July 28, 2011 ULA Rideshare Capabilities
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Vulcan Centaur
VULCAN CENTAUR The Vulcan Centaur rocket design leverages the flight-proven success of the Delta IV and Atlas V launch vehicles while introducing new technologies and innovative features to ensure a reliable and aordable space launch service. Vulcan Centaur will service a diverse range of markets including 225 ft commercial, civil, science, cargo and national security space customers. 1 The spacecraft is encapsulated in a 5.4-m- (17.7-ft-) diameter payload fairing (PLF), a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates the spacecraft. The payload attach fitting (PAF) is a similar sandwich composite structure creating the mating interface from spacecraft to second stage. The PLF separates using a debris-free horizontal and vertical separation system with 2 200 ft spring packs and frangible joint assembly. The payload fairing is available in the 15.5-m (51-ft) standard and 21.3-m (70-ft) 1 long configurations. The Centaur upper stage is 5.4 m (17.7 ft) in diameter and 3 11.7 m (38.5 ft) long with a 120,000-lb propellant capacity. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle, with two RL10C 4 engines. The Vulcan Centaur Heavy vehicle, flies the upgraded 2 Centaur using RL10CX engines with nozzle extensions. The 5 175 ft cryogenic tanks are insulated with spray-on foam insulation (SOFI) to manage boil o of cryogens during flight. An aft equipment shelf provides the structural mountings for vehicle electronics. -
General Assembly Distr.: General 29 January 2001
United Nations A/AC.105/751/Add.1 General Assembly Distr.: General 29 January 2001 Original: English Committee on the Peaceful Uses of Outer Space National research on space debris, safety of space objects with nuclear power sources on board and problems of their collisions with space debris Note by the Secretariat* Addendum Contents Chapter Paragraphs Page I. Introduction........................................................... 1-2 2 Replies received from Member States and international organizations .................... 2 United States of America ......................................................... 2 European Space Agency.......................................................... 7 __________________ * The present document contains replies received from Member States and international organizations between 25 November 2000 and 25 January 2001. V.01-80520 (E) 020201 050201 A/AC.105/751/Add.1 I. Introduction 1. At its forty-third session, the Committee on the Peaceful Uses of Outer Space agreed that Member States should continue to be invited to report to the Secretary- General on a regular basis with regard to national and international research concerning the safety of space objects with nuclear power sources, that further studies should be conducted on the issue of collision of orbiting space objects with nuclear power sources on board with space debris and that the Committee’s Scientific and Technical Subcommittee should be kept informed of the results of such studies.1 The Committee also took note of the agreement of the Subcommittee that national research on space debris should continue and that Member States and international organizations should make available to all interested parties the results of that research, including information on practices adopted that had proved effective in minimizing the creation of space debris (A/AC.105/736, para. -
The Messenger
10th anniversary of VLT First Light The Messenger The ground layer seeing on Paranal HAWK-I Science Verification The emission nebula around Antares No. 132 – June 2008 –June 132 No. The Organisation The Perfect Machine Tim de Zeeuw a groundbased spectroscopic comple thousand each semester, 800 of which (ESO Director General) ment to the Hubble Space Telescope. are for Paranal. The User Portal has Italy and Switzerland had joined ESO in about 4 000 registered users and 1981, enabling the construction of the the archive contains 74 TB of data and This issue of the Messenger marks the 3.5m New Technology Telescope with advanced data products. tenth anniversary of first light of the Very pioneering advances in active optics, Large Telescope. It is an excellent occa crucial for the next step: the construction sion to look at the broader implications of the Very Large Telescope, which Winning strategy of the VLT’s success and to consider the received the green light from Council in next steps. 1987 and was built on Cerro Paranal in The VLT opened for business some five the Atacama desert between Antofagasta years after the Keck telescopes, but the and Taltal in Northern Chile. The 8.1m decision to take the time to build a fully Mission Gemini telescopes and the 8.3m Subaru integrated system, consisting of four telescope were constructed on a similar 8.2m telescopes and providing a dozen ESO’s mission is to enable scientific dis time scale, while the Large Binocular Tele foci for a carefully thoughtout comple coveries by constructing and operating scope and the Gran Telescopio Canarias ment of instruments together with four powerful observational facilities that are now starting operations. -
Planetary Science Division Status Report
Planetary Science Division Status Report Jim Green NASA, Planetary Science Division January 26, 2017 Astronomy and Astrophysics Advisory CommiBee Outline • Planetary Science ObjecFves • Missions and Events Overview • Flight Programs: – Discovery – New FronFers – Mars Programs – Outer Planets • Planetary Defense AcFviFes • R&A Overview • Educaon and Outreach AcFviFes • PSD Budget Overview New Horizons exploresPlanetary Science Pluto and the Kuiper Belt Ascertain the content, origin, and evoluFon of the Solar System and the potenFal for life elsewhere! 01/08/2016 As the highest resolution images continue to beam back from New Horizons, the mission is onto exploring Kuiper Belt Objects with the Long Range Reconnaissance Imager (LORRI) camera from unique viewing angles not visible from Earth. New Horizons is also beginning maneuvers to be able to swing close by a Kuiper Belt Object in the next year. Giant IcebergsObjecve 1.5.1 (water blocks) floatingObjecve 1.5.2 in glaciers of Objecve 1.5.3 Objecve 1.5.4 Objecve 1.5.5 hydrogen, mDemonstrate ethane, and other frozenDemonstrate progress gasses on the Demonstrate Sublimation pitsDemonstrate from the surface ofDemonstrate progress Pluto, potentially surface of Pluto.progress in in exploring and progress in showing a geologicallyprogress in improving active surface.in idenFfying and advancing the observing the objects exploring and understanding of the characterizing objects The Newunderstanding of Horizons missionin the Solar System to and the finding locaons origin and evoluFon in the Solar System explorationhow the chemical of Pluto wereunderstand how they voted the where life could of life on Earth to that pose threats to and physical formed and evolve have existed or guide the search for Earth or offer People’sprocesses in the Choice for Breakthrough of thecould exist today life elsewhere resources for human Year forSolar System 2015 by Science Magazine as exploraon operate, interact well as theand evolve top story of 2015 by Discover Magazine. -
Centaur Dl-A Systems in a Nutshell
NASA Technical Memorandum 88880 '5 t I Centaur Dl-A Systems in a Nutshell (NASA-TM-8888o) CElTAUR D1-A SYSTEBS IN A N87- 159 96 tiljTSBELL (NASA) 29 p CSCL 22D Andrew L. Gordan Lewis Research Center Cleveland, Ohio January 1987 . CENTAUR D1-A SYSTEMS IN A NUTSHELL Andrew L. Gordan National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio 44135 SUMMARY This report identifies the unique aspects of the Centaur D1-A systems and subsystems. Centaur performance is described in terms of optimality (pro- pellant usage), flexibility, and airborne computer requirements. Major I-. systems are described narratively with some numerical data given where it may 03 CJ be useful. v, I W INTRODUCT ION The Centaur D1-A launch vehicle continues to be a key element in the Nation's space program. The Atlas/Centaur and Titan/Centaur combinations have boosted into orbit a variety of spacecraft on scientific, lunar, and planetary exploration missions and Earth orbit missions. These versatile, reliable, and accurate space booster systems will contribute to many significant space pro- grams well into the shuttle era. Centaur D1-A is the latest version of the Nation's first high-energy cryogenic launch vehicle. Major improvements in avionics and payload struc- ture have enhanced mission flexibility and mission success reliability. The liquid hydrogen and liquid oxygen propellants and the pressurized stainless steel structure provide a top-performance vehicle. Centaur's primary thrust comes from two Pratt 8, Whitney constant- thrust, turbopump-fed, regeneratively cooled, liquid-fueled rocket engines. Each RL10A-3-3a engine can generate 16 500 lb of thrust, for a total thrust of 33 000 lb. -
Atlas Launch System Mission Planner's Guide, Atlas V Addendum
ATLAS Atlas Launch System Mission Planner’s Guide, Atlas V Addendum FOREWORD This Atlas V Addendum supplements the current version of the Atlas Launch System Mission Plan- ner’s Guide (AMPG) and presents the initial vehicle capabilities for the newly available Atlas V launch system. Atlas V’s multiple vehicle configurations and performance levels can provide the optimum match for a range of customer requirements at the lowest cost. The performance data are presented in sufficient detail for preliminary assessment of the Atlas V vehicle family for your missions. This guide, in combination with the AMPG, includes essential technical and programmatic data for preliminary mission planning and spacecraft design. Interface data are in sufficient detail to assess a first-order compatibility. This guide contains current information on Lockheed Martin’s plans for Atlas V launch services. It is subject to change as Atlas V development progresses, and will be revised peri- odically. Potential users of Atlas V launch service are encouraged to contact the offices listed below to obtain the latest technical and program status information for the Atlas V development. For technical and business development inquiries, contact: COMMERCIAL BUSINESS U.S. GOVERNMENT INQUIRIES BUSINESS INQUIRIES Telephone: (691) 645-6400 Telephone: (303) 977-5250 Fax: (619) 645-6500 Fax: (303) 971-2472 Postal Address: Postal Address: International Launch Services, Inc. Commercial Launch Services, Inc. P.O. Box 124670 P.O. Box 179 San Diego, CA 92112-4670 Denver, CO 80201 Street Address: Street Address: International Launch Services, Inc. Commercial Launch Services, Inc. 101 West Broadway P.O. Box 179 Suite 2000 MS DC1400 San Diego, CA 92101 12999 Deer Creek Canyon Road Littleton, CO 80127-5146 A current version of this document can be found, in electronic form, on the Internet at: http://www.ilslaunch.com ii ATLAS LAUNCH SYSTEM MISSION PLANNER’S GUIDE ATLAS V ADDENDUM (AVMPG) REVISIONS Revision Date Rev No. -
A Ballistics Analysis of the Deep Impact Ejecta Plume: Determining Comet Tempel 1’S Gravity, Mass, and Density
Icarus 190 (2007) 357–390 www.elsevier.com/locate/icarus A ballistics analysis of the Deep Impact ejecta plume: Determining Comet Tempel 1’s gravity, mass, and density James E. Richardson a,∗,H.JayMeloshb, Carey M. Lisse c, Brian Carcich d a Center for Radiophysics and Space Research, Cornell University, Ithaca, NY 14853, USA b Lunar and Planetary Laboratory, University of Arizona, Tucson, AZ 85721-0092, USA c Planetary Exploration Group, Space Department, Johns Hopkins University Applied Physics Laboratory, 11100 Johns Hopkins Road, Laurel, MD 20723, USA d Center for Radiophysics and Space Research, Cornell University, Ithaca, NY 14853, USA Received 31 March 2006; revised 8 August 2007 Available online 15 August 2007 Abstract − In July of 2005, the Deep Impact mission collided a 366 kg impactor with the nucleus of Comet 9P/Tempel 1, at a closing speed of 10.2 km s 1. In this work, we develop a first-order, three-dimensional, forward model of the ejecta plume behavior resulting from this cratering event, and then adjust the model parameters to match the flyby-spacecraft observations of the actual ejecta plume, image by image. This modeling exercise indicates Deep Impact to have been a reasonably “well-behaved” oblique impact, in which the impactor–spacecraft apparently struck a small, westward-facing slope of roughly 1/3–1/2 the size of the final crater produced (determined from initial ejecta plume geometry), and possessing an effective strength of not more than Y¯ = 1–10 kPa. The resulting ejecta plume followed well-established scaling relationships for cratering in a medium-to-high porosity target, consistent with a transient crater of not more than 85–140 m diameter, formed in not more than 250–550 s, for the case of Y¯ = 0 Pa (gravity-dominated cratering); and not less than 22–26 m diameter, formed in not less than 1–3 s, for the case of Y¯ = 10 kPa (strength-dominated cratering). -
ESPA Ring Datasheet
PAYLOAD ADAPTERS | ESPA ESPA THE EVOLVED SECONDARY PAYLOAD ADAPTER ESPA mounts to the standard NSSL (formerly EELV) interface bolt pattern (Atlas V, Falcon 9, Delta IV, OmegA, Vulcan, Courtesy of Lockheed Martin New Glenn) and is a drop-in component in the launch stack. Small payloads mount to ESPA ports featuring either a Ø15-inch bolt circle with 24 fasteners or a 4-point mount with pads at each corner of a 15-inch square; both of these interfaces have become small satellite standards. ESPA is qualified to carry 567 lbs (257 kg), and a Heavy interface Courtesy of NASA (with Ø5/16” fastener hardware) has been introduced with a capacity of 991 lbs (450 kg). All small satellite mass capabilities require the center of gravity (CG) to be within 20 inches (50.8 cm) of the ESPA port surface. Alternative configurations can be accommodated. ESPA GRANDE ESPA Grande is a more capable version of ESPA with Ø24-inch ports; the ring height is typically 42 inches. The Ø24-inch port has been qualified by test to Courtesy of ORBCOMM & Sierra Nevada Corp. carry small satellites up to 1543 lb (700 kg). ESPA ESPA IS ADAPTABLE TO UNIQUE MISSION REQUIREMENTS • The Air Force’s STP-1 mission delivered multiple small satellites on an Atlas V. • NASA’s Lunar Crater Observation and Sensing Satellite (LCROSS): ESPA was the spacecraft hub for the LCROSS shepherding satellite in 2009. • ORBCOMM Generation 2 (OG2) launched stacks of two and three ESPA Grandes on two different Falcon 9 missions and in total deployed 17 satellites. -
Spaceflight, Inc. General Payload Users Guide
Spaceflight, Inc. SF‐2100‐PUG‐00001 Rev F 2015‐22‐15 Payload Users Guide Spaceflight, Inc. General Payload Users Guide 3415 S. 116th St, Suite 123 Tukwila, WA 98168 866.204.1707 spaceflightindustries.com i Spaceflight, Inc. SF‐2100‐PUG‐00001 Rev F 2015‐22‐15 Payload Users Guide Document Revision History Rev Approval Changes ECN No. Sections / Approved Pages CM Date A 2011‐09‐16 Initial Release Updated electrical interfaces and launch B 2012‐03‐30 environments C 2012‐07‐18 Official release Updated electrical interfaces and launch D 2013‐03‐05 environments, reformatted, and added to sections Updated organization and formatting, E 2014‐04‐15 added content on SHERPA, Mini‐SHERPA and ISS launches, updated RPA CG F 2015‐05‐22 Overall update ii Spaceflight, Inc. SF‐2100‐PUG‐00001 Rev F 2015‐22‐15 Payload Users Guide Table of Contents 1 Introduction ........................................................................................................................... 7 1.1 Document Overview ........................................................................................................................ 7 1.2 Spaceflight Overview ....................................................................................................................... 7 1.3 Hardware Overview ......................................................................................................................... 9 1.4 Mission Management Overview .................................................................................................... 10 2 Secondary -
Atlas V Cutaway Poster
ATLAS V Since 2002, Atlas V rockets have delivered vital national security, science and exploration, and commercial missions for customers across the globe including the U.S. Air Force, the National Reconnaissance Oice and NASA. 225 ft The spacecraft is encapsulated in either a 5-m (17.8-ft) or a 4-m (13.8-ft) diameter payload fairing (PLF). The 4-m-diameter PLF is a bisector (two-piece shell) fairing consisting of aluminum skin/stringer construction with vertical split-line longerons. The Atlas V 400 series oers three payload fairing options: the large (LPF, shown at left), the extended (EPF) and the extra extended (XPF). The 5-m PLF is a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates both the Centaur upper stage and the spacecraft, which separates using a debris-free pyrotechnic actuating 200 ft system. Payload clearance and vehicle structural stability are enhanced by the all-aluminum forward load reactor (FLR), which centers the PLF around the Centaur upper stage and shares payload shear loading. The Atlas V 500 series oers 1 three payload fairing options: the short (shown at left), medium 18 and long. 1 1 The Centaur upper stage is 3.1 m (10 ft) in diameter and 12.7 m (41.6 ft) long. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle. It uses a single RL10 engine producing 99.2 kN (22,300 lbf) of thrust. -
Stardust Sample Return
National Aeronautics and Space Administration Stardust Sample Return Press Kit January 2006 www.nasa.gov Contacts Merrilee Fellows Policy/Program Management (818) 393-0754 NASA Headquarters, Washington DC Agle Stardust Mission (818) 393-9011 Jet Propulsion Laboratory, Pasadena, Calif. Vince Stricherz Science Investigation (206) 543-2580 University of Washington, Seattle, Wash. Contents General Release ............................................................................................................... 3 Media Services Information ……………………….................…………….................……. 5 Quick Facts …………………………………………..................………....…........…....….. 6 Mission Overview …………………………………….................……….....……............…… 7 Recovery Timeline ................................................................................................ 18 Spacecraft ………………………………………………..................…..……...........……… 20 Science Objectives …………………………………..................……………...…..........….. 28 Why Stardust?..................…………………………..................………….....………............... 31 Other Comet Missions .......................................................................................... 33 NASA's Discovery Program .................................................................................. 36 Program/Project Management …………………………........................…..…..………...... 40 1 2 GENERAL RELEASE: NASA PREPARES FOR RETURN OF INTERSTELLAR CARGO NASA’s Stardust mission is nearing Earth after a 2.88 billion mile round-trip journey -
Commercial Orbital Transportation Services
National Aeronautics and Space Administration Commercial Orbital Transportation Services A New Era in Spaceflight NASA/SP-2014-617 Commercial Orbital Transportation Services A New Era in Spaceflight On the cover: Background photo: The terminator—the line separating the sunlit side of Earth from the side in darkness—marks the changeover between day and night on the ground. By establishing government-industry partnerships, the Commercial Orbital Transportation Services (COTS) program marked a change from the traditional way NASA had worked. Inset photos, right: The COTS program supported two U.S. companies in their efforts to design and build transportation systems to carry cargo to low-Earth orbit. (Top photo—Credit: SpaceX) SpaceX launched its Falcon 9 rocket on May 22, 2012, from Cape Canaveral, Florida. (Second photo) Three days later, the company successfully completed the mission that sent its Dragon spacecraft to the Station. (Third photo—Credit: NASA/Bill Ingalls) Orbital Sciences Corp. sent its Antares rocket on its test flight on April 21, 2013, from a new launchpad on Virginia’s eastern shore. Later that year, the second Antares lifted off with Orbital’s cargo capsule, (Fourth photo) the Cygnus, that berthed with the ISS on September 29, 2013. Both companies successfully proved the capability to deliver cargo to the International Space Station by U.S. commercial companies and began a new era of spaceflight. ISS photo, center left: Benefiting from the success of the partnerships is the International Space Station, pictured as seen by the last Space Shuttle crew that visited the orbiting laboratory (July 19, 2011). More photos of the ISS are featured on the first pages of each chapter.