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 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 Simulator for Static Liquid Configuration in Propellant Tanks Subject to Reduced Gravity written by William A. Olsen and published by . This book was released on 1966 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
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:
Download or read book Prediction of the Ullage Gas Thermal Stratification in a NASP Vehicle Propellant Tank Experimental Simulation Using FLOW 3D written by and published by . This book was released on 1990 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 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 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 1967 with total page 2300 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Computer Program Abstracts written by and published by . This book was released on 1973 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 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:
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:
Download or read book Computer Simulation of a Propellant Feed System for a Liquid Propellant Gun written by Craig Richard Dampier and published by . This book was released on 1976 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computer model was developed to simulate a projectile ram-propellant feed system for a Liquid Propellant Gun. Using a lumped parameter approach, a set of simultaneous differential equations was derived for the complex interaction of the propellant fluid, the driving injector and the projectile. The computer model was verified against a 20 mm experimental apparatus. Injector displacement, projectile displacement, and chamber pressure were compared for a nominal driving pressure of 140 psi. The important system parameters affecting projectile ram time and chamber pressure oscillations were investigated and potential problem areas for testing with actual propellant were identified. (Author).
Download or read book Proceedings of the ASME Advanced Energy Systems Division written by American Society of Mechanical Engineers. Advanced Energy Systems Division and published by . This book was released on 2007 with total page 610 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Selected Listing of NASA Scientific and Technical Reports for 1966 written by United States. National Aeronautics and Space Administration. Scientific and Technical Information Division and published by . This book was released on 1967 with total page 2084 pages. Available in PDF, EPUB and Kindle. Book excerpt:
