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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. -
Delta II Icesat-2 Mission Booklet
A United Launch Alliance (ULA) Delta II 7420-10 photon-counting laser altimeter that advances MISSION rocket will deliver the Ice, Cloud and land Eleva- technology from the first ICESat mission tion Satellite-2 (ICESat-2) spacecraft to a 250 nmi launched on a Delta II in 2003 and operated until (463 km), near-circular polar orbit. Liftoff will 2009. Our planet’s frozen and icy areas, called occur from Space Launch Complex-2 at Vanden- the cryosphere, are a key focus of NASA’s Earth berg Air Force Base, California. science research. ICESat-2 will help scientists MISSION investigate why, and how much, our cryosphere ICESat-2, with its single instrument, the is changing in a warming climate, while also Advanced Topographic Laser Altimeter System measuring heights across Earth’s temperate OVERVIEW (ATLAS), will provide scientists with height and tropical regions and take stock of the vege- measurements to create a global portrait of tation in forests worldwide. The ICESat-2 mission Earth’s third dimension, gathering data that can is implemented by NASA’s Goddard Space Flight precisely track changes of terrain including Center (GSFC). Northrop Grumman built the glaciers, sea ice, forests and more. ATLAS is a spacecraft. NASA’s Launch Services Program at Kennedy Space Center is responsible for launch management. In addition to ICESat-2, this mission includes four CubeSats which will launch from dispens- ers mounted to the Delta II second stage. The CubeSats were designed and built by UCLA, University of Central Florida, and Cal Poly. The miniaturized satellites will conduct research DELTA II For nearly 30 years, the reliable in space weather, changing electric potential Delta II rocket has been an industry and resulting discharge events on spacecraft workhorse, launching critical and damping behavior of tungsten powder in a capabilities for NASA, the Air Force Image Credit NASA’s Goddard Space Flight Center zero-gravity environment. -
Bolden Testimony
HOLD FOR RELEASE UNTIL PRESENTED BY WITNESS November 17, 2011 Statement of The Honorable Charles F. Bolden, Jr. Administrator National Aeronautics and Space Administration before the Subcommittee on Science and Space Committee on Commerce, Science and Transportation U. S. Senate Mr. Chairman and Members of the Subcommittee, thank you for the opportunity to appear before you today to discuss the outlook for NASA’s human space flight program. This has been a remarkable year, as we have completed assembling and outfitting of the U.S. On-orbit Segment (USOS) of the International Space Station (ISS), allowing us to focus on full utilization of the Station’s research capabilities; taken key steps in moving forward into the future of exploration beyond Low-Earth Orbit (LEO); celebrated the 50 th anniversary of human spaceflight; and witnessed the successful conclusion of the historic Space Shuttle Program. We are also pleased with the progress our industry partners have made in developing an American capability to transport cargo and eventually astronauts to the ISS, and end the outsourcing of this work to foreign governments. More importantly, this will add a critical level of redundancy for transporting cargo and crew to the ISS. A robust transportation architecture is important to ensuring full utilization of this amazing research facility. Enabling commercial crew and cargo transportation systems in LEO allows NASA to focus on developing its own systems for sending astronauts on missions of exploration beyond LEO. This split between commercial and Government systems allows for a cost effective approach to promote a broad base for human exploration by the United States. -
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. -
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. -
Trade Studies Towards an Australian Indigenous Space Launch System
TRADE STUDIES TOWARDS AN AUSTRALIAN INDIGENOUS SPACE LAUNCH SYSTEM A thesis submitted for the degree of Master of Engineering by Gordon P. Briggs B.Sc. (Hons), M.Sc. (Astron) School of Engineering and Information Technology, University College, University of New South Wales, Australian Defence Force Academy January 2010 Abstract During the project Apollo moon landings of the mid 1970s the United States of America was the pre-eminent space faring nation followed closely by only the USSR. Since that time many other nations have realised the potential of spaceflight not only for immediate financial gain in areas such as communications and earth observation but also in the strategic areas of scientific discovery, industrial development and national prestige. Australia on the other hand has resolutely refused to participate by instituting its own space program. Successive Australian governments have preferred to obtain any required space hardware or services by purchasing off-the-shelf from foreign suppliers. This policy or attitude is a matter of frustration to those sections of the Australian technical community who believe that the nation should be participating in space technology. In particular the provision of an indigenous launch vehicle that would guarantee the nation independent access to the space frontier. It would therefore appear that any launch vehicle development in Australia will be left to non- government organisations to at least define the requirements for such a vehicle and to initiate development of long-lead items for such a project. It is therefore the aim of this thesis to attempt to define some of the requirements for a nascent Australian indigenous launch vehicle system. -
Espinsights the Global Space Activity Monitor
ESPInsights The Global Space Activity Monitor Issue 2 May–June 2019 CONTENTS FOCUS ..................................................................................................................... 1 European industrial leadership at stake ............................................................................ 1 SPACE POLICY AND PROGRAMMES .................................................................................... 2 EUROPE ................................................................................................................. 2 9th EU-ESA Space Council .......................................................................................... 2 Europe’s Martian ambitions take shape ......................................................................... 2 ESA’s advancements on Planetary Defence Systems ........................................................... 2 ESA prepares for rescuing Humans on Moon .................................................................... 3 ESA’s private partnerships ......................................................................................... 3 ESA’s international cooperation with Japan .................................................................... 3 New EU Parliament, new EU European Space Policy? ......................................................... 3 France reflects on its competitiveness and defence posture in space ...................................... 3 Germany joins consortium to support a European reusable rocket......................................... -
Deep Space Atomic Clock
National Aeronautics and Space Administration Deep Space Atomic Clock tion and radio science. Here are some examples of how one-way deep-space tracking with DSAC can improve navigation and radio science that is not supported by current two-way tracking. Ground-based 1. Simultaneously track two spacecraft on a atomic clocks are downlink with the Deep Space Network (DSN) the cornerstone of at destinations such as Mars, and nearly dou- spacecraft navigation ble a space mission’s tracking data because it for most deep-space missions because of their use no longer has to “time-share” an antenna. in generating precision two-way tracking measure- ments. These typically include range (the distance 2. Improve tracking data precision by an order of between two objects) and Doppler (a measure of magnitude using the DSN’s Ka-band downlink the relative speed between them). A two-way link (a tracking capability. signal that originates and ends at the ground track- ing antenna) is required because today’s spacecraft 3. Mitigate Ka-band’s weather sensitivity (as clocks introduce too much error for the equivalent compared to two-way X-band) by being able one-way measurements to be useful. Ground atom- to switch from a weather-impacted receiving ic clocks, while providing extremely stable frequen- antenna to one in a different location with no cy and time references, are too large for hosting on tracking outages. a spacecraft and cannot survive the harshness of space. New technology is on the horizon that will 4. Track longer by using a ground antenna’s en- change this paradigm. -
Falcon 1 User's Guide
Falcon 1 Launch Vehicle Payload User’s Guide Rev 7 TABLE OF CONTENTS 1. Introduction 4 1.1. Revision History 4 1.2. Purpose 6 1.3. Company Description 6 1.4. Falcon Program Overview 6 1.5. Mission Management 7 2. Falcon 1 Launch Vehicles 8 2.1. Overview 8 2.1.1. Falcon 1 9 2.1.2. Falcon 1e 11 2.2. Availability 12 2.3. Reliability 13 2.4. Performance 15 2.5. Pricing 16 2.6. Standard Services 16 2.7. Non‐standard Services 16 2.8. Vehicle Axes/Attitude Definitions 17 3. Requirements & Environments 18 3.1. Mass Properties 18 3.2. Payload Interfaces 19 3.2.1. Falcon Payload Attach Fittings 19 3.2.2. Test Fittings and Fitcheck Policy 19 3.2.3. Electrical Design Criteria 19 3.3. Documentation Requirements 21 3.4. Payload Environments 23 3.4.1. Transportation Environments 23 3.4.2. Humidity, Cleanliness and Thermal Control 23 3.4.3. Payload Air Conditioning 24 3.4.4. Launch and Flight Environments 24 4. Facilities 32 4.1. Headquarters – Hawthorne, California 32 4.2. Washington, DC 32 4.3. Test Facility ‐ Central Texas 32 4.4. Launch Site – Kwajalein Atoll 33 4.4.1. Processing Services and Equipment 33 5. Launch Operations 36 5.1. Launch Control Organization 36 5.2. Mission Integration 37 5.2.1. Payload Transport to Launch Site 38 5.2.2. Payload Integration 38 5.2.3. Example Flight Profiles 41 D000973 Rev Falcon 1 User’s Guide ‐ D000973 Rev. 7 Page | 3 6. -
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 . -
Asteroid Redirect Mission (ARM) Formulation Assessment and Support Team (FAST) Final Report
NASA/TM–2016-219011 Asteroid Redirect Mission (ARM) Formulation Assessment and Support Team (FAST) Final Report Daniel D. Mazanek and David M. Reeves, Langley Research Center, Hampton, Virginia Paul A. Abell, Johnson Space Center, Houston, Texas Erik Asphaug, Arizona State University, Tempe, Arizona Neyda M. Abreu, Penn State DuBois, DuBois, Pennsylvania James F. Bell, Arizona State University, Tempe, Arizona William F. Bottke, Southwest Research Institute, Boulder, Colorado Daniel T. Britt and Humberto Campins, University of Central Florida, Orlando, Florida Paul W. Chodas, Jet Propulsion Laboratory, Pasadena, California Carolyn M. Ernst, John Hopkins University, Laurel, Maryland Marc D. Fries, Johnson Space Center, Houston, Texas Leslie S. Gertsch, Missouri University of Science and Technology, Rolla, Missouri Daniel P. Glavin, Goddard Space Flight Center, Greenbelt, Maryland Christine M. Hartzell, University of Maryland, College Park, Maryland Amanda R. Hendrix, Planetary Science Institute, Niwot, Colorado Joseph A. Nuth, Goddard Space Flight Center, Greenbelt, Maryland Daniel J. Scheeres, University of Colorado, Boulder, Colorado Joel C. Sercel, TransAstra Corporation, Lake View Terrace, California Driss Takir, United States Geological Survey, Flagstaff, Arizona Kris Zacny, Honeybee Robotics, Pasadena, California February 2016 NASA STI Program ... in Profile Since its founding, NASA has been dedicated to the CONFERENCE PUBLICATION. advancement of aeronautics and space science. The Collected papers from scientific and technical NASA scientific and technical information (STI) conferences, symposia, seminars, or other program plays a key part in helping NASA maintain meetings sponsored or this important role. co-sponsored by NASA. The NASA STI program operates under the auspices SPECIAL PUBLICATION. Scientific, technical, or of the Agency Chief Information Officer. -
Failures in Spacecraft Systems: an Analysis from The
FAILURES IN SPACECRAFT SYSTEMS: AN ANALYSIS FROM THE PERSPECTIVE OF DECISION MAKING A Thesis Submitted to the Faculty of Purdue University by Vikranth R. Kattakuri In Partial Fulfillment of the Requirements for the Degree of Master of Science in Mechanical Engineering August 2019 Purdue University West Lafayette, Indiana ii THE PURDUE UNIVERSITY GRADUATE SCHOOL STATEMENT OF THESIS APPROVAL Dr. Jitesh H. Panchal, Chair School of Mechanical Engineering Dr. Ilias Bilionis School of Mechanical Engineering Dr. William Crossley School of Aeronautics and Astronautics Approved by: Dr. Jay P. Gore Associate Head of Graduate Studies iii ACKNOWLEDGMENTS I am extremely grateful to my advisor Prof. Jitesh Panchal for his patient guidance throughout the two years of my studies. I am indebted to him for considering me to be a part of his research group and for providing this opportunity to work in the fields of systems engineering and mechanical design for a period of 2 years. Being a research and teaching assistant under him had been a rewarding experience. Without his valuable insights, this work would not only have been possible, but also inconceivable. I would like to thank my co-advisor Prof. Ilias Bilionis for his valuable inputs, timely guidance and extremely engaging research meetings. I thank my committee member, Prof. William Crossley for his interest in my work. I had a great opportunity to attend all three courses taught by my committee members and they are the best among all the courses I had at Purdue. I would like to thank my mentors Dr. Jagannath Raju of Systemantics India Pri- vate Limited and Prof.