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Considerations and Simulations About Pulse Detonation Engine
MATEC Web of Conferences 290, 04009 (2019) https://doi.org/10.1051/matecconf /2019290 04009 MSE 2019 Considerations and simulations about Pulse Detonation Engine Vasile Prisacariu1,*, Constantin Rotaru1, and Mihai Leonida Niculescu2 1Henri Coandă Air Force Academy, Aviation Department, Brașov, Romania 2INCAS, Aerodynamic Department, București, Romania Abstract. PDE propulsion can work from a subsonic regime to hypersonic regimes; this type of engine can have higher thermodynamic efficiency compared to other turbojet or turbofan engines due to the removal of rotating construction elements (compressors and turbines) that can reduce the mass and total cost of propulsion system. The PDE experimental researches focused on both the geometric configuration and the thermo- gas-dynamic flow aspects to prevent uncontrolled self-ignition. This article presents a series of numerical simulations on the functioning of PDE with hydrogen at supersonic regimens. Acronyms and symbols PDE pulse detonation engine AB PDE after burner pulse detonation engine DDT deflagration-to-detonation transition PDRE pulse detonation rocket engine ZDN Zel'dovich-von Neumann-Doering Mx, My Mach numbers p pressure v volume T temperature ρ density u1, u2 velocity h1, h2 enthalpy s1, s2 (S) entropy Vo,V∞ speed 1 INTRODUCTION Detonation is an effective means of burning a fuel mixture and transforming chemical energy into mechanical energy. However, this concept of running the propulsion systems involves difficulties both in rapidly achieving the fuel mixture at high speeds and in initiating and sustaining detonation in a controlled manner. PDE differs from conventional propulsion systems in two main aspects: it generates an intermittent pulse and produces high pressure increase in the combustion chamber, which also represents a major advantage of a PDE, see Figure 1. -
Nasa Tm X-1864 *
NASA TECHNICAL. • £HP2fKit NASA TM X-1864 * ... MEMORANDUM oo fe *' > ;ff f- •* '• . ;.*• f PROPULSION • FOR *MANN1D E30PLORATION-k '* *Of THE SOEAE " • » £ Moedkel • - " *' ' ' y Lem$ Research Center Cleveland, Qbt® NATIONAL AERONAUTICS AND SFACE ADMINISTRATION • WASHINGTON, D. €, * AUCUST 1969 NASA TM X-1864 PROPULSION SYSTEMS FOR MANNED EXPLORATION OF THE SOLAR SYSTEM By W. E. Moeckel Lewis Research Center Cleveland, Ohio NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the Clearinghouse for Federal Scientific and. Technical Information Springfield, Virginia 22151 - CFSTI price $3.00 ABSTRACT What propulsion systems are in sight for fast interplanetary travel? Only a few show promise of reducing trip times to values comparable to those of 16th century terrestrial expeditions. The first portion of this report relates planetary round-trip times to the performance parameters of two types of propulsion systems: type I is specific-impulse limited (with high thrust), and type n is specific-mass limited (with low thrust). The second part of the report discusses advanced propulsion concepts of both types and evaluates their limitations. The discussion includes nuclear-fission . rockets (solid, liquid, and gaseous core), nuclear-pulse propulsion, nuclear-electric rockets, and thermonuclear-fusion rockets. Particular attention is given to the last of these, because it is less familiar than the others. A general conclusion is that the more advanced systems, if they prove feasible, will reduce trip time to the near planets by factors of 3 to 5, and will make several outer planets accessible to manned exploration. PROPULSION SYSTEMS FOR MANNED EXPLORATION OF THE SOLAR SYSTEM* byW. E. Moeckel Lewis Research Center SUMMARY What propulsion systems are in sight for fast interplanetary travel? Only a few show promise of reducing trip times to values comparable to those of 16th century terrestrial expeditions. -
Pulsed Fusion Space Propulsion: Computational Ideal Magneto-Hydro Dynamics of a Magnetic Flux Compression Reaction Chamber
Pulsed Fusion Space Propulsion: Computational Ideal Magneto-Hydro Dynamics of a Magnetic Flux Compression Reaction Chamber G. Romanelli Master of Science Thesis Space Systems Engineering PULSED FUSION SPACE PROPULSION: COMPUTATIONAL IDEAL MAGNETO-HYDRO DYNAMICS OFA MAGNETIC FLUX COMPRESSION REACTION CHAMBER by Gherardo ROMANELLI to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Friday February 26, 2016 at 10:00 AM. Student number: 4299876 Thesis committee: Dr. A. Cervone, TU Delft, supervisor Prof. Dr. E. K. A. Gill, TU Delft Dr. Ir. E. Mooij, TU Delft Prof. A. Mignone, Politecnico di Torino An electronic version of this thesis is available at http://repository.tudelft.nl/. To boldly go where no one has gone before. James T. Kirk ACKNOWLEDGEMENTS First of all I would like to thank my supervisor Dr. A. Cervone who has always sup- ported me despite my “quite exotic” interests. He left me completely autonomous in shaping my thesis project, and still, was always there every time I needed help. Then, I would of course like to thank Prof. A. Mignone who decided to give his contribute to this seemingly crazy project of mine. His advice arrived just in time to give an happy ending to this story. Il ringraziamento più grande, però, va di certo alla mia famiglia. Alla mia mamma e a mio babbo, perché hanno sempre avuto fiducia in me e non hanno mai chiesto ragioni o spiegazioni alle mie scelte. Ai miei nonni, perché se di punto in bianco, un giorno di novembre ho deciso di intraprendere questa lunga strada verso l’Olanda, l’ho potuto fare anche per merito loro. -
In a Comprehensive New Test, the Emdrive Fails to Generate Any Thrust 7 April 2021, by Paul M
In a comprehensive new test, the EmDrive fails to generate any thrust 7 April 2021, by Paul M. Sutter conservation of momentum has been tested countless times over centuries—in fact, that principle forms the bedrock of almost every single theory of physics. So in essence, almost every time physics is tested, so is the conservation of momentum. The results of the Eagleworks experiment were not very strong. While the team claimed to measure a thrust, it wasn't statistically significant, and appeared to be a result of "cherry-picking"—the authors watching random fluctuations and waiting for the right time to report their results. But in the spirit of scientific replication, a team at the Dresden University of Technology led by Prof. Martin Tajmar rebuilt the Eagleworks experimental The EmDrive is a hypothetical rocket that setup. proponents claim can generate thrust with no exhaust. This would violate all known physics. In And they found squat. 2016, a team at NASA's Eagleworks lab claimed to measure thrust from an EmDrive device, the news Reporting their results in the Proceedings of Space of which caused quite a stir. The latest attempt to Propulsion Conference 2020, Prof. Tajmar said, replicate the shocking results has resulted in a "We found out that the cause of the 'thrust' was a simple answer: The Eagleworks measurement was thermal effect. For our tests, we used NASAs from heating of the engine mount, not any new EmDrive configuration from White et al. (which was physics. used at the Eagleworks laboratories, because it is best documented and the results were published in The EmDrive is a relatively simple device: It's an the Journal of Propulsion and Power.) empty cavity that isn't perfectly symmetrical. -
Investigation of Condensed and Early Stage Gas Phase Hypergolic Reactions Jacob Daniel Dennis Purdue University
Purdue University Purdue e-Pubs Open Access Dissertations Theses and Dissertations Fall 2014 Investigation of condensed and early stage gas phase hypergolic reactions Jacob Daniel Dennis Purdue University Follow this and additional works at: https://docs.lib.purdue.edu/open_access_dissertations Part of the Propulsion and Power Commons Recommended Citation Dennis, Jacob Daniel, "Investigation of condensed and early stage gas phase hypergolic reactions" (2014). Open Access Dissertations. 256. https://docs.lib.purdue.edu/open_access_dissertations/256 This document has been made available through Purdue e-Pubs, a service of the Purdue University Libraries. Please contact [email protected] for additional information. i INVESTIGATION OF CONDENSED AND EARLY STAGE GAS PHASE HYPERGOLIC REACTIONS A Dissertation Submitted to the Faculty of Purdue University by Jacob Daniel Dennis In Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy December 2014 Purdue University West Lafayette, Indiana ii To my parents, Jay and Susan Dennis, who have always pushed me to be the person they know I am capable of being. Also to my wife, Claresta Dennis, who not only tolerated me but suffered along with me throughout graduate school. I love you and am so proud of you! iii ACKNOWLEDGEMENTS I would like to express my sincere gratitude to my advisor, Dr. Timothée Pourpoint, for guiding me over the past four years and helping me become the researcher that I am today. In addition I would like to thank the rest of my PhD Committee for the insight and guidance. I would also like to acknowledge the help provided by my fellow graduate students who spent time with me in the lab: Travis Kubal, Yair Solomon, Robb Janesheski, Jordan Forness, Jonathan Chrzanowski, Jared Willits, and Jason Gabl. -
The SKYLON Spaceplane
The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration. -
Rocket Propulsion Fundamentals 2
https://ntrs.nasa.gov/search.jsp?R=20140002716 2019-08-29T14:36:45+00:00Z Liquid Propulsion Systems – Evolution & Advancements Launch Vehicle Propulsion & Systems LPTC Liquid Propulsion Technical Committee Rick Ballard Liquid Engine Systems Lead SLS Liquid Engines Office NASA / MSFC All rights reserved. No part of this publication may be reproduced, distributed, or transmitted, unless for course participation and to a paid course student, in any form or by any means, or stored in a database or retrieval system, without the prior written permission of AIAA and/or course instructor. Contact the American Institute of Aeronautics and Astronautics, Professional Development Program, Suite 500, 1801 Alexander Bell Drive, Reston, VA 20191-4344 Modules 1. Rocket Propulsion Fundamentals 2. LRE Applications 3. Liquid Propellants 4. Engine Power Cycles 5. Engine Components Module 1: Rocket Propulsion TOPICS Fundamentals • Thrust • Specific Impulse • Mixture Ratio • Isp vs. MR • Density vs. Isp • Propellant Mass vs. Volume Warning: Contents deal with math, • Area Ratio physics and thermodynamics. Be afraid…be very afraid… Terms A Area a Acceleration F Force (thrust) g Gravity constant (32.2 ft/sec2) I Impulse m Mass P Pressure Subscripts t Time a Ambient T Temperature c Chamber e Exit V Velocity o Initial state r Reaction ∆ Delta / Difference s Stagnation sp Specific ε Area Ratio t Throat or Total γ Ratio of specific heats Thrust (1/3) Rocket thrust can be explained using Newton’s 2nd and 3rd laws of motion. 2nd Law: a force applied to a body is equal to the mass of the body and its acceleration in the direction of the force. -
Study and Numerical Simulation of Unconventional Engine Technology
STUDY AND NUMERICAL SIMULATION OF UNCONVENTIONAL ENGINE TECHNOLOGY by ANJALI SHEKHAR B.E Aeronautical Engineering VTU, Karnataka, 2013 A thesis submitted in partial fulfillment of the requirements for the degree of Master of Science, Aerospace Engineering, College of Engineering and Applied Science, University of Cincinnati, Ohio 2018 Thesis Committee: Chair: Ephraim Gutmark, Ph.D. Member: Shaaban Abdallah, Ph.D. Member: Mark Turner, Sc.D. An Abstract of Study and Numerical Simulation of Unconventional Engine Technology by Anjali Shekhar Submitted to the Graduate Faculty as partial fulfillment of the requirements for the Master of Science Degree in Aerospace Engineering University of Cincinnati December 2018 The aim of this thesis is to understand the working of two unconventional aircraft propul- sion systems and to setup a two-dimensional transient simulation to analyze its operational mechanism. The air traffic has nearly increased by about 40% in past three decades and calls for alternative propulsion techniques to replace or support the current traditional propulsion methodology. In the light of current demand, the thesis draws motivation from renewed inter- est in two non-conventional propulsion techniques designed in the past and had not been given due importance due to various flaws/drawbacks associated. The thesis emphasizes on the work- ing of Von Ohains thermal compression engine and pulsejet combustors. Computational Fluid Dynamics is used in current study as it offers very high flexibility and can be modified easily to incorporate the required changes. Thermal Compression engine is a design suggested by Von Ohain in 1948. The engine works on the principle of pressure rise caused inside the engine which completely depends on the temperature of working fluid and independent of rotations per minute. -
MULTIPHYSICS DESIGN and SIMULATION of a TUNGSTEN-CERMET NUCLEAR THERMAL ROCKET a Thesis by BRAD APPEL Submitted to the Office O
MULTIPHYSICS DESIGN AND SIMULATION OF A TUNGSTEN-CERMET NUCLEAR THERMAL ROCKET A Thesis by BRAD APPEL Submitted to the Office of Graduate Studies of Texas A&M University in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE August 2012 Major Subject: Nuclear Engineering Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket Copyright 2012 Brad Appel ii MULTIPHYSICS DESIGN AND SIMULATION OF A TUNGSTEN-CERMET NUCLEAR THERMAL ROCKET A Thesis by BRAD APPEL Submitted to the Office of Graduate Studies of Texas A&M University in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE Approved by: Chair of Committee, Karen Vierow Committee Members, Shannon Bragg-Sitton Paul Cizmas Head of Department, Yassin Hassan August 2012 Major Subject: Nuclear Engineering iii iii ABSTRACT Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket. (August 2012) Brad Appel, B.S., Purdue University Chair of Advisory Committee: Dr. Karen Vierow The goal of this research is to apply modern methods of analysis to the design of a tungsten-cermet Nuclear Thermal Rocket (NTR) core. An NTR is one of the most viable propulsion options for enabling piloted deep-space exploration. Concerns over fuel safety have sparked interest in an NTR core based on tungsten-cermet fuel. This work investigates the capability of modern CFD and neutronics codes to design a cermet NTR, and makes specific recommendations for the configuration of channels in the core. First, the best CFD practices available from the commercial package Star-CCM+ are determined by comparing different modeling options with a hot-hydrogen flow experiment. -
9.0 BACKGROUND “What Do I Do First?” You Need to Research a Card (Thruster Or 9.1 DESIGNER’S NOTES Robonaut) with a Low Fuel Consumption
9.2 TIPS FOR INEXPERIENCED ROCKET CADETS 9.0 BACKGROUND “What do I do first?” You need to research a card (thruster or 9.1 DESIGNER’S NOTES robonaut) with a low fuel consumption. A “1” is great, a “4” The original concept for this game was a “Lords of the Sierra Madre” in is marginal. The PRC player*** can consider an dash to space. With mines, ranches, smelters, and rail lines all purchased and claim Hellas Basin on Mars, using just his crew card. He controlled by different players, who have to negotiate between them- needs 19 fuel steps (6 WT) along the red route to do this. selves to expand. But space does not work this way. “What does my rocket need?” Your rocket needs 4 things: Suppose you have a smelter on one main-belt asteroid, powered by a • A card with a thruster triangle (2.4D) to act as a thruster. • A card with an ISRU rating, if its mission is to prospect. beam-station on another asteroid, and you discover platinum on a third • A refinery, if its mission is to build a factory. nearby asteroid. Unfortunately for long-term operations, next year these • Enough fuel to get to the destination. asteroids will be separated by 2 to 6 AUs.* Furthermore, main belt Decide between a small rocket able to make multiple claims, Hohmann transfers are about 2 years long, with optimal transfer opportu- or a big rocket including a refinery and robonaut able to nities about 7 years apart. Jerry Pournelle in his book “A Step Farther industrialize the first successful claim. -
Orbital Fueling Architectures Leveraging Commercial Launch Vehicles for More Affordable Human Exploration
ORBITAL FUELING ARCHITECTURES LEVERAGING COMMERCIAL LAUNCH VEHICLES FOR MORE AFFORDABLE HUMAN EXPLORATION by DANIEL J TIFFIN Submitted in partial fulfillment of the requirements for the degree of: Master of Science Department of Mechanical and Aerospace Engineering CASE WESTERN RESERVE UNIVERSITY January, 2020 CASE WESTERN RESERVE UNIVERSITY SCHOOL OF GRADUATE STUDIES We hereby approve the thesis of DANIEL JOSEPH TIFFIN Candidate for the degree of Master of Science*. Committee Chair Paul Barnhart, PhD Committee Member Sunniva Collins, PhD Committee Member Yasuhiro Kamotani, PhD Date of Defense 21 November, 2019 *We also certify that written approval has been obtained for any proprietary material contained therein. 2 Table of Contents List of Tables................................................................................................................... 5 List of Figures ................................................................................................................. 6 List of Abbreviations ....................................................................................................... 8 1. Introduction and Background.................................................................................. 14 1.1 Human Exploration Campaigns ....................................................................... 21 1.1.1. Previous Mars Architectures ..................................................................... 21 1.1.2. Latest Mars Architecture ......................................................................... -
Conceptual Design and Optimization of Hybrid Rockets
University of Calgary PRISM: University of Calgary's Digital Repository Graduate Studies The Vault: Electronic Theses and Dissertations 2021-01-14 Conceptual Design and Optimization of Hybrid Rockets Messinger, Troy Leonard Messinger, T. L. (2021). Conceptual Design and Optimization of Hybrid Rockets (Unpublished master's thesis). University of Calgary, Calgary, AB. http://hdl.handle.net/1880/113011 master thesis University of Calgary graduate students retain copyright ownership and moral rights for their thesis. You may use this material in any way that is permitted by the Copyright Act or through licensing that has been assigned to the document. For uses that are not allowable under copyright legislation or licensing, you are required to seek permission. Downloaded from PRISM: https://prism.ucalgary.ca UNIVERSITY OF CALGARY Conceptual Design and Optimization of Hybrid Rockets by Troy Leonard Messinger A THESIS SUBMITTED TO THE FACULTY OF GRADUATE STUDIES IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF SCIENCE GRADUATE PROGRAM IN MECHANICAL ENGINEERING CALGARY, ALBERTA JANUARY, 2021 © Troy Leonard Messinger 2021 Abstract A framework was developed to perform conceptual multi-disciplinary design parametric and optimization studies of single-stage sub-orbital flight vehicles, and two-stage-to-orbit flight vehicles, that employ hybrid rocket engines as the principal means of propulsion. The framework was written in the Python programming language and incorporates many sub- disciplines to generate vehicle designs, model the relevant physics, and analyze flight perfor- mance. The relative performance (payload fraction capability) of different vehicle masses and feed system/propellant configurations was found. The major findings include conceptually viable pressure-fed and electric pump-fed two-stage-to-orbit configurations taking advan- tage of relatively low combustion pressures in increasing overall performance.