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...

Full description

Bibliographic Details
Author: Carmona Sánchez, Adrián
Format: master thesis
Publication Date:2023
Country:España
Institution:Universitat Politècnica de Catalunya (UPC)
Repository:UPCommons. Portal del coneixement obert de la UPC
Language:English
OAI Identifier:oai:upcommons.upc.edu:2117/398133
Online Access:https://hdl.handle.net/2117/398133
Access Level:Open access
Keyword: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
id ES_5b0b6022a452a0bc5fc20fe563ec6d45
oai_identifier_str oai:upcommons.upc.edu:2117/398133
network_acronym_str ES
network_name_str España
repository_id_str
spelling Study of a nuclear thermal thruster for interplanetary manned missionsCarmona Sánchez, AdriánPropulsió nuclearSpace vehicles--Propulsion systemsManned space flightPropulsió nuclearVehicles espacials--Sistemes de propulsióVol espacial tripulatÀrees temàtiques de la UPC::Aeronàutica i espai::Sistemes de propulsióThis 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.Universitat Politècnica de CatalunyaLizandra Dalmases, José OriolTejedor Herrán, Blanca20232023-07-1320232023-12-15master thesishttp://purl.org/coar/resource_type/c_bdccNAhttp://purl.org/coar/version/c_be7fb7dd8ff6fe43info:eu-repo/semantics/masterThesisapplication/pdfhttps://hdl.handle.net/2117/398133reponame:UPCommons. Portal del coneixement obert de la UPCinstname:Universitat Politècnica de Catalunya (UPC)Inglésengopen accesshttp://purl.org/coar/access_right/c_abf2Attribution 4.0 Internationalhttp://creativecommons.org/licenses/by/4.0/info:eu-repo/semantics/openAccessoai:upcommons.upc.edu:2117/3981332026-05-27T15:37:01Z
dc.title.none.fl_str_mv Study of a nuclear thermal thruster for interplanetary manned missions
title Study of a nuclear thermal thruster for interplanetary manned missions
spellingShingle Study of a nuclear thermal thruster for interplanetary manned missions
Carmona Sánchez, Adrián
Propulsió nuclear
Space vehicles--Propulsion systems
Manned space flight
Propulsió nuclear
Vehicles espacials--Sistemes de propulsió
Vol espacial tripulat
Àrees temàtiques de la UPC::Aeronàutica i espai::Sistemes de propulsió
title_short Study of a nuclear thermal thruster for interplanetary manned missions
title_full Study of a nuclear thermal thruster for interplanetary manned missions
title_fullStr Study of a nuclear thermal thruster for interplanetary manned missions
title_full_unstemmed Study of a nuclear thermal thruster for interplanetary manned missions
title_sort Study of a nuclear thermal thruster for interplanetary manned missions
dc.creator.none.fl_str_mv Carmona Sánchez, Adrián
author Carmona Sánchez, Adrián
author_facet Carmona Sánchez, Adrián
author_role author
dc.contributor.none.fl_str_mv Lizandra Dalmases, José Oriol
Tejedor Herrán, Blanca
dc.subject.none.fl_str_mv Propulsió nuclear
Space vehicles--Propulsion systems
Manned space flight
Propulsió nuclear
Vehicles espacials--Sistemes de propulsió
Vol espacial tripulat
Àrees temàtiques de la UPC::Aeronàutica i espai::Sistemes de propulsió
topic Propulsió nuclear
Space vehicles--Propulsion systems
Manned space flight
Propulsió nuclear
Vehicles espacials--Sistemes de propulsió
Vol espacial tripulat
Àrees temàtiques de la UPC::Aeronàutica i espai::Sistemes de propulsió
description 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.
publishDate 2023
dc.date.none.fl_str_mv 2023
2023-07-13
2023
2023-12-15
dc.type.none.fl_str_mv master thesis
http://purl.org/coar/resource_type/c_bdcc
NA
http://purl.org/coar/version/c_be7fb7dd8ff6fe43
dc.type.openaire.fl_str_mv info:eu-repo/semantics/masterThesis
format masterThesis
dc.identifier.none.fl_str_mv https://hdl.handle.net/2117/398133
url https://hdl.handle.net/2117/398133
dc.language.none.fl_str_mv Inglés
eng
language_invalid_str_mv Inglés
language eng
dc.rights.none.fl_str_mv open access
http://purl.org/coar/access_right/c_abf2
Attribution 4.0 International
http://creativecommons.org/licenses/by/4.0/
dc.rights.openaire.fl_str_mv info:eu-repo/semantics/openAccess
rights_invalid_str_mv open access
http://purl.org/coar/access_right/c_abf2
Attribution 4.0 International
http://creativecommons.org/licenses/by/4.0/
eu_rights_str_mv openAccess
dc.format.none.fl_str_mv application/pdf
dc.publisher.none.fl_str_mv Universitat Politècnica de Catalunya
publisher.none.fl_str_mv Universitat Politècnica de Catalunya
dc.source.none.fl_str_mv reponame:UPCommons. Portal del coneixement obert de la UPC
instname:Universitat Politècnica de Catalunya (UPC)
instname_str Universitat Politècnica de Catalunya (UPC)
reponame_str UPCommons. Portal del coneixement obert de la UPC
collection UPCommons. Portal del coneixement obert de la UPC
repository.name.fl_str_mv
repository.mail.fl_str_mv
_version_ 1869408767188140032
score 15,300724

Similar Items