National Spaceport Network Development Plan
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Electric Propulsion System Scaling for Asteroid Capture-And-Return Missions
Electric propulsion system scaling for asteroid capture-and-return missions Justin M. Little⇤ and Edgar Y. Choueiri† Electric Propulsion and Plasma Dynamics Laboratory, Princeton University, Princeton, NJ, 08544 The requirements for an electric propulsion system needed to maximize the return mass of asteroid capture-and-return (ACR) missions are investigated in detail. An analytical model is presented for the mission time and mass balance of an ACR mission based on the propellant requirements of each mission phase. Edelbaum’s approximation is used for the Earth-escape phase. The asteroid rendezvous and return phases of the mission are modeled as a low-thrust optimal control problem with a lunar assist. The numerical solution to this problem is used to derive scaling laws for the propellant requirements based on the maneuver time, asteroid orbit, and propulsion system parameters. Constraining the rendezvous and return phases by the synodic period of the target asteroid, a semi- empirical equation is obtained for the optimum specific impulse and power supply. It was found analytically that the optimum power supply is one such that the mass of the propulsion system and power supply are approximately equal to the total mass of propellant used during the entire mission. Finally, it is shown that ACR missions, in general, are optimized using propulsion systems capable of processing 100 kW – 1 MW of power with specific impulses in the range 5,000 – 10,000 s, and have the potential to return asteroids on the order of 103 104 tons. − Nomenclature -
Tianwen-1: China's Mars Mission
Tianwen-1: China's Mars Mission drishtiias.com/printpdf/tianwen-1-china-s-mars-mission Why In News China will launch its first Mars Mission - Tianwen-1- in July, 2020. China's previous ‘Yinghuo-1’ Mars mission, which was supported by a Russian spacecraft, had failed after it did not leave the earth's orbit and disintegrated over the Pacific Ocean in 2012. The National Aeronautics and Space Administration (NASA) is also going to launch its own Mars mission in July, the Perseverance which aims to collect Martian samples. Key Points The Tianwen-1 Mission: It will lift off on a Long March 5 rocket, from the Wenchang launch centre. It will carry 13 payloads (seven orbiters and six rovers) that will explore the planet. It is an all-in-one orbiter, lander and rover system. Orbiter: It is a spacecraft designed to orbit a celestial body (astronomical body) without landing on its surface. Lander: It is a strong, lightweight spacecraft structure, consisting of a base and three sides "petals" in the shape of a tetrahedron (pyramid- shaped). It is a protective "shell" that houses the rover and protects it, along with the airbags, from the forces of impact. Rover: It is a planetary surface exploration device designed to move across the solid surface on a planet or other planetary mass celestial bodies. 1/3 Objectives: The mission will be the first to place a ground-penetrating radar on the Martian surface, which will be able to study local geology, as well as rock, ice, and dirt distribution. It will search the martian surface for water, investigate soil characteristics, and study the atmosphere. -
AFSPC-CO TERMINOLOGY Revised: 12 Jan 2019
AFSPC-CO TERMINOLOGY Revised: 12 Jan 2019 Term Description AEHF Advanced Extremely High Frequency AFB / AFS Air Force Base / Air Force Station AOC Air Operations Center AOI Area of Interest The point in the orbit of a heavenly body, specifically the moon, or of a man-made satellite Apogee at which it is farthest from the earth. Even CAP rockets experience apogee. Either of two points in an eccentric orbit, one (higher apsis) farthest from the center of Apsis attraction, the other (lower apsis) nearest to the center of attraction Argument of Perigee the angle in a satellites' orbit plane that is measured from the Ascending Node to the (ω) perigee along the satellite direction of travel CGO Company Grade Officer CLV Calculated Load Value, Crew Launch Vehicle COP Common Operating Picture DCO Defensive Cyber Operations DHS Department of Homeland Security DoD Department of Defense DOP Dilution of Precision Defense Satellite Communications Systems - wideband communications spacecraft for DSCS the USAF DSP Defense Satellite Program or Defense Support Program - "Eyes in the Sky" EHF Extremely High Frequency (30-300 GHz; 1mm-1cm) ELF Extremely Low Frequency (3-30 Hz; 100,000km-10,000km) EMS Electromagnetic Spectrum Equitorial Plane the plane passing through the equator EWR Early Warning Radar and Electromagnetic Wave Resistivity GBR Ground-Based Radar and Global Broadband Roaming GBS Global Broadcast Service GEO Geosynchronous Earth Orbit or Geostationary Orbit ( ~22,300 miles above Earth) GEODSS Ground-Based Electro-Optical Deep Space Surveillance -
Space Launch System (Sls) Motors
Propulsion Products Catalog SPACE LAUNCH SYSTEM (SLS) MOTORS For NASA’s Space Launch System (SLS), Northrop Grumman manufactures the five-segment SLS heavy- lift boosters, the booster separation motors (BSM), and the Launch Abort System’s (LAS) launch abort motor and attitude control motor. The SLS five-segment booster is the largest solid rocket motor ever built for flight. The SLS booster shares some design heritage with flight-proven four-segment space shuttle reusable solid rocket motors (RSRM), but generates 20 percent greater average thrust and 24 percent greater total impulse. While space shuttle RSRM production has ended, sustained booster production for SLS helps provide cost savings and access to reliable material sources. Designed to push the spent RSRMs safely away from the space shuttle, Northrop Grumman BSMs were rigorously qualified for human space flight and successfully used on the last fifteen space shuttle missions. These same motors are a critical part of NASA’s SLS. Four BSMs are installed in the forward frustum of each five-segment booster and four are installed in the aft skirt, for a total of 16 BSMs per launch. The launch abort motor is an integral part of NASA’s LAS. The LAS is designed to safely pull the Orion crew module away from the SLS launch vehicle in the event of an emergency on the launch pad or during ascent. Northrop Grumman is on contract to Lockheed Martin to build the abort motor and attitude control motor—Lockheed is the prime contractor for building the Orion Multi-Purpose Crew Vehicle designed for use on NASA’s SLS. -
The Role and Training of NASA Astronauts in the Post-Shuttle Era
The Role and Training of NASA Astronauts in the Post-Shuttle Era Aeronautics and Space Engineering Board ∙ Air Force Studies Board ∙ Division on Engineering & Physical Sciences ∙ September 2011 As the National Aeronautics and Space Administration (NASA) retires the Space Shuttle and shifts involvement in International Space Station (ISS) operations, changes in the role and requirements of NASA’s Astronaut Corps will take place. At the request of NASA, the National Research Council (NRC) addressed three main questions about these changes: What should be the role and size of Johnson Space Center’s (JSC) Flight Crew Operations Directorate (FCOD); what will be the requirements of astronaut training facilities; and is the Astronaut Corps’ fleet of training aircraft a cost-effective means of preparing astronauts for NASA’s spaceflight program? This report presents an assessment of several issues driven by these questions. This report does not address explicitly the future of human spaceflight. Background Corps—defined in this report as the number he United States has been launching as- of astronauts qualified to fly into space. As Ttronauts into space for more than five of May 2011, the Astronaut Corps consist- decades and, for a majority of those years, ed of 61 people, compared with a peak size astronauts have been selected and trained of nearly 150 people in 2000. NASA uses a through NASA’s Astronaut Corps. Since its model for projecting minimum ISS manifest inception in 1959, the Astronaut Corps— requirements. Using the model on the next which is based at the Lyndon B. Johnson page, NASA has projected that the Astronaut Space Center (JSC) in Houston, Texas—has Corps will need a minimum of 55-60 astro- experienced periodic fluctuations in size and nauts to meet ISS crew requirements through training emphasis based on various program 2016. -
The SKYLON Spaceplane
The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration. -
Commercial Space Transportation Advisory Committee (COMSTAC
COMMERCIAL SPACE TRANSPORTATIONFAA/AST Staff ADVISORY COMMITTEE October 2020 Membership Major General James Armor, USAF (Ret) CEO, The Armor Group Ms. Sharon L. Pinkerton Senior Vice President, Legislative and Regulatory Policy Dr. Greg Autry Airlines for America Vice President of Space Development National Space Society Mr. Lee Rosen Vice President of Customer Operations and Integration Mr. Bill Beckman Space Exploration Technologies Director, NASA Programs The Boeing Company Ms. Robbie Sabathier Vice President, Government Operations & Strategic Communications Major General Edward L. Bolton, USAF (Ret) United Launch Alliance Former FAA Assistant Administrator Mr. Eric Stallmer Hon. Shana Dale President Board Member Commercial Spaceflight Federation Firefly Black, LLC Ms. Charity Weeden Mr. Paul E. Damphousse Vice President of Global Space Policy Vice President of Business Development Astroscale U.S., Inc. Calspan Holdings, LLC Ms. Ann Zulkosky Dr. Mary Lynne Dittmar Director President & CEO Lockheed Martin Corporation The Coalition for Deep Space Exploration Ms. Karina Drees CEO and General Manager Mojave Air and Space Port Mr. Mike French Vice President, Space Systems Aerospace Industries Association Mr. Christopher C. Hassler President & CEO Syndetics Inc. Mr. Dale Ketcham Vice President, Government & External Relations Space Florida Ms. Kate Kronmiller Vice President of Government Relations Jacobs Mr. Steven Lindsey Senior Vice President of Strategy and Programs Sierra Nevada Corporation Space Systems Mr. Mike Moses President Virgin Galactic Mr. Clay Mowry Vice President, Sales, Marketing & Customer Experience Blue Origin Mr. Dale K. Nash CEO and Executive Director Virginia Commercial Space Flight Authority . -
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. -
The Role and Training of NASA Astronauts In
Co-chairs: Joe Rothenberg, Fred Gregory Briefing: October 18-19, 2011 Statement of Task An ad hoc committee will conduct a study and prepare a report on the activities of NASA’s human spaceflight crew office. In writing its report the committee will address the following questions: • How should the role and size of the activities managed by the Johnson Space Center Flight Crew Operations Directorate change after space shuttle retirement and completion of the assembly of the International Space Station (ISS)? • What are the requirements of crew-related ground-based facilities after the space shuttle program ends? • Is the fleet of aircraft used for the training the Astronaut Corps a cost-effective means of preparing astronauts to meet the requirements of NASA’s human spaceflight program? Are there more cost-effective means of meeting these training requirements? The NRC was not asked to consider whether or not the United States should continue human spaceflight, or whether there were better alternatives to achieving the nation’s goals without launching humans into space. Rather, the NRC’s charge was to assume that U.S. human spaceflight would continue. 2 Committee on Human Spaceflight Crew Operations • FREDERICK GREGORY, Lohfeld Consulting Group, Inc., Co-Chair • JOSEPH H. ROTHENBERG, Swedish Space Corporation, Co-Chair • MICHAEL J. CASSUTT, University of Southern California • RICHARD O. COVEY, United Space Alliance, LLC (retired) • DUANE DEAL, Stinger Ghaffarian Technologies, Inc. • BONNIE J. DUNBAR, President and CEO, Dunbar International, LLC • WILLIAM W. HOOVER, Independent Consultant • THOMAS D. JONES, Florida Institute of Human and Machine Cognition • FRANKLIN D. MARTIN, Martin Consulting, Inc. -
2017 State of the System Report
2017 STATE OF THE SYSTEM 2017 State of the System Report Space Coast Transportation Planning Organization Brevard County, Florida Prepared By: Kittelson & Associates, Inc. 225 E. Robinson Street, Suite 355 Orlando, FL 32801 (407) 540-0555 Project No. 20741.02 October 2018 i The preparation of this report has been financed in part through grant(s) from the Federal Highway Administration and Federal Transit Administration, U.S. Department of Transportation, under the State Planning and Research Program, Section 505 [or Metropolitan Planning Program, Section 104(f)] of Title 23, U.S. Code. The contents of this report do not necessarily reflect the official views or policy of the U.S. Department of Transportation. ii TABLE OF CONTENTS Executive Summary ...................................................................................................................................... ix Countywide Performance Measures ........................................................................................................................................... ix Countywide Trends ..................................................................................................................................................................... ix Countywide Safety ....................................................................................................................................................................... x Introduction…………….. .................................................................................................................................. -
Computational Fluid Dynamic Analysis of Scaled Hypersonic Re-Entry Vehicles
Computational Fluid Dynamic Analysis of Scaled Hypersonic Re-Entry Vehicles A project presented to The Faculty of the Department of Aerospace Engineering San Jose State University In partial fulfillment of the requirements for the degree Master of Science in Aerospace Engineering by Simon H.B. Sorensen March 2019 approved by Dr. Periklis Papadopoulous Faculty Advisor 1 i ABSTRACT With the advancement of technology in space, reusable re-entry space planes have become a focus point with their ability to save materials and utilize existing flight data. Their ability to not only supply materials to space stations or deploy satellites, but also in atmosphere flight makes them versatile in their deployment and recovery. The existing design of vehicles such as the Space Shuttle Orbiter and X-37 Orbital Test Vehicle can be used to observe the effects of scaling existing vehicle geometry and how it would operate in identical conditions to the full-size vehicle. These scaled vehicles, if viable, would provide additional options depending on mission parameters without losing the advantages of reusable re-entry space planes. 2 Table of Contents Abstract . i Nomenclature . .1 1. Introduction. .1 2. Literature Review. 2 2.1 Space Shuttle Orbiter. 2 2.2 X-37 Orbital Test Vehicle. 3 3. Assumptions & Equations. 3 3.1 Assumptions. 3 3.2 Equations to Solve. 4 4. Methodology. 5 5. Base Sized Vehicles. 5 5.1 Space Shuttle Orbiter. 5 5.2 X-37. 9 6. Scaled Vehicles. 11 7. Simulations. 12 7.1 Initial Conditions. 12 7.2 Initial Test Utilizing X-37. .13 7.3 X-37 OTV. -
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