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:
Download or read book Pressurization System for Liquid Rockets written by National Aeronautics and Space Administration and published by CreateSpace. This book was released on 2014-04-15 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Advanced Pressurization System for Liquid Rockets written by R. A. Byron and published by . This book was released on 1968 with total page 7 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 Rocket Propellant and Pressurization Systems written by Elliot Ring and published by . This book was released on 1964 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Fundamentals of Theory and Calculation of Liquid propellant Rocket Engines Volume i written by and published by . This book was released on 1969 with total page 300 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Download or read book Liquid Rocket Booster Lrb for the Space Transportion System Sts Systems Study Appendix D written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-08 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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...
Download or read book Pressurization Systems Design Guide System analysis and selection written by Aerojet-General Corporation and published by . This book was released on 1966 with total page 516 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressurization Systems Design Guide pt A B Design procedures and data written by Aerojet-General Corporation and published by . This book was released on 1966 with total page 458 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Liquid Rocket and Propellants written by L.E. Bollinger and published by Elsevier. This book was released on 2013-04-22 with total page 699 pages. Available in PDF, EPUB and Kindle. Book excerpt: Liquid Rocket and Propellants
Download or read book Liquid Rocket Valve Components written by H. J. Ellis and published by . This book was released on 1973 with total page 156 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 Chemical Rocket Propulsion written by and published by . This book was released on 1962 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Development and Demonstration of Main Tank Injection mti Pressurization System written by R. J. Kenny and published by . This book was released on 1963 with total page 616 pages. Available in PDF, EPUB and Kindle. Book excerpt: A liquid rocket engine main tank injection (MTI) pressurization system which employs a chemical method of propellant tank pressurization, is studied. The process is initiated by injecting a small quantity of hypergolic reagent into the main propellant tank. The technical approach has been to study the important factors influencing the pressurization process by laboratory experiments and analytically determine system operating characteristics to evaluate various possible designs. Several engineering studies were completed initially to establish the pertinent design requirements of such a system, identify desirable configurations, and determine the most promising applications. Verification of the theoretical performance and development of a practical system was accomplished by a considerable amount of testing on 5 1/3-cu ft thick wall spherical tanks and subsequent demonstration in a 2,000-gal. full-scale flight-type ground test article. The research fixture was fabricated to investigate the actual reaction process and de develop components and operating procedures on a small-scale basis at pressures up to 200 psia.
Download or read book High pressure Flows for Propulsion Applications written by Josette Bellan and published by . This book was released on 2020 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Describes observations and modelling of high-pressure flows encountered in aeronautics and astronautics. They have been selected to present the current understanding of high-pressure flows. Experimental, theoretical and numerical studies are all represented. Fundamental investigations are presented first, followed by practical studies.
