Download or read book The Development of a Heated hybrid Generated Gas Pressurization System for Propellant Tanks written by Donald H. Lee and published by . This book was released on 1963 with total page 21 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 1994 with total page 772 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Report Jet Propulsion Laboratory California Institute of Technology written by Jet Propulsion Laboratory (U.S.) and published by . This book was released on 1963 with total page 726 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 Keywords Index to U S Government Technical Reports written by and published by . This book was released on 1963-07-15 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Publications of the Jet Propulsion Laboratory written by and published by . This book was released on 1963 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Keywords Index to U S Government Technical Reports permuted Title Index written by United States. Department of Commerce. Office of Technical Services and published by . This book was released on 1963 with total page 618 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Propellant tank pressurization system technology program task 1 report catalytic heating of pressurant written by W. R. C. Graham and published by . This book was released on 1990 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Stress corrosion cracking can potentially cause fuel failures at circumferential ridges in the sheath. finite element computer codes elestres and feast are used to calculate two-dimensional, axisymmetric, elastic-plastic sheath stresses at and near the circumferential ridges. the level of stresses is given by the fuel design (such as pellet/sheath diameters, pellet length, pellet density) and by the operating conditions (such as power history). the accuracy, convergence, and cost of the stress calculations, however, are determined by the discretization used in the calculations: the number of nodes in the finite element mesh; the shape of the individual finite elements; the pattern into which the finite elements are arranged; and the size of the calculation-steps into which the power history is subdivided. in this study, we determined the discretization that gives a reasonable compromise of accuracy, convergence, and cost for the stress calculations. the highest accuracy is obtained by using triangular finite elements of aspect ratios close to one, and assembling them into hexagonal patterns. to caputure the stress gradients, five nodes are required across the sheath wall at the ridge, but two nodes are sufficient near the midplane of the pellet. the resulting mesh contains about 200 nodes and about 300 finite elements. calculation-steps of 6 kw/m provide a convergent solution, with a factor of two margin against numerical divergence. with the above arrangement, feast needs about 2.4 seconds on a cdc/cyber 175 computer to calculate sheath stresses per calculation-step. six radial nodes at the ridge would double the computing cost. decreasing the size of the calculation-steps means more calculations are needed to analyze a given power history, giving a linear increase in computing cost.
Download or read book REIC Memorandum written by Battelle Memorial Institute. Radiation Effects Information Center and published by . This book was released on with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressurization Systems Design Guide written by Aerojet-General Corporation and published by . This book was released on 1966 with total page 462 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Catalog of Copyright Entries Third Series written by Library of Congress. Copyright Office and published by Copyright Office, Library of Congress. This book was released on 1964 with total page 1222 pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes Part 1, Number 1: Books and Pamphlets, Including Serials and Contributions to Periodicals (January - June)
Download or read book Technical Abstract Bulletin written by Defense Documentation Center (U.S.) and published by . This book was released on 1963 with total page 1032 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Development and Optimization of a Tridyne Pressurization System for Pressure Fed Launch Vehicles written by and published by . This book was released on 2006 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: Over the recent years, Microcosm has been pursuing the development of a Tridyne-based pressurization system and its implementation in the Scorpius family of launch vehicles to obtain substantial gain in payload to orbit. This technology program was initiated with an IR & D program and matured with contracts from the National Reconnaissance Office (NRO), and the Air Force Research Laboratory (AFRL). The Tridyne pressurization system functions by mixing small amounts of hydrogen and oxygen with the pressurant gas (typically helium). When the mixture is passed through a catalyst bed, the hydrogen and oxygen react to produce heat. The result is hot pressurant gas, with a small amount of water vapor remaining from the combustion process. The implementation scheme developed for the Scorpius family of launch vehicles involves returning some of the heat to the Tridyne mixture in the pressurant tank by means of an internal heat exchanger. This offsets the expansion cooling such that the temperature of the pressurant actually rises as the pressurant is used. The remaining energy is used to elevate the temperature of the gas delivered to the propellant tanks to near the maximum allowable operating temperature of the downstream components (typically about 200 to 250 deg F) such as the regulator and the composite over-wrapped propellant tanks. The result of heating the helium in this way was shown to reduce the mass and volume of required helium and the associated tankage by nearly 50%, resulting in substantial payload gain.
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1998 with total page 980 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book U S Government Research Development Reports written by and published by . This book was released on 1967 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt:
