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Final EA for the Launch and Reentry of Spaceshiptwo Reusable Suborbital Rockets at the Mojave Air and Space Port
Final Environmental Assessment for the Launch and Reentry of SpaceShipTwo Reusable Suborbital Rockets at the Mojave Air and Space Port May 2012 HQ-121575 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Office of Commercial Space Transportation; Finding of No Significant Impact AGENCY: Federal Aviation Administration (FAA) ACTION: Finding of No Significant Impact (FONSI) SUMMARY: The FAA Office of Commercial Space Transportation (AST) prepared a Final Environmental Assessment (EA) in accordance with the National Environmental Policy Act of 1969, as amended (NEPA; 42 United States Code 4321 et seq.), Council on Environmental Quality NEPA implementing regulations (40 Code of Federal Regulations parts 1500 to 1508), and FAA Order 1050.1E, Change 1, Environmental Impacts: Policies and Procedures, to evaluate the potential environmental impacts of issuing experimental permits and/or launch licenses to operate SpaceShipTwo reusable suborbital rockets and WhiteKnightTwo carrier aircraft at the Mojave Air and Space Port in Mojave, California. After reviewing and analyzing currently available data and information on existing conditions and the potential impacts of the Proposed Action, the FAA has determined that issuing experimental permits and/or launch licenses to operate SpaceShipTwo and WhiteKnightTwo at the Mojave Air and Space Port would not significantly impact the quality of the human environment. Therefore, preparation of an Environmental Impact Statement is not required, and the FAA is issuing this FONSI. The FAA made this determination in accordance with all applicable environmental laws. The Final EA is incorporated by reference in this FONSI. FOR A COPY OF THE EA AND FONSI: Visit the following internet address: http://www.faa.gov/about/office_org/headquarters_offices/ast/environmental/review/permits/ or contact Daniel Czelusniak, Environmental Program Lead, Federal Aviation Administration, 800 Independence Ave., SW, Suite 325, Washington, DC 20591; email [email protected]; or phone (202) 267-5924. -
Future Space Launch Vehicles
Future Space Launch Vehicles S. Krishnan Professor of Aerospace Engineering Indian Institute of Technology Madras Chennnai - 600 036, India (Written in 2001) Introduction Space technology plays a very substantial role in the economical growth and the national security needs of any country. Communications, remote sensing, weather forecasting, navigation, tracking and data relay, surveillance, reconnaissance, and early warning and missile defence are its dependent user-technologies. Undoubtedly, space technology has become the backbone of global information highway. In this technology, the two most important sub-technologies correspond to spacecraft and space launch vehicles. Spacecraft The term spacecraft is a general one. While the spacecraft that undertakes a deep space mission bears this general terminology, the one that orbits around a planet is also a spacecraft but called specifically a satellite more strictly an artificial satellite, moons around their planets being natural satellites. Cassini is an example for a spacecraft. This was developed under a cooperative project of NASA, the European Space Agency, and the Italian Space Agency. Cassini spacecraft, launched in 1997, is continuing its journey to Saturn (about 1274 million km away from Earth), where it is scheduled to begin in July 2004, a four- year exploration of Saturn, its rings, atmosphere, and moons (18 in number). Cassini executed two gravity-assist flybys (or swingbys) of Venus one in April 1998 and one in June 1999 then a flyby of Earth in August 1999, and a flyby of Jupiter (about 629 million km away) in December 2000, see Fig. 1. We may note here with interest that ISRO (Indian Space Research Organisation) is thinking of a flyby mission of a spacecraft around Moon (about 0.38 million km away) by using its launch vehicle PSLV. -
THE HELIUM NEAR SPACE LABORATORY Human Near Space Access, Now, More Affordable, Reliable and Safe
66th International Astronautical Congress, Jerusalem, Israel. Copyright ©2015 by the International Astronautical Federation. All rights reserved. IAC-15-B3.2.8.30387 THE HELIUM NEAR SPACE LABORATORY Human Near Space Access, Now, More Affordable, Reliable and Safe. Annelie Schoenmaker, David Ferrer Desclaux, José Mariano López-Urdiales, Gerard Illana Meler zero2infinity SL Cerdanyola del Vallès, Barcelona, Spain +34 935 824 422 [email protected], [email protected], [email protected], [email protected] Abstract The HELIUM (High European Laboratory for Institutes, Universities and Markets) project offers European and international companies, researchers and scientists a platform to access Near Space. Space technologies are on a continuous growth path and many new developments (related to flag-ship Space programmes like Galileo or Copernicus, and a long tail of other Space initiatives) need to be tested, demonstrated and validated before being accepted by the industry. Currently, these newly developed technologies are tested on the ground, using climatic chambers that simulate one, or a few, Space conditions. However, it remains difficult to simulate the integrated effect of all Space conditions. It’s even more difficult to have a human in the loop, which can help understand the interactions between the environment and the experiment. zero2infinity is developing a balloon-borne laboratory that provides cost effective access to Near Space. It’s an environmentally friendly solution that. In Europe there is an increasing demand of flight opportunities to test, validate, demonstrate and calibrate technologies, equipment and new concepts that need to increase their TRL. This is essential to retain the competitiveness of the European Space sector. -
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. -
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 -
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 . -
PARAMETRIC ANALYSIS of PERFORMANCE and DESIGN CHARACTERISTICS for ADVANCED EARTH-TO-ORBIT SHUTTLES by Edwurd A
NASA TECHNICAL NOTE -6767 . PARAMETRIC ANALYSIS OF PERFORMANCE AND DESIGN CHARACTERISTICS FOR ADVANCED EARTH-TO-ORBIT SHUTTLES by Edwurd A. Willis, Jr., Wz'llium C. Struck, und John A. Pudratt Lewis Reseurch Center Clevelund, Ohio 44135 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. APRIL 1972 f TECH LIBRARY KAFB, NM I111111 Hlll11111 Ill# 11111 11111 lllllIll1Ill -. -- 0133bOL 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. - NASA TN D-6767 4. Title and Subtitle PAR I 5. Report Date METRIC NALYSIS OF PERFORMA K! E ND April 1972 DESIGN CHARACTERISTICS FOR ADVANCED EARTH-TO- 6. Performing Organization Code ORBIT SHUTTLES 7. Author(s) 8. Performing Organization Report No. Edward A. Willis, Jr. ; William C. Strack; and John A. Padrutt E-6749 10. Work Unit No. 9. Performing Organization Name and Address 110-06 Lewis Research Center 11. Contract or Grant No. National Aeronautics and Space Administration Cleveland, Ohio 44135 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Technical Note National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington, D. C. 20546 ~~ .. ~~ 16. Abstract Performance, trajectory, and design characteristics are presented for (1) a single-stage shuttle with a single advanced rocket engine, (2) a single-stage shuttle with an initial parallel chemical-engine and advanced-engine burn followed by an advanced-engine sustainer burn (parallel-burn configuration), (3) a single-stage shuttle with an initial chemical-engine burn followed by an advanced-engine burn (tandem-burn configuration), and (4)a two-stage shuttle with a chemical-propulsion booster stage and an advanced-propulsion upper stage. -
A Irb Reathing Hypersonic Vi Sion
1999-01-5515 Ai r b r eathing Hypersonic Vis i o n - O p e r a t i o n a l - V ehicles Design Matrix James L. Hunt Robert J. Pegg Dennis H. Petley NASA Langley Research Center, Hampton, VA ABSTRACT ASCA) is presented in figure 1 along with the airbreath- ing corridor in which these vehicles operate. It includes This paper presents the status of the airbreathing hyper- endothermically-fueled theater defense and transport sonic airplane and space-access vision-operational-vehi- aircraft below Mach 8; above Mach 8, the focus is on cle design matrix, with emphasis on horizontal takeoff dual-fuel and/or hydrogen-fueled airplanes for long and landing systems being studied at Langley; it reflects range cruise, first or second stage launch platforms the synergies and issues, and indicates the thrust of the and/or single-stage-to-orbit (SSTO) vehicles. effort to resolve the design matrix including Mach 5 to The space-access portion of the matrix has been 10 airplanes with global-reach potential, pop-up and expanded and now includes pop-up and launch from dual-role transatmospheric vehicles and airbreathing hypersonic cruise platforms as well as vertical-takeoff, launch systems. The convergence of several critical horizontal-landing (VTHL) launch vehicles. Also, systems/technologies across the vehicle matrix is indi- activities at the NASA centers are becoming integrated; cated. This is particularly true for the low speed propul- LaRC, GRC and MSFC are now participating in an sion system for large unassisted horizontal takeoff vehi- advanced launch vehicle study of airbreathing systems cles which favor turbines and/or perhaps pulse detona- for single-stage-to-orbit. -
Developing Evaluation Measures for the Second Stage Next Generation Engine on Evolved Expendable Launch Vehicles
Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection 2012-03 Developing Evaluation Measures for the Second Stage Next Generation Engine on Evolved Expendable Launch Vehicles Panczenko, Jason A. Monterey, California. Naval Postgraduate School http://hdl.handle.net/10945/6849 NAVAL POSTGRADUATE SCHOOL MONTEREY, CALIFORNIA THESIS DEVELOPING EVALUATION MEASURES FOR THE SECOND STAGE NEXT GENERATION ENGINE ON EVOLVED EXPENDABLE LAUNCH VEHICLES by Jason A. Panczenko March 2012 Thesis Co-Advisors: Doug Nelson Jeff Emdee Second Reader: Christopher Brophy Approved for public release; distribution is unlimited THIS PAGE INTENTIONALLY LEFT BLANK REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704-0188 Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instruction, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188) Washington DC 20503. 1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE 3. REPORT TYPE AND DATES COVERED March 2012 Master’s Thesis 4. TITLE AND SUBTITLE Developing Evaluation Measures for the Second Stage 5. FUNDING NUMBERS Next Generation Engine on Evolved Expendable Launch Vehicles 6. AUTHOR(S) Jason A. Panczenko 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) 8. PERFORMING ORGANIZATION Naval Postgraduate School REPORT NUMBER Monterey, CA 93943-5000 9. -
Suborbital Reusable Launch Vehicles and Applicable Markets
SUBORBITAL REUSABLE LAUNCH VEHICLES AND APPLICABLE MARKETS Prepared by J. C. MARTIN and G. W. LAW Space Launch Support Division Space Launch Operations October 2002 Space Systems Group THE AEROSPACE CORPORATION El Segundo, CA 90245-4691 Prepared for U. S. DEPARTMENT OF COMMERCE OFFICE OF SPACE COMMERCIALIZATION Herbert C. Hoover Building 14th and Constitution Ave., NW Washington, DC 20230 (202) 482-6125, 482-5913 Contract No. SB1359-01-Z-0020 PUBLIC RELEASE IS AUTHORIZED Preface This report has been prepared by The Aerospace Corporation for the Department of Commerce, Office of Space Commercialization, under contract #SB1359-01-Z-0020. The objective of this report is to characterize suborbital reusable launch vehicle (RLV) concepts currently in development, and define the military, civil, and commercial missions and markets that could capitalize on their capabilities. The structure of the report includes a brief background on orbital vs. suborbital trajectories, as well as an overview of expendable and reusable launch vehicles. Current and emerging market opportunities for suborbital RLVs are identified and discussed. Finally, the report presents the technical aspects and program characteristics of selected U.S. and international suborbital RLVs in development. The appendix at the end of this report provides further detail on each of the suborbital vehicles, as well as the management biographies for each of the companies. The integration of suborbital RLVs with existing airports and/or spaceports, though an important factor that needs to be evaluated, was not the focus of this effort. However, it should be noted that the RLV concepts discussed in this report are being designed to minimize unique facility requirements. -
Toward a History of the Space Shuttle an Annotated Bibliography
Toward a History of the Space Shuttle An Annotated Bibliography Part 2, 1992–2011 Monographs in Aerospace History, Number 49 TOWARD A HISTORY OF THE SPACE SHUTTLE AN ANNOTATED BIBLIOGRAPHY, PART 2 (1992–2011) Compiled by Malinda K. Goodrich Alice R. Buchalter Patrick M. Miller of the Federal Research Division, Library of Congress NASA History Program Office Office of Communications NASA Headquarters Washington, DC Monographs in Aerospace History Number 49 August 2012 NASA SP-2012-4549 Library of Congress – Federal Research Division Space Shuttle Annotated Bibliography PREFACE This annotated bibliography is a continuation of Toward a History of the Space Shuttle: An Annotated Bibliography, compiled by Roger D. Launius and Aaron K. Gillette, and published by NASA as Monographs in Aerospace History, Number 1 in December 1992 (available online at http://history.nasa.gov/Shuttlebib/contents.html). The Launius/Gillette volume contains those works published between the early days of the United States’ manned spaceflight program in the 1970s through 1991. The articles included in the first volume were judged to be most essential for researchers writing on the Space Shuttle’s history. The current (second) volume is intended as a follow-on to the first volume. It includes key articles, books, hearings, and U.S. government publications published on the Shuttle between 1992 and the end of the Shuttle program in 2011. The material is arranged according to theme, including: general works, precursors to the Shuttle, the decision to build the Space Shuttle, its design and development, operations, and management of the Space Shuttle program. Other topics covered include: the Challenger and Columbia accidents, as well as the use of the Space Shuttle in building and servicing the Hubble Space Telescope and the International Space Station; science on the Space Shuttle; commercial and military uses of the Space Shuttle; and the Space Shuttle’s role in international relations, including its use in connection with the Soviet Mir space station. -
Ground and Launch Systems
NASA Technology Roadmaps TA 13: Ground and Launch Systems May 2015 Draft 2015 NASA Technology Roadmaps DRAFT TA 13: Ground and Launch Systems Foreword NASA is leading the way with a balanced program of space exploration, aeronautics, and science research. Success in executing NASA’s ambitious aeronautics activities and space missions requires solutions to difficult technical challenges that build on proven capabilities and require the development of new capabilities. These new capabilities arise from the development of novel cutting-edge technologies. The promising new technology candidates that will help NASA achieve our extraordinary missions are identified in our Technology Roadmaps. The roadmaps are a set of documents that consider a wide range of needed technology candidates and development pathways for the next 20 years. The roadmaps are a foundational element of the Strategic Technology Investment Plan (STIP), an actionable plan that lays out the strategy for developing those technologies essential to the pursuit of NASA’s mission and achievement of National goals. The STIP provides prioritization of the technology candidates within the roadmaps and guiding principles for technology investment. The recommendations provided by the National Research Council heavily influence NASA’s technology prioritization. NASA’s technology investments are tracked and analyzed in TechPort, a web-based software system that serves as NASA’s integrated technology data source and decision support tool. Together, the roadmaps, the STIP, and TechPort provide NASA the ability to manage the technology portfolio in a new way, aligning mission directorate technology investments to minimize duplication, and lower cost while providing critical capabilities that support missions, commercial industry, and longer-term National needs.