Pressurization System For Liquid Rockets

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Pressurization Systems For Liquid Rockets

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Author : United States. National Aeronautics and Space Administration
language : en
Publisher:
Release Date : 1976

Pressurization Systems For Liquid Rockets written by United States. National Aeronautics and Space Administration and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with Liquid propellant rockets categories.

Pressurization System For Liquid Rockets

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Author : National Aeronautics and Space Administration
language : en
Publisher: CreateSpace
Release Date : 2014-04-15

Pressurization System For Liquid Rockets written by National Aeronautics and Space Administration and has been published by CreateSpace this book supported file pdf, txt, epub, kindle and other format this book has been release on 2014-04-15 with categories.

The purpose of this monograph is to organize and present, for effective use in deign, the significance experience and knowledge accumulated in development and operational programs to date. It reviews and assesses current design practices, and from them establishes firm guidance for achieving consistency in design, increased reliability in the end product, and greater efficiency in the design effort.

Advanced Pressurization System For Liquid Rockets

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Author : R. A. Byron
language : en
Publisher:
Release Date : 1968

Advanced Pressurization System For Liquid Rockets written by R. A. Byron and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1968 with Liquid propellant rockets categories.

Fundamentals Of Theory And Calculation Of Liquid Propellant Rocket Engines Volume I

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Author :
language : en
Publisher:
Release Date : 1969

Fundamentals Of Theory And Calculation Of Liquid Propellant Rocket Engines Volume I written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1969 with categories.

Theoretical and design principles of liquid rocket engines are presented. Extensive coverage is given to processes taking place in the combustion chamber, calculations of mixing systems, the cooling and contour calculation of the nozzles, calculation and selection of optimal parameters, turbopump and fuel feed pressurization systems, generation of the working medium for the turbine and fuel feed pressurization system, design and integration of pneumohydraulic systems for liquid rocket engines, calculation methods and selection of a liquid rocket engine parameters with a closed generation circuit of the working medium for the turbine. Basic theoretical and design principles of processes taking place in different types of liquid rocket engines are presented. The operation of main subsystems and the calculation of their characteristics are discussed. (Author).

Propellant Tank Pressurization Modeling For A Hybrid Rocket

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Author : Margaret Mary Fernandez
language : en
Publisher:
Release Date : 2009

Propellant Tank Pressurization Modeling For A Hybrid Rocket written by Margaret Mary Fernandez and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2009 with Hybrid propellant rockets categories.

"Hybrid rockets are currently being examined as a simpler and safer alternative to solid and liquid rocket propulsion. A basic hybrid rocket oxidizer delivery system utilizes the self-pressurizing nature of a liquid oxidizer at ambient temperatures in conjunction with a non-condensable to provide a high oxidizer tank pressure that drives liquid oxidizer flow to the combustion chamber. In this study, the oxidizer fluid is nitrous oxide since it produces high vapor pressures at ambient temperatures, and helium is the pressurant. The goal of this thesis is to model the pressure draining history of the oxidizer tank to within +/- 5% accuracy. Previous studies of the self-pressurization processes in a propellant tank have focused on long-term cryogenic storage applications where the primary concern is heat leaking into the tank, causing unwanted pressure increases that result in propellant loss through necessary venting. Results of these cryogenic studies have been used to justify the inclusion of heat and mass transfer resistances in propellant tank models in order to be sufficiently accurate. However, these cryogenic studies were performed under conditions of very low vapor pressure and temperatures, and it is not clear that the conclusions drawn from such studies are valid for self-pressurization under ambient temperature conditions. Thus, the validity of simpler thermodynamically-based models has not been considered for self-pressurizing, draining tanks under high pressure conditions. In this study, two models are developed, both assuming thermodynamic equilibrium states at every point in time throughout draining. The firs model assumes the P-V-T behavior of the nitrous oxide/helium mixture follows the ideal gas law; the second model assumes that the mixture adheres to the non-ideal Peng-Robinson equation-of-state. Both models are compared to experimental data from pure nitrous oxide draining tests, published in G. Zilliac & M. Karabeyoglu (Modeling of Propellant Tank Pressurization, AIAA 2005-3549, 41st AIAA/ASME/ASEE Joint Propulsion Conference). Sensitivity studies have been performed in order to determine the effect of experimental error on the time-dependent flow from the tank and to assess the behavior of the models near physical extremes, such as high or low initial nitrous oxide fill-levels. Theoretical draining histories for the Peregrine hybrid sounding rocket (a joint effort between NASA Ames Research Center and Stanford University, soon to be launched from NASA Wallops Flight Facility, have also been examined. A variety of comparisons with available experimental data, theoretical sensitivity studies, and theoretical launch data demonstrates that the non-ideal draining model provides favorable agreement. The additional complexity introduced by a non-ideal equation-of-state is necessary due to the high pressures encountered in the tank during draining. Sensitivity studies reveal that small deviations in the initial temperature, initial fill-level, or the discharge coeffient can produce nearly 5% errors in liquid drain time, demonstrating the need for accurately measured model inputs and suggesting sources of error in experimental design. It is found that despite the highly desirable characteristic of a rocket oxidizer delivery system. The study provides a proposal for a new set of experiments necessary to assess and refine the theoretical models to allow for design and scale-up of hybrid rocket oxidizer delivery systems."--Abstract.

Rocket Propellant And Pressurization Systems

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Author : Elliot Ring
language : en
Publisher:
Release Date : 1964

Rocket Propellant And Pressurization Systems written by Elliot Ring and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1964 with Liquid propellant rockets categories.

Liquid Rocket And Propellants

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Author : L.E. Bollinger
language : en
Publisher: Elsevier
Release Date : 2013-04-22

Liquid Rocket And Propellants written by L.E. Bollinger and has been published by Elsevier this book supported file pdf, txt, epub, kindle and other format this book has been release on 2013-04-22 with Science categories.

Liquid Rocket and Propellants

Liquid Propellant Rockets

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Author : David Altman
language : en
Publisher: Princeton University Press
Release Date : 2015-12-08

Liquid Propellant Rockets written by David Altman and has been published by Princeton University Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2015-12-08 with Science categories.

David Altman, James M. Carter, S. S. Penner, Martin Summerfield. High Temperature Equilibrium, Expansion Processes, Combustion of Liquid Propellants, The Liquid Propellants Rocket Engine. Originally published in 1960. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.

Chemical Rocket Propulsion

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Author :
language : en
Publisher:
Release Date : 1962

Chemical Rocket Propulsion written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with Rockets (Aeronautics) categories.

Liquid Propellant Rocket Combustion Instability

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Author : David T. Harrje
language : en
Publisher:
Release Date : 1972

Liquid Propellant Rocket Combustion Instability written by David T. Harrje and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1972 with Liquid propellant rockets categories.

The solution of problems of combustion instability for more effective communication between the various workers in this field is considered. The extent of combustion instability problems in liquid propellant rocket engines and recommendations for their solution are discussed. The most significant developments, both theoretical and experimental, are presented, with emphasis on fundamental principles and relationships between alternative approaches.