Lesson 2: YOU're LAUNCHING a ROCKET!
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Back to the the Future? 07> Probing the Kuiper Belt
SpaceFlight A British Interplanetary Society publication Volume 62 No.7 July 2020 £5.25 SPACE PLANES: back to the the future? 07> Probing the Kuiper Belt 634089 The man behind the ISS 770038 Remembering Dr Fred Singer 9 CONTENTS Features 16 Multiple stations pledge We look at a critical assessment of the way science is conducted at the International Space Station and finds it wanting. 18 The man behind the ISS 16 The Editor reflects on the life of recently Letter from the Editor deceased Jim Beggs, the NASA Administrator for whom the building of the ISS was his We are particularly pleased this supreme achievement. month to have two features which cover the spectrum of 22 Why don’t we just wing it? astronautical activities. Nick Spall Nick Spall FBIS examines the balance between gives us his critical assessment of winged lifting vehicles and semi-ballistic both winged and blunt-body re-entry vehicles for human space capsules, arguing that the former have been flight and Alan Stern reports on his grossly overlooked. research at the very edge of the 26 Parallels with Apollo 18 connected solar system – the Kuiper Belt. David Baker looks beyond the initial return to the We think of the internet and Moon by astronauts and examines the plan for a how it helps us communicate and sustained presence on the lunar surface. stay in touch, especially in these times of difficulty. But the fact that 28 Probing further in the Kuiper Belt in less than a lifetime we have Alan Stern provides another update on the gone from a tiny bleeping ball in pioneering work of New Horizons. -
The Piedmont Service: Hydrogen Fuel Cell Locomotive Feasibility
The Piedmont Service: Hydrogen Fuel Cell Locomotive Feasibility Andreas Hoffrichter, PhD Nick Little Shanelle Foster, PhD Raphael Isaac, PhD Orwell Madovi Darren Tascillo Center for Railway Research and Education Michigan State University Henry Center for Executive Development 3535 Forest Road, Lansing, MI 48910 NCDOT Project 2019-43 FHWA/NC/2019-43 October 2020 -i- FEASIBILITY REPORT The Piedmont Service: Hydrogen Fuel Cell Locomotive Feasibility October 2020 Prepared by Center for Railway Research and Education Eli Broad College of Business Michigan State University 3535 Forest Road Lansing, MI 48910 USA Prepared for North Carolina Department of Transportation – Rail Division 860 Capital Boulevard Raleigh, NC 27603 -ii- Technical Report Documentation Page 1. Report No. 2. Government Accession No. 3. Recipient’s Catalog No. FHWA/NC/2019-43 4. Title and Subtitle 5. Report Date The Piedmont Service: Hydrogen Fuel Cell Locomotive Feasibility October 2020 6. Performing Organization Code 7. Author(s) 8. Performing Organization Report No. Andreas Hoffrichter, PhD, https://orcid.org/0000-0002-2384-4463 Nick Little Shanelle N. Foster, PhD, https://orcid.org/0000-0001-9630-5500 Raphael Isaac, PhD Orwell Madovi Darren M. Tascillo 9. Performing Organization Name and Address 10. Work Unit No. (TRAIS) Center for Railway Research and Education 11. Contract or Grant No. Michigan State University Henry Center for Executive Development 3535 Forest Road Lansing, MI 48910 12. Sponsoring Agency Name and Address 13. Type of Report and Period Covered Final Report Research and Development Unit 104 Fayetteville Street December 2018 – October 2020 Raleigh, North Carolina 27601 14. Sponsoring Agency Code RP2019-43 Supplementary Notes: 16. -
Hydrogen Storage for Mobility: a Review
materials Review Hydrogen Storage for Mobility: A Review Etienne Rivard * , Michel Trudeau and Karim Zaghib * Centre of Excellence in Transportation Electrification and Energy Storage, Hydro-Quebec, 1806, boul. Lionel-Boulet, Varennes J3X 1S1, Canada; [email protected] * Correspondence: [email protected] (E.R.); [email protected] (K.Z.) Received: 18 April 2019; Accepted: 11 June 2019; Published: 19 June 2019 Abstract: Numerous reviews on hydrogen storage have previously been published. However, most of these reviews deal either exclusively with storage materials or the global hydrogen economy. This paper presents a review of hydrogen storage systems that are relevant for mobility applications. The ideal storage medium should allow high volumetric and gravimetric energy densities, quick uptake and release of fuel, operation at room temperatures and atmospheric pressure, safe use, and balanced cost-effectiveness. All current hydrogen storage technologies have significant drawbacks, including complex thermal management systems, boil-off, poor efficiency, expensive catalysts, stability issues, slow response rates, high operating pressures, low energy densities, and risks of violent and uncontrolled spontaneous reactions. While not perfect, the current leading industry standard of compressed hydrogen offers a functional solution and demonstrates a storage option for mobility compared to other technologies. Keywords: hydrogen mobility; hydrogen storage; storage systems assessment; Kubas-type hydrogen storage; hydrogen economy 1. Introduction According to the Intergovernmental Panel on Climate Change (IPCC), it is almost certain that the unusually fast global warming is a direct result of human activity [1]. The resulting climate change is linked to significant environmental impacts that are connected to the disappearance of animal species [2,3], decreased agricultural yield [4–6], increasingly frequent extreme weather events [7,8], human migration [9–11], and conflicts [12–14]. -
Development of Turbopump for LE-9 Engine
Development of Turbopump for LE-9 Engine MIZUNO Tsutomu : P. E. Jp, Manager, Research & Engineering Development, Aero Engine, Space & Defense Business Area OGUCHI Hideo : Manager, Space Development Department, Aero Engine, Space & Defense Business Area NIIYAMA Kazuki : Ph. D., Manager, Space Development Department, Aero Engine, Space & Defense Business Area SHIMIYA Noriyuki : Space Development Department, Aero Engine, Space & Defense Business Area LE-9 is a new cryogenic booster engine with high performance, high reliability, and low cost, which is designed for H3 Rocket. It will be the first booster engine in the world with an expander bleed cycle. In the designing process, the performance requirements of the turbopump and other components can be concurrently evaluated by the mathematical model of the total engine system including evaluation with the simulated performance characteristic model of turbopump. This paper reports the design requirements of the LE-9 turbopump and their latest development status. Liquid oxygen 1. Introduction turbopump Liquid hydrogen The H3 rocket, intended to reduce cost and improve turbopump reliability with respect to the H-II A/B rockets currently in operation, is under development toward the launch of the first H3 test rocket in FY 2020. In rocket development, engine is an important factor determining reliability, cost, and performance, and as a new engine for the H3 rocket first stage, an LE-9 engine(1) is under development. A rocket engine uses a turbopump to raise the pressure of low-pressure propellant supplied from a tank, injects the pressurized propellant through an injector into a combustion chamber to combust it under high-temperature and high- pressure conditions. -
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. -
H2@Railsm Workshop
SANDIA REPORT SAND2019-10191 R Printed August 2019 H2@RailSM Workshop Workshop and report sponsored by the US Department of Energy Office of Energy Efficiency and Renewable Energy Fuel Cell Technologies Office, and the US Department of Transportation Federal Railroad Administration. Prepared by Mattie Hensley, Jonathan Zimmerman Prepared by Sandia National Laboratories Albuquerque, New MexiCo 87185 and Livermore, California 94550 Issued by Sandia National Laboratories, operated for the United States Department of Energy by National Technology & Engineering Solutions of Sandia, LLC. NOTICE: This report was prepared as an account of work sponsored by an agency of the United States Government. Neither the United States Government, nor any agency thereof, nor any of their employees, nor any of their contractors, subcontractors, or their employees, make any warranty, express or implied, or assume any legal liability or responsibility for the accuracy, completeness, or usefulness of any information, apparatus, product, or process disclosed, or represent that its use would not infringe privately owned rights. References herein to any specific commercial product, process, or service by trade name, trademark, manufacturer, or otherwise, does not necessarily constitute or imply its endorsement, recommendation, or favoring by the United States Government, any agency thereof, or any of their contractors or subcontractors. The views and opinions expressed herein do not necessarily state or reflect those of the United States Government, any agency thereof, or any of their contractors. Printed in the United States of America. This report has been reproduced directly from the best available copy. Available to DOE and DOE contractors from U.S. Department of Energy Office of Scientific and Technical Information P.O. -
Orion Capsule Launch Abort System Analysis
Orion Capsule Launch Abort System Analysis Assignment 2 AE 4802 Spring 2016 – Digital Design and Manufacturing Georgia Institute of Technology Authors: Tyler Scogin Michel Lacerda Jordan Marshall Table of Contents 1. Introduction ......................................................................................................................................... 4 1.1 Mission Profile ............................................................................................................................. 7 1.2 Literature Review ........................................................................................................................ 8 2. Conceptual Design ............................................................................................................................. 13 2.1 Design Process ........................................................................................................................... 13 2.2 Vehicle Performance Characteristics ......................................................................................... 15 2.3 Vehicle/Sub-Component Sizing ................................................................................................. 15 3. Vehicle 3D Model in CATIA ................................................................................................................ 22 3.1 3D Modeling Roles and Responsibilities: .................................................................................. 22 3.2 Design Parameters and Relations:............................................................................................ -
Comparison of Hydrogen Powertrains with the Battery Powered Electric Vehicle and Investigation of Small-Scale Local Hydrogen Production Using Renewable Energy
Review Comparison of Hydrogen Powertrains with the Battery Powered Electric Vehicle and Investigation of Small-Scale Local Hydrogen Production Using Renewable Energy Michael Handwerker 1,2,*, Jörg Wellnitz 1,2 and Hormoz Marzbani 2 1 Faculty of Mechanical Engineering, University of Applied Sciences Ingolstadt, Esplanade 10, 85049 Ingolstadt, Germany; [email protected] 2 Royal Melbourne Institute of Technology, School of Engineering, Plenty Road, Bundoora, VIC 3083, Australia; [email protected] * Correspondence: [email protected] Abstract: Climate change is one of the major problems that people face in this century, with fossil fuel combustion engines being huge contributors. Currently, the battery powered electric vehicle is considered the predecessor, while hydrogen vehicles only have an insignificant market share. To evaluate if this is justified, different hydrogen power train technologies are analyzed and compared to the battery powered electric vehicle. Even though most research focuses on the hydrogen fuel cells, it is shown that, despite the lower efficiency, the often-neglected hydrogen combustion engine could be the right solution for transitioning away from fossil fuels. This is mainly due to the lower costs and possibility of the use of existing manufacturing infrastructure. To achieve a similar level of refueling comfort as with the battery powered electric vehicle, the economic and technological aspects of the local small-scale hydrogen production are being investigated. Due to the low efficiency Citation: Handwerker, M.; Wellnitz, and high prices for the required components, this domestically produced hydrogen cannot compete J.; Marzbani, H. Comparison of with hydrogen produced from fossil fuels on a larger scale. -
Fuel Cell Power Spring 2021
No 67 Spring 2021 www.fuelcellpower.wordpress.com FUEL CELL POWER The transition from combustion to clean electrochemical energy conversion HEADLINE NEWS CONTENTS Hydrogen fuel cell buses in UK cities p.2 The world’s first hydrogen fuel cell Zeroavia’s passenger plane flight p.5 double decker buses have been Intelligent Energy’s fuel cell for UAV p.6 delivered to the City of Aberdeen. Bloom Energy hydrogen strategy p.7 Wrightbus is following this up with Hydrogen from magnesium hydride paste p.11 orders from several UK cities. ITM expanding local production of zero emission hydrogen p.12 The Scottish Government is support- Alstom hydrogen fuel cell trains p.13 ing the move to zero emission Zero carbon energy for emerging transport prior to the meeting of World markets p.16 COP26 in Glasgow later this year. Nel hydrogen infrastructure p.18 Australia’s national hydrogen strategy p.20 The United Nations states that the Ballard international programmes p.22 world is nowhere close to the level FuelCell Energy Government Award p.26 of action needed to stop dangerous Ulemco’s ZERRO ambulance p.27 climate change. 2021 is a make or Adelan fuel cells in UK programme p.28 break year to deal with the global Wilhelmsen zero emission HySHIP p.29 climate emergency. Hydrogen fuel cell yacht p.30 NEWS p.10 EVENTS p.30 HYDROGEN FUEL CELL BUSES IN UK CITIES WORLD’S FIRST in tackling air pollution in the city.” Councillor Douglas Lumsden added: “It is HYDROGEN FUEL CELL fantastic to see the world’s first hydrogen- DOUBLE DECKER BUS IN powered double decker bus arrive in ABERDEEN Aberdeen. -
Combustion Tap-Off Cycle
College of Engineering Honors Program 12-10-2016 Combustion Tap-Off Cycle Nicole Shriver Embry-Riddle Aeronautical University, [email protected] Follow this and additional works at: https://commons.erau.edu/pr-honors-coe Part of the Aeronautical Vehicles Commons, Other Aerospace Engineering Commons, Propulsion and Power Commons, and the Space Vehicles Commons Scholarly Commons Citation Shriver, N. (2016). Combustion Tap-Off Cycle. , (). Retrieved from https://commons.erau.edu/pr-honors- coe/6 This Article is brought to you for free and open access by the Honors Program at Scholarly Commons. It has been accepted for inclusion in College of Engineering by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. Honors Directed Study: Combustion Tap-Off Cycle Date of Submission: December 10, 2016 by Nicole Shriver [email protected] Submitted to Dr. Michael Fabian Department of Aerospace Engineering College of Engineering In Partial Fulfillment Of the Requirements Of Honors Directed Study Fall 2016 1 1.0 INTRODUCTION The combustion tap-off cycle is also known as the “topping cycle” or “chamber bleed cycle.” It is an open liquid bipropellant cycle, usually of liquid hydrogen and liquid oxygen, that combines the fuel and oxidizer in the main combustion chamber. Gases from the edges of the combustion chamber are used to power the engine’s turbine and are expelled as exhaust. Figure 1.1 below shows a picture representation of the cycle. Figure 1.1: Combustion Tap-Off Cycle The combustion tap-off cycle is rather unconventional for rocket engines as it has only been put into practice with two engines. -
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. -
Interstellar Probe on Space Launch System (Sls)
INTERSTELLAR PROBE ON SPACE LAUNCH SYSTEM (SLS) David Alan Smith SLS Spacecraft/Payload Integration & Evolution (SPIE) NASA-MSFC December 13, 2019 0497 SLS EVOLVABILITY FOUNDATION FOR A GENERATION OF DEEP SPACE EXPLORATION 322 ft. Up to 313ft. 365 ft. 325 ft. 365 ft. 355 ft. Universal Universal Launch Abort System Stage Adapter 5m Class Stage Adapter Orion 8.4m Fairing 8.4m Fairing Fairing Long (Up to 90’) (up to 63’) Short (Up to 63’) Interim Cryogenic Exploration Exploration Exploration Propulsion Stage Upper Stage Upper Stage Upper Stage Launch Vehicle Interstage Interstage Interstage Stage Adapter Core Stage Core Stage Core Stage Solid Solid Evolved Rocket Rocket Boosters Boosters Boosters RS-25 RS-25 Engines Engines SLS Block 1 SLS Block 1 Cargo SLS Block 1B Crew SLS Block 1B Cargo SLS Block 2 Crew SLS Block 2 Cargo > 26 t (57k lbs) > 26 t (57k lbs) 38–41 t (84k-90k lbs) 41-44 t (90k–97k lbs) > 45 t (99k lbs) > 45 t (99k lbs) Payload to TLI/Moon Launch in the late 2020s and early 2030s 0497 IS THIS ROCKET REAL? 0497 SLS BLOCK 1 CONFIGURATION Launch Abort System (LAS) Utah, Alabama, Florida Orion Stage Adapter, California, Alabama Orion Multi-Purpose Crew Vehicle RL10 Engine Lockheed Martin, 5 Segment Solid Rocket Aerojet Rocketdyne, Louisiana, KSC Florida Booster (2) Interim Cryogenic Northrop Grumman, Propulsion Stage (ICPS) Utah, KSC Boeing/United Launch Alliance, California, Alabama Launch Vehicle Stage Adapter Teledyne Brown Engineering, California, Alabama Core Stage & Avionics Boeing Louisiana, Alabama RS-25 Engine (4)