 to 20:1 are achieved by nuclear thermal systems, enabling reductions in Mars transit time of 30–50% compared to chemical propulsion. Nuclear electric systems, though characterized by substantially lower thrust, can achieve very high specific impulse values, offering optimal performance for deep space scientific missions where extended operational durations are acceptable. It is further demonstrated through mission analysis that ambitious exploration objectives are uniquely enabled by nuclear systems, including crewed Mars missions, outer planets exploration, and potential planetary defense applications. Risk assessment methodologies, regulatory frameworks, public perception challenges, and strategic international collaboration models necessary for nuclear propulsion development are also addressed by the research. It is concluded that despite technical complexity and policy challenges, nuclear propulsion represents the only viable approach for ambitious solar system exploration within reasonable time frames and budgets. It is a technology with the potential to transform humanity’s capabilities for space exploration, while necessitating thoughtful international cooperation and regulatory adaptation. |
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