Download or read book Analysis of Thermal protection Systems for Space vehicle Cryogenic propellant Tanks written by George R. Smolak and published by . This book was released on 1962 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Analytical techniques are presented that permit the calculation of heat-transfer rates with various thermal-protection systems for liquid-cryogenic-propellant tanks subjected to on-board, solar, and planetary heat fluxes. The effectiveness of these protection systems in reducing propellant heating is shown both for ideal heat-transfer models and for a simplified hydrogen-oxygen terminal state used for typical Mars missions.
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 Thermal Structures Technology Development for Reusable Launch Vehicle Cryogenic Propellant Tanks written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-11 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Analytical and experimental studies conducted at the NASA, Langley Research Center (LaRC) for investigating integrated cryogenic propellant tank systems for a reusable launch vehicle (RLV) are described. The cryogenic tanks are investigated as an integrated tank system. An integrated tank system includes the tank wall, cryogenic insulation, thermal protection system (TPS) attachment sub-structure, and TPS. Analysis codes are used to size the thicknesses of cryogenic insulation and TPS insulation for thermal loads, and to predict tank buckling strengths at various ring frame spacings. The unique test facilities developed for the testing of cryogenic tank components are described. Testing at cryogenic and high-temperatures verifies the integrity of materials, design concepts, manufacturing processes, and thermal/structural analyses. Test specimens ranging from the element level to the subcomponent level are subjected to projected vehicle operational mechanical loads and temperatures. The analytical and experimental studies described in this paper provide a portion of the basic information required for the development of light-weight reusable cryogenic propellant tanks.Johnson, Theodore F. and Natividad, Roderick and Rivers, H. Kevin and Smith, Russell W.Langley Research CenterCRYOGENICS; PROPELLANT TANKS; REUSABLE LAUNCH VEHICLES; STRUCTURAL ANALYSIS; THERMAL PROTECTION; TEST FACILITIES; TECHNOLOGY UTILIZATION; SINGLE STAGE TO ORBIT VEHICLES; LIQUID OXYGEN; HONEYCOMB STRUCTURES; BUCKLING; SYSTEMS INTEGRATION
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 Sloshing of Cryogenic Liquids in a Cylindrical Tank Under Normal Gravity Conditions written by Tim Arndt and published by Cuvillier. This book was released on 2012-06-04 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt: Particularly in the upper stage development of rockets (launchers), gravity dominated fluid motion in upper stage tanks (sloshing) during flight represents an undesired dynamic effect. On the one hand the sloshing forces lead to disturbances, which have to be compensated by the reaction control system. On the other hand, when cryogenic fluids are considered, the fluctuations in tank pressure may be critical under some circumstances compromising the structural stability of the tank. In this field, the utilization of cryogenic propellants represents a high challenge to layout and design of the propulsion components including the propellant tanks. This work deals with two effects that are directly coupled to the sloshing content inside the propellant tank. To investigate these effects a dedicated test setup has been developed. At first, the damping characteristics of sloshing cryogenic nitrogen - which is used as a substitute for the rocket propellants liquid hydrogen and liquid oxygen - are determined. The results are correlated to the theory based on storable propellants. The main part of this work is linked to a characteristic pressure drop inside the propellant tank caused by the sloshing liquid. For the effect to occur, the tank must be pressurized to enable the formation of a thermal stratification below the liquid surface. Sloshing leads to the mixing of liquid in this region with subcooled liquid from the bulk. This affects the decrease of the temperature at the free surface leading to the condensation of superheated vapor. Thus, the pressure in the tank must decreases. Three different pressurization concepts are introduced in this work; self-pressurization where the tank is pressurized by evaporating liquid caused by the heat flowing into the tank. Furthermore, the tank is pressurized with gaseous nitrogen taken from an external gas bottle and at last gaseous helium from an external supply is used for pressurization purpose. By the application of helium as no
Download or read book Pressure Volume Temperature Pvt Gauging of an Isothermal Cryogenic Propellant Tank Pressurized with Gaseous Helium written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2019-01-13 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented for pressure-volume-temperature (PVT) gauging of a liquid oxygen/liquid nitrogen tank pressurized with gaseous helium that was supplied by a high-pressure cryogenic tank simulating a cold helium supply bottle on a spacecraft. The fluid inside the test tank was kept isothermal by frequent operation of a liquid circulation pump and spray system, and the propellant tank was suspended from load cells to obtain a high-accuracy reference standard for the gauging measurements. Liquid quantity gauging errors of less than 2 percent of the tank volume were obtained when quasi-steady-state conditions existed in the propellant and helium supply tanks. Accurate gauging required careful attention to, and corrections for, second-order effects of helium solubility in the liquid propellant plus differences in the propellant/helium composition and temperature in the various plumbing lines attached to the tanks. On the basis of results from a helium solubility test, a model was developed to predict the amount of helium dissolved in the liquid as a function of cumulative pump operation time. Use of this model allowed correction of the basic PVT gauging calculations and attainment of the reported gauging accuracy. This helium solubility model is system specific, but it may be adaptable to other hardware systems. VanDresar, Neil T. and Zimmerli, Gregory A. Glenn Research Center WBS 645454.01.04.04.02
Download or read book Cyclic Cryogenic Thermal Mechanical Testing of an X 33 RLV Liquid Oxygen Tank Concept written by H. Kevin Rivers and published by . This book was released on 1999 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hybrid Thermal Control Testing of a Cryogenic Propellant Tank written by David W. Plachta and published by . This book was released on 1999 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analysis of Thermal protection Systems for Space vehicle Cryogenic propellant Tanks with List of References written by and published by . This book was released on 1962 with total page 39 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 Experimental Investigation of Glass Flakes as a Liner for Fiber glass Cryogenic Propellant Tanks written by Robert W. Frischmuth (Jr.) 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 Analysis of Thermal protection Systems for Space vehicle Cryogenic propellant Tanks written by George R. Smolak and published by . This book was released on 1962 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt: Analytical techniques are presented that permit the calculation of heat-transfer rates with various thermal-protection systems for liquid-cryogenic-propellant tanks subjected to on-board, solar, and planetary heat fluxes. The effectiveness of these protection systems in reducing propellant heating is shown both for ideal heat-transfer models and for a simplified hydrogen-oxygen terminal state used for typical Mars missions.
Download or read book Computational Modelling of Jet Induced Mixing in Cryogenic Propellant Tanks in Low G written by John I. Hochstein and published by . This book was released on 1984 with total page 684 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Filament Wound Metal Lined Propellant Tanks for Future Earth to orbit Transports written by and published by . This book was released on 1988 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure volume temperature PVT gauging of an isothermal cryogenic propellant tank pressurized with gaseous helium written by Neil T. Van Dresar and published by . This book was released on 2014 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Cyclic Cryogenic Thermal Mechanical Testing of an X 33 Rlv Liquid Oxygen Tank Concept written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-16 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: An important step in developing a cost-effective, reusable, launch vehicle is the development of durable, lightweight, insulated, cryogenic propellant tanks. Current cryogenic tanks are expendable so most of the existing technology is not directly applicable to future launch vehicles. As part of the X-33/Reusable Launch Vehicle (RLV) Program, an experimental apparatus developed at the NASA Langley Research Center for evaluating the effects of combined, cyclic, thermal and mechanical loading on cryogenic tank concepts was used to evaluate cryogenic propellant tank concepts for Lockheed-Martin Michoud Space Systems. An aluminum-lithium (Al 2195) liquid oxygen tank concept, insulated with SS-1171 and PDL-1034 cryogenic insulation, is tested under simulated mission conditions, and the results of those tests are reported. The tests consists of twenty-five simulated Launch/Abort missions and twenty-five simulated flight missions with temperatures ranging from -320 F to 350 F and a maximum mechanical load of 71,300 lb. in tension. Rivers, H. Kevin Langley Research Center NASA/TM-1999-209560, L-17818, NAS 1.15:209560
Download or read book Reusable Launch Vehicle written by Committee on Reusable Launch Vehicle Technology and Test Program and published by National Academies Press. This book was released on 1996-01-22 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt: The key to opening the use of space to private enterprise and to broader public uses lies in reducing the cost of the transportation to space. More routine, affordable access to space will entail aircraft-like quick turnaround and reliable operations. Currently, the space Shuttle is the only reusable launch vehicle, and even parts of it are expendable while other parts require frequent and extensive refurbishment. NASA's highest priority new activity, the Reusable Launch Vehicle program, is directed toward developing technologies to enable a new generation of space launchers, perhaps but not necessarily with single stage to orbit capability. This book assesses whether the technology development, test and analysis programs in propulsion and materials-related technologies are properly constituted to provide the information required to support a December 1996 decision to build the X-33, a technology demonstrator vehicle; and suggest, as appropriate, necessary changes in these programs to ensure that they will support vehicle feasibility goals.
