Pressurization Systems 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).

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.

Pressurization Systems Design Guide System Analysis And Selection

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Author : Aerojet-General Corporation
language : en
Publisher:
Release Date : 1966

Pressurization Systems Design Guide System Analysis And Selection written by Aerojet-General Corporation and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1966 with Rocket engines categories.

Pressurization System Analysis For Cryogenic Propulsion Systems

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Author : Frederick Chopp
language : en
Publisher:
Release Date : 1965

Pressurization System Analysis For Cryogenic Propulsion Systems written by Frederick Chopp and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1965 with categories.

Stored gas pressurization and boost pump liquid rocket engine propellant transfer systems were investigated to compare their suitability for use on hydrogen-oxygen upper stage vehicles. The purpose of this document is to present the results of this study and to describe the method of analysis used. System comparisons were based on the overall system weight. The mission duty cycle, NPSH, propellant weight, and propellant type were held constant. Results indicated that liquid transfer with boost pumps will provide a minimum system weight for the selected baseline configuration and ground rules. For stored gas pressurization, it was determined that storage of the gas bottle should be in the hydrogen tank with the pressurant heated prior to entering the tanks. Optimum pressurant temperature for the hydrogen tank was found to be 350 R. No calculations were made to optimize the oxygen tank pressurant temperature. (Author).

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.

Liquid Rocket Booster Lrb For The Space Transportion System Sts Systems Study Appendix D

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Author : National Aeronautics and Space Adm Nasa
language : en
Publisher: Independently Published
Release Date : 2018-10-29

Liquid Rocket Booster Lrb For The Space Transportion System Sts Systems Study Appendix D written by National Aeronautics and Space Adm Nasa and has been published by Independently Published this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-10-29 with categories.

Trade studies plans for a number of elements in the Liquid Rocket Booster (LRB) component of the Space Transportation System (STS) are given in viewgraph form. Some of the elements covered include: avionics/flight control; avionics architecture; thrust vector control studies; engine control electronics; liquid rocket propellants; propellant pressurization systems; recoverable spacecraft; cryogenic tanks; and spacecraft construction materials. Unspecified Center...

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.