DOCSLIB.ORG

Saturn 5 Launch Vehicle Flight Evaluation Report: AS-506, Apollo

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Saturn 5 Launch Vehicle Flight Evaluation Report: AS-506, Apollo ( e.- GEORSE 8., U MPR- SAT- FE- 69-9 SEPTEMBER 20, 1969 )N NUMBER) (THRU_ _" (.PAG - (,_COI_ o (NASA CR OR TMX OR AD NUMBER) (CATEGORY) SATURN V LAUNCH VEHICLE FLIGHT EVALUATION REPORT-AS-506 APOLLO !1 MISSION _3 ('NASA-_ N-X-625:58) SATURN L _I U t_'_C !I_ VkHICLE _'4'? O- 70 _ :"3i F t. I O•H T _: V A L U A T I_0 i_I_ _'__'_p i3 i::t.T : A S- 5 0 5 A.'v'i" ___L ,.I_"-_ i 1 MIS.,.S[L._ (NASA) Z6# p u n c I a s _O/Z _' "_ _ ___'_ 74 PREPARED BY "'_,,'-// - C "%"_ SATURN FLIGHT EVALUATION WORKING GR_h _ )_.'}:"_ NATIONAL AERONAUTICS AND SPACE ADMINISTRATION _C - Form 774 (Rev October 1967) GEORGE C. MARSHALL SPACE FLIGHT CENTER MPR-SAT-FE-69- 9 SATURNV LAUNCH VEHI CLE FLIGHT EVALUATION REPORT-AS-.506 APOLLO 11 MI SSION PREPARED BY SATURN FLIGHT EVALUATION WORKING GROUP _i_ _:!:!iiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiii_iii!iiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiii!!_!_::i_!ii_:!_i:_>:_ AS-506 LAUNCH VEHICLE MPR-SAT-FE-69-9 SATURN V LAUNCH VEHICLE FLIGHT EVALUATION REPORT - AS-506 APOLLO II MISSION BY Saturn Flight Evaluation Working Group George C. Marshall Space Flight Center ABSTRACT Saturn V AS-506 (Apollo II Mission) was launched at 09:32:00 Eastern Daylight Time on July 16, 1969, from Kennedy Space Center, Complex 39, Pad A. The vehicle lifted off on schedule on a launch azimuth of 90 degrees east of north and rolled to a flight azimuth of 72.058 degrees east of north. The launch vehicle successfully placed the manned spacecraft in the planned translunar injection coast mode. The S-IVB/IU was placed in a solar orbit with a period of 342 days by a combination of continuous LH2 vent, a LOX dump and APS ullage burn. The Principal and Secondary Detailed Objectives of this mission were completely accomplished. No failures, anomalies, or deviations occurred that seriously affected the flight or mission. Any questions or comments pertaining to the information contained in this report are invited and should be directed to: Director, George C. Marshall Space Flight Center Huntsville, Alabama 35812 Attention: Chairman, Saturn Flight Evaluation Working Group, S&E-CSE-LE (Phone 453-2575) TABLEOF CONTENTS Section Page TABLEOF CONTENTS iii LIST OF ILLUSTRATIONS xi LIST OF TABLES xvi ACKNOWLEDGEMENT xix ABBREVIATIONS XX MISSION PLAN xxiii FLIGHT TESTSUMMARY XXV INTRODUCTION I.I Purpose 1.2 Scope EVENTTIMES 2.1 Summaryof Events 2-I 2.2 Variable Time and CommandedSwitch Selector Events 2-2 LAUNCHOPERATIONS 3.1 Summary 3-I 3.2 Prel aunch Milestones 3-I 3.3 Countdown Events 3-I 3.4 Propella'nt Loading 3-I 3.4.1 RP-I Loading 3-I 3.4.2 LOX Loading 3-3 3.4.3 LH2 Loading 3-3 3.4.4 Auxiliary Propulsion System Propellant Loading 3-4 3.5 S-II Insulation, Purge and Leak Detection 3-4 iii TABLEOF CONTENTS(CONTINUED) Section Page 3.6 Ground Support Equipment 3-4 3.6.1 Ground/Vehicle Interface 3-4 3.6.2 MSFCFurnished Ground Support Equipment 3-5 3.6.3 Camera Coverage 3-6 4 TRAJECTORY 4.1 Summary 4.2 Tracking Data Utilization 4.2.1 Tracking During the Ascent Phase of F1 i ght 4-2 Tracking During Orbital Flight 4-2 Tracking During the Injection Phase of F1 ight 4-2 4.2.4 Tracking During the Post Injection Phase of Flight 4-3 4.3 Trajectory Evaluation 4-3 4.3.1 Ascent Trajectory 4-3 4.3.2 Parking Orbit Trajectory 4-6 4.3.3 Injection Trajectory 4-6 4.3.4 Post TLI Trajectory 4-10 4.3.5 S-IVB/IU Post Separation Trajectory 4-11 S-IC PROPULSION 5.1 Summa ry 5-I 5.2 S-IC Ignition Transient Performance 5-I 5.3 S-IC Mainstage Performance 5-3 5.4 S-IC Engine Shutdown Transient Performance 5-5 5.5 S-IC Stage Propellant Management 5-6 5.6 S-lC Pressurization Systems 5-7 5.6.1 S-IC Fuel Pressurization System 5-7 5.6.2 S-IC LOX Pressurization System 5-7 5.7 S-IC Pneumatic Control Pressure System 5-8 5.8 S-IC Purge Systems 5-8 5.9 S-IC POGO Suppression System 5-9 iv TABLE OF CONTENTS (CONTINUED) Section Page 6 S-II PROPULSION 6.1 Summary 6-I 6.2 S-II Chilldown and Buildup Transient Performance 6-2 6.3 S-II Mainstage Performance 6-4 6.4 S-II Shutdown Transient Performance 6-8 6.5 S-II Stage Propellant Management 6-8 6.6 S-II Pressurization Systems 6-9 6.6.1 S-II Fuel Pressurization System 6-9 6.6,2 S-II LOX Pressurization System 6-11 6.7 S-II Pneumatic Control Pressure Sys tern 6-13 6.8 S-II Helium Injection System 6-13 7 S-IVB PROPULSION 7.1 Summary 7-I 7.2 S-IVB Chilldown and Buildup Transient Performance for First Burn 7-I 7.3 S-IVB Mainstage Performance for First Burn 7-3 7.4 S-IVB Shutdown Transient Performance for First Burn 7-5 7.5 S-IVB Parking Orbit Coast Phase Condi ti oni ng 7-5 7.6 S-IVB Chilldown and Restart for Second Burn 7-8 7.7 S-IVB Mainstage Performance for Second Burn 7-12 7.8 S-IVB Shutdown Transient Performance for Second Burn 7-12 7.9 S-IVB Stage Propellant Management 7-12 7.10 S-IVB Pressurization System 7-14 7.10.1 S-IVB Fuel Pressurization System 7-14 7.10.2 S-IVB LOX Pressurization System 7-19 TABLEOF CONTENTS(CONTINUED) Section Page 7.11 S-IVB Pneumatic Control System 7-25 7.12 S-IVB Auxiliary Propulsion System 7-25 7.13 S-IVB Orbital Safing Operations 7-27 7.13.1 Fuel Tank Safing 7-27 7.13.2 LOXTank Dumpand Safing 7-27 7.13.3 Cold Helium Dump 7-29 7.13.4 Ambient Helium Dump 7-29 7.13.5 Stage Pneumatic Control Sphere Safing 7-29 7.13.6 Engine Start Sphere Safing 7-31 7.13.7 Engine Control Sphere Safing 7-31 8 HYDRAULICSYSTEMS 8.1 Summary 8-I 8.2 S-IC Hydraulic System 8-I 8.3 S-II Hydraulic System 8-I 8.4 S-IVB Hydraulic System 8-2 STRUCTURES 9.1 Summary 9-I 9.2 Total Vehicle Structures Evaluation 9-I 9.2.1 Longitudinal Loads 9-I 9.2.2 Bending Moments 9-2 9.2.3 Vehicle Dynamic Characteristics 9-3 9.2.3.1 Longitudinal Dynamic Characteristics 9-3 9,2.3.2 Lateral Dynamic Characteristics 9-12 I0 GUIDANCEANDNAVIGATION 10. 1 Summary I0-I I0.I,I Flight Program I0-I 10.1.2 Instrument Unit Components I0-I 10.2 Guidance Comparisons I0-I 10.2.1 Late S-II Stage EMRShift 10-4 10.3 Navigation and Guidance Scheme Evaluation 10-9 10.4 Guidance System Component Evaluation I0-I0 10.4.1 LVDCPerformance I0-I0 10.4.2 LVDA Performance I0-I0 10.4.3 Ladder Outputs I0-I0 vi TABLE OF CONTENTS(CONTINUED) Secti on Page I0.4.4 Telemetry Outputs I0-I0 10.4.5 Discrete Outputs I0-13 I0.4.6 Switch Selector Functions I0-13 10.4.7 ST-124M-3 Inertial Platform I0-14 II CONTROLSYSTEM II .I Summary II-I II .2 S-IC Control System Evaluation II-I II ,2.1 Liftoff Clearances 11-2 II ,2.2 S-lC Flight Dynamics 11-2 II .3 S-II Control System Evaluation 11-6 II .4 S-IVB Control System Evaluation 11-13 II .4.1 Control System Eval uation During First Burn 11-13 II ,4.2 Control System Evaluation During Parking Orbit 11-13 II .4.3 Control System Evaluation During Second Burn 11-14 II .4.4 Control System Evaluation After S-IVB Second Burn 11-15 12 SEPARATION 12.1 Summary 12-I 12.2 S-IC/S-II Separation Evaluation 12-I 12.3 S-II/S-IVB Separation Evaluation 12-I 12.4 S-IVB/IU/LM/CSM Separation Evaluation 12-I 12.5 Lunar Module Docking and Ejection Evaluation 12-2 13 ELECTRICALNETWORKS 13.1 Summary 13-I 13.2 S-IC Stage Electrical System 13-I 13.3 S-II Stage Electrical System 13-2 13.4 S-IVB Stage Electrical System 13-3 13.5 Instrument Unit Electrical System 13-6 14 RANGESAFETYAND COMMANDSYSTEMS 14.1 Summary 14-I 14.2 Secure Range Safety CommandSystems 14-I vii TABLEOF CONTENTS(CONTINUED) Section Page 14.3 Commandand Communications System 14-I 15 EMERGENCYDETECTIONSYSTEM 15.1 Summary 15-I 15.2 System Evaluation 15-I 15.2.1 General Performance 15-I 15.2.2 Propulsion System Sensors 15-I 15.2.3 Flight Dynamics and Control Sensors 15-I 16 VEHICLEPRESSUREENVIRONMENT 16.1 Summary 16-I 16.2 Base Pressures 16-I 16.2,1 S-IC Base Pressures 16-I 16.2.2 S-II Base Pressures 16-I 16.3 Surface Pressure and Compartment Venting 16-5 16.3.1 S-IC Stage 16-5 16.3.2 S-II Stage 16-5 17 VEHICLETHERMALENVIRONMENT 17.1 Summary 17-I 17.2 S-IC Base Heating 17-I 17.3 S-II Base Region Environment 17-4 17.4 Vehicle Aeroheating Thermal Environment 17-7 17.4.1 S-IC Stage Aeroheating Environment 17-7 17.4.2 S-II Stage Aeroheating Environment 17-8 18 ENVIRONMENTALCONTROLSYSTEM 18.1 Summary 18-I 18.2 S-IC Environmental Control 18-I 18.3 S-II Environmental Control 18-2 18.4 IU Environmental Control 18-2 18.4.1 Thermal Conditioning System 18-2 18.4,2 Gas Bearing Supply System 18-7 19 DATASYSTEMS 19.1 Summary 19-I 19.2 Vehicle Measurement Evaluation 19-I 19.3 Airborne Tel emetry Systems 19-2 viii TABLEOF CONTENTS(CONTINUED) Section Page 19.4 RF Systems Evaluation 19-6 19.4.1 Telemetry System RF Propagation Evaluation 19-6 19.4.2 Tracking Systems RF Propagation Evaluation 19-6 19.4.3 CommandSystems RF Evaluation 19-8 19.5 Optical Instrumentation 19-12 2O MASSCHARACTERISTICS 20.1 Summary 20-I 20.2 Mass Evaluation 20-I 21 MISSION OBJECTIVESACCOMPLISHMENT 21-I 22 FAILURES, ANOMALIESANDDEVIATIONS 22.1 Summary 22-I 22.2 System Failures and Anomalies 22-I 22.3 System Devi ati ons 22-I 23 SPACECRAFTSUMMARY 23-I Appendix A ATMOSPHERE A.I Summary A-I A.2 General Atmospheric Conditions at Launch Time A-I A.3 Surface Observations at Launch Time A-I A.4 Upper Air Measurements A-I A.4.1 Wind Speed A-I A.4.2 Wind Direction A-I A.4.3 Pitch Wind Component A-2 A.4.4 Yaw Wind Component A-2 A.4.5 Component Wind Shears A-2 A.4.6 Extreme Wind Data in the High Dynamic Region A-3 A.5 Thermodynamic Data A-3 A.5.1 Temperature A-3 A.5.2 Atmospheric Pressure A-IO ix TABLE OF CONTENTS (CONTINUED) Appendix Page A.5.3 Atmospheric Density A-IO A.5.4 Optical Index of Refraction A-13 A.6 Comparison of Selected Atmospheric Data for Saturn V Launches A-13 B • AS-506 SIGNIFICANT CONFIGURATION CHANGES B.
Load more

Recommended publications
  • Vasari's Castration of Caelus: Invention and Programme
    VASARI’S CASTRATION OF CAELUS: INVENTION AND PROGRAMME GIORGIO VASARI: The “CASTRAZIONE DEL CIELO FATTA DA SATURNO” [1558], in: Ragionamento di Giorgio Vasari Pittore Aretino fatto in Firenze sopra le invenzioni delle storie dipinte nelle stanze nuove nel palazzo ducale Con lo Illustrissimo Don Francesco De’ Medici primo genito del Duca Cosimo duca di Fiorenza, Firenze, Biblioteca della Galleria degli Uffizi (Manoscritto 11) and COSIMO BARTOLI: „CASTRATIONE DEL CIELO“, 1555, in: “Lo Zibaldone di Giorgio Vasari”, Arezzo, Casa Vasari, Archivio vasariano, (Codice 31) edited with an essay by CHARLES DAVIS FONTES 47 [10 February 2010] Zitierfähige URL: http://archiv.ub.uni-heidelberg.de/artdok/volltexte/2010/894/ urn:nbn:de:bsz:16-artdok-8948 1 PREFACE: The Ragionamenti of Giorgio Vasari, describing his paintings in the Palazzo Vecchio in Florence, the Medici ducal palace, is a leading example of a sixteenth-century publication in which the author describes in extenso his own works, explicating the inventions and, at times, the artistry that lie behind them, as well as documenting the iconographic programme which he has followed. Many of the early surviving letters by Vasari follow a similar intention. Vasari began working in the Palazzo Vecchio in 1555, and he completed the painting of the Salone dei Cinquecento in 1565. Vasari had completed a first draft of the Ragionamenti in 1558, and in 1560 he brought it to Rome, where it was read by Annibale Caro and shown to Michelangelo (“et molti ragionamenti fatte delle cose dell’arte per poter finire quel Dialogo che già Vi lessi, ragionando lui et io insieme”: Vasari to Duke Cosimo, 9 April 1560).
    [Show full text]
  • Space Launch System (Sls) Motors
    Propulsion Products Catalog SPACE LAUNCH SYSTEM (SLS) MOTORS For NASA’s Space Launch System (SLS), Northrop Grumman manufactures the five-segment SLS heavy- lift boosters, the booster separation motors (BSM), and the Launch Abort System’s (LAS) launch abort motor and attitude control motor. The SLS five-segment booster is the largest solid rocket motor ever built for flight. The SLS booster shares some design heritage with flight-proven four-segment space shuttle reusable solid rocket motors (RSRM), but generates 20 percent greater average thrust and 24 percent greater total impulse. While space shuttle RSRM production has ended, sustained booster production for SLS helps provide cost savings and access to reliable material sources. Designed to push the spent RSRMs safely away from the space shuttle, Northrop Grumman BSMs were rigorously qualified for human space flight and successfully used on the last fifteen space shuttle missions. These same motors are a critical part of NASA’s SLS. Four BSMs are installed in the forward frustum of each five-segment booster and four are installed in the aft skirt, for a total of 16 BSMs per launch. The launch abort motor is an integral part of NASA’s LAS. The LAS is designed to safely pull the Orion crew module away from the SLS launch vehicle in the event of an emergency on the launch pad or during ascent. Northrop Grumman is on contract to Lockheed Martin to build the abort motor and attitude control motor—Lockheed is the prime contractor for building the Orion Multi-Purpose Crew Vehicle designed for use on NASA’s SLS.
    [Show full text]
  • Paper Session IA-Shuttle-C Heavy-Lift Vehicle of the 90'S
    The Space Congress® Proceedings 1989 (26th) Space - The New Generation Apr 25th, 2:00 PM Paper Session I-A - Shuttle-C Heavy-Lift Vehicle of the 90's Robert G. Eudy Manager, Shuttle-C Task Team, Marshall Space Flight Center Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Eudy, Robert G., "Paper Session I-A - Shuttle-C Heavy-Lift Vehicle of the 90's" (1989). The Space Congress® Proceedings. 5. https://commons.erau.edu/space-congress-proceedings/proceedings-1989-26th/april-25-1989/5 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]. SHUTTLE-C HEAVY-LIFT VEHICLE OF THE 90 ' S Mr. Robert G. Eudy, Manager Shuttle-C Task Team Marshall Space Flight Center ABSTRACT United States current and planned space activities identify the need for increased payload capacity and unmanned flight to complement the existing Shuttle. To meet this challenge the National Aeronautics and Space Administration is defining an unmanned cargo version of the Shuttle that can give the nation early heavy-lift capability. Called Shuttle-C, this unmanned vehicle is a natural, low-cost evolution of the current Space Shuttle that can be flying 100,000 to 170,000 pound payloads by late 1994. At the core of Shuttle-C design philosophy is the principle of evolvement from the United State's Space Transportation System.
    [Show full text]
  • View / Download
    www.arianespace.com www.starsem.com www.avio Arianespace’s eighth launch of 2021 with the fifth Soyuz of the year will place its satellite passengers into low Earth orbit. The launcher will be carrying a total payload of approximately 5 518 kg. The launch will be performed from Baikonur, in Kazakhstan. MISSION DESCRIPTION 2 ONEWEB SATELLITES 3 Liftoff is planned on at exactly: SOYUZ LAUNCHER 4 06:23 p.m. Washington, D.C. time, 10:23 p.m. Universal time (UTC), LAUNCH CAMPAIGN 4 00:23 a.m. Paris time, FLIGHT SEQUENCES 5 01:23 a.m. Moscow time, 03:23 a.m. Baikonur Cosmodrome. STAKEHOLDERS OF A LAUNCH 6 The nominal duration of the mission (from liftoff to separation of the satellites) is: 3 hours and 45 minutes. Satellites: OneWeb satellite #255 to #288 Customer: OneWeb • Altitude at separation: 450 km Cyrielle BOUJU • Inclination: 84.7degrees [email protected] +33 (0)6 32 65 97 48 RUAG Space AB (Linköping, Sweden) is the prime contractor in charge of development and production of the dispenser system used on Flight ST34. It will carry the satellites during their flight to low Earth orbit and then release them into space. The dedicated dispenser is designed to Flight ST34, the 29th commercial mission from the Baikonur Cosmodrome in Kazakhstan performed by accommodate up to 36 spacecraft per launch, allowing Arianespace and its Starsem affiliate, will put 34 of OneWeb’s satellites bringing the total fleet to 288 satellites Arianespace to timely deliver the lion’s share of the initial into a near-polar orbit at an altitude of 450 kilometers.
    [Show full text]
  • Saturn As the “Sun of Night” in Ancient Near Eastern Tradition ∗
    Saturn as the “Sun of Night” in Ancient Near Eastern Tradition ∗ Marinus Anthony van der Sluijs – Seongnam (Korea) Peter James – London [This article tackles two issues in the “proto-astronomical” conception of the planet Saturn, first attested in Mesopotamia and followed by the Greeks and Hindus: the long-standing problem of Saturn’s baffling association with the Sun; and why Saturn was deemed to be “black”. After an extensive consideration of explanations offered from the 5th century to the 21st, as well as some new “thought experiments”, we suggest that Saturn’s connection with the Sun had its roots in the observations that Saturn’s course appears to be the steadiest one among the planets and that its synodic period – of all the planets – most closely resembles the length of the solar year. For the black colour attributed to Saturn we propose a solution which is partly lexical and partly observational (due to atmospheric effects). Finally, some thoughts are offered on the question why in Hellenistic times some considered the “mock sun” Phaethon of Greek myth to have been Saturn]. Keywords: Saturn, planets, Sun, planet colour. 1. INTRODUCTION Since the late 19th century scholars have been puzzled by a conspicuous peculiarity in the Babylonian nomenclature for the planet Saturn: a number of texts refer to Saturn as the “Sun” ( dutu/20 or Šamaš ), instead of its usual astronomical names Kayam ānu and mul UDU.IDIM. 1 This curious practice was in vogue during the period c. 750-612 BC 2 and is not known from earlier periods, with a single possible exception, discussed below.
    [Show full text]
  • Spaceport Infrastructure Cost Trends
    AIAA 2014-4397 SPACE Conferences & Exposition 4-7 August 2014, San Diego, CA AIAA SPACE 2014 Conference and Exposition Spaceport Infrastructure Cost Trends Brian S. Gulliver, PE1, and G. Wayne Finger, PhD, PE2 RS&H, Inc. The total cost of employing a new or revised space launch system is critical to understanding its business potential, analyzing its business case and funding its development. The design, construction and activation of a commercial launch complex or spaceport can represent a significant portion of the non-recurring costs for a new launch system. While the historical cost trends for traditional launch site infrastructure are fairly well understood, significant changes in the approach to commercial launch systems in recent years have required a reevaluation of the cost of ground infrastructure. By understanding the factors which drive these costs, informed decisions can be made early in a program to give the business case the best chance of economic success. The authors have designed several NASA, military, commercial and private launch complexes and supported the evaluation and licensing of commercial aerospaceports. Data from these designs has been used to identify the major factors which, on a broad scale, drive their non-recurring costs. Both vehicle specific and location specific factors play major roles in establishing costs. I. Introduction It is critical for launch vehicle operators and other stakeholders to understand the factors and trends that affect the non-recurring costs of launch site infrastructure. These costs are often an area of concern when planning for the development of a new launch vehicle program as they can represent a significant capital investment that must be recovered over the lifecycle of the program.
    [Show full text]
  • Ancient Rome
    HISTORY AND GEOGRAPHY Ancient Julius Caesar Rome Reader Caesar Augustus The Second Punic War Cleopatra THIS BOOK IS THE PROPERTY OF: STATE Book No. PROVINCE Enter information COUNTY in spaces to the left as PARISH instructed. SCHOOL DISTRICT OTHER CONDITION Year ISSUED TO Used ISSUED RETURNED PUPILS to whom this textbook is issued must not write on any page or mark any part of it in any way, consumable textbooks excepted. 1. Teachers should see that the pupil’s name is clearly written in ink in the spaces above in every book issued. 2. The following terms should be used in recording the condition of the book: New; Good; Fair; Poor; Bad. Ancient Rome Reader Creative Commons Licensing This work is licensed under a Creative Commons Attribution-NonCommercial-ShareAlike 4.0 International License. You are free: to Share—to copy, distribute, and transmit the work to Remix—to adapt the work Under the following conditions: Attribution—You must attribute the work in the following manner: This work is based on an original work of the Core Knowledge® Foundation (www.coreknowledge.org) made available through licensing under a Creative Commons Attribution-NonCommercial-ShareAlike 4.0 International License. This does not in any way imply that the Core Knowledge Foundation endorses this work. Noncommercial—You may not use this work for commercial purposes. Share Alike—If you alter, transform, or build upon this work, you may distribute the resulting work only under the same or similar license to this one. With the understanding that: For any reuse or distribution, you must make clear to others the license terms of this work.
    [Show full text]
  • Launcherone Success Opens New Space Access Gateway Guy Norris January 22, 2021
    1/22/21 7:05 1/6 LauncherOne Success Opens New Space Access Gateway Guy Norris January 22, 2021 With San Nicolas Island far below, LauncherOne headed for polar orbit. Credit: Virgin Orbit Virgin Orbit had barely tweeted news of the successful Jan. 17 space debut of its LauncherOne vehicle on social media when new launch contracts began arriving in the company’s email inbox. A testament to the pent-up market demand for small-satellite launch capability, the speedy reaction to the long-awaited demonstration of the new space-access vehicle paves the way for multiple follow-on Virgin Orbit missions by year-end and a potential doubling of the rate in 2022. First successful privately developed air-launched, liquid-fueled rocket Payloads deployed for NASA’s Venture Class Launch Services program The glitch-free !ight of LauncherOne on its second demonstration test was a critical and much-welcomed milestone for the Long Beach, California-based company. Coming almost nine years a"er the air-launch concept was #rst unveiled by Virgin founder Richard Branson, and six years a"er the start of full-scale development, the !ight followed last May’s #rst demonstration mission, which ended abruptly when the rocket motor shut o$ a"er just 4 sec. 1/22/21 7:05 2/6 A"er an exhaustive analysis and modi#cations to beef up the oxidizer feed line at the heart of the #rst !ight failure, the path to the Launch Demo 2 test was then delayed until January 2021 by the COVID-19 pandemic. With the LauncherOne system now proven, design changes veri#ed and the #rst 10 small satellites placed in orbit, Virgin Orbit is already focusing on the next steps to ramp up its production and launch-cadence capabilities.
    [Show full text]
  • The Soviet Space Program
    C05500088 TOP eEGRET iuf 3EEA~ NIE 11-1-71 THE SOVIET SPACE PROGRAM Declassified Under Authority of the lnteragency Security Classification Appeals Panel, E.O. 13526, sec. 5.3(b)(3) ISCAP Appeal No. 2011 -003, document 2 Declassification date: November 23, 2020 ifOP GEEAE:r C05500088 1'9P SloGRET CONTENTS Page THE PROBLEM ... 1 SUMMARY OF KEY JUDGMENTS l DISCUSSION 5 I. SOV.IET SPACE ACTIVITY DURING TfIE PAST TWO YEARS . 5 II. POLITICAL AND ECONOMIC FACTORS AFFECTING FUTURE PROSPECTS . 6 A. General ............................................. 6 B. Organization and Management . ............... 6 C. Economics .. .. .. .. .. .. .. .. .. .. .. ...... .. 8 III. SCIENTIFIC AND TECHNICAL FACTORS ... 9 A. General .. .. .. .. .. 9 B. Launch Vehicles . 9 C. High-Energy Propellants .. .. .. .. .. .. .. .. .. 11 D. Manned Spacecraft . 12 E. Life Support Systems . .. .. .. .. .. .. .. .. 15 F. Non-Nuclear Power Sources for Spacecraft . 16 G. Nuclear Power and Propulsion ..... 16 Te>P M:EW TCS 2032-71 IOP SECl<ET" C05500088 TOP SECRGJ:. IOP SECREI Page H. Communications Systems for Space Operations . 16 I. Command and Control for Space Operations . 17 IV. FUTURE PROSPECTS ....................................... 18 A. General ............... ... ···•· ................. ····· ... 18 B. Manned Space Station . 19 C. Planetary Exploration . ........ 19 D. Unmanned Lunar Exploration ..... 21 E. Manned Lunar Landfog ... 21 F. Applied Satellites ......... 22 G. Scientific Satellites ........................................ 24 V. INTERNATIONAL SPACE COOPERATION ............. 24 A. USSR-European Nations .................................... 24 B. USSR-United States 25 ANNEX A. SOVIET SPACE ACTIVITY ANNEX B. SOVIET SPACE LAUNCH VEHICLES ANNEX C. SOVIET CHRONOLOGICAL SPACE LOG FOR THE PERIOD 24 June 1969 Through 27 June 1971 TCS 2032-71 IOP SLClt~ 70P SECRE1- C05500088 TOP SEGR:R THE SOVIET SPACE PROGRAM THE PROBLEM To estimate Soviet capabilities and probable accomplishments in space over the next 5 to 10 years.' SUMMARY OF KEY JUDGMENTS A.
    [Show full text]
  • IAF SPACE TRANSPORTATION SOLUTIONS and INNOVATIONS SYMPOSIUM (D2) Small Launchers: Concepts and Operations (Part I) (7)
    69th International Astronautical Congress 2018 Paper ID: 44054 oral IAF SPACE TRANSPORTATION SOLUTIONS AND INNOVATIONS SYMPOSIUM (D2) Small Launchers: Concepts and Operations (Part I) (7) Author: Ms. Sirisha Bandla Virgin Galactic L.L.C, United States, [email protected] Ms. Monica Jan Virgin Galactic L.L.C, United States, [email protected] LAUNCHERONE: RESPONSIVE LAUNCH FOR SMALL SATELLITES Abstract Virgin Orbit is a developing small launch platform that will provide affordable, dedicated rides to orbit for small satellites starting this year. We are in the midst of a small satellite revolution and with technology advancement packing more capability in smaller packages, small satellites are progressively pro- viding solutions for remote sensing, communications, earth observation and other low-Earth orbit needs. Currently, a small satellite operator is typically forced to ride as a secondary payload, constrained to the primary payload's launch schedule and orbit. However, Virgin Orbit's small launch vehicle, LauncherOne, will soon begin providing frequent, affordable, and dedicated transportation to orbit for small payloads. LauncherOne is a two stage, liquid propulsion (LOX/RP) rocket launched from a Boeing 747-400. By utilizing air-launch, the system is designed to conduct operations from a variety of locations, removing the complexity and scheduling typically associated with traditional launch ranges. LauncherOne will allow customers to select from various launch azimuths, including equatorial inclinations, and will increase avail- able orbital launch windows. The Long Beach, California, USA facility where the team is based has been outfitted with the equipment needed for the manufacture of the LauncherOne rocket, and currently staffs over 300 employees.
    [Show full text]
  • Roman Gods and Goddesses
    History Romans History | LKS2 | Romans | Gods and Goddesses | Lesson 5 Aim • I can understand what religious beliefs the Romans had and know about some of the gods and goddesses that they worshipped. SuccessSuccess Criteria • IStatement can explain 1 Lorem the different ipsum dolor elements sit amet of Roman, consectetur religion. adipiscing elit. • IStatement can tell you 2 the names of some of the main Roman gods and • Sub statement goddesses and write about what they represented to the Roman people. Roman Religion In the earlier Roman times, the Roman people believed in many different gods and goddesses whom they believed controlled different aspects of their lives. They did not have a central belief system of their own as such, but rather borrowed gods, rituals and superstitions from a number of sources and adapted them to suit their own needs. The Romans believed in good and bad omens and they performed many rituals in the hope of receiving good luck. Prayer and sacrifice was important and the Romans held festivals every month to honour the gods. They would worship their gods and goddesses at temples. Elements of Religion Read through the Roman religion information text. Discuss the words below with your partner and work out what they mean. You can use dictionaries to help you. Why did the Romans have/do these things? omen prayer ritual superstition sacrifice festivals worship Roman Gods and Goddesses The Romans had lots of gods and goddesses. Many of their gods and goddesses are the same as the Greek gods, but with different names. They make things very confusing! We are going to look at some of the more popular Roman gods and goddesses.
    [Show full text]
  • Tinker​Ing Gods
    THE NGY REVIEW, 16 Dec. 2018 Tinkering Gods ​ The Plot of Paul Harding’s novel, Tinkers​ : Characters as Metaphors for the Gods in ​ Greek and Roman Mythology by C. Omaña Villanueva Paul Harding was a drummer in a rock band on tour of Europe when he made the choice to write. He had always been a prolific reader, but during one of his road trips between gigs he read a title that seemed to encompass all of humanity. His band broke up and it was then and there that he decided to write. He signed up for a summer writing workshop at Skidmore College and his teacher, Marilynne Robinson, steered him toward the Iowa Writers’ Workshop (Harding, interview). In his first book, Tinkers,​ ​ Harding describes the inner workings of the death of an old man. But in doing so, Harding uses such formidable descriptions and symbolic language that his work can be interpreted in multiple ways. Here, I propose that the three main characters of Harding’s prose, George, his father Howard, and the minister (the unnamed father of Howard), can be interpreted as metaphors for the gods, Cronus/Saturn, Uranus/Caelus, and Hermes/Mercury of Greek and Roman Mythology. THE NGY REVIEW (16 Dec. 2018) ・Omaña Villanueva What does the reader do with the plot of this book? It is a story that made “absolutely” all agents avoid taking on the book (Harding, interview). What is the appeal for the reader? Regarding plot in general, Bell states that “the one thing you will have no matter how lousy” is plot.
    [Show full text]