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.
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:
Download or read book Liquid Acquisition Devices for Advanced In Space Cryogenic Propulsion Systems written by Jason William Hartwig and published by Academic Press. This book was released on 2015-11-21 with total page 489 pages. Available in PDF, EPUB and Kindle. Book excerpt: Liquid Acquisition Devices for Advanced In-Space Cryogenic Propulsion Systems discusses the importance of reliable cryogenic systems, a pivotal part of everything from engine propulsion to fuel deposits. As some of the most efficient systems involve advanced cryogenic fluid management systems that present challenging issues, the book tackles issues such as the difficulty in obtaining data, the lack of quality data and models, and the complexity in trying to model these systems. The book presents models and experimental data based on rare and hard-to-obtain cryogenic data. Through clear descriptions of practical data and models, readers will explore the development of robust and flexible liquid acquisition devices (LAD) through component-level and full-scale ground experiments, as well as analytical tools. This book presents new and rare experimental data, as well as analytical models, in a fundamental area to the aerospace and space-flight communities. With this data, the reader can consider new and improved ways to design, analyze, and build expensive flight systems. Presents a definitive reference for design ideas, analysis tools, and performance data on cryogenic liquid acquisition devices Provides historical perspectives to present fundamental design models and performance data, which are applied to two practical examples throughout the book Describes a series of models to optimize liquid acquisition device performance, which are confirmed through a variety of parametric component level tests Includes video clips of experiments on a companion website
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.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Thermomechanical Simulation of an Aerogel RTV 655 Based Cryogenic Propellant Tank written by William Dalton Bowen and published by . This book was released on 2021 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Developing an effective solution for long duration storage of cryogenic liquids is crucial for future, manned space exploration missions. Current storage tanks are made of metals or composites. Although these materials have a relatively high mechanical strength, their high thermal conductivity is a disadvantage with regards to heat infiltration. The influx of heat causes vaporization, increasing the pressure in the tank. To reduce tank pressurization rates, novel materials with densities and thermal conductivities which are lower than metals, such as RTV-655 and aerogels, have been developed which may be feasible for space applications. Due to the complexity and costs of performing experiments, a thermomechanical computational model is desired to further study the feasibility of using these novel materials. A thermomechanical finite element simulation is used to simulate the Cooldown and Pressurization phases of RTV-655 and RTV-655/Aerogel tank experiments and a comparison of the simulation and experimental results are presented.
Download or read book Modeling of cryogenic sloshing including heat and mass transfer written by Arnold van Foreest and published by Cuvillier Verlag. This book was released on 2014-03-10 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt: Sloshing of cryogenic liquid propellants in launch vehicle tanks creates unwanted thermodynamic side-effects such as pressure changes in the tank. The goal of this PhD research was to develop a practical engineering model which is able to describe the influence of the sloshing of a cryogenic liquid on the heat and mass transfer and the associated temperature and pressure. The pressure changes caused by sloshing were investigated experimentally and numerically. Using the experimental and numerical results, a one dimensional (1D) engineering model was developed which is able to describe the experimental results.
Download or read book Simulating Self Pressurization in Propellant Tanks Using an Energy of Fluid Approach written by Amanda Paige Winter and published by . This book was released on 2014 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Recent studies focusing on predicting the self pressurization play a significant role in the design of cryogenic storage systems since tank pressure must be controlled for long duration space missions. Incident solar radiation heats the fluid 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 Computational Fluid Dynamic (CFD) model of tank pressurization in reduced gravity using an Energy of Fluid (EOF) approach. The FLUENT pressure-based computational model is significantly enhanced to include the EOF method, which will solve the energy equation in terms of internal energy. The enhanced model will numerically predict the thermodynamic properties in each computational cell. The simulation results will provide temperature and pressure histories for a given tank geometry and fill. The objectives of the current study are to complete the model development and validate the model using existing experimental data for tank pressure.
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.
Download or read book Large Space Structures Systems in the Space Station Era written by and published by . This book was released on 1991 with total page 356 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1999 with total page 1042 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Space Station Systems written by and published by . This book was released on 1986 with total page 606 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Analysis of the Problem of Tank Pressurization During Outflow written by William H. Roudebush and published by . This book was released on 1965 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book Pressurization System Analysis for Cryogenic Propulsion Systems written by Frederick Chopp and published by . This book was released on 1965 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
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 1970 with total page 966 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Selected Listing of 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 1970 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt:
