Technology for Fuel Depots (Cont.) Subcooling Propellant
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Safety Consideration on Liquid Hydrogen
Safety Considerations on Liquid Hydrogen Karl Verfondern Helmholtz-Gemeinschaft der 5/JULICH Mitglied FORSCHUNGSZENTRUM TABLE OF CONTENTS 1. INTRODUCTION....................................................................................................................................1 2. PROPERTIES OF LIQUID HYDROGEN..........................................................................................3 2.1. Physical and Chemical Characteristics..............................................................................................3 2.1.1. Physical Properties ......................................................................................................................3 2.1.2. Chemical Properties ....................................................................................................................7 2.2. Influence of Cryogenic Hydrogen on Materials..............................................................................9 2.3. Physiological Problems in Connection with Liquid Hydrogen ....................................................10 3. PRODUCTION OF LIQUID HYDROGEN AND SLUSH HYDROGEN................................... 13 3.1. Liquid Hydrogen Production Methods ............................................................................................ 13 3.1.1. Energy Requirement .................................................................................................................. 13 3.1.2. Linde Hampson Process ............................................................................................................15 -
Materials for Liquid Propulsion Systems
https://ntrs.nasa.gov/search.jsp?R=20160008869 2019-08-29T17:47:59+00:00Z CHAPTER 12 Materials for Liquid Propulsion Systems John A. Halchak Consultant, Los Angeles, California James L. Cannon NASA Marshall Space Flight Center, Huntsville, Alabama Corey Brown Aerojet-Rocketdyne, West Palm Beach, Florida 12.1 Introduction Earth to orbit launch vehicles are propelled by rocket engines and motors, both liquid and solid. This chapter will discuss liquid engines. The heart of a launch vehicle is its engine. The remainder of the vehicle (with the notable exceptions of the payload and guidance system) is an aero structure to support the propellant tanks which provide the fuel and oxidizer to feed the engine or engines. The basic principle behind a rocket engine is straightforward. The engine is a means to convert potential thermochemical energy of one or more propellants into exhaust jet kinetic energy. Fuel and oxidizer are burned in a combustion chamber where they create hot gases under high pressure. These hot gases are allowed to expand through a nozzle. The molecules of hot gas are first constricted by the throat of the nozzle (de-Laval nozzle) which forces them to accelerate; then as the nozzle flares outwards, they expand and further accelerate. It is the mass of the combustion gases times their velocity, reacting against the walls of the combustion chamber and nozzle, which produce thrust according to Newton’s third law: for every action there is an equal and opposite reaction. [1] Solid rocket motors are cheaper to manufacture and offer good values for their cost. -
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 ......................................................................... -
On-Orbit Servicing and Refueling Concepts!
On-orbit Servicing and Refueling Concepts! June 17, 2015 Benjamin B. Reed Deputy Project Manager Satellite Servicing Capabilities Office http://ssco.gsfc.nasa.gov Pre-decisional. Do not forward or post without the consent of [email protected] Introduction! • Over the past five years, NASA has: – Invested in satellite-servicing technologies and tested them on the ground and in orbit – Examined several different “design reference missions” • Non-Shuttle-based Hubble Space Telescope • Propellant depot • 30-m telescope assembly • GOES-12 refueling (GEO) • Landsat 7 refueling (LEO) Growing momentum towards robotic satellite servicing capability. Pre-decisional. Do not forward or post without the consent of [email protected] 2 In Space Robotic Servicing ! • The Satellite Servicing Capabilities Office is responsible for the overall management, coordination, and implementation of satellite servicing technologies and capabilities for NASA. To meet these objectives it: – Conducts studies – Conducts demonstration experiments in orbit and on the ground – Manages technology development and satellite servicing missions – Advises and designs cooperative servicing elements and subsystems Pre-decisional. Do not forward or post without the consent of [email protected] 3 In Space Robotic Servicing Team and Partners! Johnson Space Canadian Space Center Agency Goddard Space Flight Center Department of Defense Space Test Program Glenn Research Center WVU RPI JHU UMD Naval Research Kennedy Laboratory Space Center Pre-decisional. Do not forward or post without the consent of [email protected] 4 Servicing Supports Multiple Objectives! On-orbit Assembly Asteroid Infrastructure Redirection Inspection and Maintenance Fleet Management Government and Commercial Human Exploration Observatory Servicing Servicing Planetary Capabilities! Defense Propellant Depot 5 5 Pre-decisional. -
Cryogenic Technology & Rocket Engines
ISSN (O): 2393-8609 International Journal of Aerospace and Mechanical Engineering Volume 2 – No.5, August 2015 Cryogenic Technology & Rocket Engines AKHIL GARG KARTIK JAKHU KISHAN SINGH ABHINAV B.Tech – Aerospace B.Tech – Aerospace B.Tech – Aerospace MAURYA Engg. Engg. Engg. B.Tech – Aerospace PUNJAB PUNJAB PUNJAB Engg. TECHNICAL TECHNICAL TECHNICAL PUNJAB UNIVERSITY, UNIVERSITY, UNIVERSITY, TECHNICAL JALANDHAR JALANDHAR JALANDHAR UNIVERSITY, akhilgarg.313@g kartik.lphawk@g kishansngh1996 JALANDHAR mail.com mail.com @gmail.com abhinavguru123 @gmail.com ABSTRACT 3.2 What is Cryogenic Rocket Engine? This paper is all about the rocket engine involving the use of A cryogenic rocket engine is a rocket engine that cryogenic technology at a cryogenic temperature (123K). This uses a cryogenic fuel or oxidizer, that is, its fuel or basically uses the liquid oxygen and liquid hydrogen as an oxidizer (or both) is gases liquefied and stored at oxidizer and fuel, which are very clean and non-pollutant very low temperatures. Notably, these engines were fuels compared to other hydrocarbon fuels like petrol, diesel, one of the main factors of the ultimate success in gasoline, LPG, CNG, etc., sometimes, liquid nitrogen is also reaching the Moon by the Saturn V rocket. used as an fuel. During World War II, when powerful rocket engines were first considered by the German, American and Keywords Soviet engineers independently, all discovered that Rocket engine, Cryogenic technology, Cryogenic temperature, rocket engines need high mass flow rate of both Liquid hydrogen and Oxygen. oxidizer and fuel to generate a sufficient thrust. At that time oxygen and low molecular weight 1. -
A Value Proposition for Lunar Architectures Utilizing On-Orbit Propellant Refueling
A VALUE PROPOSITION FOR LUNAR ARCHITECTURES UTILIZING ON-ORBIT PROPELLANT REFUELING By James Jay Young In Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy in the School of Aerospace Engineering Georgia Institute of Technology May 2009 Copyright © 2009 by James J. Young A VALUE PROPOSITION FOR LUNAR ARCHITECTURES UTILIZING ON-ORBIT PROPELLANT REFUELING Approved by: Dr. Alan W. Wilhite, Chairman Dr. Douglas Stanley School of Aerospace Engineering School of Aerospace Engineering Georgia Institute of Technology Georgia Institute of Technology Dr. Trina M. Chytka Dr. Daniel P. Schrage Vehicle Analysis Branch School of Aerospace Engineering NASA Langley Research Center Georgia Institute of Technology Dr. Carlee A. Bishop Electronics Systems Laboratory Georgia Tech Research Institute Date Approved: October 29, 2008 ACKNOWLEDGEMENTS As I sit down to acknowledge all the people who have helped me throughout my career as a student I realized that I could spend pages thanking everyone. I may never have reached all of my goals without your endless support. I would like to thank all of you for helping me achieve me goals. I would like to specifically thank my thesis advisor, Dr. Alan Wilhite, for his guidance throughout this process. I would also like to thank my committee members, Dr. Carlee Bishop, Dr. Trina Chytka, Dr. Daniel Scharge, and Dr. Douglas Stanley for the time they dedicated to helping me complete my dissertation. I would also like to thank Dr. John Olds for his guidance during my first two years at Georgia Tech and introducing me to the conceptual design field. I must also thank all of the current and former students of the Space Systems Design Laboratory for helping me overcome any technical challenges that I encountered during my research. -
Cryogenics Unit- I
Department of Aeronautical Engineering Sem ;VII SAEX1041- CRYOGENICS UNIT- I Cryogenics is the branch of physics that deals with the production and effects of very low temperatures. The Large Hadron Collider (LHC) is the largest cryogenic system in the world and one of the coldest places on Earth. All of the magnets on the LHC are electromagnets – magnets in which the magnetic field is produced by the flow of electric current. The LHC's main magnets operate at a temperature of 1.9 K (-271.3°C), colder than the 2.7 K (-270.5°C) of outer space. The LHC's cryogenic system requires 40,000 leak-tight pipe seals, 40 MW of electricity – 10 times more than is needed to power a locomotive – and 120 tonnes of helium to keep the magnets at 1.9 K. Extreme cold for exceptional performances Magnets produce a magnetic field of 8.33 tesla to keep particle beams on course around the LHC's 27-kilometre ring. A current of 11,850 amps in the magnet coils is needed to reach magnetic fields of this amplitude. The use of superconducting materials – those that conduct electricity with no resistance – has proven to be the best way of avoiding overheating in the coils and of keeping them as small as possible. Superconductivity could not happen without the use of cryogenic systems. The coils' niobium-titanium (NbTi) wires must be kept at low temperatures to reach a superconducting state. The LHC's superconducting magnets are therefore maintained at 1.9 K (-271.3°C) by a closed liquid-helium circuit. -
Depot for Martian and Extraterrestrial Transport Resupply (Demetr)
University of Tennessee, Knoxville TRACE: Tennessee Research and Creative Exchange Supervised Undergraduate Student Research Chancellor’s Honors Program Projects and Creative Work 5-2018 Depot for Martian and Extraterrestrial Transport Resupply (DeMETR) Emily Beckman University of Tennessee-Knoxville, [email protected] Ethan Vogel University of Tennessee-Knoxville Caleb Peck University of Tennessee-Knoxville Nicholas Patterson University of Tennessee-Knoxville Follow this and additional works at: https://trace.tennessee.edu/utk_chanhonoproj Part of the Navigation, Guidance, Control and Dynamics Commons, Propulsion and Power Commons, Space Vehicles Commons, and the Systems Engineering and Multidisciplinary Design Optimization Commons Recommended Citation Beckman, Emily; Vogel, Ethan; Peck, Caleb; and Patterson, Nicholas, "Depot for Martian and Extraterrestrial Transport Resupply (DeMETR)" (2018). Chancellor’s Honors Program Projects. https://trace.tennessee.edu/utk_chanhonoproj/2191 This Dissertation/Thesis is brought to you for free and open access by the Supervised Undergraduate Student Research and Creative Work at TRACE: Tennessee Research and Creative Exchange. It has been accepted for inclusion in Chancellor’s Honors Program Projects by an authorized administrator of TRACE: Tennessee Research and Creative Exchange. For more information, please contact [email protected]. PROPELLANT RESUPPLY CAPABILITY DEPOT FOR MARTIAN AND EXTRATERRESTRIAL TRANSPORT RESUPPLY (DEMETR) UNIVERSITY OF TENNESSEE Faculty Advisor: Dr. James Lyne I. INTRODUCTION This mission architecture was designed to meet the requirements of the NASA RASC-ALs propellant resupply capability theme. The Depot for Martian and Extraterrestrial Transport Resupply (DeMETR) station and the High-orbit Resupply Module for Exploratory Spacecraft (HRMES) will deliver 19.6 T of Xenon and a combined 8.1 T of dinitrogen tetroxide (NTO) and Monomethylhydrazine (MMH) oxidizer to the Deep Space Transport in cis-lunar space [1]. -
NASA Perspectives on Cryo H2 Storage
NASA Perspectives on Cryo H2 Storage DOE Hydrogen Storage Workshop Marriott Crystal Gateway Arlington, VA February 15, 2011 David J. Chato NASA Glenn Research Center Michael P. Doherty NASA Glenn Research Center Objectives Purposes of this Presentation • To show the role of Cryogenics in NASA prior missions • To show recent NASA accomplishments in cryogenic fluid management technology • To highlight the importance of long term cryogenic storage to future NASA missions (especially Human Space flight) 2 What is Cryogenic Fluid Management? The Cartoon Guide to Cryogenic Fluid Management Illustrating Key Concepts in Iconic Form 33 GRC Cryogenic Fluid Management Accomplishments 2010 Methane Lunar Surface Thermal Control COLD-SAT Test demonstrate Experiment advanced MLI Experiment Design completes Phase A (1990) SloshSAT experiment with ESA flown (2005) LH2 Zero Boil-off Shuttle Experiments: 1962-> Centaur storage feasibility Tank Pressure LO2/LH2 stage demonstrated (1998) development Control Experiment (1992), Vented Tank Resupply Experiment(1996) Pioneering cryogenic 2005-2010 Liquid propellant 1996-2001: Propellant acquisition, gauging, properties, densification pressure control, behavior, and development culminates modeling matured instrumentation in X-33 GSE studies 1960s-70s 2004 Creek Road Cryogenic Complex 1988-1994: NASP opens – over 30 test Slush H2 programs conducted to Technology mature CFM technology Program. >200,000 in next 6 years gallons of SLH2 produced 4 Cryogenic Systems Propulsion Power and Life Support Possible Option Exploration -
LEO Propellant Depot: Commercially Viable?
LEOLEO PropellantPropellant Depot:Depot: AA CommercialCommercial Opportunity?Opportunity? LEAGLEAG PrivatePrivate SectorSector InvolvementInvolvement October 1 - 5, 2007 Dallas Bienhoff October 1 - 5, 2007 The Boeing Company Houston,Houston, TexasTexas 703-414-6139 TheThe ESASESAS RecommendedRecommended ArchitectureArchitecture 1.5 Launch architecture: Ares I & V Earth orbit rendezvous: CEV to LSAM/EDS EDS performs Earth orbit insertion & circularization and TLI burns LSAM DS performs LOI with CEV and lunar descent and landing Lunar orbit rendezvous: LSAM AS to CEV LOx/LH in EDS and LSAM DS Lox/Methane in LSAM AS and CEV PagePage 11 of of 1212 070720_Beyond_COTS_Panel070720_Beyond_COTS_Panel FollowedFollowed byby Dr.Dr. Griffin’sGriffin’s CommentsComments atat 52nd52nd AASAAS AnnualAnnual MeetingMeeting inin Houston,Houston, 11/0511/05 “But if there were a fuel depot available on orbit, one capable of being replenished at any time, the Earth departure stage could after refueling carry significantly more payload to the Moon…” “The architecture which we have advanced places about 150 metric tons in LEO, 25 MT on the Crew Launch Vehicle and 125 MT on the heavy-lifter. ” During ascent, the Ares V Earth Departure Stage uses approximately 125 t of propellant to deliver 125 t to LEO “…at a conservatively low government price of $10,000/kg in LEO, 250 MT of fuel for two missions per year is worth $2.5 B, at government rates.” PagePage 22 of of 1212 070720_Beyond_COTS_Panel070720_Beyond_COTS_Panel TwoTwo LEOLEO PropellantPropellant DepotsDepots -
Propellant Depots for In-Orbit Lunar Infrastructures
PropellantPropellant DepotsDepots forfor InIn--orbitorbit LunarLunar infrastructuresinfrastructures D.Galli, F.Piccolo – D’Appolonia S.p.A. 9th ILEWG, Sorrento 22-26 October, 2007 Scenario Even if planned to be one of the component of the Lunar mission support infrastructure, NASA cut back Orbital Depot in 2005 when the agency decided it was not required to fulfill the short-term goal of returning humans to the Moon. “even if such a station would be a highly valuable enhancement", it isn’t affordable under current budget constraints and "the mission [to the Moon] was not hostage to its availability". Mike Griffin’s speech to the American Astronautical Society, November 2005 Why a Depot? An In-Space Cryogenic Propellant Depot (ISCPD) is an important stepping stone to provide the capability to: 9 Preposition 9 Store 9 Manufacture 9 Use propellants for Earth–neighborhood campaigns and beyond. Main reason to have a depot in orbit is the selection of a modular/incremental design approach: • Affordability • Adaptability • Reusability • CapabilityKey Technology: Propellant storage and transfer • Dependability • Incremental developability • Feasibilty MSFC/Boeing concept Why a Depot… There really is a lot of prior art and experience that demonstrates that it is possible to make a depot a reality. Fluid Coupling Orbital RDV and Docking Fuel Transfer & storage Autonomous RDV & Docking Transportation policy Propellant depots allow you to develop reusable in-space transportation vehicles. While you could possibly refuel and reuse a reusable space tug without the benefit of a fuel depot, a depot would be a lot nicer. Depots• allow you to decrease the size of your launch vehicles (propellant is often 75-90% of the mass of transfer vehicle in LEO) The• ability to launch dry and fuel-up in orbit means: much• smaller vehicles flying at a higher flight rate, . -
Methods and Models for the Concept Design of Liquefied Natural Gas Fuel Systems on Ships Jonas Thiaucourt
Methods and models for the concept design of liquefied natural gas fuel systems on ships Jonas Thiaucourt To cite this version: Jonas Thiaucourt. Methods and models for the concept design of liquefied natural gas fuel systems on ships. Thermics [physics.class-ph]. École centrale de Nantes, 2019. English. NNT : 2019ECDN0032. tel-02462527 HAL Id: tel-02462527 https://tel.archives-ouvertes.fr/tel-02462527 Submitted on 31 Jan 2020 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. THESE DE DOCTORAT DE L'ÉCOLE CENTRALE DE NANTES COMUE UNIVERSITE BRETAGNE LOIRE ECOLE DOCTORALE N° 602 Sciences pour l'Ingénieur Spécialité : « Energétique-Thermique-Combustion » Par Jonas THIAUCOURT Méthodes et modèles pour l’étude de faisabilité des navires propulsés au gaz naturel liquéfié Thèse présentée et soutenue à Nantes, le 30 septembre 2019 Unité de recherche : UMR 6598 Laboratoire de recherche en Hydrodynamique, Energétique et Environnement Atmosphérique Rapporteurs avant soutenance Laura A. Pellegrini Professeure, Ecole Polytechnique de Milan Christelle Perilhon Maitre de conférences HDR, Conservatoire National des Arts et Métiers (CNAM) Composition du Jury Président Sofiane Khelladi Professeur, Arts et Métiers ParisTech Examinateur Gordon Paker Professeur, Université Technologique du Michigan Dir.