Progress of the X-33 Reusable Launch Vehicle Program
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NASA Lessons Learned on Reusable and Expendable Launch Vehicle Operations and Their Application Towards DARPA’S Experimental Spaceplane (XS-1) Program
NASA Lessons Learned on Reusable and Expendable Launch Vehicle Operations and Their Application Towards DARPA’s Experimental Spaceplane (XS-1) Program C. H. Williams NASA GRC R. G. Johnson NASA KSC 15 Jan 15 Outline • Selected Historic Shuttle Operations Data • Shuttle Lessons Learned Recommendations for Lower Cost, Operationally Efficient Launch Vehicle Systems • Selected Expendable launch vehicle experiences • Past NASA Launch Vehicle Development Programs, Studies (1985 to present) • Discussion: Suggested applications of NASA Lessons Learned to already-baselined contractor XS-1 Phase I concepts Selected Historic Shuttle Operations Data 3 Original Shuttle Ops Concept vs. Actual Concept Phase (c. 1974) Operational Phase 4 Overall Results of Cost Analysis • “Direct” (Most Visible) Work Drives Massive (and Least Visible) Technical & Administrative Support Infrastructure STS Budget "Pyramid" (FY 1994 Access to Space Study) • Example: Direct Unplanned Repair Activity Drives Ops Support Infra, Logistics, Sustaining Engineering, Total SR&QA and Flight Certification Generic $M Total Operations Function FY94 (%) Elem. Receipt & Accept. 1.4 0.04% Landing/Recovery 19.6 0.58% Direct (Visible) Work “Tip of the Iceberg” Veh Assy & Integ 27.1 0.81% <10% Launch 56.8 1.69% Offline Payload/Crew 75.9 2.26% + Turnaround 107.3 3.19% Vehicle Depot Maint. 139.0 4.14% Indirect (Hidden) Traffic/Flight Control 199.4 5.93% ~20% Operations Support Infra 360.5 10.73% + Concept-Uniq Logistics 886.4 Support (Hidden) 26.38% ~70% Trans Sys Ops Plan'g & Mgmnt 1487.0 44.25% -
The Flight to Orbit
There are numerous ways to get there— Around the Corner Th As then–US Space Command chief from rocket The Gen. Howell M. Estes III said to launch to space defense writers just before his re- tirement in August, “This is going maneuver to come along a lot quicker than we vehicles—and the think it is. ... We tend to think this stuff is way out there in the future, Air Force is but it’s right around the corner.” keeping its Flight The Air Force and NASA have divided the task of providing the options open. US government with a means of reliable, low-cost transportation to Earth orbit. The Air Force, with the largest immediate need, is heading to up the effort to revamp the Expend- to able Launch Vehicles now used to loft military and other government satellites. Called the Evolved ELV, this program is focused on derivatives of existing rockets. Competitors have been invited to redesign or value- engineer their proven boosters with new materials and technologies to provide reliable launch services at a he Air Force would like to go Orbit far lower price than today’s bench- back and forth to Earth orbit as bit mark of around $10,000 a pound to T O easily as it goes back and forth to Low Earth Orbit. The reasoning is 30,000 feet—routinely, reliably, and that an “evolved”—rather than an relatively cheaply. Such a capability all-new—vehicle will yield cost sav- goes hand in hand with being a true ings while reducing technical risk. -
L AUNCH SYSTEMS Databk7 Collected.Book Page 18 Monday, September 14, 2009 2:53 PM Databk7 Collected.Book Page 19 Monday, September 14, 2009 2:53 PM
databk7_collected.book Page 17 Monday, September 14, 2009 2:53 PM CHAPTER TWO L AUNCH SYSTEMS databk7_collected.book Page 18 Monday, September 14, 2009 2:53 PM databk7_collected.book Page 19 Monday, September 14, 2009 2:53 PM CHAPTER TWO L AUNCH SYSTEMS Introduction Launch systems provide access to space, necessary for the majority of NASA’s activities. During the decade from 1989–1998, NASA used two types of launch systems, one consisting of several families of expendable launch vehicles (ELV) and the second consisting of the world’s only partially reusable launch system—the Space Shuttle. A significant challenge NASA faced during the decade was the development of technologies needed to design and implement a new reusable launch system that would prove less expensive than the Shuttle. Although some attempts seemed promising, none succeeded. This chapter addresses most subjects relating to access to space and space transportation. It discusses and describes ELVs, the Space Shuttle in its launch vehicle function, and NASA’s attempts to develop new launch systems. Tables relating to each launch vehicle’s characteristics are included. The other functions of the Space Shuttle—as a scientific laboratory, staging area for repair missions, and a prime element of the Space Station program—are discussed in the next chapter, Human Spaceflight. This chapter also provides a brief review of launch systems in the past decade, an overview of policy relating to launch systems, a summary of the management of NASA’s launch systems programs, and tables of funding data. The Last Decade Reviewed (1979–1988) From 1979 through 1988, NASA used families of ELVs that had seen service during the previous decade. -
Delta Clipper a Path to the Future
Delta Clipper A Path to the Future By Jason Moore & Ashraf Shaikh Executive Summary Although the Space Shuttle has well served its purpose for years, in order to revitalize and advance the American space program, a new space launch vehicle is needed. A prime candidate for the new manned launch vehicle is the DC-X. The DC-X isn’t a state-of-the-art rocket that would require millions of dollars of new development. The DC-X is a space launch vehicle that has already been tested and proven. Very little remains to be done in order to complete the process of establishing the DC-X as an operational vehicle. All that’s left is the building and final testing of a full-size DC-X, followed by manufacture and distribution. The Space Shuttle, as well as expendable rockets, is very expensive to build, maintain and launch. Costing approximately half a billion dollars for each flight, NASA can only afford to do a limited number of Space Shuttle missions. Also, the Shuttle is maintenance intensive, requiring hundreds of man-hours of maintenance after each flight. The DC-X, however, is very cheap to build, easy to maintain, and much cheaper to operate. If the DC-X was used as NASA’s vehicle of choice, NASA could afford to put more payloads into orbit, and manned space missions wouldn’t be the relative rarity they are now. Since not much remains in order to complete the DC-X, a new private organization dedicated solely to the DC-X would be the ideal choice for the company that would build it. -
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. -
Twolstage REUSABLE LAUNCH SYSTEM UTILIZING a WINGED CORE VEHICLE and GLIDEBACK BOOSTERS
NASA Technical Memorandum 101513 I. TWOlSTAGE REUSABLE LAUNCH SYSTEM UTILIZING A WINGED CORE VEHICLE AND GLIDEBACK BOOSTERS Ian 0. MacConochie James A. Martin James S. Wood Miles 0. Duquette July 1989 - (flASA-TM-lo%!513) TUO-STaGE REUSABLE UUUCH B89-268 78 t SYSTEil UTILIBIFSG A UIBCBD COBE VlzEICLE BllD 6UDBBACX BOOSTERS (HAS., Langley Besearch Center) 21 p CSCL 22B Unclas # 63/16 0324583 National Aeronautics and Space Administration Langley Research Center Hampton, Virginia 23665 TWO-STAGE REUSABLE LAUNCH SYSTEM UTILIZING A WINGED CORE VEHICLE AND GLIDEBACK BOOSTERS BY Ian 0. MacConochie James A. Martin James S. Wood* Miles 0. Duquette* ABSTRACT A near-term technology launch system is descrlbed in which Space Shuttle main engines are used on a manned orbiter and also on twin strap-on unmanned boosters. The orbiter is configured with a circular body and clipped delta wings. The twin strap-on boosters have a circular body and deployable oblique wings for the glideback recovery. The dry and gross weights of the system, capable of delivering 70 klb of cargo to orbit, are compared with the values for the current Shuttle and a core vehicle with hydrocarbon-fuel ed boosters. INTRODUCTION In recent conceptual design studies of launch vehicles (Ref. l), emphasis has been placed on reducing operational complexity by employing comnonality in systems and propellants. In this regard, a launch vehicle has been configured in which liquid oxygen, liquid hydrogen, and current Space Shuttle main engines are used in both a manned core vehicle (orbiting stage) and its strap-on unmanned boosters. The principal objective of this study was to investigate the size and performance of an all-oxygen/hydrogen system using fixed numbers of Shuttle main engines. -
Columbia Accident Investigation Board
COLUMBIA ACCIDENT INVESTIGATION BOARD Report Volume I August 2003 COLUMBIA ACCIDENT INVESTIGATION BOARD On the Front Cover This was the crew patch for STS-107. The central element of the patch was the microgravity symbol, µg, flowing into the rays of the Astronaut symbol. The orbital inclination was portrayed by the 39-degree angle of the Earthʼs horizon to the Astronaut symbol. The sunrise was representative of the numerous science experiments that were the dawn of a new era for continued microgravity research on the International Space Station and beyond. The breadth of science conduct- ed on this mission had widespread benefits to life on Earth and the continued exploration of space, illustrated by the Earth and stars. The constellation Columba (the dove) was chosen to symbolize peace on Earth and the Space Shuttle Columbia. In addition, the seven stars represent the STS-107 crew members, as well as honoring the original Mercury 7 astronauts who paved the way to make research in space possible. The Israeli flag represented the first person from that country to fly on the Space Shuttle. On the Back Cover This emblem memorializes the three U.S. human space flight accidents – Apollo 1, Challenger, and Columbia. The words across the top translate to: “To The Stars, Despite Adversity – Always Explore“ Limited First Printing, August 2003, by the Columbia Accident Investigation Board Subsequent Printing and Distribution by the National Aeronautics and Space Administration and the Government Printing Office Washington, D.C. 2 Report Volume I August 2003 COLUMBIA ACCIDENT INVESTIGATION BOARD IN MEMORIAM Rick D. Husband Commander William C. -
Space Planes and Space Tourism: the Industry and the Regulation of Its Safety
Space Planes and Space Tourism: The Industry and the Regulation of its Safety A Research Study Prepared by Dr. Joseph N. Pelton Director, Space & Advanced Communications Research Institute George Washington University George Washington University SACRI Research Study 1 Table of Contents Executive Summary…………………………………………………… p 4-14 1.0 Introduction…………………………………………………………………….. p 16-26 2.0 Methodology…………………………………………………………………….. p 26-28 3.0 Background and History……………………………………………………….. p 28-34 4.0 US Regulations and Government Programs………………………………….. p 34-35 4.1 NASA’s Legislative Mandate and the New Space Vision………….……. p 35-36 4.2 NASA Safety Practices in Comparison to the FAA……….…………….. p 36-37 4.3 New US Legislation to Regulate and Control Private Space Ventures… p 37 4.3.1 Status of Legislation and Pending FAA Draft Regulations……….. p 37-38 4.3.2 The New Role of Prizes in Space Development…………………….. p 38-40 4.3.3 Implications of Private Space Ventures…………………………….. p 41-42 4.4 International Efforts to Regulate Private Space Systems………………… p 42 4.4.1 International Association for the Advancement of Space Safety… p 42-43 4.4.2 The International Telecommunications Union (ITU)…………….. p 43-44 4.4.3 The Committee on the Peaceful Uses of Outer Space (COPUOS).. p 44 4.4.4 The European Aviation Safety Agency…………………………….. p 44-45 4.4.5 Review of International Treaties Involving Space………………… p 45 4.4.6 The ICAO -The Best Way Forward for International Regulation.. p 45-47 5.0 Key Efforts to Estimate the Size of a Private Space Tourism Business……… p 47 5.1. -
First Stage of a Highly Reliable Reusable Launch System
First Stage of a Highly Reliable Reusable Launch System * $ Kurt J. Kloesel , Jonathan B. Pickrelf, and Emily L. Sayles NASA Dryden Flight Research Center, Edwards, California, 93523-0273 Michael Wright § NASA Goddard Space Flight Center, Greenbelt, Maryland, 20771-0001 Darin Marriott** Embry-Riddle University, Prescott, Arizona, 86301-3720 Dr. Leo Hollandtf General Atomics Electromagnetic Systems Division, San Diego, California, 92121-1194 Dr. Stephen Kuznetsov$$ Power Superconductor Applications Corporation, New Castle, Pennsylvania, 16101-5241 Electromagnetic launch assist has the potential to provide a highly reliable reusable first stage to a space access system infrastructure at a lower overall cost. This paper explores the benefits of a smaller system that adds the advantages of a high specific impulse air-breathing stage and supersonic launch speeds. The method of virtual specific impulse is introduced as a tool to emphasize the gains afforded by launch assist. Analysis shows launch assist can provide a 278-s virtual specific impulse for a first-stage solid rocket. Additional trajectory analysis demonstrates that a system composed of a launch-assisted first-stage ramjet plus a bipropellant second stage can provide a 48-percent gross lift-off weight reduction versus an all-rocket system. The combination of high-speed linear induction motors and ramjets is identified, as the enabling technologies and benchtop prototypes are investigated. The high-speed response of a standard 60 Hz linear induction motor was tested with a pulse width modulated variable frequency drive to 150 Hz using a 10-lb load, achieving 150 mph. A 300-Hz stator-compensated linear induction motor was constructed and static-tested to 1900 lbf average. -
MIT Japan Program Working Paper 01.10 the GLOBAL COMMERCIAL
MIT Japan Program Working Paper 01.10 THE GLOBAL COMMERCIAL SPACE LAUNCH INDUSTRY: JAPAN IN COMPARATIVE PERSPECTIVE Saadia M. Pekkanen Assistant Professor Department of Political Science Middlebury College Middlebury, VT 05753 [email protected] I am grateful to Marco Caceres, Senior Analyst and Director of Space Studies, Teal Group Corporation; Mark Coleman, Chemical Propulsion Information Agency (CPIA), Johns Hopkins University; and Takashi Ishii, General Manager, Space Division, The Society of Japanese Aerospace Companies (SJAC), Tokyo, for providing basic information concerning launch vehicles. I also thank Richard Samuels and Robert Pekkanen for their encouragement and comments. Finally, I thank Kartik Raj for his excellent research assistance. Financial suppport for the Japan portion of this project was provided graciously through a Postdoctoral Fellowship at the Harvard Academy of International and Area Studies. MIT Japan Program Working Paper Series 01.10 Center for International Studies Massachusetts Institute of Technology Room E38-7th Floor Cambridge, MA 02139 Phone: 617-252-1483 Fax: 617-258-7432 Date of Publication: July 16, 2001 © MIT Japan Program Introduction Japan has been seriously attempting to break into the commercial space launch vehicles industry since at least the mid 1970s. Yet very little is known about this story, and about the politics and perceptions that are continuing to drive Japanese efforts despite many outright failures in the indigenization of the industry. This story, therefore, is important not just because of the widespread economic and technological merits of the space launch vehicles sector which are considerable. It is also important because it speaks directly to the ongoing debates about the Japanese developmental state and, contrary to the new wisdom in light of Japan's recession, the continuation of its high technology policy as a whole. -
Space Launch Vehicles: Government Activities, Commercial Competition, and Satellite Exports
Order Code IB93062 CRS Issue Brief for Congress Received through the CRS Web Space Launch Vehicles: Government Activities, Commercial Competition, and Satellite Exports Updated March 22, 2002 Marcia S. Smith Resources, Science, and Industry Division Congressional Research Service The Library of Congress CONTENTS SUMMARY MOST RECENT DEVELOPMENTS BACKGROUND AND ANALYSIS U.S. Launch Vehicle Policy From “Shuttle-Only” to “Mixed Fleet” Clinton Administration Policy U.S. Launch Vehicle Programs and Issues NASA’s Space Shuttle Program Future Launch Vehicle Development Programs DOD’s Evolved Expendable Launch Vehicle (EELV) Program Government-Led Reusable Launch Vehicle (RLV) Programs Private Sector RLV Development Efforts U.S. Commercial Launch Services Industry Congressional Interest Foreign Competition (Including Satellite Export Issues) Europe China Russia Ukraine India Japan LEGISLATION IB93062 03-22-02 Space Launch Vehicles: Government Activities, Commercial Competition, and Satellite Exports SUMMARY Launching satellites into orbit, once the Since 1999, projections for launch services exclusive domain of the U.S. and Soviet gov- demand have decreased dramatically, however. ernments, today is an industry in which compa- At the same time, NASA’s main RLV nies in the United States, Europe, China, Rus- program, X-33, suffered delays. NASA termi- sia, Ukraine, Japan, and India compete. In the nated the program in March 2001. Companies United States, the National Aeronautics and developing new launch vehicles are reassessing Space Administration (NASA) continues to be their plans, and NASA has initiated a new responsible for launches of its space shuttle, and “Space Launch Initiative” (SLI) to broaden the the Air Force has responsibility for launches choices from which it can choose a new RLV associated with U.S. -
1 Design of an Integral Thermal Protection System
DESIGN OF AN INTEGRAL THERMAL PROTECTION SYSTEM FOR FUTURE SPACE VEHICLES By SATISH KUMAR BAPANAPALLI A DISSERTATION PRESENTED TO THE GRADUATE SCHOOL OF THE UNIVERSITY OF FLORIDA IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF DOCTOR OF PHILOSOPHY UNIVERSITY OF FLORIDA 2007 1 © 2007 Satish Kumar Bapanapalli 2 To my loving wife Debamitra, my parents Nagasurya and Adinarayana Bapanapalli, brother Gopi Krishna and sister Lavanya 3 ACKNOWLEDGMENTS I would like to express my sincere gratitude to my advisor and mentor Dr. Bhavani Sankar for his constant support (financial and otherwise) and motivation throughout my PhD studies. He allowed me to work with freedom, was always supportive of my ideas and provided constant motivation for my research work, which helped me grow into a mature and confident researcher under his tutelage. I also thank my committee co-chair Dr. Rafi Haftka for his invaluable inputs and guidance, which have been instrumental for my research work. I am also grateful to him for getting my interest into the field of Structural Optimization, which I hope would be a huge part of all my future research endeavors. I am also thankful to Dr. Max Blosser (NASA Langley) for his crucial inputs in my research work, which kept us on track with the expectations of NASA. I sincerely thank my dissertation committee members Dr. Ashok Kumar and Dr. Gary Consolazio for evaluating my research work and my candidature for the PhD degree. I also would like to acknowledge Dr. Peter Ifju and Dr. Nam-Ho Kim for their useful inputs and comments.