User's Manual SC LV Option Standard Working Days : Within 45 Launch Operations Special Consideration for Over 45 Days

Total Page:16

File Type:pdf, Size:1020Kb

User's Manual SC LV Option Standard Working Days : Within 45 Launch Operations Special Consideration for Over 45 Days NASDA-HDBK-1007D CB H-IIA User’s Manual Second Edition December 2001 Published by NATIONAL SPACE DEVELOPMENT AGENCY OF JAPAN PREFACE This H-IIA User’s Manual presents information regarding the H-IIA launch vehicle and its related systems and launch services. This document contains information for launch services including mission performance capability, environmental conditions, spacecraft and launch vehicle interface conditions, launch operations and interface management. A brief description of the H-IIA launch vehicles and the launch facilities of Tanegashima Space Center is also included. As the H-IIA program is progressing, this document is subject to change and will be revised periodically. Requests for further information or inquiries related to this manual or interfaces between spacecraft and the H-IIA launch system should be addressed to: National Space Development Agency of Japan Mission Operations Department Office of Space Transportation Systems World Trade Center Building 26F 2-4-1 Hamamatsu-cho, Minato-ku Tokyo, 105-8060 Japan Telephone + 81-3-3438-6465 Fax + 81-3-5402-6527 © NASDA This manual cannot be copied, duplicated, or quoted in part or whole (including drawings and photographs) without permission from NASDA. 0-1 H-IIA User’s Manual revision control sheet Revision Date Revised page Approved A F7irst J—une. 199 ———— ——— All pages are redesigned. Major revised items : S7econd Dec. 199 - 4.6.9 RF Link Interface - Table A2.5.1 Tsechnicals Other Contents 0-1 ~ 0-15 0-17 etc. 0-18 0-19 0-21 Tsechnicals Other 1-2 1-3 1-3 1-4 1-4 1-7 Chapter 1 1-5 1-9 1-8 1-10 1-11 1-13 1-16 ~ 1-20 1-15 1-22 1-22 Second Dec. 1998 1-23 Revision A Tsechnicals Other 2-1 ~ 2-12 2-1 2-15 2-3 Chapter 2 2-17 ~ 2-23 2-4 2-8 2-9 2-13 Tsechnicals Other 3-3 3-1 3-5 3-2 Chapter 3 3-11 3-3 3-12 3-5 ~ 3-11 3-13 3-21 3-23 3-24 3-24 3-25 0-2 Revision Date Revised page Approved A Tsechnicals Other 4-6 ~ 4-18 4-1 4-26 ~ 4-33 4-2 4-38 ~ 4-43 4-41 4-48 4-53 4-52 4-54 Chapter 4 4-56 4-55 4-59 4-57 4-60 4-58 4-61 4-63 4-64 ~ 4-68 4-69 4-71 4-74 4-72 4-73 Tsechnicals Other Second Dec. 1998 Revision A 5-1 5-1 5-2 5-3 5-4 5-5 5-7 5-6 5-10 5-7 5-12 5-11 5-14 5-18 Chapter 5 5-15 5-19 5-20 5-21 5-23 5-25 5-26 5-28 5-29 5-31 5-32 0-2-10-3 Revision Date Revised page Approved A Tsechnicals Other 6-1 6-3 6-2 6-4 Chapter 6 6-10 ~ 6-14 6-5 6-19 6-9 6-20 6-14 6-19 6-22 Tsechnicals Other Appendix 1 A1-2 Tsechnicals Other A2-9 A2-4 A2-10 A2-5 A2-15 A2-6 Second Dec. 1998 A2-16 A2-12 Revision A A2-17 A2-13 Appendix 2 A2-20 ~ A2-21 A2-17 A2-24 A2-18 A2-27 A2-21 A2-22 A2-23 A2-25 A2-26 A2-28 ~ A2-32 Tsechnicals Other All Appendix 3.3 (except the A3.5-2 Appendix 3 pages A3.5-3 mentioned in A3.5-6 ~ 9 the right table) Appendix 3.8 Appendix 3.9 0-2-20-4 Revision Date Revised page Approved B Tsechnicals Other Cover 0-2-3 0-3 Contents 0-10 0-11 etc. 0-12 0-14 0-16 0-17 0-18 Tsechnicals Other Chapter 1 1-4 1-13 1-8 1-15 1-19 Tsechnicals Other 2-2 2-8 Second Dec. 1999 2-5 2-15 Revision B 2-7 2-16 2-10 2-24 2-11 2-25 2-12 Chapter 2 2-13 2-14 2-15 2-16 2-18 2-19 2-22 2-23 Tsechnicals Other 3-5 3-1 3-12 3-2 Chapter 3 3-14 3-9 3-10 3-13 3-15 0-2-30-5 Revision Date Revised page Approved B Tsechnicals Other 4-3 4-36 4-24 4-56 4-38 4-39 4-40 4-41 4-42 4-53 Chapter 4 4-54 4-55 4-57 4-63 4-64 4-65 4-67 4-68 4-69 Second Dec. 1999 4-70 Revision B Tsechnicals Other 5-10 5-18 Chapter 5 5-20 5-11 5-31 5-32 Tsechnicals Other Chapter 6 6-9 6-10 Tsechnicals Other Appendix 1 A1-1 A1-2 Tsechnicals Other Appendix 2 A2-12 A2-22 A2-26 0-60-2-4 Revision Date Revised page Approved B Tsechnicals Other A3.1-2 A3.1-1 A3.1-7 A3.1-6 A3.2-1 A3.2-6 A3.2-2 A3.3-1 A3.2-3 A3.4-6 A3.2-7 A3.5-1 A3.4-1 A3.5-9 A3.4-2 A3.6-1 A3.4-3 A3.7-1 Second D3ec. 1999 Appendix A3.4-7 A3.8-1 Revision B A3.5-10 A3.9-1 A3.6-2 A3.6-5 A3.6-6 A3.6-9 A3.7-2 A3.7-5 A3.7-6 A3.7-9 A3.9-1 A3.9-2 0-2-50-7 Revision Date Revised page Approved C Tsechnicals Other Contents etc. 0-3~6 0-10~19 Tsechnicals Other Chapter 1 1-4~7 1-1~3 1-18~19 1-13 1-20~21 Tsechnicals Other 2-1 Chapter 2 2-7 21-14~2 Tsechnicals Other 3-12 Chapter 3 3-16~18 3-21~22 Second 3-26 Dec. 2001 Revision C Tsechnicals Other 4-4~8 4-24~28 4-21~23 4-30~36 Chapter 4 4-29 4-46~49 4-37~45 4-54~56 4-50~51 4-58~59 4-71 Tsechnicals Other 5-1 Chapter 5 5-4 5-7 5-17 5-19 Tsechnicals Other Chapter 6 6-10 6-3 6-12 6-9 0-2-60-8 C Revision Date Revised page Approved Tsechnicals Other Appendix 1 A11-2 A1- Tsechnicals Other Appendix 2 A62-25 A2- A2-11 A2-20 Tsechnicals Other A3.1-1~2 A3.1-3~5 A3.1-6 A3.2-4~5 A3.2-1~3 A3.4-2 Second Dec. 2001 A3.2-6~7 A3.4-4~5 Revision C A3.3-1 A3.4-7 A3.3-3 A3.5-4 A3.3-5~7 A3.6-2 Appendix 3 A3.4-1~3 A3.6-5 A3.4-6 A3.7-2 A3.5-1 A3.5-4 A3.6-1 A3.7-1 A3.8-1 A3.9-1 A3.10-1~10 A3.11-1~4 0-2-70-9 CONTENTS CHAPTER 1. INTRODUCTION 1.1 Purpose of the User’s Manual ...................................................................1-1 1.2 H-IIA Launch System .................................................................................1-1 1.2.1 H-IIA launch vehicle .............................................................................. 1-1 1.2.2 Launch facilities ..................................................................................... 1-4 1.2.3 Payload accommodations ..................................................................... 1-5 1.2.4 Users / NASDA relationship .................................................................. 1-5 1.2.5 Advantages of H-IIA .............................................................................. 1-5 CA 1.3 H-IIA Launch System Related Documents .............................................1-22 1.3.1 H-IIA Payload-Related Facilities and GSE Manual (in preparation) .... 1-22 1.3.2 Launch Vehicle Payload Safety Requirements ................................... 1-22 1.4 Definition of terms ....................................................................................1-22 CHAPTER 2. MISSION PERFORMANCE 2.1 General .....................................................................................................2-1 2.1.1 Mission profile ....................................................................................... 2-1 2.1.1.1 Booster and first stage phase .......................................................... 2-1 2.1.1.2 Second stage phase ........................................................................ 2-2 A 2.2 Performance Ground Rules .......................................................................2-7 2.2.1 Payload mass definition ......................................................................... 2-7 A 2.2.2 Launch vehicle configurations ............................................................... 2-7 2.2.3 Launch vehicle performance confidence levels ..................................... 2-7 2.3 Geostationary Transfer Orbit (GTO) Mission .............................................2-7 2.3.1 Payload capability for single launch....................................................... 2-7 2.3.2 Payload capability for dual (GTO and GTO) launch .............................. 2-8 2.3.3 Typical orbital parameters ...................................................................... 2-8 2.3.4 Injection accuracies ............................................................................... 2-8 2.3.5 Typical sequence of events.................................................................... 2-8 2.3.6 Typical trajectory .................................................................................... 2-8 B 2.3.7 Typical flight parameters ........................................................................ 2-9 2.4 Sun-Synchronous Orbit (SSO) Mission ...................................................2-16 C 2.4.1 Payload capability ............................................................................... 2-16 2.4.2 Typical orbital parameters ................................................................... 2-16 2.4.3 Injection accuracies ............................................................................. 2-16 2.4.4 Typical trajectory ................................................................................. 2-16 2.5 Low Earth Orbit (LEO) Mission ................................................................2-18 2.5.1 Payload capability ............................................................................... 2-18 2.6 Earth Escape Mission ..............................................................................2-21 2.6.1 Payload capability ............................................................................... 2-21 0-3 2.7 Spacecraft Orientation and Separation ..................................................2-22 2.7.1 General description ............................................................................. 2-22 2.7.2 Separation sequence .......................................................................... 2-22 2.7.3 Spin-up performance ........................................................................... 2-22 2.7.4 Pointing accuracy ................................................................................ 2-22 2.7.5 Relative separation velocity................................................................. 2-23 2.7.6 Separation tip-off rate .......................................................................... 2-23 2.7.7 Dual launch sequence ......................................................................... 2-23 CHAPTER 3. ENVIRONMENTS 3.1 General .....................................................................................................3-1 3.2 Mechanical Environments .........................................................................3-1 3.2.1 General .................................................................................................
Recommended publications
  • Call for M5 Missions
    ESA UNCLASSIFIED - For Official Use M5 Call - Technical Annex Prepared by SCI-F Reference ESA-SCI-F-ESTEC-TN-2016-002 Issue 1 Revision 0 Date of Issue 25/04/2016 Status Issued Document Type Distribution ESA UNCLASSIFIED - For Official Use Table of contents: 1 Introduction .......................................................................................................................... 3 1.1 Scope of document ................................................................................................................................................................ 3 1.2 Reference documents .......................................................................................................................................................... 3 1.3 List of acronyms ..................................................................................................................................................................... 3 2 General Guidelines ................................................................................................................ 6 3 Analysis of some potential mission profiles ........................................................................... 7 3.1 Introduction ............................................................................................................................................................................. 7 3.2 Current European launchers ...........................................................................................................................................
    [Show full text]
  • Launch Options for the Future: a Buyer's Guide (Part 7 Of
    — Chapter 3 Enhanced Baseline CONTENTS , Page Improving the Shuttle . 27 Advanced Solid Rocket Motors (ASRMs) . 27 Liquid Rocket Boosters (LRBs) . 28 Lighter Tanks . 29 Improving Shuttle Ground Operations . 29 Improving Existing ELVs . 29 Delta . 30 Atlas-Centaur . ● ● . .* . 30 Titan . ● . ✎ ✎ . 30 Capability . ✎ . ✎ ✎ . ● ✎ ✎ . 30 Table 3-1. Theoretical Lift Capability of Enhanced U.S. Launch Systems. 31 Chapter 3 Enhanced Baseline The ENHANCED BASELINE option is the U.S. Government’s “Best Buy” if . it desires a space program with current or slightly greater levels of activity. By making in- cremental improvements to existing launch vehicles, production and launch facilities, the U.S. could increase its launch capacity to about 1.4 million pounds per year to LEO. The investment required would be low compared to building new vehicles; however, the ade- quacy of the resulting fleet resiliency and dependability is uncertain. This option would not provide the low launch costs (e.g. 10 percent of current costs) sought for SDI deploy- ment or an aggressive civilian space initiative, like a piloted mission to Mars, IMPROVING THE SHUTTLE The Shuttle, though a remarkable tech- . reducing the number of factory joints and nological achievement, never achieved its in- the number of parts, tended payload capacity and recent safety . designing the ASRMs so that the Space modifications have further degraded its per- Shuttle Main Engines no longer need to formance by approximately 4,800 pounds. be throttled during the region of maxi- Advanced Solid Rocket Motors (ASRMs) or mum dynamic pressure, Liquid Rocket Boosters (LRBs) have the potential to restore some of this perfor- ● replacing asbestos-bearing materials, mance; studies on both are underway.
    [Show full text]
  • ミルスペース 140710------[What’S New in Virtual Library?]
    - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -ミルスペース 140710- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - [What’s New in Virtual Library?] AW&ST Aviation Week & Space Technology 1406F_Contents.pdf, Cover.jpg 140630AWST_Contents.pdf, Cover.jpg 1405F_Contents.pdf, Cover.jpg NASA Spaceport Magazine 1404F_Contents.pdf, Cover.jpg 1407ksc_Spaceport_Mag_27pages.pdf 1403F_Contents.pdf, Cover.jpg 1407ksc_Spaceport_Mag_Contents.pdf, Cover.jpg Military Technology BIS Space Flight 1406MT_Contents.pdf, Cover.jpg 1407SF_Contents.pdf, Cover.jpg [What’s New in Real Library?] [謝辞] - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2014.7.10 12:30 http://sankei.jp.msn.com/wired/ スマートフォンが国際宇宙ステーション・ロボットの頭脳に 7 月 11 日に ISS に向け打上げる宇宙船には、グーグル 3D ヴィジョン Satellites」(姿勢保持、連動、方向修正同期型実験衛星)の略で、 搭載スマホ「Tango」が積込まれる。ISS 船内で浮遊しながら飛行士た 将来的には、ISS 船外での危険作業を含め、宇宙飛行士の代わりに ちを支援するロボットに利用される。 日常雑務をこなせるようになることが期待されていた。ただし、2006 年に 初めて ISS に送込まれたときには、正確な浮遊動作をする以外に大し たことはできなかった。カリフォルニア州マウンテンヴューにある NASA のエ イムズ研究センタの研究者たちは、2010 年から、SPHERES を改良す る最も優れた方法を探すべく取組んできた。 悩んだ結果、スマホにた どり着いた。 「SPHERES 高度化プロジェクト・マネージャー」のクリス・プ ロヴェンチャーは、Reuters に次のように話している。「われわれは、通信 やカメラ、処理能力の向上、加速度計をはじめとする各種センサなどを NASA は 7 月 11 日(米時間)、ISS に向けて、グーグル新型スマートフ 追加したかった。どうすればよいか頭を悩ませていたときに、その答えは ォンを乗せた宇宙船を打上げ予定。3D ヴィジョン技術「Tango」(日本 自分たちの手の中にあったことに気づいた。つまり、スマートフォンを使お 語版記事) うということになったのだ」 グーグルの「Tango」技術を搭載したスマートフ http://wired.jp/2014/05/26/google-creating-project-tango-tablets-with ォンには、SPHERES が利用するための 3D マップの作成に使用できる -3d-computer-vision/ 赤外線深度センサなど、魅力的な多数の技術が搭載されている。もち
    [Show full text]
  • Paper Session I-A - Liquid Rocket Boosters for Shuttle
    The Space Congress® Proceedings 1989 (26th) Space - The New Generation Apr 25th, 2:00 PM Paper Session I-A - Liquid Rocket Boosters for Shuttle James E. Hughes Manager, LRB Studies, Marshall Space Flight Center, NASA Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Hughes, James E., "Paper Session I-A - Liquid Rocket Boosters for Shuttle" (1989). The Space Congress® Proceedings. 8. https://commons.erau.edu/space-congress-proceedings/proceedings-1989-26th/april-25-1989/8 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. LIQUID ROCKET BOOSTERS FOR SHUTTLE James E. Hughes, Manager LRB Studies Marshall Space Flight Center, NASA ABSTRACT The Liquid Rocket Booster study was initiated vehicles, and a pressure fed system, once by NASA to define an alternative to the Solid referred to as the "Big Dumb Booster". The Rocket Boosters used on the STS. These prime study contractors, Martin Marietta Cor­ studies have involved MSFC, JSC and KSC poration and General Dynamics Space Sys­ and their contractors. The prime study con­ tems, were assisted considerably by the ef­ tractors, Martin Marietta Corporation and forts of Lockheed Space Operations Co. General Dynamics Space Systems, have (LSOC) at the Kennedy Space Center and identified Liquid Booster configurations which Lockheed Engineering and Sciences Co. would replace the SRB's in the Shuttle stack. (LESC) at Johnson Space Center, as well as wind tunnel testing at MSFC, and other sup­ The Liquid Rocket Booster increases Shuttle port.
    [Show full text]
  • + Part 17: Acronyms and Abbreviations (265 Kb PDF)
    17. Acronyms and Abbreviations °C . Degrees.Celsius °F. Degrees.Fahrenheit °R . Degrees.Rankine 24/7. 24.Hours/day,.7.days/week 2–D. Two-Dimensional 3C. Command,.Control,.and.Checkout 3–D. Three-Dimensional 3–DOF . Three-Degrees.of.Freedom 6-DOF. Six-Degrees.of.Freedom A&E. Architectural.and.Engineering ACEIT. Automated.Cost-Estimating.Integrated.Tools ACES . Acceptance.and.Checkout.Evaluation.System ACP. Analytical.Consistency.Plan ACRN. Assured.Crew.Return.Vehicle ACRV. Assured.Crew.Return.Vehicle AD. Analog.to.Digital ADBS. Advanced.Docking.Berthing.System ADRA. Atlantic.Downrange.Recovery.Area AEDC. Arnold.Engineering.Development.Center AEG . Apollo.Entry.Guidance AETB. Alumina.Enhanced.Thermal.Barrier AFB .. .. .. .. .. .. .. Air.Force.Base AFE. Aero-assist.Flight.Experiment AFPG. Apollo.Final.Phase.Guidance AFRSI. Advanced.Flexible.Reusable.Surface.Insulation AFV . Anti-Flood.Valve AIAA . American.Institute.of.Aeronautics.and.Astronautics AL. Aluminum ALARA . As.Low.As.Reasonably.Achievable 17. Acronyms and Abbreviations 731 AL-Li . Aluminum-Lithium ALS. Advanced.Launch.System ALTV. Approach.and.Landing.Test.Vehicle AMS. Alpha.Magnetic.Spectrometer AMSAA. Army.Material.System.Analysis.Activity AOA . Analysis.of.Alternatives AOD. Aircraft.Operations.Division APAS . Androgynous.Peripheral.Attachment.System APS. Auxiliary.Propulsion.System APU . Auxiliary.Power.Unit APU . Auxiliary.Propulsion.Unit AR&D. Automated.Rendezvous.and.Docking. ARC . Ames.Research.Center ARF . Assembly/Remanufacturing.Facility ASE. Airborne.Support.Equipment ASI . Augmented.Space.Igniter ASTWG . Advanced.Spaceport.Technology.Working.Group ASTP. Advanced.Space.Transportation.Program AT. Alternate.Turbopump ATCO. Ambient.Temperature.Catalytic.Oxidation ATCS . Active.Thermal.Control.System ATO . Abort-To-Orbit ATP. Authority.to.Proceed ATS. Access.to.Space ATV . Automated.Transfer.Vehicles ATV .
    [Show full text]
  • Round Trip to Orbit: Human Spaceflight Alternatives
    Round Trip to Orbit: Human Spaceflight Alternatives August 1989 NTIS order #PB89-224661 Recommended Citation: U.S. Congress, Office of Technology Assessment, Round Trip to Orbit: Human Spaceflight Alternatives Special Report, OTA-ISC-419 (Washington, DC: U.S. Government Printing Office, August 1989). Library of Congress Catalog Card Number 89-600744 For sale by the Superintendent of Documents U.S. Government Printing Office, Washington, DC 20402-9325 (order form can be found in the back of this special report) Foreword In the 20 years since the first Apollo moon landing, the Nation has moved well beyond the Saturn 5 expendable launch vehicle that put men on the moon. First launched in 1981, the Space Shuttle, the world’s first partially reusable launch system, has made possible an array of space achievements, including the recovery and repair of ailing satellites, and shirtsleeve research in Spacelab. However, the tragic loss of the orbiter Challenger and its crew three and a half years ago reminded us that space travel also carries with it a high element of risk-both to spacecraft and to people. Continued human exploration and exploitation of space will depend on a fleet of versatile and reliable launch vehicles. As this special report points out, the United States can look forward to continued improvements in safety, reliability, and performance of the Shuttle system. Yet, early in the next century, the Nation will need a replacement for the Shuttle. To prepare for that eventuality, NASA and the Air Force have begun to explore the potential for advanced launch systems, such as the Advanced Manned Launch System and the National Aerospace Plane, which could revolutionize human access to space.
    [Show full text]
  • Large Reusable Liquid Rocket Booster
    Determination of the Nose Cone Shape for a Large Reusable Liquid Rocket Booster by ROBERT LAUREN ACKER B.S., Massachusetts Institute of Technology 1987 SUBMITTED IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF SCIENCE IN AERONAUTICS AND ASTRONAUTICS at the MASSACHUSETTS INSTITUTE OF TECHNOLOGY February 1988 ©Robert L. Acker 1988 The author hereby grants M.I.T. and Hughes Aircraft Company permission to reproduce and to distribute copies of this thesis document in whole or in part. Signature of Author Department of Aeronautics and Astronautics January 12, 1988 Reviewed by C. P. Rubin Hughes Aircraft Company Certified by - rv -- - Prof. Walter M. Hollister Thesis Supervisor, Deprtment of Aeronautics and Astronautics Accepted by , {"' Prof. Harold Y. Wachman Chairman, Department Graduate Committee Department of Aeronautics and Astronautics MASSACHUSETTSINST:7, a OF TECHNOLOGY WHDAWN I FEB 0 4198 M.LT.W LIB-RAiES , J Determination of the Nose Cone Shape for a Large Reusable Liquid Rocket Booster by Robert L. Acker Submitted to the Department of Aeronautics and Astronautics in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics January 15, 1988 Abstract Recently there has been a lot of interest in making reusable space vehicles in an effort to lower launch costs. In addition, the use of liquid propellant in a multistage vehicle provides for the maximum performance. This study examines the forces on the nose cone of the first stage of such a rocket and uses them to determine the best shape for the nose cone. The specific stage looked at is a strap-on booster on a design proposed at Hughes Aircraft Company.
    [Show full text]
  • NASA Range Capabilities Roadmap
    NASA Transformational Spaceport and Range Capabilities Roadmap Interim Review to National Research Council External Review Panel March 31, 2005 Karen Poniatowski NASA Space Operation Mission Directorate Asst. Assoc. Administrator, Launch Services Agenda • Overview/Introduction • Roadmap Approach/Considerations – Roadmap Timeline/Spirals – Requirements Development • Spaceport/Range Capabilities – Mixed Range Architecture • User Requirements/Customer Considerations – Manifest Considerations – Emerging Launch User Requirements • Capability Breakdown Structure/Assessment • Roadmap Team Observations – Transformational Range Test Concept • Roadmap Team Conclusions • Next Steps 2 National Space Transportation Policy Signed December 2004 • National Policy Focus on Assuring Access to Space “The Federal space launch bases and ranges are vital components of the U.S. space transportation infrastructure and are national assets upon which access to space depends for national security, civil, and commercial purposes. The Secretary of Defense and the Administrator of the National Aeronautics and Space Administration shall operate the Federal launch bases and ranges in a manner so as to accommodate users from all sectors; and shall transfer these capabilities to a predominantly space-based range architecture to accommodate, among others, operationally responsive space launch systems and new users.” • NASA seeks to link the Transformational Spaceport and Range Capability Roadmap activity with the new National Space Transportation Policy direction as we
    [Show full text]
  • RX-V665 AV Receiver
    U RX-V665 AV Receiver OWNER’S MANUAL IMPORTANT SAFETY INSTRUCTIONS 1 Read these instructions. CAUTION 2 Keep these instructions. 3 Heed all warnings. RISK OF ELECTRIC SHOCK 4 Follow all instructions. DO NOT OPEN 5 Do not use this apparatus near water. 6 Clean only with dry cloth. CAUTION: TO REDUCE THE RISK OF 7 Do not block any ventilation openings. Install in accordance ELECTRIC SHOCK, DO NOT REMOVE with the manufacturer’s instructions. COVER (OR BACK). NO USER-SERVICEABLE 8 Do not install near any heat sources such as radiators, heat PARTS INSIDE. REFER SERVICING TO registers, stoves, or other apparatus (including amplifiers) QUALIFIED SERVICE PERSONNEL. that produce heat. 9 Do not defeat the safety purpose of the polarized or • Explanation of Graphical Symbols grounding-type plug. A polarized plug has two blades with one wider than the other. A grounding type plug has two The lightning flash with arrowhead symbol, within an blades and a third grounding prong. The wide blade or the equilateral triangle, is intended to alert you to the third prong are provided for your safety. If the provided plug presence of uninsulated “dangerous voltage” within does not fit into your outlet, consult an electrician for the product’s enclosure that may be of sufficient replacement of the obsolete outlet. magnitude to constitute a risk of electric shock to 10 Protect the power cord from being walked on or pinched persons. particularly at plugs, convenience receptacles, and the point The exclamation point within an equilateral triangle where they exit from the apparatus. is intended to alert you to the presence of important 11 Only use attachments/accessories specified by the operating and maintenance (servicing) instructions in manufacturer.
    [Show full text]
  • October, 1974 National Aeronautics and Space Administration 0 Space Shuttle Fact Sheet
    https://ntrs.nasa.gov/search.jsp?R=19740027171 2020-03-23T02:05:58+00:00Z l0 RELEASE NO: 74-267 NASA Headquarters Library 300 E St. SW Rm.1120 Washington, DC 20546 OCTOBER, 1974 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 0 SPACE SHUTTLE FACT SHEET Introduction The Space Shuttle will be a reusable space vehicle operated as a transportation system for a wide variety of space missions in low Earth orbit. The Shuttle will deploy scientific and applications satellites of all types. Since it can carry payloads weigh- ing up to 29,500 kilograms (65,000 pounds) it will replace most of the expendable launch vehicles currently used. The Shuttle will be able to retrieve satellites from Earth orbit; to repair and redeploy them; or bring them back to Earth for refurbishment and reuse. It can also be used to carry out missions in which scientists and technicians conduct experiments in Earth orbit or ser- vice automated satellites already orbiting. The National Aeronautics and Space Administration plans A to develop the Shuttle over the next six years. Horizontal test flights are to begin in 1977, orbital test flights in 1979, and the complete vehicle is to be operational in 1980. The Shuttle will provide an effective and economical means for the United States to utilize and advance its capa- 40 bilities in space. It will reduce substantially the cost of space operations for civilian and defense needs in the decade of the 1980's and beyond. The Shuttle will consist of a reusable orbiter, mounted piggy back at launch on a large expendable liquid propellant tank and two recoverable and reusable solid propellant rocket boosters.
    [Show full text]
  • Anais Do 4O Workshop De Pesquisa Científica
    EDUFRN Eduardo Lacerda Campos Gabriela Oliveira da Trindade Jhoseph Kelvin Lopes de Jesus Carine Azevedo Dantas Luiz Marcos Garcia Gonçalves Anais do 4º Workshop de Pesquisa Científica 1a Edição Natal EDUFRN 2017 Coordenação de Serviços Técnicos Catalogação da Publicação na Fonte. UFRN / Biblioteca Central Zila Mamede Workshop de Pesquisa Científica (4. : 2017 : Natal, RN) Anais do 4º Workshop de Pesquisa científica / [organização] Eduardo Lacerda Campos... [et. al.]. – 1. ed. – Natal, RN : EDUFRN, 2017. 127 p. : il. ISBN : 978-85-425-0726-3 1. Pesquisa científica – Congressos. I. Título. II. Campos, Eduardo Lacerda. CDD 001.42 RN/UF/BCZM CDU 001.891 APRESENTAÇÃO Organizado por alunos da disciplina de Metodologia da Pesquisa Científica do Programa de Pós-Graduação em Engenharia Elétrica e de Computação (PGEEC), Pós-Graduação em Sistemas e Computação (PPGSC) e Pós-Graduação em Engenharia Mecatrônica (PPGEMECA), o Workshop de Pesquisa Científica (WPC) é um meio encontrado por este programa para permitir que os alunos aprendam na prática como os eventos científicos são organizados. O WPC também é importante para instigar nos alunos a busca pelo modo de fazer ciência. COMITÊ ORGANIZADOR Chair’s de Organização: Eduardo Lacerda Campos Bruno de Melo Pinheiro Chair’s de Programa: Jhoseph Kelvin Lopes de Jesus Carine Azevedo Dantas Chair’s de Publicidade: Gabriela Oliveira da Trindade Rafael Magalhães Nóbrega de Araújo Chair’s do Comitê de Informática: Sebastião Ricardo Costa Rodrigues Chair Honorário: Prof. Luiz Marcos G. Gonçalves - UFRN Anais do 4o Workshop de Pesquisa Científica - WPC 2017 Sumário Simulação ParALELA DA Propagação DE Ondas Sísmicas PELO Método DE Elementos EspectrAIS............................................... 5 Protótipo PARA A Avaliação DE Medição DE Vazão EM Poços Injetores MultizONAS .
    [Show full text]
  • Aon ISB Space Insurance Fundamentals PART 1 – Introduction to Space Risk Management
    Aon ISB Space Insurance Fundamentals PART 1 – Introduction to Space Risk Management Aon International Space Brokers Proprietary Why take insurance ? 2 Why Take Insurance ? 3 Why Take Insurance ? 4 Why Take Insurance ? 5 Introduction to Space Missions Typical Space Missions Mobile Satellite Fixed Satellite Remote Navigation Services Services Sensing Aon Proprietary 7 Telecom GEO mission Aon Proprietary Fixed Satellite Services 8 Examples of Remote Sensing Missions Optical (GeoEye) Radar (TerraSAR) Mobile Telecom (Globalstar) Aon Proprietary 9 Examples of MEO missions Navigation (GPS) Mobile Communications (ICO F series) Broadband (O3b) Aon Proprietary 10 Introduction to Satellite Architecture General Satellites Architecture ● The satellite is an autonomous object which needs to fulfil a specific mission over a long period of time ● Its architecture is directly driven by the mission and the specific constraints of the space environment ● Every satellite is essentially composed of: – A payload (instruments or communication module) dedicated to the mission – A platform which provides all elements necessary to the payload over the satellite lifetime ● The satellite must cope with specific space environment constraints: – Energy (i.e. full autonomy including during sun eclipses) – Thermal (-160°C in the shadow of the Earth; + 150°C in direct sunlight) – Electromagnetic (Earth radiation belts, solar storms) – Mechanical (acceleration, acoustic and vibrations constraints during launch) – Mass (with respect to the launcher capability) Aon Proprietary
    [Show full text]