Orbital Sciences 2013 Annual Report Final Version.Pdf
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Launch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite
46th AIAA Aerospace Sciences Meeting and Exhibit AIAA 2008-1131 7 – 10 January 20006, Reno, Nevada Launch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite Stephen A. Whitmore* and Tyson K. Smith† Utah State University, Logan, UT, 84322-4130 A trade study investigating the economics, mass budget, and concept of operations for delivery of a small technology-demonstration satellite to a medium-altitude earth orbit is presented. The mission requires payload deployment at a 19,000 km orbit altitude and an inclination of 55o. Because the payload is a technology demonstrator and not part of an operational mission, launch and deployment costs are a paramount consideration. The payload includes classified technologies; consequently a USA licensed launch system is mandated. A preliminary trade analysis is performed where all available options for FAA-licensed US launch systems are considered. The preliminary trade study selects the Orbital Sciences Minotaur V launch vehicle, derived from the decommissioned Peacekeeper missile system, as the most favorable option for payload delivery. To meet mission objectives the Minotaur V configuration is modified, replacing the baseline 5th stage ATK-37FM motor with the significantly smaller ATK Star 27. The proposed design change enables payload delivery to the required orbit without using a 6th stage kick motor. End-to-end mass budgets are calculated, and a concept of operations is presented. Monte-Carlo simulations are used to characterize the expected accuracy of the final orbit. -
Stratolaunch Chooses Megadoors for the Hangar Housing the World's
Aircraft Manufacturing Mojave, CA End user: Stratolaunch chooses Megadoors for the Stratolaunch stratolaunch.com hangar housing the world’s largest aircraft. Design build © ASSA ABLOY Entrance Systems AB CS.AVS/ORG.EN-1.1/1901 contractor: Background Wallace & Smith ASSA ABLOY Entrance Systems proudly provided Business entrepreneur Richard Branson of Virgin Group has General Contractors Stratolaunch Systems, a Paul G. Allen Project, with a since licensed the technology behind SpaceShipOne for wallacesmith.com 420’w x 68’h (128m x 21m) Megadoor hangar door Virgin Galactic, a venture that will take paying customers into system for their new fabrication facility located in Mojave suborbital space. Metal building California. Inside this facility, the world’s largest aircraft supplier: is being fabricated by Scaled Composites which has a Critical issues: CBC Steel Buildings wingspan of 380’ (116m) and thrust provided by (6) 747 Desert Conditions: cbcsteelbuildings.com aircraft engines. This aircraft will be used as a carrier The composite carrier vehicle being crafted inside by the Hangar Statistics: vehicle, flying to 30,000ft with a rocket that will then be highly skilled technicians requires an environment protected • 103 257sq ft. launched with a payload destined for space. This system from the harsh conditions of the Mojave desert. For example, (9 592 m2) will revolutionize space transportation. the fine dust blowing around the desert airport is notorious for coating everything not properly protected. Keeping • 420’ clear span (128m) In 2004, SpaceShipOne ushered in a new era of space sensitive aviation electronics, engines and other aircraft • 3,000,000lbs of travel, when it became the first non-govern-mental components from being affected by the dust and sand structural steel manned rocket ship to fly beyond the earth’s atmosphere. -
Small Space Launch: Origins & Challenges Lt Col Thomas H
Small Space Launch: Origins & Challenges Lt Col Thomas H. Freeman, USAF, [email protected], (505)853-4750 Maj Jose Delarosa, USAF, [email protected], (505)846-4097 Launch Test Squadron, SMC/SDTW Small Space Launch: Origins The United States Space Situational Awareness capability continues to be a key element in obtaining and maintaining the high ground in space. Space Situational Awareness satellites are critical enablers for integrated air, ground and sea operations, and play an essential role in fighting and winning conflicts. The United States leads the world space community in spacecraft payload systems from the component level into spacecraft, and in the development of constellations of spacecraft. The United States’ position is founded upon continued government investment in research and development in space technology [1], which is clearly reflected in the Space Situational Awareness capabilities and the longevity of these missions. In the area of launch systems that support Space Situational Awareness, despite the recent development of small launch vehicles, the United States launch capability is dominated by an old, unresponsive and relatively expensive set of launchers [1] in the Expandable, Expendable Launch Vehicles (EELV) platforms; Delta IV and Atlas V. The EELV systems require an average of six to eight months from positioning on the launch table until liftoff [3]. Access to space requires maintaining a robust space transportation capability, founded on a rigorous industrial and technology base. The downturn of commercial space launch service use has undermined, for the time being, the ability of industry to recoup its significant investment in current launch systems. -
Review of Nasa's Acquisition of Commercial Launch Services
FEBRUARY 17, 2011 AUDIT REPORT OFFICE OF AUDITS REVIEW OF NASA’S ACQUISITION OF COMMERCIAL LAUNCH SERVICES OFFICE OF INSPECTOR GENERAL National Aeronautics and Space Administration REPORT NO. IG-11-012 (ASSIGNMENT NO. A-09-011-00) Final report released by: Paul K. Martin Inspector General Acronyms COTS Commercial Orbital Transportation Services CRS Commercial Resupply Services DOD Department of Defense EELV Evolved Expendable Launch Vehicle ELV Expendable Launch Vehicle ESMD Exploration Systems Mission Directorate GAO Government Accountability Office GLAST Gamma-ray Large Area Space Telescope IBEX Interstellar Boundary Explorer ICBM Intercontinental Ballistic Missile ICESat-II Ice, Cloud, and Land Elevation Satellite IDIQ Indefinite-Delivery, Indefinite-Quantity ISS International Space Station LADEE Lunar Atmosphere and Dust Environment Explorer LCROSS Lunar Crater Observation and Sensing Satellite LRO Lunar Reconnaissance Orbiter LSP Launch Services Program NLS NASA Launch Services OCO Orbiting Carbon Observatory OIG Office of Inspector General PPBE Planning, Programming, Budgeting, and Execution SMAP Soil Moisture Active Passive SMD Science Mission Directorate SOMD Space Operations Mission Directorate ULA United Launch Alliance REPORT NO. IG-11-012 FEBRUARY 17, 2011 OVERVIEW REVIEW OF NASA’S ACQUISITION OF COMMERCIAL LAUNCH SERVICES The Issue Commercial U.S. launch services providers compete domestically and internationally for contracts to carry satellites and other payloads into orbit using unmanned, single-use vehicles known as expendable launch vehicles (ELVs). However, since the late 1990s the global commercial launch market has generally declined following the downturn in the telecommunications services industry, which was the primary customer of the commercial space industry. Given this trend, U.S. launch services providers struggling to remain economically viable have been bolstered by the Commercial Space Act of 1998 (Public Law 105-303), which requires NASA and other Federal agencies to plan missions and procure space transportation services from U.S. -
Minotaur I User's Guide
This page left intentionally blank. Minotaur I User’s Guide Revision Summary TM-14025, Rev. D REVISION SUMMARY VERSION DOCUMENT DATE CHANGE PAGE 1.0 TM-14025 Mar 2002 Initial Release All 2.0 TM-14025A Oct 2004 Changes throughout. Major updates include All · Performance plots · Environments · Payload accommodations · Added 61 inch fairing option 3.0 TM-14025B Mar 2014 Extensively Revised All 3.1 TM-14025C Sep 2015 Updated to current Orbital ATK naming. All 3.2 TM-14025D Sep 2018 Branding update to Northrop Grumman. All 3.3 TM-14025D Sep 2020 Branding update. All Updated contact information. Release 3.3 September 2020 i Minotaur I User’s Guide Revision Summary TM-14025, Rev. D This page left intentionally blank. Release 3.3 September 2020 ii Minotaur I User’s Guide Preface TM-14025, Rev. D PREFACE This Minotaur I User's Guide is intended to familiarize potential space launch vehicle users with the Mino- taur I launch system, its capabilities and its associated services. All data provided herein is for reference purposes only and should not be used for mission specific analyses. Detailed analyses will be performed based on the requirements and characteristics of each specific mission. The launch services described herein are available for US Government sponsored missions via the United States Air Force (USAF) Space and Missile Systems Center (SMC), Advanced Systems and Development Directorate (SMC/AD), Rocket Systems Launch Program (SMC/ADSL). For technical information and additional copies of this User’s Guide, contact: Northrop Grumman -
Aas 14-281 Suborbital Intercept And
AAS 14-281 SUBORBITAL INTERCEPT AND FRAGMENTATION OF ASTEROIDS WITH VERY SHORT WARNING TIMES Ryan Hupp,∗ Spencer Dewald,∗ and Bong Wiey The threat of an asteroid impact with very short warning times (e.g., 1 to 24 hrs) is a very probable, real danger to civilization, yet no viable countermeasures cur- rently exist. The utilization of an upgraded ICBM to deliver a hypervelocity as- teroid intercept vehicle (HAIV) carrying a nuclear explosive device (NED) on a suborbital interception trajectory is studied in this paper. Specifically, this paper focuses on determining the trajectory for maximizing the altitude of intercept. A hypothetical asteroid impact scenario is used as an example for determining sim- plified trajectory models. Other issues are also examined, including launch vehicle options, launch site placement, late intercept, and some undesirable side effects. It is shown that silo-based ICBMs with modest burnout velocities can be utilized for a suborbital asteroid intercept mission with an NED explosion at reasonably higher altitudes (> 2,500 km). However, further studies will be required in the following key areas: i) NED sizing for properly fragmenting small (50 to 150 m) asteroids, ii) the side effects caused by an NED explosion at an altitude of 2,500 km or higher, iii) the rapid launch readiness of existing or upgraded ICBMs for a suborbital asteroid intercept with short warning times (e.g., 1 to 24 hrs), and iv) precision ascent guidance and terminal intercept guidance. It is emphasized that if an earlier alert (e.g., > 1 week) can be assured, then an interplanetary inter- cept/fragmentation may become feasible, which requires an interplanetary launch vehicle. -
Minotaur I Users Guide
ORBITAL SCIENCES CORPORATION January 2006 Minotaur I User’s Guide Release 2.1 Approved for Public Release Distribution Unlimited Copyright 2006 by Orbital Sciences Corporation. All Rights Reserved. Minotaur I User’s Guide Revision Summary REVISION SUMMARY VERSION DOCUMENT DATE CHANGE PAGE 1.0 TM-14025 Mar 2002 Initial Release All 2.0 TM-14025A Oct 2004 Changes thoughout. Major updates include All • Performance plots • Environments • Payload accommodations • Added 61 inch fairing option 2.1 TM-14025B Jan 2006 General nomenclature, history, and administrative updates All (no technical updates) • Changed “Minotaur” to “Minotaur I” • Updated launch history • Corrected contact information Release 1.1 January 2006 ii Minotaur I User’s Guide Preface This Minotaur I User's Guide is intended to familiarize potential space launch vehicle users with the Minotaur I launch system, its capabilities and its associated services. All data provided herein is for reference purposes only and should not be used for mission specific analyses. Detailed analyses will be performed based on the requirements and characteristics of each specific mission. The launch services described herein are available for US Government sponsored missions via the United States Air Force (USAF) Space and Missile Systems Center, Detachment 12, Rocket Systems Launch Program (RSLP). Readers desiring further information on Minotaur I should contact the USAF Program Office: USAF SMC Det 12/RP 3548 Aberdeen Ave SE Kirtland AFB, NM 87117-5778 Telephone: (505) 846-8957 Fax: (505) 846-5152 Additional copies of this User's Guide and Technical information may also be requested from Orbital at: Orbital Suborbital Program - Mission Development Orbital Sciences Corporation Launch Systems Group 3380 S. -
THAICOM 8 Set to Launch in 2016 to Support Thailand’S Growing Broadcasting Industry, and Serve the Asia and Africa Markets
THAICOM 8 Set to Launch in 2016 To support Thailand’s growing broadcasting industry, And serve the Asia and Africa Markets Nonthaburi, 29 April 2014: Thaicom Public Company Limited, Thailand’s satellite operator, announced today that its planned Thaicom 8 satellite will be launched in the first half of 2016. This new satellite will support the growth of the country’s broadcasting industry and strengthen its competitiveness in the international market. Suphajee Suthumpun, Chairman of the Executive Committee and CEO, Thaicom Public Company Limited said that, “the Company has been preparing the ground work for the Thaicom 8 satellite, including the investment plan, technical design, project feasibility, pre-marketing, as well as, the ITU process to secure the additional frequency rights for Thailand at the 78.5 degrees East orbital slot. Now that the Company has been awarded a license for Thaicom 8 by the National Broadcasting and Telecommunications Commission (NBTC), we can proceed, and we expect to launch Thaicom 8 within the first half of 2016. THAICOM 8 will support the growth of Thailand’s broadcasting industry and provide adequate capacity to serve the HDTV trend. The satellite will also allow us to meet the Ultra-HD demands for Thailand and the international market expected in the future.” Thaicom 8 will expand Thaicom’s existing fleet of Thaicom 5 and 6 positioned at the 78.5 degrees East orbital slot, while Thaicom 7, to be launched in mid-2014, will be positioned at 120 degrees East. The Company’s Thaicom 4 (IPSTAR) broadband satellite is located at the 119.5 degrees East orbital slot and provides broadband and backhaul services to 13 countries throughout the Asia Pacific region. -
Do Not Circulate
LA-7328-PR Progress Report a . Laser Fusion Program July 1—December 31, 1977 ,- .. .. .. ..-— — DO NOT CIRCULATE PERMANENT RETENTION ! REQUIREDBY CONTRACT v LOS ALAMOS SCIENTIFIC LABORATORY Lail!lik — post Office Box 1663 Los Alamos, New Mexico 87545 An AffumativeAction/EqualOpportunityEmployex . The four most recent reports in this series,un- classified, are LA-65 10-PR, LAY6 16-PR, LA4834-PR, and LA-6982-PR. This work was supported by the US Department of Energy, Office of Laser Fusion. TM. report was prep.rcd as m .CLWUII1O( work sponsored by the United SUICS Go”enlme”l. Neither the Un,ted Stiles I nor the United Slates Department cd Enersy. nor any of their employees. nor any 0( their CO.114C10rS. subcontrar tom. or their ●w.loyecs. makes any warranty. .xD,,!s O, irnPlled. ., P .isume. any Iesal Ii. biiity or responsibkbw for the accuracy. cmnpletcncm. y usefulness of any information. app.; .t.s. product. or Pro..= dl=losed. or rrpreacnm that its w would “.1 i“fri”le privately owned rlthls. UNITED STATES DEPARTMENT OF CNCRGV CONTRACT W-7408 -CNO. S6 LA-7328-PR Progress Report UC-21 IssI,W: December 1978 . Laser Fusion Program at LASL July 1—December 31, 1977 Compiled by Frederick Skoberne 4 .! L-. — .— - . ABSTRACT . ...”” 1 SUMMARY . ...0000oo 2 Introduction . 2 CO, Laser Program . 2 Antares . 2 CO, Laser Technology . 3 Laser Fusion Theory, Experiments, and Target Design . 3 Laser Fusion Target Fabrication . 4 1, CO, LASER PROGRAM . 6 Single-Beam System . 6 llvo-Beam System . 6 Eight-Beam System . 8 II. ANTARES-HIGH-ENERGY GAS IJM3ERFAClLITY . -
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 . -
The Lunar Atmosphere and Dust Environment Explorer Mission
The Lunar Atmosphere and Dust Environment Explorer Mission Butler Hine, Stevan Spremo, Mark Turner NASA Ames Research Center Mail Stop 240-5 Moffett Field, CA 94035 650-604-4449 [email protected] Robert Caffrey NASA Goddard Space Flight Center Mail Stop 401.0 Greenbelt, MD 20771 301-286-0846 [email protected] Abstract— The Lunar Atmosphere and Dust Environment TABLE OF CONTENTS Explorer (LADEE) is a Lunar science orbiter mission 1. INTRODUCTION ................................................................ 1 currently under development to address the goals of the 2. MISSION REQUIREMENTS................................................ 2 National Research Council decadal surveys and the recent 3. MISSION DESIGN.............................................................. 2 “Scientific Context for Exploration of the Moon” (SCEM) 4. SPACECRAFT DESIGN ...................................................... 5 [1] report to study the pristine state of the lunar atmosphere 12 5. MISSION SYSTEM ARCHITECTURE.................................. 8 and dust environment prior to significant human activities. 6. LAUNCH VEHICLE ........................................................... 9 LADEE will determine the composition of the lunar 7. SUMMARY ........................................................................ 9 atmosphere and investigate the processes that control its REFERENCES........................................................................ 9 distribution and variability, including sources, sinks, and surface interactions. -
Minotuar-User-Guide-3.Pdf
This page left intentionally blank. Minotaur IV • V • VI User’s Guide Revision Summary TM-17589, Rev. E REVISION SUMMARY VERSION DOCUMENT DATE CHANGE PAGE 1.0 TM-17589 Jan 2005 Initial Release All 1.1 TM-17589A Jan 2006 General nomenclature, history, and administrative up- All dates (no technical updates) 1. Updated launch history 2. Corrected contact information 2.0 TM-17589B Jun 2013 Extensively Revised All 2.1 TM-17589C Aug 2015 Updated to current Orbital ATK naming. All 2.2 TM-17589D Aug 2015 Minor updates to correct Orbital ATK naming. All 2.3 TM-17589E Apr 2019 Branding update to Northrop Grumman. All Corrected Figures 4.2.2-1 and 4.2.2-2. Corrected Section 6.2.1, paragraph 3. 2.4 TM-17589E Sep 2020 Branding update. All Updated contact information. Updated footer. Release 2.4 September 2020 i Minotaur IV • V • VI User’s Guide Revision Summary TM-17589, Rev. E This page left intentionally blank. Release 2.4 September 2020 ii Minotaur IV • V • VI User’s Guide User’s Guide Preface TM-17589, Rev. E The information provided in this user’s guide is for initial planning purposes only. Information for develop- ment/design is determined through mission specific engineering analyses. The results of these analyses are documented in a mission-specific Interface Control Document (ICD) for the payloader organization to use in their development/design process. This document provides an overview of the Minotaur system design and a description of the services provided to our customers. For technical information and additional copies of this User’s