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Self Pressurizing Propellant Tank Dynamics
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Book Synopsis Self-pressurizing Propellant Tank Dynamics by : Jonah E. Zimmerman
Download or read book Self-pressurizing Propellant Tank Dynamics written by Jonah E. Zimmerman and published by . This book was released on 2015 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Hybrid rockets frequently use nitrous oxide as a self-pressurizing oxidizer, where the high vapor pressure of the oxidizer is used to force the liquid out of the propellant tank and into the combustion chamber. To study this system, a series of small-scale pressure vessels with optical access have been developed that can be filled with nitrous oxide and then drained in a manner that replicates the conditions within a hybrid rocket. A high-speed camera has been used to visualize the nitrous oxide within the propellant tank and identify relevant phenomena. Experiments have identified two separate temporal regimes that are common to all blowdown tests: a transient and steady state, each described by distinct features. The transient regime is characterized by a rapid pressure drop and recovery, with homogeneous condensation of the ullage and heterogeneous nucleation and growth of bubbles. During steady state regime the liquid and vapor are both homogeneous two-phase mixtures and the pressure drops in a linear fashion as the liquid drains from the tank. Carbon dioxide was identified as a possible simulant fluid for nitrous oxide, and comparison tests showed that it behaves as an accurate analog. This low-cost and safe simulant fluid enabled a large number of tests that examined the effect of parameter variations, including flow rate, fill level, temperature, and scaling effects. Experimental data from this system have been used to develop a new model for self-pressurizing propellant tank dynamics. This was done by blending the 0-D lumped-node methods of previous researchers with a novel 1-D method that captures the dynamics of a changing bubble population. The direct quadrature method of moments was used to develop partial differential equations for parameters of this distribution. The proposed model was compared against experimental data and shown to have good agreement. The pressure drop and recovery seen in the transient regime, which is not captured by previous models, is visible in the model predictions. Convergence studies were performed in order to determine suitable parameters of the numerical integration schemes and the discretizations used. To complete the model, numerous submodels were incorporated by using relations from various sources in the literature. The effect of variations in these submodels was studied in order to justify the selection of adjustable constants.
Book Synopsis EOTV Propellant Tank Pressure Control and Liquid Dynamics by : J. R. Pietrzyk
Download or read book EOTV Propellant Tank Pressure Control and Liquid Dynamics written by J. R. Pietrzyk and published by . This book was released on 1993 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Propellant Tank Pressurization Modeling for a Hybrid Rocket by : Margaret Mary Fernandez
Download or read book Propellant Tank Pressurization Modeling for a Hybrid Rocket written by Margaret Mary Fernandez and published by . This book was released on 2009 with total page 300 pages. Available in PDF, EPUB and Kindle. Book excerpt: "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.
Book Synopsis Principles of Design of Dynamically Similar Models for Large Propellant Tanks by : Paul E. Sandorff
Download or read book Principles of Design of Dynamically Similar Models for Large Propellant Tanks written by Paul E. Sandorff and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Principles of Design of Dynamically Similar Models for Large Propellant Tanks by : Paul Edwin Sandorff
Download or read book Principles of Design of Dynamically Similar Models for Large Propellant Tanks written by Paul Edwin Sandorff and published by . This book was released on 1960 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of Cryogenic Propellant Tank Pressurization based upon Experiments and Numerical Simulations by : Carina Ludwig
Download or read book Analysis of Cryogenic Propellant Tank Pressurization based upon Experiments and Numerical Simulations written by Carina Ludwig and published by Cuvillier Verlag. This book was released on 2014-09-04 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt: Focus of this study is the pressurization system of a cryogenic liquid propellant tank for the launcher application. Objective of the pressurization system is to provide the required pressure evolution in the propellant tank for a proper operation of the engine. The motivation of this study is an improved understanding of the complex fluid-dynamic and thermodynamic phenomena during the active-pressurization process of cryogenic propellants in order to optimize the on-board pressurant gas mass. Therefore ground experiments, numerical simulations and analytical considerations were performed for the investigation of the initial active-pressurization phase. For the performed experiments, liquid nitrogen was used as cryogenic model propellant, which was actively pressurized under normal gravity conditions up to different final tank pressures. As pressurant gases, gaseous nitrogen and gaseous helium were used with different inlet temperatures. For the numerical analyses the commercial CFD program Flow-3D, a three-dimensional Navier-Stokes equation solver, was used.
Book Synopsis Hybrid Rocket Propulsion Design Handbook by : Ashley Chandler Karp
Download or read book Hybrid Rocket Propulsion Design Handbook written by Ashley Chandler Karp and published by Academic Press. This book was released on 2023-10-07 with total page 344 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hybrid Rocket Propulsion Design Handbook provides system scaling laws, design methodologies, and a summary of available test data, giving engineers all the tools they need to develop realistic hybrid system designs.Important supporting theory from chemistry, thermodynamics, and rocket propulsion is addressed, helping readers from a variety of backgrounds to understand this interdisciplinary subject. This book also suggests guidelines for standardized reporting of test data, in response to difficulties researchers have in working with results from different research institutes. Covers general theory, recent advances and current fragmented experimental results of hybrid rocket engines Outlines testing standards for hybrid researchers Provides guidance on how to use a freely available online code from NASA
Book Synopsis A Self-pressurization System for Cryogenic Propellant Tanks by : Alexander A. Kozlov
Download or read book A Self-pressurization System for Cryogenic Propellant Tanks written by Alexander A. Kozlov and published by . This book was released on 1996 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Advances in Hybrid Rocket Technology and Related Analysis Methodologies by : Carmine Carmicino
Download or read book Advances in Hybrid Rocket Technology and Related Analysis Methodologies written by Carmine Carmicino and published by MDPI. This book was released on 2020-12-07 with total page 352 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book is an amazing collection of technical papers dealing with hybrid rockets. Once perceived as a niche technology, for about a decade, hybrid rockets have enjoyed renewed interest from both the propulsion technical community and industry. Hybrid motors can be used in practically all applications where a rocket is employed, but there are certain cases where they present a superior fit, such as sounding rockets, tactical missile systems, launch boosters and the emerging field of commercial space transportation. The novel space tourism business, indeed, will benefit from their safety and lower recurrent development costs. The subjects addressed in the book include the cutting edge technology employed to push forward this relatively new propulsion concept, spanning systems to improve fuel regression rate, control of the mixture ratio to optimize performance, computational fluid dynamics applied to the simulation of the internal ballistics, and some other novel system applications.
Book Synopsis Chemical Kinetics in Combustion and Reactive Flows: Modeling Tools and Applications by : V. I. Naoumov
Download or read book Chemical Kinetics in Combustion and Reactive Flows: Modeling Tools and Applications written by V. I. Naoumov and published by Cambridge University Press. This book was released on 2019-08-22 with total page 449 pages. Available in PDF, EPUB and Kindle. Book excerpt: Introduces advanced mathematical tools for the modeling, simulation, and analysis of chemical non-equilibrium phenomena in combustion and flows, following a detailed explanation of the basics of thermodynamics and chemical kinetics of reactive mixtures. Researchers, practitioners, lecturers, and graduate students will find this work valuable.
Book Synopsis Pressurization Systems for Liquid Rockets by : United States. National Aeronautics and Space Administration
Download or read book Pressurization Systems for Liquid Rockets written by United States. National Aeronautics and Space Administration and published by . This book was released on 1976 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Advanced Technologies in Flow Dynamics and Combustion in Propulsion and Power by : Lei Luo
Download or read book Advanced Technologies in Flow Dynamics and Combustion in Propulsion and Power written by Lei Luo and published by Frontiers Media SA. This book was released on 2022-08-05 with total page 358 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Modern Engineering for Design of Liquid-Propellant Rocket Engines by : Dieter K. Huzel
Download or read book Modern Engineering for Design of Liquid-Propellant Rocket Engines written by Dieter K. Huzel and published by AIAA. This book was released on 1992 with total page 452 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Simulation of Bulk Evaporation and Condensation in Cryogenic Propellant Tanks Using the Energy of Fluid Method by : Elijah Gasmen
Download or read book Simulation of Bulk Evaporation and Condensation in Cryogenic Propellant Tanks Using the Energy of Fluid Method written by Elijah Gasmen and published by . This book was released on 2021 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The design of cryogenic propellant storage systems for long duration space missions relies on accurate prediction of tank self-pressurization. Incident solar radiation heats the cryogenic liquids in the tank over time, vaporizing the cryogenic liquid. As the liquid vaporizes, the tank pressure increases. The objective of the current research is to develop a finite volume based Compuational Fluid Dynamic (CFD) model of tank pressurization in reduced gravity using an Energy of Fluid (EOF) method. A commercially available CFD model is significantly enhanced to include the EOF method, which will solve the energy equation in terms of internal energy. Model validation results are presented which include a comparison of temperature and pressure predictions to the data collected during the terrestrial experiments performed by Aydelott and the low gravity experiment conducted onboard the Saturn IB AS203 tank.
Book Synopsis Liquid Rocket Metal Tanks and Tank Components by : W. A. Wagner
Download or read book Liquid Rocket Metal Tanks and Tank Components written by W. A. Wagner and published by . This book was released on 1974 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :United States. National Aeronautics and Space Administration Scientific and Technical Information Division Publisher : ISBN 13 : Total Pages :472 pages Book Rating :4.F/5 ( download)
Book Synopsis NASA Scientific and Technical Reports by : United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Download or read book NASA Scientific and Technical Reports written by United States. National Aeronautics and Space Administration Scientific and Technical Information Division and published by . This book was released on with total page 472 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Prediction of Propellant Tank Pressurization Requirements by Dimensional Analysis by : J. F. Thompson
Download or read book Prediction of Propellant Tank Pressurization Requirements by Dimensional Analysis written by J. F. Thompson and published by . This book was released on 1966 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: