Download or read book Applications of Liquid Oxygen Handling Techniques to Rocket Engine Testing written by Floyd Twight and published by . This book was released on 1957 with total page 8 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 of a Liquid Oxygen Facility for Rocket Engine Testing written by H. W. Mulkey and published by . This book was released on 2012 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Propulsion Research Center at the University of Alabama Huntsville has developed a liquid oxygen propellant feed system that has advanced into operational maturity. In support of safe system functional development, an oxygen compatibility and hazards assessment was completed in order to identify and minimize operational risks. The objective of this effort was to minimize potential risks that might have been overlooked in the initial design phase or resulted from a discontinuity between design and fabrication. The effort involved an internal review of the operating procedures and the system configuration, as well as an overall review by an oxygen safety engineering consultant. This paper outlines the review procedures applied to the oxygen propellant systems, summarizes the significant findings, and details configuration changes made to the system. The review process identified several areas in which reliance on procedural control, without compromising safe system operation, could be reduced or removed through design changes. Such changes were implemented so as to create a more fault tolerant system and minimize risks to test equipment, system hardware, and test personnel. Major upgrades included initiatives to manage the oxygen risk and mitigate specific oxygen ignition mechanisms. Oxygen compatible materials and facility configuration changes enabled safer experimentation in the demonstration testing of the cryogenic propellant facility. The findings presented in this paper represent the system changes made in an effort to increase safety and decrease the risk of fire in order to achieve a low probability of ignition and a low consequence of ignition.
Download or read book Development of a Liquid Oxygen Facility for Rocket Engine Injector Performance Testing written by Henry W. Mulkey and published by . This book was released on 2010 with total page 438 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Handling and Use of Fluorine and Fluorine oxygen Mixtures in Rocket Systems written by Harold W. Schmidt and published by . This book was released on 1967 with total page 292 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation in an Altitude Test Facility of Burning of Excess Combustibles in a Rocket Engine Exhaust written by Harry E. Bloomer and published by . This book was released on 1960 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Liquid Rocket Engine written by Rene Nardi Rezende and published by SAE International. This book was released on 2018-11-15 with total page 158 pages. Available in PDF, EPUB and Kindle. Book excerpt: The great engineering achievement required to overcome most of the challenges and obstacles that prevented turning rocket design from art into science took place in Europe and the United States between the 1930s and the 1950s. With the vast majority of the engines currently in operation developed in the “pre-computer” age, there are new opportunities to update the design methodologies using technology that can now handle highly complex calculations fast. The space sector with an intense focus on efficiency is driving the need for updating, adapting or replacing the old modeling practices with new tools capable of reducing the volume of resources and the time required to complete simulations and analysis. This book presents an innovative parametric model applicable to the project of some elements of the liquid rocket thrust chamber with the level of detail and accuracy appropriate to the preliminary design phase. It addresses the operating characteristics and dimensioning of some thrust chamber elements through a set of equations and parameters, which include thrust or propellant characteristics. The model degree of sophistication was adjusted to the requirements of the Project Life Cycle Phase B, while also enabling quick analysis of new configurations from changes in initial project parameters.
Download or read book Rockets Using Liquid Oxygen written by Adolf Busemann and published by BiblioGov. This book was released on 2013-07 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: It is my task to discuss rocket propulsion using liquid oxygen and my treatment must be highly condensed for the ideas and experiments pertaining to this classic type of rocket are so numerous that one could occupy a whole morning with a detailed presentation. First, with regard to oxygen itself as compared with competing oxygen carriers, it is known that the liquid state of oxygen, in spite of the low boiling point, is more advantageous than the gaseous form of oxygen in pressure tanks, therefore only liquid oxygen need be compared with the oxygen carriers. The advantages of liquid oxygen are absolute purity and unlimited availability at relatively small cost in energy. The disadvantages are those arising from the impossibility of absolute isolation from heat; consequently, allowance must always be made for a certain degree of vaporization and only vented vessels can be used for storage and transportation. This necessity alone eliminates many fields of application, for example, at the front lines. In addition, liquid oxygen has a lower specific weight than other oxygen carriers, therefore many accessories become relatively larger and heavier in the case of an oxygen rocket, for example, the supply tanks and the pumps. The advantages thus become effective only in those cases where definitely scheduled operation and a large ground organization are possible and when the flight requires a great concentration of energy relative to weight. With the aim of brevity, a diagram of an oxygen rocket will be presented and the problem of various component parts that receive particularly thorough investigation in this classic case but which are also often applicable to other rocket types will be referred to.
Download or read book National Altitude Rocket Test Facilities written by J. A. Suddreth and published by . This book was released on 1964 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: The necessity for experimental verification of rocket-engine performance at altitude or near-space conditions has long been recognized in the aerospace industry. Recent spacecraft rocket-engine research and development trends toward higher area ratios, advanced nozzle concepts, and nonequilibrium flow conside ations have made altitude simulation a requirement of development pro- grams. Recause the need for information regarding the capabilities and char- acteristics of altitude test facilities that are suitable for l%id-rocket%- engine operation was recognized, this survey was compiled with the help of representatives of industry and government agencies;% % INTROPUCTION The advent of upper-stage and spacecraft engine-vehicle development pro- grams along with the need for more rigorous performance and reliability data justified the construction of a number of altitude test facilities. The test capabilities of these facilities range from small attitude-control engines to large upper-stage engines. The altitude-simulating systems include simple diffusers coupled to the engine nozzle exit (fig. 1), steam ejector coupled to the engine-driven diffuser (fig. 2), and pumped environmental chambers coupled to a diffuser or ejector system for use during engine firing (fig. 3). Several techniques for vacuum generation exist. In addition to the conventional sys- tems of mechanical pumps and steam boilers for stem% ejectors, there are semi- portable liquid-propellant-driven steam generators.
Download or read book Modeling of the Break up of Liquid Oxygen Droplets for Application in a Cryogenic Rocket Engine Simulation Code written by Emmanuel Bodele and published by . This book was released on 2002 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Orbital Transfer Vehicle Oxygen Turbopump Technology Volume 3 written by National Aeronaut Administration (Nasa) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-10 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report covers the work done in preparation for a liquid oxygen rocket engine turbopump test utilizing high pressure hot oxygen gas for the turbine drive. The turbopump (TPA) is designed to operate with 400 F oxygen turbine drive gas. The goal of this test program was to demonstrate the successful operation of the TPA under simulated engine conditions including the hot oxygen turbine drive. This testing follows a highly successful series of tests pumping liquid oxygen with gaseous nitrogen as the turbine drive gas. That testing included starting of the TPA with no assist to the hydrostatic bearing. The bearing start entailed a rubbing start until the pump generated enough pressure to support the bearing. The articulating, self-centering hydrostatic bearing exhibited no bearing load or stability problems. The TPA was refurbished for the hot gas drive tests and facility work was begun, but unfortunately funding cuts prohibited the actual testing. Urke, Robert L. Unspecified Center...
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 High pressure Calorimeter Chamber Tests for Liquid Oxygen kerosene LOX RP 1 Rocket Combustion written by Philip A. Masters and published by . This book was released on 1988 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book High pressure Calorimeter Chamber Tests for Liquid Oxygen kerosene LOX RP 1 Rocket Combustion written by Philip A. Masters and published by . This book was released on 1988 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Spinoff written by and published by . This book was released on 1982 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Patent Abstracts Bibliography written by United States. National Aeronautics and Space Administration. Scientific and Technical Information Office and published by . This book was released on 1972 with total page 396 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Nuclear Energy written by and published by . This book was released on 1962 with total page 452 pages. Available in PDF, EPUB and Kindle. Book excerpt:
