Hybrid Rocket
Mostrando 1-12 de 15 artigos, teses e dissertações.
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1. PROPRIEDADES DE PROTEÇÃO TÉRMICA DO CARBETO DE SILÍCIO EM REVESTIMENTOS CERÂMICOS
In recent years, research on the development of protective materials has expanded significantly in order to find efficient and economically viable solutions for application in various industrial segments. Among these materials, those aimed at protecting metallic substrates against high temperatures that end up causing corrosive processes, stand out due to th
Quím. Nova. Publicado em: 2021-01
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2. A Reliable Method for Predicting the Specific Impulse of Chemical Propellants
ABSTRACT The specific impulse (Isp) is an important performance parameter that describes energy efficiency of propellant combustion and is intimately related to the rocket engine thrust. In this study, it was possible by using only two variables, i.e., the heat of reaction (Q) and the number of moles of gaseous reaction products per gram of propellant (Ng) c
J. Aerosp. Technol. Manag.. Publicado em: 16/07/2018
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3. Swirl Injection Effects on Hybrid Rocket Motors
ABSTRACT: In the last decades, hybrid rocket engines have been increasingly studied and used in space vehicles. However, the low regression rates and specific impulses still represent major drawbacks to this technology. The objective of this study was to quantify the relative improvement of regression rate values with the use of a swirling flow injector in c
J. Aerosp. Technol. Manag.. Publicado em: 2015-12
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4. Effect of Varying Design Options on the Transient Behavior of a Hybrid Rocket Motor
ABSTRACT: Hybrid rockets provide compelling features for use in atmospheric and space rocket propulsion. One of the prominent applications of hybrid rockets which foster on its characteristics is the propulsion of micro air launch vehicles. In this paper, a set of design options of a hybrid rocket motor is evaluated for propulsion of micro air launch vehicle
J. Aerosp. Technol. Manag.. Publicado em: 2014-03
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5. An Overview of the Technological Progress in Propellants Using Hydroxyl-Terminated Polybutadiene as Binder During 2002-2012
ABSTRACT: The purpose of this article is to present a study on the technological development of propellants, which are used in solid and hybrid rocket motor, that have been employing hydroxyl-terminated polybutadiene (HTPB) as a binder, for the past ten years. The results prove that major research conducted on propulsion technologies continues using HTPB as
J. Aerosp. Technol. Manag.. Publicado em: 2013-09
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6. Experimental Study of Polyurethane-Based Fuels with Addition of Paraffin and Aluminum for Hybrid Rocket Motors
ABSTRACT: Experimental investigation was conducted to determine the relative propulsive and combustion behavior of several polyurethane-based solid-fuel formulations containing 30% w/w of paraffin or 10% of aluminum powder. In total, seven solid-fuel formulations were investigated, four containing 30% of paraffin and three with 10% of aluminum. The polyureth
J. Aerosp. Technol. Manag.. Publicado em: 2013-09
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7. An Optimized Hybrid Rocket Motor for the SARA Platform Reentry System
Abstract: This paper has described a system design process, based on a multidisciplinary optimization technique, of a conceptual optimized hybrid propellant rocket motor. The proposed engine could be a technological option for the reentry maneuvering system of the Brazilian recoverable satellite (SARA), which was designed by the Brazilian Institute of Aerona
J. Aerosp. Technol. Manag.. Publicado em: 2012-09
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8. Preliminary analysis of hybrid rockets for launching nanosats into LEO
This work determines the preliminary mass distribution of hybrid rockets using 98% H2O2 and solid paraffin mixed with aluminum as propellants. An iterative process is used tocalculate the rocket performance characteristics and to determine the inert mass fractionfrom given initial conditions. It is considered a mission to place a 20 kg payload into a 300 km
Journal of the Brazilian Society of Mechanical Sciences and Engineering. Publicado em: 2010-12
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9. Experimental investigation of a hybrid rocket for satellites and spacecrafts using paraffin and N2O4 as propellants / Investigação experimental de um propulsor híbrido para satélites e veículos espaciais usando parafina e N2O4 como propelentes
Foi realizada uma investigação experimental de um propulsor híbrido de 70 N de empuxo usando parafina sólida (C_20H_42) e tetróxido de nitrogênio (N_2O_4) como propelentes, a uma pressão de câmara de 25 bar. Uma vez que a parafina não apresenta ação hipergólica com o N_2O_4, a ignição do motor foi realizada mediante a injeção de uma pequena q
Publicado em: 2009
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10. Desenvolvimento de uma bancada de testes de propulsores híbridos de baixo empuxo / Design of a test stand of hybrid rockets
A busca por propulsores de baixo custo, boa confiabilidade, baixo impacto ambiental e nível de segurança elevado aumentam o interesse pelo desenvolvimento dos propulsores híbridos. Este trabalho descreve o projeto, a construção e a operacionalização de uma bancada de testes de propulsores híbridos com empuxo até 500 N. Um propulsor híbrido de 400 N
Publicado em: 2009
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11. Desenvolvimento de uma bancada de testes de propulsores híbridos de baixo empuxo / Design of a test stand of hybrid rockets
A busca por propulsores de baixo custo, boa confiabilidade, baixo impacto ambiental e nível de segurança elevado aumentam o interesse pelo desenvolvimento dos propulsores híbridos. Este trabalho descreve o projeto, a construção e a operacionalização de uma bancada de testes de propulsores híbridos com empuxo até 500 N. Um propulsor híbrido de 400 N
Publicado em: 2009
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12. Análise de desempenho de um motor híbrido utilizando parafina e peróxido e hidrogênio como propelentes / Performance analysis of a hybrid rocket motor using paraffin and hydrogen peroxide as propellants
The objective of this work is to perform a theoretical and experimental analysis of the utilization of paraffin and hydrogen peroxide (H2O2) as propellants in a hybrid propulsion system. Initially, a chemical equilibrium code was written in MATLAB language to determine the propulsive characteristics of those propellants. Next, it was performed an analysis of
Publicado em: 2007