Research on Innovative High Performance and Low-Cost Solid Rocket Fuel

Total Page:16

File Type:pdf, Size:1020Kb

Research on Innovative High Performance and Low-Cost Solid Rocket Fuel Impact Objectives • Investigate designs for innovative high performance and low-cost solid rocket fuel • Demonstrate the use of the low-melting point propellant in a practical setting • Develop further improvements to the full-scale rocket-grade solid fuel Fuelling rocket launching success Dr Yasuhiro Morita leads a team that is revolutionising the space rocket industry with its low cost, high performance solid rocket fuel What research is satellite launches, ultimately invigorating its puncture-proof tyres of bicycles. The underway by your the space industry as a whole. We also company’s knowledge in its field is essential department at the want to make the same low-cost solid fuel in our current research on low-melting Institute of Space available for model rockets, with the goal point solid rocket fuel resin. Uematsu has and Astronautical of promoting scientific education to the experience in developing and using small- Science at JAXA? younger generation. scale hybrid rockets, and is our trusted partner in developing demonstration At the Institute, we What did you learn from your recent rockets and conducting static firing tests primarily focus on the development and demonstration flight? and launch procedures. HASTIC has been scientific research of challenges related to vital in fostering good relations with Taiki, spacecraft, such as satellites and planetary The flight has helped us demonstrate the in Hokkaido, where we have our launch site. probes, and their launch methods (space ability to significantly increase the efficiency To upscale the development, contributions rockets). One example of the former are the of rocket production. We have shown that of IA and NOF are inevitable with their missions of Hayabusa 2, the asteroid probe even as a model rocket-grade solid fuel, the experiences in full-scale solid fuel rockets scheduled to return to Earth in December low-melting point propellant is practically like Epsilon. 2020 with samples from its mission. We usable. Previously, it had taken us several have also been involved in SLIM, which months to produce and prepare the fuel, What results have you seen from your involves a small-scale lunar explorer, and but in our latest launch, we were able to launch tests so far? the MMX, which aims to provide a return complete this in around four hours. I believe sample from one of the two moons of that this is one of the biggest innovations so Radically reducing the cost of building a Mars. As for the launch methods, various far achieved in solid fuel rockets research! rocket is the primary goal of our work. Our research projects, such as the development We now hope to apply this to larger scale launch tests have proven most satisfactorily of Epsilon’s guidance system and small-scale rockets such as our Epsilon Launch Vehicle. that a significant increase in efficiency is reusable rockets, are underway. possible in new generations of rockets. In Can you talk about the importance of addition, the fact that our model rocket One of your projects involves research on collaborative relationships? grade rated, low-melting point fuel is innovative high performance and low-cost already practically usable is very significant. solid rocket fuel. What are your goals for To further push space development and Currently, model rockets for educational this? utilisation forward, we believe that it is vital use often require expensive imported to involve all key players at a fundamental solid fuel. By replacing it with our new The objective of this research project is to level. We want to incorporate other low-melting point solid fuel, we will make significantly reduce the cost of solid fuel businesses and organisations so we can all substantial contributions to the spread of rockets, with the final milestone being the benefit from these proprietary technologies related scientific education to the younger practical application of this fuel to a rocket in practical space applications. Katazen generation. l on the same scale as Epsilon. This will is a mid-scale private manufacturer that enable us to increase the frequency of small develops low-melting point resins for 36 www.impact.pub Epsilon rocket ©JAXA The future of rocket fuel Researchers at the Japanese Aerospace Exploration Agency (JAXA) are propelling humanity further than ever before by working in partnership with industrial partners to create low-cost, high-grade rocket fuel Pushing the final frontier is an incredibly Morita’s team has already successfully tested low melting point propellant for real use with expensive endeavour, and as a result, space their innovative low melting point solid rockets. It must have a low melting point, exploration programmes take many years and rocket fuel in model rocket test launches. As preferably being able to melt in hot water huge budgets to complete. Vast resources in a result, they have been working on scaling at around 90 °C and be able to withstand terms of talent, finances and research work are up these developments to produce fuels that the vibrations and shock of a rocket launch. poured into the design of not just the payload can be used in full-scale rockets. They are also ‘The difficulty in the development of a low- that will be taken into space, but also of the exploring cost-saving, innovative technologies melting point solid propellant is the opposing rockets themselves. focusing on the launch itself. requirement for both its thermoplastic and mechanical/physical properties,’ explains The fuel for the rockets represents a With a background in general systems and Morita. ‘We have been working very hard significant investment for space programmes control, specifically related to rocket guidance researching this issue, including the as the energy required to propel the shuttles and spacecraft hardware dynamics, Morita is reformation of the low-melting point resins beyond our gravitational sphere is immense. ideally suited to this work. His specialty is in and oxidiser/resin mixture ratios,’ he adds. Dr Yasuhiro Morita, from the Japanese space launch systems, a niche field that has Aerospace Exploration Agency (JAXA), and seen him successfully building a robust, high- Morita’s ground-breaking solid fuel relies on his team have been developing new, high level control system for the M-5 rocket. ‘As the addition of a thermoplastic resin, and the performance, low-cost solid rocket fuels that the predecessor of the Epsilon launch vehicle, process he has developed can be modified to could revolutionise the industry. ‘Much like the developments on the M-5 saw our group allow smaller scale manufacturing to enable our Epsilon rockets, our country’s solid-fuel as one of the world pioneers in developing a smaller facilities to produce it. ‘With grant- rockets have been taking us to the global practical system utilising the H-infinity control funded research and cooperation from a local forefront of technology and development, theory for satellite launch vehicles,’ comments government, our partners, UE and THINKY, bringing huge contributions to the small- Morita. ‘We also successfully developed an have attempted to build a prototype mixer the scale satellite launch community,’ he autonomous antenna deployment mechanism size of a standard laboratory,’ he outlines. ‘The highlights. ‘We must now work on reducing for the Martian probe Nozomi.’ mixer has a combined rotation and revolution the operational costs involved in these cycle and automatically mixes the low-melting projects, and this means reducing the cost GROUND-BREAKING METHODOLOGY point resin and oxidiser into a solution with of fuel.’ There are many important considerations to heat introduced by friction as it operates.’ take into account when developing an effective He explains that no additional heating is www.impact.pub 37 required and the hardening process at normal single year, so these large-scale facilities are developing his solid fuel for large scale rockets temperatures can complete in a significantly usually never used for the rest of that time,’ like the Epsilon. By working on the mechanical short period as is not a time consuming he outlines. This inefficiency of large-scale properties of his existing product, as well as chemical reaction. This has resulted in a huge manufacturing with low output frequency and improving refuelling methods on large scales, reduction in production time, and Morita has long production times is one reason why costs he hopes to drive his research forward to been able to finetune the process so that the remain so high for solid-fuel rockets. benefit space research. Morita and his team timeframe from mixing to ignition is just two hours. ‘This marks an incredible improvement Much like our Epsilon rockets, our country’s solid-fuel from a couple of weeks it previously took to produce the fuel and represents what we rockets have been taking us to the global forefront of believe is a historical first in solid-fuel rocket innovation,’ enthuses Morita. technology and development, bringing huge contributions to the small-scale satellite launch community CHALLENGING THE ODDS These innovations are achieved in the face of great challenges as they overturn much of PUSHING THE BOUNDARIES have already made great strides in developing the accepted theories on solid rocket fuels. Solid rocket fuel manufacturing is currently a ground-breaking new solid fuel for evolving ‘All solid fuels in use today have some sort an intensive and inefficient process and a the rocket technology and his contributions of irreversible thermosetting property, and contributing factor to the high cost of space towards youth education will hopefully begin as such require large-scale manufacturing programmes. Where a low-melting point to bear fruit as more institutions are able to equipment,’ Morita states. In addition, the propellant such as that developed by Morita provide young scientists with the opportunities equipment used for this process can only be and his team can be used instead, a huge to use model rockets in their education.
Recommended publications
  • Corporate Profile
    2013 : Epsilon Launch Vehicle 2009 : International Space Station 1997 : M-V Launch Vehicle 1955 : The First Launched Pencil Rocket Corporate Profile Looking Ahead to Future Progress IHI Aerospace (IA) is carrying out the development, manufacture, and sales of rocket projectiles, and has been contributing in a big way to the indigenous space development in Japan. We started research on rocket projectiles in 1953. Now we have become a leading comprehensive manufacturer carrying out development and manufacture of rocket projectiles in Japan, and are active in a large number of fields such as rockets for scientific observation, rockets for launching practical satellites, and defense-related systems, etc. In the space science field, we cooperate with the Japan Aerospace Exploration Agency (JAXA) to develop and manufacture various types of observational rockets named K (Kappa), L (Lambda), and S (Sounding), and the M (Mu) rockets. With the M rockets, we have contributed to the launch of many scientific satellites. In 2013, efforts resulted in the successful launch of an Epsilon Rocket prototype, a next-generation solid rocket which inherited the 2 technologies of all the aforementioned rockets. In the practical satellite booster rocket field, We cooperates with the JAXA and has responsibilities in the solid propellant field including rocket boosters, upper-stage motors in development of the N, H-I, H-II, and H-IIA H-IIB rockets. We have also achieved excellent results in development of rockets for material experiments and recovery systems, as well as the development of equipment for use in a space environment or experimentation. In the defense field, we have developed and manufactured a variety of rocket systems and rocket motors for guided missiles, playing an important role in Japanese defense.
    [Show full text]
  • The Annual Compendium of Commercial Space Transportation: 2017
    Federal Aviation Administration The Annual Compendium of Commercial Space Transportation: 2017 January 2017 Annual Compendium of Commercial Space Transportation: 2017 i Contents About the FAA Office of Commercial Space Transportation The Federal Aviation Administration’s Office of Commercial Space Transportation (FAA AST) licenses and regulates U.S. commercial space launch and reentry activity, as well as the operation of non-federal launch and reentry sites, as authorized by Executive Order 12465 and Title 51 United States Code, Subtitle V, Chapter 509 (formerly the Commercial Space Launch Act). FAA AST’s mission is to ensure public health and safety and the safety of property while protecting the national security and foreign policy interests of the United States during commercial launch and reentry operations. In addition, FAA AST is directed to encourage, facilitate, and promote commercial space launches and reentries. Additional information concerning commercial space transportation can be found on FAA AST’s website: http://www.faa.gov/go/ast Cover art: Phil Smith, The Tauri Group (2017) Publication produced for FAA AST by The Tauri Group under contract. NOTICE Use of trade names or names of manufacturers in this document does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the Federal Aviation Administration. ii Annual Compendium of Commercial Space Transportation: 2017 GENERAL CONTENTS Executive Summary 1 Introduction 5 Launch Vehicles 9 Launch and Reentry Sites 21 Payloads 35 2016 Launch Events 39 2017 Annual Commercial Space Transportation Forecast 45 Space Transportation Law and Policy 83 Appendices 89 Orbital Launch Vehicle Fact Sheets 100 iii Contents DETAILED CONTENTS EXECUTIVE SUMMARY .
    [Show full text]
  • Successful Launch of the First Epsilon Launch Vehicle
    Mitsubishi Heavy Industries Technical Review Vol. 51 No. 1 (March 2014) 59 Contribution to Japan's Flagship Launch Vehicle – part 2 -Successful Launch of the first Epsilon Launch Vehicle- TATSURU TOKUNAGA*1 NOBUHIKO KOHARA*2 KATSUYA HAKOH*3 TSUTOMU TAKAI*4 KYOICHI UI*5 TETSUYA ONO*6 On September 14, 2013, the first Epsilon Launch Vehicle was launched from (Independent Administrative Institution) Japan Aerospace Exploration Agency (JAXA) Uchinoura Space Center, and succeeded in properly injecting a satellite into orbit. In Epsilon Launch Vehicle development, we participate in the development/manufacture of the second-stage reaction control system(RCS) and modification maintenance of the launcher for the Epsilon launch system. The development/maintenance details and launch results are introduced in this report. |1. Introduction JAXA started development of the Epsilon Launch Vehicle in 2010, going through the stages of vehicle development, manufacturing, and maintenance of launch-related facilities, until the first Epsilon Launch Vehicle was launched from Uchinoura Space Center in 2013. We contributed to the successful launch of the first Epsilon Launch Vehicle through development of the second-stage reaction control system, which was equipped onto the launch vehicle, and modification maintenance of the launcher. Details of the development/maintenance and the launch results are introduced here. |2. Approach to Epsilon Launch Vehicle Development 2.1 General The Epsilon Launch Vehicle is the three-staged solid rocket developed by JAXA since 2010, and is the successor to the M-V launch vehicle technology, which completed operations in 2006, and develops to organize technical application/commonality of the H-IIA launch vehicle.
    [Show full text]
  • The Official Magazine of the Tau Epsilon Phi Fraternity
    the Plume The Official Magazine of the Tau Epsilon Phi Fraternity Winter 2017 Issue Volume 75 Issue 1 THE CONSUL’S CORNER the Consul’s Corner Brothers, I’d like to welcome you all to the first new edition of TEΦ’s Plume in over 20 years. We hope this finds you all well. To our alumni members I hope that this brings back great memories of your time in Tau Epsilon Phi. To our lifeblood, our undergraduates, I hope you find our National publication filled with interesting articles. As always, we’d love to hear of your accomplishments, both individually and as a chapter. I’d also like to extend to you the warm fraternal greetings of our Grand Council. It is certainly an honor and privilege to serve as the 47th Consul of TEΦ and lead this prestigious group of Brothers. I’d like to thank everyone who was able to attend our 2016 Grand Chapter in Orlando, Florida. We had such a diverse group of attendees and I’m glad that many of you are remaining involved whether serving on a committee, the Grand Council, or the TEΦ Foundation. I look forward to working with each of you and meeting many more of you as I continue to visit our chapters and attend alumni meet and greets around the country. I’d like to take a moment to recognize and thank my predecessor, Lane Koplon, for his many years of service to our great Fraternity, particularly as our Consul for the past five years. He helped lead our Fraternity out of bankruptcy and pave a path forward for the revitalization of TEΦ.
    [Show full text]
  • Apollo Rocket Propulsion Development
    REMEMBERING THE GIANTS APOLLO ROCKET PROPULSION DEVELOPMENT Editors: Steven C. Fisher Shamim A. Rahman John C. Stennis Space Center The NASA History Series National Aeronautics and Space Administration NASA History Division Office of External Relations Washington, DC December 2009 NASA SP-2009-4545 Library of Congress Cataloging-in-Publication Data Remembering the Giants: Apollo Rocket Propulsion Development / editors, Steven C. Fisher, Shamim A. Rahman. p. cm. -- (The NASA history series) Papers from a lecture series held April 25, 2006 at the John C. Stennis Space Center. Includes bibliographical references. 1. Saturn Project (U.S.)--Congresses. 2. Saturn launch vehicles--Congresses. 3. Project Apollo (U.S.)--Congresses. 4. Rocketry--Research--United States--History--20th century-- Congresses. I. Fisher, Steven C., 1949- II. Rahman, Shamim A., 1963- TL781.5.S3R46 2009 629.47’52--dc22 2009054178 Table of Contents Foreword ...............................................................................................................................7 Acknowledgments .................................................................................................................9 Welcome Remarks Richard Gilbrech ..........................................................................................................11 Steve Fisher ...................................................................................................................13 Chapter One - Robert Biggs, Rocketdyne - F-1 Saturn V First Stage Engine .......................15
    [Show full text]
  • Basic Plan on Space Policy” Implementation Schedule (Draft) 4
    New “Basic Plan on Space Policy” Implementation Schedule (Draft) 4. (2)i) Satellite positioning 2025 2015 2016 2017 2018 2019 2020 2021 2022 2023 2024 FY onward 1-satellite constellation 4-satellite constellation operation 7-satellite operation constellation (GPS-linked positioning services) operation (Maintenance and operation) [CAO] (sustained [CAO, MIC, MEXT] positioning) [CAO] 2-4 satellite constellation (In progress) development and development, improvement [CAO] operation operation Launch Development and improvement of successors to Michibiki initial model (In progress) [CAO] Launch (In progress) improvement, and improvement, Zenith Satellite System - Development and improvement of three additional Models units for 7-satellite constellation 5,6,7 Quasi [CAO] Launch (In progress) 1 4. (2)i) Satellite positioning 2025 2015 2016 2017 2018 2019 2020 2021 2022 2023 2024 FY onward Promotion of utilization of Quasi-Zenith Satellite System, etc. in Japan and abroad, particularly in the Asia-Pacific region Support for construction of electronic control point network and reinforcement of utilization infrastructure for positioning satellites [CAO, MLIT, , etc.] Realization of a “G-spatial society” through linkage of Quasi-Zenith Satellite and Geographic Information System (GIS) [CAO, MLIT, etc.] Deliberation on generation of new business on a private-sector platform (From FY2014) [CAO] (Ref.) Deliberation on operational testing (Ref.) 2020 Tokyo Olympics and Paralympics [CAO, METI, etc.] Operational testing (Ref.) Application of results in public society [CAO, etc.] [Relevant ministries and agencies] (Ref.) Deliberation on Zenith Satellite System, etc. System, Zenith Satellite - private-sector funding for (Ref.) Implementation of necessary measures new projects and services [CAS, CAO, MIC, MEXT, MHLW, MAFF, METI, MLIT, etc.] utilizing space, use of various supportive measures, etc.
    [Show full text]
  • Computational Modeling and Sensitivity Evaluation of Liquid Rocket Injector Flow
    43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit AIAA 2007-5592 8 - 11 July 2007, Cincinnati, OH Computational Modeling and Sensitivity Evaluation of Liquid Rocket Injector Flow Yolanda Mack,* Raphael Haftka,† and Corin Segal‡ University of Florida, Gainesville, FL 32611-6250 Nestor Queipo§ University of Zulia, Maracaibo, Venezuela and Wei Shyy** University of Michigan, Ann Arbor, MI 48109 A three-dimensional computational model of an experimental rectangular combustion chamber was developed to explore the wall heat transfer of a GO2/GH2 shear coaxial single element injector. The CFD model allowed for the direct analysis of heat transfer effects due to flow dynamics—an analysis that would be very difficult using experimental studies alone. The use of a 3-D CFD model revealed heat transfer effects due to flow streamlines and eddy conductivity, and provided insight into the two-dimensional nature of the wall heat flux. A grid sensitivity study was conducted to determine the effects of grid resolution on the combustion chamber length and heat flux. The results of a grid sensitivity study were inconclusive, as a grid-independent solution could not be reached. However, it was found that the predicted heat flux was largely independent of the grid resolution, as long as the near-wall region was well resolved. Finally, a single-element injector model was constructed to explore the sensitivity of the peak heat flux and combustion chamber length to the circumferential and radial spacing of injector elements in the outer row of a multi-element injector. Many cases, including the baseline case, had a recirculation region that was oriented such that the outer shear layer was directed at the combustion chamber wall, resulting in a large peak heat flux near the injector face.
    [Show full text]
  • Epsilon Launch Vehicle's Development Status for the Further Evolution
    Abstract for 11th Low Cost Planetary Missions Conference June 9-11, 2015, Berlin, Germany Epsilon Launch Vehicle's Development Status For The Further Evolution Ryoma Yamashiro, Epsilon Rocket Project Team in JAXA; Yasuhiro Morita, Epsilon Rocket Project Team in JAXA; Takayuki Imoto, Epsilon Rocket Project Team in JAXA; Shinichiro Tokudome, Epsilon Rocket Project Team in JAXA; The purpose of the Epsilon launch vehicle, the newest version of Japan’s solid propulsion rocket, is to provide small satellites and probes with responsive launching with low-cost, user-friendly and e cient launch system. Epsilon made its maiden flight in September of 2013 and successfully deployed the extreme ultraffi- violet planetary telescope satellite, “Hisaki”. JAXA appreciates the advantages of the combined power of standardized small satellites and Epsilon’s highly e cient launch system to increase space activities. Now that the first flight was successfully finished, JAXAffi has been conducting intensive researches on a next generation Epsilon to launch a more powerful and lower cost version of Epsilon. In order to minimize technical risks and to keep up with demand of future payloads, JAXA plans to take a step- by-step approach toward this next Epsilon. As the first step, the effective development in the short term is ongoing. That includes the development of the new second stage motor, the compactization of the avionics component, and the optimization of the liquid propulsion system in the post boost stage. The development will increase the launch capacity and payload usable volume, and reduce the launch cost. This development will be applied to the second flight of Epsilon to be scheduled for 2016, that is for the launch of the ERG (Exploration of energization and Radiation in Geospace).
    [Show full text]
  • Viability of an Electrically Driven Pump-Fed Hybrid Rocket for Small Launcher Upper Stages
    aerospace Article Viability of an Electrically Driven Pump-Fed Hybrid Rocket for Small Launcher Upper Stages Lorenzo Casalino † , Filippo Masseni † and Dario Pastrone ∗,† Dipartimento di Ingegneria Meccanica e Aerospaziale, Politecnico di Torino, Corso Duca degli Abruzzi, 24, 10129 Torino, Italy; [email protected] (L.C.); fi[email protected] (F.M.) * Correspondence: [email protected] † These authors contributed equally to this work. Received: 31 January 2019; Accepted: 11 March 2019; Published: 14 March 2019 Abstract: An electrically driven pump-fed cycle for a hybrid rocket engine is proposed and compared to a simpler gas-pressurized feed system. A liquid-oxygen/paraffin-based fuel hybrid rocket engine which powers the third stage of a Vega-like launcher is considered. Third-stage ignition conditions are assigned, and engine design and payload mass are defined by a proper set of parameters. Uncertainties in the classical regression rate correlation coefficients are taken into account and robust design optimization is carried out with an approach based on an epsilon-constrained evolutionary algorithm. A mission-specific objective function, which takes into account both the payload mass and the ability of the rocket to reach the required final orbit despite uncertainties, is determined by an indirect trajectory optimization approach. The target orbit is a 700 km altitude polar orbit. Results show that electrically driven pump-fed cycle is a viable option for the replacement of the conventional gas-pressurized feed system. Robustness in the design is granted and a remarkable payload gain is achieved, using both present and advanced technologies for electrical systems. Keywords: hybrid rocket engines; multidisciplinary design optimization; robust optimization; electric feed system 1.
    [Show full text]
  • Implementation Plan of the Basic Plan on Space Policy (Revised FY2017)
    Implementation Plan of the Basic Plan on Space Policy (revised FY2017) (Tentative Translation) December 12, 2017 National Space Policy Secretariat Implementation Plan of the Basic Plan on Space Policy / Table of Contents No. Measures 1Quasi‐Zenith Satellite System development, improvement, and operation 2Promotion of utilization of Quasi‐Zenith Satellite System, etc. 3 Application of utilization needs to various projects 4 Information Gathering Satellites, etc. (optical satellites, etc.) 5 Information Gathering Satellites, etc. (radar satellites, etc.) 6Operationally Responsive Small Satellites, etc. 7Advanced optical and radar satellites 8 Deliberation on improvement, etc. of systems required for the Earth Observation Satellite program 9Geostationary Meteorological Satellite 10 Greenhouse Gases Observing Satellite 11 Advancement of other remote sensing satellites and sensor technologies(1) 12 Advancement of other remote sensing satellites and sensor technologies(2) 13 Experimental satellites 14 Optical Data Relay Satellite 15 X‐band defense satellite communication network 16 Prioritized utilization of core rockets 17 Next Generation Mainstay Launch Vehicle (H3 Launch Vehicle) 18 Epsilon Launch Vehicle 19 Deliberation on launch sites, etc. 20 Launch systems for small‐size Operationally Responsive Satellites, etc. 21 Space Situational Awareness (SSA) 22 Maritime Domain Awareness (MDA) 23 Early‐warning functions, etc. 24 Enhancement of the overall mission assurance of space systems 25 Space science / exploration 26 Human space activities including the International Space Station (ISS) 27 International human space missions 28 Systemic frameworks for encouragement of new private‐sector participants Utilization of private‐sector financing and various support measures, etc. to create new space‐related businesses 29 and service 30 Formulation of tech strategies related to components, etc.
    [Show full text]
  • English Words from Greek Letters
    254 ENGLISH WORDS FROM GREEK LETTERS DARRYL FRANCIS Sutton, Surrey, England [email protected]. uk Riddle: What common six-letter English word can be spelled using two Greek letters? Answer: AUTHOR, because it 's made up from TAU and RHO. For some time I've been bemused by the word UNIX , the name of a computer operating m. because it can be spelled out from the names of two letters of the Greek alphabet. I and . Additionally the two letters are simply spelled in order backwards. This set me thinking about what other words might exist whose letters could be used to spell out the name of two or more Greek letters. And wou ld any of them display their Greek letters in order or re erse order? The 24 letters of the modem Greek alphabet are alpha, beta gamma, delta, ep ilon z ta, ela. theta, iota, kappa, lambda, mu, nu, xi, omicron, pi , rho sigma, tau, up ilon, phi, hi, p i and omega. Additionally, there are 6 letters that appear in earlier version of the Greek alpha t: digamma, episemon, koppa, sampi, san and vau. These 30 letter can be combined in 450 \\8} . 1 have managed to find real words for exactly one-sixth, or 75, of them. In the Ii t b 10\ ,w rd n I in Webster's Third New International are labeled, and the> ymbol indicates that th nanl f the Greek letters are spelled out forwards « symbol, spell ed out backward ). alpha, nu = pulahan kappa, nu = paukpan beta, chi = Thebaic lambda, nu = labdanum beta, mu = beatum (OED nil admirari) lambda, rho = rhabdomal beta, nu = butane mu, mu = mumu beta, omicron = embrocation mu, nu = unum< II"IED unum r.
    [Show full text]
  • Design of Launch Pad for Mitigating Acoustic Loads on Launch Vehicle at Liftoff 우주발사체 발사 시 음향하중 저감을 위한 발사대 설계
    한국음향학회지 제39권 제4호 pp. 331~341 (2020) The Journal of the Acoustical Society of Korea Vol.39, No.4 (2020) pISSN : 1225-4428 https://doi.org/10.7776/ASK.2020.39.4.331 eISSN : 2287-3775 Design of launch pad for mitigating acoustic loads on launch vehicle at liftoff 우주발사체 발사 시 음향하중 저감을 위한 발사대 설계 Seiji Tsutsumi1† 1Japan Aerospace Exploration Agency (Received June 17, 2020; accepted July 18, 2020) ABSTRACT: At liftoff, launch vehicles are subject to harmful acoustic loads due to the intense acoustic waves generated by propulsion systems. Because these waves can cause electronic and mechanical components of launch vehicles and payloads to fail, predicting and mitigating acoustic loads is an important design issue. This article presents the latest information about the generation of acoustic waves and the acoustic design methods applicable to the launch pad. The development of the Japanese Epsilon solid launcher is given as an example of the new methodology for launch pad design. Computational fluid dynamics together with 1/42 scale model testing were performed for this development. Effectiveness of the launch pad design to reduce acoustic loads was confirmed by the post-flight analysis. Keywords: Launch vehicle, Aeroacoustics, Computational fluid dynamics, Computational aeroacoustics PACS numbers: 43.50.Nm, 43.28.Js 초 록: 우주발사체는 발사 시 추진장치에서 발생하는 고강도 소음에 의한 음향하중의 영향을 받는다. 로켓소음은 발사체와 페이로드 내 전자 및 기계 부품의 손상 및 오작동을 유발할 수 있기 때문에 음향하중의 예측 및 저감은 설계에 있어 중요한 고려사항이다. 본 논문에서는 로켓 소음의 생성 및 발사대의 음향설계 기법에 대한 최신 연구동향을 논하 였다.
    [Show full text]