Starliner Rudolf Spoor Vertregt-Raket Van De Hoofdredacteur
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ULA Atlas V Launch to Feature Full Complement of Aerojet Rocketdyne Solid Rocket Boosters
April 13, 2018 ULA Atlas V Launch to Feature Full Complement of Aerojet Rocketdyne Solid Rocket Boosters SACRAMENTO, Calif., April 13, 2018 (GLOBE NEWSWIRE) -- The upcoming launch of the U.S. Air Force Space Command (AFSPC)-11 satellite aboard a United Launch Alliance Atlas V rocket from Cape Canaveral Air Force Station, Florida, will benefit from just over 1.74 million pounds of added thrust from five AJ-60A solid rocket boosters supplied by Aerojet Rocketdyne. The mission marks the eighth flight of the Atlas V 551 configuration, the most powerful Atlas V variant that has flown to date. The Atlas V 551 configuration features a 5-meter payload fairing, five AJ-60As and a Centaur upper stage powered by a single Aerojet Rocket RL10C-1 engine. This configuration of the U.S. government workhorse launch vehicle is capable of delivering 8,900 kilograms of payload to geostationary transfer orbit (GTO), and also has been used to send scientific probes to explore Jupiter and Pluto. The Centaur upper stage also uses smaller Aerojet Rocketdyne thrusters for pitch, yaw and roll control, while both stages of the Atlas V employ pressurization vessels built by Aerojet Rocketdyne's ARDÉ subsidiary. "The Atlas V is able to perform a wide variety of missions for both government and commercial customers, and the AJ-60A is a major factor in that versatility," said Aerojet Rocketdyne CEO and President Eileen Drake. "Aerojet Rocketdyne developed the AJ-60A specifically for the Atlas V, delivering the first booster just 42 months after the contract award, which underscores our team's ability to design and deliver large solid rocket motors in support of our nation's strategic goals and efforts to explore our solar system." The flight of the 100th AJ-60A, the largest monolithically wound solid rocket booster ever flown, took place recently as part of a complement of four that helped an Atlas V 541 place the nation's newest weather satellite into GTO. -
Richard Hunter1, Mike Loucks2, Jonathan Currie1, Doug Sinclair3, Ehson Mosleh1, Peter Beck1
Co-Authors: Richard Hunter1, Mike Loucks2, Jonathan Currie1, Doug Sinclair3, Ehson Mosleh1, Peter Beck1 1 Rocket Lab USA, Inc. 2Space Exploration Engineering 3Sinclair by Rocket Lab (formerly Sinclair Interplanetary) Photon-enabled Planetary Small Spacecraft Missions For Decadal Science A White Paper for the 2023-2032 Planetary Decadal Survey 1. OVERVIEW Regular, low-cost Decadal-class science missions to planetary destinations enabled by small high-ΔV spacecraft, like the high-energy Photon, support expanding opportunities for scientists and increase the rate of science return. The high-energy Photon can launch on Electron to precisely target escape asymptotes for planetary small spacecraft missions with payload masses up to ~50 kg without the need for a medium or heavy lift launch vehicle. The high-energy Photon can also launch as a secondary payload with even greater payload masses to deep-space science targets. This paper describes planetary mission concepts connected to science objectives that leverage Rocket Lab’s deep space mission approach. The high-energy Photon can access various planetary science targets of interest including the cislunar environment, Small Bodies, Mars, Venus, and the Outer Planets. Additional planetary small spacecraft missions with focused investigations are recommended, including dedicated small spacecraft missions that do not rely on launch as a secondary payload. 2. HIGH-ENERGY PHOTON Figure 1: The high-energy The high-energy Photon (Figure 1) is a self-sufficient small spacecraft Photon enables small planetary capable of long-duration interplanetary cruise. Its power system is science missions, including Venus probe missions. conventional, using photovoltaic solar arrays and lithium-polymer secondary batteries. The attitude control system includes star trackers, sun sensors, an inertial measurement unit, three reaction wheels, and a cold-gas reaction control system (RCS). -
Safety Consideration on Liquid Hydrogen
Safety Considerations on Liquid Hydrogen Karl Verfondern Helmholtz-Gemeinschaft der 5/JULICH Mitglied FORSCHUNGSZENTRUM TABLE OF CONTENTS 1. INTRODUCTION....................................................................................................................................1 2. PROPERTIES OF LIQUID HYDROGEN..........................................................................................3 2.1. Physical and Chemical Characteristics..............................................................................................3 2.1.1. Physical Properties ......................................................................................................................3 2.1.2. Chemical Properties ....................................................................................................................7 2.2. Influence of Cryogenic Hydrogen on Materials..............................................................................9 2.3. Physiological Problems in Connection with Liquid Hydrogen ....................................................10 3. PRODUCTION OF LIQUID HYDROGEN AND SLUSH HYDROGEN................................... 13 3.1. Liquid Hydrogen Production Methods ............................................................................................ 13 3.1.1. Energy Requirement .................................................................................................................. 13 3.1.2. Linde Hampson Process ............................................................................................................15 -
Interstellar Probe on Space Launch System (Sls)
INTERSTELLAR PROBE ON SPACE LAUNCH SYSTEM (SLS) David Alan Smith SLS Spacecraft/Payload Integration & Evolution (SPIE) NASA-MSFC December 13, 2019 0497 SLS EVOLVABILITY FOUNDATION FOR A GENERATION OF DEEP SPACE EXPLORATION 322 ft. Up to 313ft. 365 ft. 325 ft. 365 ft. 355 ft. Universal Universal Launch Abort System Stage Adapter 5m Class Stage Adapter Orion 8.4m Fairing 8.4m Fairing Fairing Long (Up to 90’) (up to 63’) Short (Up to 63’) Interim Cryogenic Exploration Exploration Exploration Propulsion Stage Upper Stage Upper Stage Upper Stage Launch Vehicle Interstage Interstage Interstage Stage Adapter Core Stage Core Stage Core Stage Solid Solid Evolved Rocket Rocket Boosters Boosters Boosters RS-25 RS-25 Engines Engines SLS Block 1 SLS Block 1 Cargo SLS Block 1B Crew SLS Block 1B Cargo SLS Block 2 Crew SLS Block 2 Cargo > 26 t (57k lbs) > 26 t (57k lbs) 38–41 t (84k-90k lbs) 41-44 t (90k–97k lbs) > 45 t (99k lbs) > 45 t (99k lbs) Payload to TLI/Moon Launch in the late 2020s and early 2030s 0497 IS THIS ROCKET REAL? 0497 SLS BLOCK 1 CONFIGURATION Launch Abort System (LAS) Utah, Alabama, Florida Orion Stage Adapter, California, Alabama Orion Multi-Purpose Crew Vehicle RL10 Engine Lockheed Martin, 5 Segment Solid Rocket Aerojet Rocketdyne, Louisiana, KSC Florida Booster (2) Interim Cryogenic Northrop Grumman, Propulsion Stage (ICPS) Utah, KSC Boeing/United Launch Alliance, California, Alabama Launch Vehicle Stage Adapter Teledyne Brown Engineering, California, Alabama Core Stage & Avionics Boeing Louisiana, Alabama RS-25 Engine (4) -
Los Motores Aeroespaciales, A-Z
Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 < aeroteca.com > Depósito Legal B 9066-2016 Título: Los Motores Aeroespaciales A-Z. © Parte/Vers: 1/12 Página: 1 Autor: Ricardo Miguel Vidal Edición 2018-V12 = Rev. 01 Los Motores Aeroespaciales, A-Z (The Aerospace En- gines, A-Z) Versión 12 2018 por Ricardo Miguel Vidal * * * -MOTOR: Máquina que transforma en movimiento la energía que recibe. (sea química, eléctrica, vapor...) Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 Este facsímil es < aeroteca.com > Depósito Legal B 9066-2016 ORIGINAL si la Título: Los Motores Aeroespaciales A-Z. © página anterior tiene Parte/Vers: 1/12 Página: 2 el sello con tinta Autor: Ricardo Miguel Vidal VERDE Edición: 2018-V12 = Rev. 01 Presentación de la edición 2018-V12 (Incluye todas las anteriores versiones y sus Apéndices) La edición 2003 era una publicación en partes que se archiva en Binders por el propio lector (2,3,4 anillas, etc), anchos o estrechos y del color que desease durante el acopio parcial de la edición. Se entregaba por grupos de hojas impresas a una cara (edición 2003), a incluir en los Binders (archivadores). Cada hoja era sustituíble en el futuro si aparecía una nueva misma hoja ampliada o corregida. Este sistema de anillas admitia nuevas páginas con información adicional. Una hoja con adhesivos para portada y lomo identifi caba cada volumen provisional. Las tapas defi nitivas fueron metálicas, y se entregaraban con el 4 º volumen. O con la publicación completa desde el año 2005 en adelante. -Las Publicaciones -parcial y completa- están protegidas legalmente y mediante un sello de tinta especial color VERDE se identifi can los originales. -
Dual Thrust Axis Lander (DTAL) Lands Horizontally
Robust Lunar Exploration Using an Efficient Lunar Lander Derived from Existing Upper Stages AIAA 2009-6566 Bernard F. Kutter 1, Frank Zegler 2, Jon Barr 3, Tim Bulk 4, Brian Pitchford 5 United Launch Alliance Denver, CO Future large scale lunar exploration is impeded by the high cost of accessing the lunar surface. This cost is composed of terrestrial launch costs and the cost of developing and operating efficient lunar landers capable of delivering crew and large payloads to the lunar surface. Developing lunar landers from a platform based upon an operational upper stage minimizes development and recurring costs while increasing crew safety and reliability. The Dual Thrust Axis Lander (DTAL) lands horizontally. It uses an RL10 engine to accomplish the descent deceleration to just above the lunar surface. Final landing is accomplished using thrusters mounted along the DTAL body. This configuration places the crew and payloads safely and conveniently close to the lunar surface. This paper describes DTAL and its benefits in supporting a robust lunar exploration program. Initial DTAL-enabled large robotic missions allow NASA to return to the moon quickly and demonstrate hardware to be used by crews that follow. This same mission design supports placement of large lunar base elements (habitats, power plants, rovers, excavation equipment, etc). As the uncrewed missions are completed, and the system matures, astronauts will then use the same, now proven system to access the lunar surface. The reliable DTAL propulsion stage provides the flexibility to visit destinations other than the moon. DTAL’s mass and thermal efficient design provides the capability to visit NEO’s or possibly even Mars. -
Photographs Written Historical and Descriptive
CAPE CANAVERAL AIR FORCE STATION, MISSILE ASSEMBLY HAER FL-8-B BUILDING AE HAER FL-8-B (John F. Kennedy Space Center, Hanger AE) Cape Canaveral Brevard County Florida PHOTOGRAPHS WRITTEN HISTORICAL AND DESCRIPTIVE DATA HISTORIC AMERICAN ENGINEERING RECORD SOUTHEAST REGIONAL OFFICE National Park Service U.S. Department of the Interior 100 Alabama St. NW Atlanta, GA 30303 HISTORIC AMERICAN ENGINEERING RECORD CAPE CANAVERAL AIR FORCE STATION, MISSILE ASSEMBLY BUILDING AE (Hangar AE) HAER NO. FL-8-B Location: Hangar Road, Cape Canaveral Air Force Station (CCAFS), Industrial Area, Brevard County, Florida. USGS Cape Canaveral, Florida, Quadrangle. Universal Transverse Mercator Coordinates: E 540610 N 3151547, Zone 17, NAD 1983. Date of Construction: 1959 Present Owner: National Aeronautics and Space Administration (NASA) Present Use: Home to NASA’s Launch Services Program (LSP) and the Launch Vehicle Data Center (LVDC). The LVDC allows engineers to monitor telemetry data during unmanned rocket launches. Significance: Missile Assembly Building AE, commonly called Hangar AE, is nationally significant as the telemetry station for NASA KSC’s unmanned Expendable Launch Vehicle (ELV) program. Since 1961, the building has been the principal facility for monitoring telemetry communications data during ELV launches and until 1995 it processed scientifically significant ELV satellite payloads. Still in operation, Hangar AE is essential to the continuing mission and success of NASA’s unmanned rocket launch program at KSC. It is eligible for listing on the National Register of Historic Places (NRHP) under Criterion A in the area of Space Exploration as Kennedy Space Center’s (KSC) original Mission Control Center for its program of unmanned launch missions and under Criterion C as a contributing resource in the CCAFS Industrial Area Historic District. -
Launch Vehicle Control Center Architectures
Launch Vehicle Control Center Architectures Michael D. Watson1, Amy Epps2, and Van Woodruff3 NASA Marshall Space Flight Center, Huntsville, AL 35812 Michael Jacob Vachon4 NASA Johnson Space Center, Houston, TX 77058 Julio Monreal5 European Space Agency, Launchers Directorate, Paris, France Marl Levesque6 United Launch Alliance, Vandenberg AFB and Randall Williams7 and Tom McLaughlin8 Aerospace Corporation, El Segundo, CA 90245 Launch vehicles within the international community vary greatly in their configuration and processing. Each launch site has a unique processing flow based on the specific launch vehicle configuration. Launch and flight operations are managed through a set of control centers associated with each launch site. Each launch site has a control center for launch operations; however flight operations support varies from being co-located with the launch site to being shared with the space vehicle control center. There is also a nuance of some having an engineering support center which may be co-located with either the launch or flight control center, or in a separate geographical location altogether. A survey of control center architectures is presented for various launch vehicles including the NASA Space Launch System (SLS), United Launch Alliance (ULA) Atlas V and Delta IV, and the European Space Agency (ESA) Ariane 5. Each of these control center architectures shares some similarities in basic structure while differences in functional distribution also exist. The driving functions which lead to these factors are considered and a model of control center architectures is proposed which supports these commonalities and variations. I. INTRODUCTION Launch vehicles in both Europe and the United States have been operating successfully for several decades. -
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 . -
Internal Aerodynamics in Solid Rocket Propulsion (L’Aérodynamique Interne De La Propulsion Par Moteurs-Fusées À Propergols Solides)
NORTH ATLANTIC TREATY RESEARCH AND TECHNOLOGY ORGANISATION ORGANISATION AC/323(AVT-096)TP/70 www.rta.nato.int RTO EDUCATIONAL NOTES EN-023 AVT-096 Internal Aerodynamics in Solid Rocket Propulsion (L’aérodynamique interne de la propulsion par moteurs-fusées à propergols solides) The material in this publication was assembled to support a RTO/VKI Special Course under the sponsorship of the Applied Vehicle Technology Panel (AVT) and the von Kármán Institute for Fluid Dynamics (VKI) presented on 27-31 May 2002 in Rhode-Saint-Genèse, Belgium. Published January 2004 Distribution and Availability on Back Cover NORTH ATLANTIC TREATY RESEARCH AND TECHNOLOGY ORGANISATION ORGANISATION AC/323(AVT-096)TP/70 www.rta.nato.int RTO EDUCATIONAL NOTES EN-023 AVT-096 Internal Aerodynamics in Solid Rocket Propulsion (L’aérodynamique interne de la propulsion par moteurs-fusées à propergols solides) The material in this publication was assembled to support a RTO/VKI Special Course under the sponsorship of the Applied Vehicle Technology Panel (AVT) and the von Kármán Institute for Fluid Dynamics (VKI) presented on 27-31 May 2002 in Rhode-Saint-Genèse, Belgium. The Research and Technology Organisation (RTO) of NATO RTO is the single focus in NATO for Defence Research and Technology activities. Its mission is to conduct and promote co-operative research and information exchange. The objective is to support the development and effective use of national defence research and technology and to meet the military needs of the Alliance, to maintain a technological lead, and to provide advice to NATO and national decision makers. The RTO performs its mission with the support of an extensive network of national experts. -
Exploring Space
EXPLORING SPACE: Opening New Frontiers Past, Present, and Future Space Launch Activities at Cape Canaveral Air Force Station and NASA’s John F. Kennedy Space Center EXPLORING SPACE: OPENING NEW FRONTIERS Dr. Al Koller COPYRIGHT © 2016, A. KOLLER, JR. All rights reserved. No part of this book may be reproduced without the written consent of the copyright holder Library of Congress Control Number: 2016917577 ISBN: 978-0-9668570-1-6 e3 Company Titusville, Florida http://www.e3company.com 0 TABLE OF CONTENTS Page Foreword …………………………………………………………………………2 Dedications …………………………………………………………………...…3 A Place of Canes and Reeds……………………………………………….…4 Cape Canaveral and The Eastern Range………………………………...…7 Early Missile Launches ...……………………………………………….....9-17 Explorer 1 – First Satellite …………………….……………………………...18 First Seven Astronauts ………………………………………………….……20 Mercury Program …………………………………………………….……23-27 Gemini Program ……………………………………………..….…………….28 Air Force Titan Program …………………………………………………..29-30 Apollo Program …………………………………………………………....31-35 Skylab Program ……………………………………………………………….35 Space Shuttle Program …………………………………………………..36-40 Evolved Expendable Launch Program ……………………………………..41 Constellation Program ………………………………………………………..42 International Space Station ………………………………...………………..42 Cape Canaveral Spaceport Today………………………..…………………43 ULA – Atlas V, Delta IV ………………………………………………………44 Boeing X-37B …………………………………………………………………45 SpaceX Falcon 1, Falcon 9, Dragon Capsule .………….........................46 Boeing CST-100 Starliner …………………………………………………...47 Sierra -
N AS a Facts
National Aeronautics and Space Administration NASA’s Launch Services Program he Launch Services Program (LSP) manufacturing, launch operations and rockets for launching Earth-orbit and Twas established at Kennedy Space countdown management, and providing interplanetary missions. Center for NASA’s acquisition and added quality and mission assurance in In September 2010, NASA’s Launch program management of expendable lieu of the requirement for the launch Services (NLS) contract was extended launch vehicle (ELV) missions. A skillful service provider to obtain a commercial by the agency for 10 years, through NASA/contractor team is in place to launch license. 2020, with the award of four indefinite meet the mission of the Launch Ser- Primary launch sites are Cape Canav- delivery/indefinite quantity contracts. The vices Program, which exists to provide eral Air Force Station (CCAFS) in Florida, expendable launch vehicles that NASA leadership, expertise and cost-effective and Vandenberg Air Force Base (VAFB) has available for its science, Earth-orbit services in the commercial arena to in California. and interplanetary missions are United satisfy agencywide space transporta- Other launch locations are NASA’s Launch Alliance’s (ULA) Atlas V and tion requirements and maximize the Wallops Flight Facility in Virginia, the Delta II, Space X’s Falcon 1 and 9, opportunity for mission success. Kwajalein Atoll in the South Pacific’s Orbital Sciences Corp.’s Pegasus and facts The principal objectives of the LSP Republic of the Marshall Islands, and Taurus XL, and Lockheed Martin Space are to provide safe, reliable, cost-effec- Kodiak Island in Alaska. Systems Co.’s Athena I and II.