Like-Doublet Injectors: the Effects of Varying the Impingement Distance
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Project Number: JMW-USC1
Project Number: JMW-USC1 Department of Social Science and Policy Studies THE FUTURE OF UNMANNED SPACE: A SPECULATIVE ANALYSIS OF THE COMMERCIAL MARKET An Interactive Qualifying Project Report: Submitted to the Faculty of the WORCESTER POLYTECHNIC INSTITUTE in partial fulfillment of the requirements for the Degree of Bachelor of Science by ______________________________ Peter Brayshaw ______________________________ Brooks Farnham ______________________________ Jon Leslie December 16, 2004 _____________________________ ________________________________ Professor John M. Wilkes, Advisor Professor Peter Campisano, Co-Advisor Abstract: This report is one of many which deal with the unmanned space race. It is a prediction of who will have the greatest competitive advantage in the commercial market over the next 25 years, based on historical analogy. Background information on Russia, China, Japan, the United States and the European Space Agency, including the launch vehicles and launch services each provides, is covered. The new prospect of space platforms is also investigated. 2 Table of Contents Abstract: ...................................................................................................... 2 Table of Contents ......................................................................................... 3 Introduction ................................................................................................. 5 Literature Review ...................................................................................... 5 Project -
Einicke Diplom.Pdf
Zum Erlangen des akademischen Grades DIPLOMINGENIEUR (Dipl.-Ing.) Betreuer: Dr. Christian Bach Verantwortlicher Hochschullehrer: Prof. Dr. techn. Martin Tajmar Tag der Einreichung: 20.04.2021 Erster Gutachter: Prof. Dr. techn. Martin Tajmar Zweiter Gutachter: Dr. Christian Bach Hiermit erkläre ich, dass ich die von mir dem Institut für Luft-und Raumfahrttechnik der Fakultät Maschinenwesen eingereichte Diplomarbeit zum Thema Mischungsverhältnis- und Brennkammerdruckregelung eines Expander-Bleed Raketentriebwerks mit Reinforcement Learning (Mixture Ratio and Combustion Chamber Pressure Control of an Expander-Bleed Rocket Engine with Reinforcement Learning) selbstständig verfasst und keine anderen als die angegebenen Quellen und Hilfsmittel benutzt sowie Zitate kenntlich gemacht habe. Berlin, 20.04.2021 Karina Einicke Contents Nomenclature iv Acronyms vii 1. Introduction 1 1.1. Motivation . .1 1.2. Objectives and Approach . .2 2. Fundamentals of Liquid Rocket Engines 3 2.1. Control Loops . .5 2.1.1. Open-Loop Control . .5 2.1.2. Closed-Loop Control . .5 2.1.3. Reusable Liquid Rocket Engine Control . .6 2.2. Control Valves . .8 2.2.1. Flow Characteristics . .9 2.2.2. Valve Types . .9 2.3. Liquid Rocket Engine Control: Historical Background . 11 2.4. Summary . 13 3. LUMEN 15 3.1. LUMEN Components . 15 3.2. Operating Points . 17 3.3. EcosimPro/ESPSS Model . 18 3.3.1. LUMEN System Analysis . 21 3.3.2. LUMEN System Validation . 26 3.4. Summary . 27 4. Reinforcement Learning 28 4.1. Fundamentals of Reinforcement Learning . 28 4.2. Reinforcement Learning Algorithms . 31 4.2.1. Model-based and Model-free Reinforcement Learning . 31 4.2.2. Policy Optimization . -
Atomization of Viscous Fluids Using Counterflow Nozzle
Atomization of Viscous Fluids using Counterflow Nozzle A THESIS SUBMITTED TO THE FACULTY OF THE GRADUATE SCHOOL OF THE UNIVERSITY OF MINNESOTA BY Roshan Rangarajan IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF SCIENCE Prof.Vinod Srinivasan August, 2020 c Roshan Rangarajan 2020 ALL RIGHTS RESERVED Acknowledgements I would like to express my sincere gratitude to my academic advisor, Prof.V.Srinivasan for his continuous support throughout this pursuit. His consistent motivation guided me during the course of this rigorous experimental effort. He helped instill a deep sense of work ethic and discipline towards academic research. In addition, I would like to thank Prof.Strykowski (ME Dept, University of Minnesota- Twin Cities) and Prof.Hoxie (ME Dept, University of Minnesota-Duluth) for their en- gaging technical insights into my present work. In particular, I was able to develop a sound understanding of techniques used in Image processing through my interactions with Eric and Prof.Hoxie at UMN-Duluth. I would like to thank my fellow lab mates Akash, Ian, Chinmayi, Manish, Sankar, Ankit, Peter and Amber for simulating discussions and sleepless nights before important deadlines. Research becomes not just interesting but also fun when you have the right minds around. Besides my advisor, I would like to thank Prof.Hogan and Prof.Ramaswamy for their time and encouragement in this work. i Dedication Parents and my sister for always believing in me. ii Abstract In the present work, we study the enhanced atomization of viscous liquids by using a novel twin-fluid atomizer. A two-phase mixing region is developed within the nozzle us- ing counterflow configuration by supplying air and liquid streams in opposite directions. -
Design of a 500 Lbf Liquid Oxygen and Liquid Methane Rocket Engine for Suborbital Flight Jesus Eduardo Trillo University of Texas at El Paso, [email protected]
University of Texas at El Paso DigitalCommons@UTEP Open Access Theses & Dissertations 2016-01-01 Design Of A 500 Lbf Liquid Oxygen And Liquid Methane Rocket Engine For Suborbital Flight Jesus Eduardo Trillo University of Texas at El Paso, [email protected] Follow this and additional works at: https://digitalcommons.utep.edu/open_etd Part of the Aerospace Engineering Commons, and the Mechanical Engineering Commons Recommended Citation Trillo, Jesus Eduardo, "Design Of A 500 Lbf Liquid Oxygen And Liquid Methane Rocket Engine For Suborbital Flight" (2016). Open Access Theses & Dissertations. 767. https://digitalcommons.utep.edu/open_etd/767 This is brought to you for free and open access by DigitalCommons@UTEP. It has been accepted for inclusion in Open Access Theses & Dissertations by an authorized administrator of DigitalCommons@UTEP. For more information, please contact [email protected]. DESIGN OF A 500 LBF LIQUID OXYGEN AND LIQUID METHANE ROCKET ENGINE FOR SUBORBITAL FLIGHT JESUS EDUARDO TRILLO Master’s Program in Mechanical Engineering APPROVED: Ahsan Choudhuri, Ph.D., Chair Norman Love, Ph.D. Luis Rene Contreras, Ph.D. Charles H. Ambler, Ph.D. Dean of the Graduate School Copyright © by Jesus Eduardo Trillo 2016 DESIGN OF A 500 LBF LIQUID OXYGEN AND LIQUID METHANE ROCKET ENGINE FOR SUBORBITAL FLIGHT by JESUS EDUARDO TRILLO, B.S.ME THESIS Presented to the Faculty of the Graduate School of The University of Texas at El Paso in Partial Fulfillment of the Requirements for the Degree of MASTER OF SCIENCE Department of Mechanical Engineering THE UNIVERSITY OF TEXAS AT EL PASO December 2016 Acknowledgements Foremost, I would like to express my sincere gratitude to my advisor Dr. -
Laboratory Experiments on Rain-Driven Convection: Implications for Planetary Dynamos Peter Olson, Maylis Landeau, Benjamin Hirsh
Laboratory experiments on rain-driven convection: Implications for planetary dynamos Peter Olson, Maylis Landeau, Benjamin Hirsh To cite this version: Peter Olson, Maylis Landeau, Benjamin Hirsh. Laboratory experiments on rain-driven convection: Implications for planetary dynamos. Earth and Planetary Science Letters, Elsevier, 2017, 457, pp.403- 411. 10.1016/j.epsl.2016.10.015. hal-03271246 HAL Id: hal-03271246 https://hal.archives-ouvertes.fr/hal-03271246 Submitted on 25 Jun 2021 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. 1 Laboratory experiments on rain-driven convection: 2 implications for planetary dynamos 3 Peter Olson*, Maylis Landeau, & Benjamin H. Hirsh Department of Earth & Planetary Sciences Johns Hopkins University, Baltimore, MD 21218 4 August 22, 2016 5 Abstract 6 Compositional convection driven by precipitating solids or immiscible liquids has been 7 invoked as a dynamo mechanism in planets and satellites throughout the solar system, 8 including Mercury, Ganymede, and the Earth. Here we report laboratory experiments 9 on turbulent rain-driven convection, analogs for the flows generated by precipitation 10 within planetary fluid interiors. We subject a two-layer fluid to a uniform intensity 11 rainfall, in which the rain is immiscible in the upper layer and miscible in the lower 12 layer. -
Inkjet-Printed Light-Emitting Devices: Applying Inkjet Microfabrication to Multilayer Electronics
Inkjet-Printed Light-Emitting Devices: Applying Inkjet Microfabrication to Multilayer Electronics by Peter D. Angelo A thesis submitted in conformity with the requirements for the degree of Doctor of Philosophy Department of Chemical Engineering & Applied Chemistry University of Toronto Copyright by Peter David Angelo 2013 Inkjet-Printed Light-Emitting Devices: Applying Inkjet Microfabrication to Multilayer Electronics Peter D. Angelo Doctor of Philosophy Department of Chemical Engineering & Applied Chemistry University of Toronto 2013 Abstract This work presents a novel means of producing thin-film light-emitting devices, functioning according to the principle of electroluminescence, using an inkjet printing technique. This study represents the first report of a light-emitting device deposited completely by inkjet printing. An electroluminescent species, doped zinc sulfide, was incorporated into a polymeric matrix and deposited by piezoelectric inkjet printing. The layer was printed over other printed layers including electrodes composed of the conductive polymer poly(3,4-ethylenedioxythiophene), doped with poly(styrenesulfonate) (PEDOT:PSS) and single-walled carbon nanotubes, and in certain device structures, an insulating species, barium titanate, in an insulating polymer binder. The materials used were all suitable for deposition and curing at low to moderate (<150°C) temperatures and atmospheric pressure, allowing for the use of polymers or paper as supportive substrates for the devices, and greatly facilitating the fabrication process. ii The deposition of a completely inkjet-printed light-emitting device has hitherto been unreported. When ZnS has been used as the emitter, solution-processed layers have been prepared by spin- coating, and never by inkjet printing. Furthermore, the utilization of the low-temperature- processed PEDOT:PSS/nanotube composite for both electrodes has not yet been reported. -
The European Launchers Between Commerce and Geopolitics
The European Launchers between Commerce and Geopolitics Report 56 March 2016 Marco Aliberti Matteo Tugnoli Short title: ESPI Report 56 ISSN: 2218-0931 (print), 2076-6688 (online) Published in March 2016 Editor and publisher: European Space Policy Institute, ESPI Schwarzenbergplatz 6 • 1030 Vienna • Austria http://www.espi.or.at Tel. +43 1 7181118-0; Fax -99 Rights reserved – No part of this report may be reproduced or transmitted in any form or for any purpose with- out permission from ESPI. Citations and extracts to be published by other means are subject to mentioning “Source: ESPI Report 56; March 2016. All rights reserved” and sample transmission to ESPI before publishing. ESPI is not responsible for any losses, injury or damage caused to any person or property (including under contract, by negligence, product liability or otherwise) whether they may be direct or indirect, special, inciden- tal or consequential, resulting from the information contained in this publication. Design: Panthera.cc ESPI Report 56 2 March 2016 The European Launchers between Commerce and Geopolitics Table of Contents Executive Summary 5 1. Introduction 10 1.1 Access to Space at the Nexus of Commerce and Geopolitics 10 1.2 Objectives of the Report 12 1.3 Methodology and Structure 12 2. Access to Space in Europe 14 2.1 European Launchers: from Political Autonomy to Market Dominance 14 2.1.1 The Quest for European Independent Access to Space 14 2.1.3 European Launchers: the Current Family 16 2.1.3 The Working System: Launcher Strategy, Development and Exploitation 19 2.2 Preparing for the Future: the 2014 ESA Ministerial Council 22 2.2.1 The Path to the Ministerial 22 2.2.2 A Look at Europe’s Future Launchers and Infrastructure 26 2.2.3 A Revolution in Governance 30 3. -
UCLA Electronic Theses and Dissertations
UCLA UCLA Electronic Theses and Dissertations Title Minimizing hydraulic losses in additively-manufactured swirl coaxial rocket injectors via analysis-driven design methods Permalink https://escholarship.org/uc/item/7n51c078 Author Morrow, David Publication Date 2020 Peer reviewed|Thesis/dissertation eScholarship.org Powered by the California Digital Library University of California UNIVERSITY OF CALIFORNIA Los Angeles Minimizing hydraulic losses in additively-manufactured swirl coaxial rocket injectors via analysis-driven design methods A thesis submitted in partial satisfaction of the requirements for the degree Master of Science in Aerospace Engineering by David Morrow 2020 c Copyright by David Morrow 2020 ABSTRACT OF THE THESIS Minimizing hydraulic losses in additively-manufactured swirl coaxial rocket injectors via analysis-driven design methods by David Morrow Master of Science in Aerospace Engineering University of California, Los Angeles, 2020 Professor Raymond M. Spearrin, Chair Additive manufacturing (AM) has matured significantly over the past decade and become a highly attractive tool for reducing manufacturing complexity and removing traditional de- sign constraints. This is particularly desirable for rocket combustion devices which often feature hundreds of individual parts with precise tolerances. The degree to which AM can be used to improve combustion device performance, however, has been less rigorously ex- plored. In this work, hydraulic performance impacts associated with and enabled by AM are assessed for a liquid bi-propellant swirl coaxial injector. Specifically, a single-element liquid oxygen/kerosene injector based on a canonical design was manufactured from inconel using Direct Metal Laser Sintering at two different coaxial recess depths. Cold-flow testing for the as-manufactured baseline injector found a reduction in the designed discharge coefficients, which is primarily attributed to increased surface roughness inherent in the AM process. -
Ideas Into Hardware: a History of the Rocket Engine Test Facility
Ideas Into Hardware IDEAS INTO HARDWARE A History of the Rocket Engine Test Facility at the NASA Glenn Research Center Virginia P. Dawson National Aeronautics and Space Administration NASA Glen Research Center Cleveland, Ohio 2004 This document was generated for the NASA Glenn Research Center, in accor- dance with a Memorandum of Agreement among the Federal Aviation Administration, National Aeronautics and Space Administration (NASA), The Ohio State Historic Preservation Officer, and the Advisory Council on Historic Preservation. The City of Cleveland’s goal to expand the Cleveland Hopkins International Airport required the NASA Glenn Research Center’s Rocket Engine Test Facility, located adjacent to the airport, to be removed before this expansion could be realized. To mitigate the removal of this registered National Historic Landmark, the National Park Service stipulated that the Rocket Engine Test Facility be documented to Level I standards of the Historic American Engineering Record (HAER). This history project was initiated to fulfill and supplement that requirement. Produced by History Enterprises, Inc. Cover and text design by Diana Dickson. Library of Congress Cataloging-in-Publication Data Dawson, Virginia P. (Virginia Parker) —Ideas into hardware : a history of NASA’s Rocket Engine Test Facility / by Virginia P. Dawson. ——p.——cm. —Includes bibliographical references. —1. Rocket engines—Research—United States—History.—2.—United States. National Aeronautics and Space Administration—History.—I. Title. TL781.8.U5D38 2004 621.43'56'072077132—dc22 2004024041 Table of Contents Introduction / v 1. Carving Out a Niche / 1 2. RETF: Complex, Versatile, Unique / 37 3. Combustion Instability and Other Apollo Era Challenges, 1960s / 64 4. -
Extensions to the Time Lag Models for Practical Application to Rocket
The Pennsylvania State University The Graduate School College of Engineering EXTENSIONS TO THE TIME LAG MODELS FOR PRACTICAL APPLICATION TO ROCKET ENGINE STABILITY DESIGN A Dissertation in Mechanical Engineering by Matthew J. Casiano © 2010 Matthew J. Casiano Submitted in Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy August 2010 The dissertation of Matthew J. Casiano was reviewed and approved* by the following: Domenic A. Santavicca Professor of Mechanical Engineering Co-chair of Committee Vigor Yang Adjunct Professor of Mechanical Engineering Dissertation Advisor Co-chair of Committee Richard A. Yetter Professor of Mechanical Engineering André L. Boehman Professor of Fuel Science and Materials Science and Engineering Tomas E. Nesman Aerospace Engineer at NASA Marshall Space Flight Center Special Member Karen A. Thole Professor of Aerospace Engineering Head of the Department of Mechanical and Nuclear Engineering *Signatures are on file in the Graduate School iii ABSTRACT The combustion instability problem in liquid-propellant rocket engines (LREs) has remained a tremendous challenge since their discovery in the 1930s. Improvements are usually made in solving the combustion instability problem primarily using computational fluid dynamics (CFD) and also by testing demonstrator engines. Another approach is to use analytical models. Analytical models can be used such that design, redesign, or improvement of an engine system is feasible in a relatively short period of time. Improvements to the analytical models can greatly aid in design efforts. A thorough literature review is first conducted on liquid-propellant rocket engine (LRE) throttling. Throttling is usually studied in terms of vehicle descent or ballistic missile control however there are many other cases where throttling is important. -
Scenarios of Drop Deformation and Breakup in Sprays T´Imea Kékesi
Scenarios of drop deformation and breakup in sprays by T´ımeaK´ekesi September 2017 Technical Report Royal Institute of Technology Department of Mechanics SE-100 44 Stockholm, Sweden Akademisk avhandling som med tillst˚andav Kungliga Tekniska H¨ogskolan i Stockholm framl¨aggestill offentlig granskning f¨oravl¨aggandeav teknologie dok- torsexamen fredagen den 15 september 2017 kl 10.15 i D3, Lindstedtsv¨agen5, Kungliga Tekniska H¨ogskolan, Stockholm. TRITA-MEK Technical report 2017:10 ISSN 0348-467X ISRN KTH/MEK/TR-2017/10-SE ISBN 978-91-7729-500-6 c T. K´ekesi 2017 Tryckt av Universitetsservice US-AB, Stockholm 2017 Scenarios of drop deformation and breakup in sprays T´ımeaK´ekesi Linn´eFLOW Centre, KTH Mechanics, The Royal Institute of Technology SE-100 44 Stockholm, Sweden Abstract Sprays are used in a wide range of engineering applications, in the food and pharmaceutical industry in order to produce certain materials in the desired powder-form, or in internal combustion engines where liquid fuel is injected and atomized in order to obtain the required air/fuel mixture for ideal combustion. The optimization of such processes requires the detailed understanding of the breakup of liquid structures. In this work, we focus on the secondary breakup of medium size liquid drops that are the result of primary breakup at earlier stages of the breakup process, and that are subject to further breakup. The fragmentation of such drops is determined by the competing disruptive (pressure and viscous) and cohesive (surface tension) forces. In order to gain a deeper understanding on the dynamics of the deformation and breakup of such drops, numerical simulations on single drops in uniform and shear flows, and on dual drops in uniform flows have been performed employing a Volume of Fluid (VOF) method. -
Expendable Launch Vehicle Propulsion
N91-28199 NASA Space Transportation Propulsion Technology Symposium EXPENDABLE LAUNCH VEHICLE PROPULSION June 1990 P.N. Fuller, Chairman COMSTAC Technology & Innovation Working Group 131 CONTENTS This presentation will review the current status of the U.S. ELV fleet, the international competition, and the propulsion technology of both domestic and foreign expendable launch vehicles. The ELV propulsion technology areas where research, development, and demonstration are most needed will be identified. These propulsion technology recommendations are based on the work performed by the Commercial Space Transportation Advisory Committee (COMSTAC), an industry panel established by the Department of Transportation. Expendable Launch Vehicle Propulsion Contents • Introduction • COMSTAC • Domestic ELV Launch Fleet • Foreign ELV Launch Fleet . ELV Propulsion Systems • ELV Propulsion Technology Needs • Conclusions 132 INTRODUCTION There have been extensive changes in America's space launch architecture since the Challenger tragedy occurred in January 1986. The major impact has been the revival of the U.S. Expendable Launch Vehicle (ELV) fleet in response to changes in National Space Launch policy. The NASA and the Air Force have adoped use of a "Mixed Fleet" of space launchers, and have prohibited.the Shuttle Space Transportation System (STS) from competing for launch of commercial payloads. The availability of this diverse stable of launch systems has helped to assure access to space for critical payloads. The foundation for a commercial launch industry has been established in the United States for the Delta, Atlas, and Titan III launch systems. The NASA and Air Force have provided a base for a commercial launch industry by long-range procurements of ELV launch services, and access to government facilities.