전기펌프사이클 엔진 등 민간분야 우주발사체 신기술고찰 New Technologies of Space Launch Vehicles Includin
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First Level Design and System Design of Janus Liquid Oxygen-Liquid Methane Lander Jahir Fernandez University of Texas at El Paso, J [email protected]
University of Texas at El Paso DigitalCommons@UTEP Open Access Theses & Dissertations 2017-01-01 First Level Design And System Design Of Janus Liquid Oxygen-Liquid Methane Lander Jahir Fernandez University of Texas at El Paso, [email protected] Follow this and additional works at: https://digitalcommons.utep.edu/open_etd Part of the Mechanical Engineering Commons Recommended Citation Fernandez, Jahir, "First Level Design And System Design Of Janus Liquid Oxygen-Liquid Methane Lander" (2017). Open Access Theses & Dissertations. 444. https://digitalcommons.utep.edu/open_etd/444 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]. FIRST LEVEL DESIGN AND SYSTEM DESIGN OF JANUS LIQUID OXYGEN-LIQUID METHANE LANDER JAHIR FERNANDEZ Master’s Program in Mechanical Engineering APPROVED: Ahsan Choudhuri, Ph.D., Chair John F. Chessa, Ph.D., Co-chair Luis Rene Contreras, Ph.D. Charles H. Ambler, Ph.D. Dean of the Graduate School Copyright © By Jahir Fernandez 2017 FIRST LEVEL DESIGN AND SYSTEM DESIGN OF JANUS LIQUID OXYGEN-LIQUID METHANE LANDER By JAHIR FERNANDEZ, B.S. MECHANICAL ENGINEERIN 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 2017 Acknowledgements I would like to thank Dr. Ahsan Choudhuri for the opportunity to work at the cSETR. It has been an amazing experience working at the center, where the research has opened many doors for me and through which I was able to intern with NASA at Marshall Space Flight Center. -
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 . -
액체로켓 메탄엔진 개발동향 및 시사점 Development Trends of Liquid
Journal of the Korean Society of Propulsion Engineers Vol. 25, No. 2, pp. 119-143, 2021 119 Technical Paper DOI: https://doi.org/10.6108/KSPE.2021.25.2.119 액체로켓 메탄엔진 개발동향 및 시사점 임병직 a, * ㆍ 김철웅 a⋅ 이금오 a ㆍ 이기주 a ㆍ 박재성 a ㆍ 안규복 b ㆍ 남궁혁준 c ㆍ 윤영빈 d Development Trends of Liquid Methane Rocket Engine and Implications Byoungjik Lim a, * ㆍ Cheulwoong Kim a⋅ Keum-Oh Lee a ㆍ Keejoo Lee a ㆍ Jaesung Park a ㆍ Kyubok Ahn b ㆍ Hyuck-Joon Namkoung c ㆍ Youngbin Yoon d a Future Launcher R&D Program Office, Korea Aerospace Research Institute, Korea b School of Mechanical Engineering, Chungbuk National University, Korea c Guided Munitions Team, Hyundai Rotem, Korea d Department of Aerospace Engineering, Seoul National University, Korea * Corresponding author. E-mail: [email protected] ABSTRACT Selecting liquid methane as fuel is a prevailing trend for recent rocket engine developments around the world, triggered by its affordability, reusability, storability for deep space exploration, and prospect for in-situ resource utilization. Given years of time required for acquiring a new rocket engine, a national-level R&D program to develop a methane engine is highly desirable at the earliest opportunity in order to catch up with this worldwide trend towards reusing launch vehicles for competitiveness and mission flexibility. In light of the monumental cost associated with development, fabrication, and testing of a booster stage engine, it is strategically a prudent choice to start with a low-thrust engine and build up space application cases. -
LEO on the Cheap Methods for Achieving Drastic Reductions in Space Launch Costs
Research Report No. AU-ARI-93-8 LEO on the Cheap Methods for Achieving Drastic Reductions in Space Launch Costs JOHN R. LONDON III Lt Col, USAF ARI Command-Sponsored Research Fellow Air Force Materiel Command Air University Press Maxwell Air Force Base, Alabama October 1994 Disclaimer This publication was produced in the Department of Defense school environment in the interest of academic freedom and the advancement of national defense-related concepts. The views ex- pressed in this publication are those of the author and do not reflect the official policy or position of the Department of Defense or the United States government. This publication has been reviewed by security and policy review authorities and is cleared for public release. Contents Chapter Page DISCLAIMER ............................ ii FOREWORD ............................. xv ABOUTTHEAUTHOR ....................... xvii PREFACE .............................. xix ACKNOWLEDGMENTS ...................... xxi INTRODUCTION .......................... xxu Study Boundaries ......................... xxvii Some Definitions .......................... xxvii Notes ................................ xxviii 1 THE PROBLEM.. ......................... 1 Expensive Transportation with Broad Impacts ......... 1 Current Launch Vehicle Cost Range .............. 1 Unique Transportation Requirements ............. 2 Establishing the Cost per Launch of Expendables ....... 2 Establishing the Cost per Launch of the Shuttle ........ 2 Representative Vehicle Costs ................... 4 Pegasus ............................ -
Jpc-Final-Program.Pdf
49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit (JPC) Advancing Propulsion Capabilities in a New Fiscal Reality 14–17 July 2013 San Jose Convention Center 11th International Energy Conversion San Jose, California Engineering Conference (IECEC) FINAL PROGRAM www.aiaa.org/jpc2013 www.iecec.org #aiaaPropEnergy www.aiaa.org/jpc2013 • www.iecec.org 1 #aiaaPropEnergy GET YOUR CONFERENCE INFO ON THE GO! Download the FREE Conference Mobile App FEATURES • Browse Program – View the program at your fingertips • My Itinerary – Create your own conference schedule • Conference Info – Including special events • Take Notes – Take notes during sessions • Venue Map – San Jose Convention Center • City Map – See the surrounding area • Connect to Twitter – Tweet about what you’re doing and who you’re meeting with #aiaaPropEnergy HOW TO DOWNLOAD Any version can be run without an active Internet connection! You can also sync an Compatible with itinerary you created online with the app by entering your unique itinerary name. iPhone/iPad, MyItinerary Mobile App MyItinerary Web App Android, and • For optimal use, we recommend • For optimal use, we recommend: rd BlackBerry! iPhone 3GS, iPod Touch (3 s iPhone 3GS, iPod Touch (3rd generation), iPad iOS 4.0, or later generation), iPad iOS 4.0, • Download the MyItinerary app by or later searching for “ScholarOne” in the s Most mobile devices using Android App Store directly from your mobile 2.2 or later with the default browser device. Or, access the link below or scan the QR code to access the iTunes s BlackBerry Torch or later device Sponsored by: page for the app. -
Forever Remembered
July 2015 Vol. 2 No. 7 National Aeronautics and Space Administration KENNEDY SPACE CENTER’S magazine FOREVER REMEMBERED Earth Solar Aeronautics Mars Technology Right ISS System & Research Now Beyond NASA’S National Aeronautics and Space Administration LAUNCH KENNEDY SPACE CENTER’S SCHEDULE SPACEPORT MAGAZINE Date: July 3, 12:55 a.m. EDT Mission: Progress 60P Cargo Craft CONTENTS Description: In early July, the Progress 60P resupply vehicle — 4 �������������������Solemn shuttle exhibit shares enduring lessons an automated, unpiloted version of the Soyuz spacecraft that is used to ����������������Flyby will provide best ever view of Pluto 10 bring supplies and fuel — launches 14 ����������������New Horizons spacecraft hones in on Pluto to the International Space Station. http://go.nasa.gov/1HUAYbO 24 ����������������Firing Room 4 used for RESOLVE mission simulation Date: July 22, 5:02 p.m. EDT 28 ����������������SpaceX, NASA will rebound from CRS-7 loss Mission: Expedition 44 Launch to 29 ����������������Backup docking adapter to replace lost IDA-1 the ISS Description: In late July, Kjell SHUN FUJIMURA 31 ����������������Thermal Protection System Facility keeping up Lindgren of NASA, Kimiya Yui of JAXA and Oleg Kononenko of am an education specialist in the Education Projects and 35 ����������������New crew access tower takes shape at Cape Roscosmos launch aboard a Soyuz I Youth Engagement Office. I work to inspire students to pursue science, technology, engineering, mathematics, or 36 ����������������Innovative thinking converts repair site into garden spacecraft from the Baikonur Cosmodrome, Kazakhstan to the STEM, careers and with teachers to better integrate STEM 38 ����������������Proposals in for new class of launch services space station. -
Foundational Methane Propulsion Related Technology Efforts, and Challenges for Applications to Human Exploration Beyond Earth Orbit
https://ntrs.nasa.gov/search.jsp?R=20160006983 2019-07-23T15:36:47+00:00Z Foundational Methane Propulsion Related Technology Efforts, and Challenges for Applications to Human Exploration Beyond Earth Orbit SPACE PROPULSION 2016 MARRIOTT PARK HOTEL, ROME, ITALY / 2-6 May 2016 Thomas Brown Mark Klem Patrick McRight NASA Engineering and Safety Center Propulsion Division Propulsion Department NASA Marshall Space Flight Center NASA Glenn Research Center NASA Marshall Space Flight Center Huntsville, AL 35812 Cleveland, Ohio 44135 Huntsville, AL 35812 Agenda • Introduction • Background • Needs for Beyond Earth Orbit (BEO) human exploration • LOX/CH4 Igniters • Reaction Control System (RCS) Thrusters • Large (870 – 1000 lbf) LOX/LH2 and LOX/Ethanol thrusters (TRW & Aerojet) • 100 lbf LOX/CH4 thrusters (Aerojet & Northrop Grumman) • Main Engine Injector Parametric Testing • Pressure Fed Main Engine Efforts • 7500 lbf LOX/CH4 (XCOR & KT Engineering) • 5500 lbf LOX/CH4 (Aerojet) • Additively Manufactured 4K Regeneratively Cooled Engine • Pump Fed Main Engine Efforts • Common Extensible Cryogenic Engine – LOX/LH2 throttle-able engine • 7000 lbf LOX/LH2 (TRW/Northrop Grumman) • 7000 lbf LOX/LH2 two stage injector • Current efforts with the Additive Manufacturing Demonstration engine • Cryogenic Fluid Management (CFM) and Distribution • Integrated Systems Demonstration • Challenges for future Human Exploration • Summary and Conclusions 2 Introduction Background • Human, beyond earth orbit, exploration architecture studies have identified Methane/Oxygen -
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. -
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. -
Aerospace America
June 2016 Ambition: Europa NASA might find more than life in this moon’s ocean. It could find a new strategy for exploring other worlds. Page 22 Oklahoma’s Bridenstine on climate, term limits/8 20 years of Design/Build/Fly/30 Smart bombs for wildfires/38 A PUBLICATION OF THE AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS • COVER-0616ƒ.indd 1 5/19/16 1:18 PM 2O16 13 –17 JUNE 2016 WASHINGTON, D.C. AIAA AVIATION 2016 is the only aviation Exclusive Premier Sponsor event that covers the entire integrated spectrum of aviation business and technology. Confirmed Speakers Charles F. Michimasa Maj. Gen. Mike Delaney John S. Richard A. Clarke Bolden Jr. Fujino Joe Engle Langford Vice President, Chairman & CEO, Administrator, President & CEO, United States Air Airplane Chairman and Good Harbor NASA Honda Aircraft Force (Ret.) Development, Chief Executive Security Risk Company The Boeing Officer, Aurora Management, LLC Company Flight Sciences Corporation REGISTER TODAY! AIAA-AVIATION.ORG 16-1132 June 2016 DEPARTMENTS Page 16 EDITOR’S NOTEBOOK 2 Congress’s dynamic aerospace duo IN BRIEF 4 3D-printed drone; status change at Ames? smart repair manuals; Page 34 subscale aircraft CONVERSATION 8 Change agent for aerospace CASE STUDY 12 Preventing more MH370s ENGINEERING NOTEBOOK 16 Making a money saver OUT OF THE PAST 46 Page 4 CAREER OPPORTUNITIES 48 FEATURES AMBITION: EUROPA 22 Jupiter’s moon Europa could have life in the ocean under its shell. NASA came up with a step-by-step plan to find out. Then, along came a congressman from Texas. by Debra Werner Page 38 DESIGNING A WINNER 30 AIAA’s Design/Build/Fly contest gives college students a chance to pit their engineering smarts against international competitors in a remote-controlled aircraft flyoff.