Low Cost Catalysts for Hydrazine Monopropellant Thrusters

Neto, G. Soares; Zacharias, M.; Palandi, Jalusa A. L.

doi:10.2514/6.2009-5232

Cited by 7 publications

(6 citation statements)

References 4 publications

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“…It is considered the most successful hydrazine decomposition catalyst to date thus; similar catalyst is considered in this study. Cost decreasing of hydrazine catalyst is one of the most important objectives in catalysts research nowadays [13,14]. For more information readers are referred to [2,15].…”

Section: Thruster Subsystem Modelingmentioning

confidence: 99%

Multidisciplinary Design Optimization and Analysis of Hydrazine Monopropellant Propulsion System

Adami

Mortazavi

Nosratollahi

et al. 2015

International Journal of Aerospace Engineering

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Monopropellant propulsion systems are widely used especially for low cost attitude control or orbit correction (orbit maintenance). To optimize the total propulsion system, subsystems should be optimized. Chemical decomposition, aerothermodynamics, and structure disciplines demand different optimum condition such as tank pressure, catalyst bed length and diameter, catalyst bed pressure, and nozzle geometry. Subsystem conflicts can be solved by multidisciplinary design optimization (MDO) technique with simultaneous optimization of all subsystems with respect to any criteria and limitations. In this paper, monopropellant propulsion system design algorithm is presented and the results of the proposed algorithm are validated. Then, multidisciplinary design optimization of hydrazine propulsion system is proposed. The goal of optimization can be selected as minimizing the total mass (including propellant), minimizing the propellant mass (maximizing the Isp), or minimizing the dry mass. Minimum total mass, minimum propellant mass, and minimum dry mass are derived using MDO technique. It is shown that minimum total mass, minimum dry mass, and minimum propellant mass take place in different conditions. The optimum parameters include bed-loading, inlet pressure, mass flow, nozzle geometry, catalyst bed length and diameter, propellant tank mass, specific impulse (Isp), and feeding mass which are derived using genetic algorithm (GA).

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Section: Thruster Subsystem Modelingmentioning

confidence: 99%

Multidisciplinary Design Optimization and Analysis of Hydrazine Monopropellant Propulsion System

Adami

Mortazavi

Nosratollahi

et al. 2015

International Journal of Aerospace Engineering

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“…Low cost catalysts were tested in 1 N, 35 N, and 400 N hydrazine thrusters 19 . Schmitz describes the qualification test sequence for a long life monopropellant thruster for a satellite reaction control system 20 .…”

Section: Introductionmentioning

confidence: 99%

Propellant Grade Hydrazine in Mono/Bi-propellant Thrusters: Preparation and Performance Evaluation

Krishnamachary¹,

Mohan²,

Kulkarni³

et al. 2015

DSJ

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Propellant grade hydrazine was prepared with 64 per cent yield and 95.5 per cent purity. Purity of the propellant grade hydrazine was determined using wet chemical, gas chromatographic (GC) and eudiometric methods. It was observed that the compositions containing blends of hydrazine-methyl alcohol-ammonium nitrate and hydrazine-methyl alcohol-ammonium perchlorate were not found to be frozen even after cooling to -65 °C for 30 minutes. Mono and bi-propellant thrusters were designed and developed to demonstrate the performance of prepared propellant grade hydrazine as a promising rocket fuel. Five static tests with 22 N thruster and one static test with 1 N thruster were performed successfully in mono-propellant mode. The hurdles of chamber pressure oscillations were overcome by compact packing of the catalyst. The desired decomposition and chamber pressure were achieved. One static test was performed successfully with 60 N bi-propellant thruster. The desired chamber pressure and thrust were achieved. The combustion was smooth and C* achieved was higher than that of UH-25, N 2 O 4 combination. The performance of prepared propellant grade hydrazine shows it as a promising rocket fuels.

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“…O ciclo de vida e os requisitos de empuxo dos propulsores a monopropelente dependem fortemente da missão à qual eles são destinados. As duas principais aplicações para este tipo de propulsores são: em sistemas de controle de atitude de satélites e plataformas espaciais e em sistemas de controle de rolamento de estágios superiores de veículos lançadores de satélites (HINCKEL et al, 2009).…”

Section: Propelente Hidrazinaunclassified

“…Propulsores utilizados em sistemas de controle de rolamento são projetados para apresentar altos valores de empuxo, porém durante tempos de acionamentos curtos, de aproximadamente 600 segundos, englobando acionamentos pulsados de curta duração e acionamentos contínuos de até um minuto (HINCKEL et al, 2009).…”

Section: Propelente Hidrazinaunclassified

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Materiais baseados em óxidos de nióbio e alumínio utilizados como suportes para catalisadores destinados à propulsão de satélites

Soares¹

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Materiais baseados em óxidos de nióbio e alumínio utilizados como suportes para catalisadores destinados à propulsão de satélites Lorena -SP 2017 MÁRCIO STEINMETZ SOARES Materiais baseados em óxidos de nióbio e alumínio utilizados como suportes para catalisadores destinados à propulsão de satélites Versão reimpressa e corrigida Lorena -SP Março, 2017 Dedico este trabalha aos meus pais, que foram o meu porto seguro ao longo desta jornada e ao meu filho Vítor pela alegria e carinho dados. AGRADECIMENTOS Ao Prof. Dr. Sebastião Ribeiro pela disponibilidade em me orientar e por todo o suporte dispensado a mim ao longo desse trabalho.Ao Dr. José Augusto pela oportunidade de co-orientação, sem a qual não seria possível a concretização deste sonho e que juntamente com o Dr. Gilberto Marques da Cruz contribuíram para a minha formação científica e intelectual através das discussões, sugestões e ensinamentos durante todo esse tempo de convivência.A toda a equipe técnica do Laboratório Associado de Combustão e Propulsão (LCP/INPE) em especial ao Pedro, a Priscila e a Odaize pelos ensinamentos compartilhados, por toda a ajuda e apoio nas análises realizadas neste trabalho e principalmente pelo agradável convívio durante este tempo.A toda a equipe do Banco de Testes com Simulação de Altitude (BTSA/INPE) pelos testes em micropropulsor, em especial ao seu chefe Dr. Agnaldo Martins Serra Junior, e as membros de sua equipe ao Álvaro, ao Jeferson e ao Marcelo pelo apoio durante e após a realização dos testes em propulsão.Ao Prof. Gérald Djéga-Mariadassou pelas valiosas informações e agradáveis dias de discussão e aprendizagem.

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Low Cost Catalysts for Hydrazine Monopropellant Thrusters

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Cited by 7 publications

References 4 publications

Multidisciplinary Design Optimization and Analysis of Hydrazine Monopropellant Propulsion System

Multidisciplinary Design Optimization and Analysis of Hydrazine Monopropellant Propulsion System

Propellant Grade Hydrazine in Mono/Bi-propellant Thrusters: Preparation and Performance Evaluation

Materiais baseados em óxidos de nióbio e alumínio utilizados como suportes para catalisadores destinados à propulsão de satélites

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