Premier Multi-User Spaceport
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Mobile Launcher Moves to Vehicle Assembly Building EGS MONTHLY HIGHLIGHTS
National Aeronautics and Space Administration EXPLORATION GROUND SYSTEMS HIGHLIGHTS SEPTEMBER 2018 Mobile Launcher Moves to Vehicle Assembly Building EGS MONTHLY HIGHLIGHTS 3 Mobile launcher on the move 4 In the driver’s seat 5 Prepping for Underway Recovery Test 7 6 Employees, guests view ML move MOBILE LAUNCHER ON THE MOVE NASA’s mobile launcher is inside High Bay 3 at the Vehicle Assembly Building (VAB) on Sept. 11, 2018, at NASA’s Kennedy Space Center in Florida. Photo credit: NASA/Frank Michaux NASA’s mobile launcher, atop crawler-transporter 2, traveled from Launch Pad 39B to the Vehicle Assembly Building at the agency’s Kennedy Space Center in Florida, on Sept. 7, 2018. Arriving late in the afternoon, the mobile launcher stopped at the entrance to the VAB. Early the next day, Sept. 8, engineers and technicians rotated and extended the crew access arm near the top of the mobile launcher tower. Then the mobile launcher was moved inside High Bay 3, where it will spend about seven months undergoing verification and validation testing with the 10 levels of new work platforms, ensuring that it can provide support to the agency’s Space Launch System (SLS). The 380-foot-tall structure is equipped with the crew access Cliff Lanham, NASA project manager for the mobile launcher, takes a break arm and several umbilicals that will provide power, environmental to attend the employee event for the mobile launcher move to the Vehicle control, pneumatics, communication and electrical connections Assembly Building on Sept. 7, 2018, at NASA’s Kennedy Space Center in Florida. -
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 -
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 -
NASA Space Life and Physical Sciences and Research Applications
NASA Space Life and Physical Sciences and Research Applications SLSPRA has 11 topics listed below and on the following pages for your consideration and possible involvement. (1) Program: Physical Sciences Program (2) Research Title: Dusty Plasmas (3) Research Overview: Dusty plasma research uses dusty plasmas – mixtures of electrons, ions, and charged micron-size particles as a model system to understand astronomical phenomena involving dust-laden plasmas, and as a simplified system modelling the behavior of many-body systems in problems of statistical and condensed matter physics. Dusty plasma research also addresses practical questions of dust management in planetary exploration missions. Proposals are sought for research on dusty plasmas, particularly on the transport of particles in dusty plasmas. 4) NASA Contact a. Name: Bradley Carpenter, Ph.D. b. Organization: NASA Headquarters Space Life and Physical Sciences Research and Applications (SLPSRA) c. Work Phone: (202) 358-0826 d. Email: [email protected] 5) Commercial Entity: a. Company Name: na b. Contact Name: na c. Work Phone: na d. Cell Phone: na e Email: na 6) Partner contribution No NASA Partner contributions 7) Intellectual property management: No NASA Partner intellectual property concerns 8) Additional Information: All publications that result from an awarded EPSCOR study shall acknowledge NASA Space Life and Physical Sciences Research and Applications (SLPSRA). NNH20ZHA001C NASA EPSCoR Rapid Response Research (R3) NASA Space Life and Physical Sciences and Research Applications (continued) 1) Program: Fluids Physics and Combustion Science 2) Research Title: Drop Tower Studies 3) Research Overview: Fundamental discoveries made by NASA researchers over the last 50 years in fluids physics and combustion have helped enable advances in fluids management on spacecraft water recovery and thermal management systems, spacecraft fire safety, and fundamental combustion and fluids physics including low-temperature hydrocarbon oxidation, soot formation and flame stability. -
Race to Space Educator Edition
National Aeronautics and Space Administration Grade Level RACE TO SPACE 10-11 Key Topic Instructional Objectives U.S. space efforts from Students will 1957 - 1969 • analyze primary and secondary source documents to be used as Degree of Difficulty supporting evidence; Moderate • incorporate outside information (information learned in the study of the course) as additional support; and Teacher Prep Time • write a well-developed argument that answers the document-based 2 hours essay question regarding the analogy between the Race to Space and the Cold War. Problem Duration 60 minutes: Degree of Difficulty -15 minute document analysis For the average AP US History student the problem may be at a moderate - 45 minute essay writing difficulty level. -------------------------------- Background AP Course Topics This problem is part of a series of Social Studies problems celebrating the - The United States and contributions of NASA’s Apollo Program. the Early Cold War - The 1950’s On May 25, 1961, President John F. Kennedy spoke before a special joint - The Turbulent 1960’s session of Congress and challenged the country to safely send and return an American to the Moon before the end of the decade. President NCSS Social Studies Kennedy’s vision for the three-year old National Aeronautics and Space Standards Administration (NASA) motivated the United States to develop enormous - Time, Continuity technological capabilities and inspired the nation to reach new heights. and Change Eight years after Kennedy’s speech, NASA’s Apollo program successfully - People, Places and met the president’s challenge. On July 20, 1969, the world witnessed one of Environments the most astounding technological achievements in the 20th century. -
Mars, the Nearest Habitable World – a Comprehensive Program for Future Mars Exploration
Mars, the Nearest Habitable World – A Comprehensive Program for Future Mars Exploration Report by the NASA Mars Architecture Strategy Working Group (MASWG) November 2020 Front Cover: Artist Concepts Top (Artist concepts, left to right): Early Mars1; Molecules in Space2; Astronaut and Rover on Mars1; Exo-Planet System1. Bottom: Pillinger Point, Endeavour Crater, as imaged by the Opportunity rover1. Credits: 1NASA; 2Discovery Magazine Citation: Mars Architecture Strategy Working Group (MASWG), Jakosky, B. M., et al. (2020). Mars, the Nearest Habitable World—A Comprehensive Program for Future Mars Exploration. MASWG Members • Bruce Jakosky, University of Colorado (chair) • Richard Zurek, Mars Program Office, JPL (co-chair) • Shane Byrne, University of Arizona • Wendy Calvin, University of Nevada, Reno • Shannon Curry, University of California, Berkeley • Bethany Ehlmann, California Institute of Technology • Jennifer Eigenbrode, NASA/Goddard Space Flight Center • Tori Hoehler, NASA/Ames Research Center • Briony Horgan, Purdue University • Scott Hubbard, Stanford University • Tom McCollom, University of Colorado • John Mustard, Brown University • Nathaniel Putzig, Planetary Science Institute • Michelle Rucker, NASA/JSC • Michael Wolff, Space Science Institute • Robin Wordsworth, Harvard University Ex Officio • Michael Meyer, NASA Headquarters ii Mars, the Nearest Habitable World October 2020 MASWG Table of Contents Mars, the Nearest Habitable World – A Comprehensive Program for Future Mars Exploration Table of Contents EXECUTIVE SUMMARY .......................................................................................................................... -
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. -
Orbit and Spin
Orbit and Spin Overview: A whole-body activity that explores the relative sizes, distances, orbit, and spin of the Sun, Earth, and Moon. Target Grade Level: 3-5 Estimated Duration: 2 40-minute sessions Learning Goals: Students will be able to… • compare the relative sizes of the Earth, Moon, and Sun. • contrast the distance between the Earth and Moon to the distance between the Earth and Sun. • differentiate between the motions of orbit and spin. • demonstrate the spins of the Earth and the Moon, as well as the orbits of the Earth around the Sun, and the Moon around the Earth. Standards Addressed: Benchmarks (AAAS, 1993) The Physical Setting, 4A: The Universe, 4B: The Earth National Science Education Standards (NRC, 1996) Physical Science, Standard B: Position and motion of objects Earth and Space Science, Standard D: Objects in the sky, Changes in Earth and sky Table of Contents: Background Page 1 Materials and Procedure 5 What I Learned… Science Journal Page 14 Earth Picture 15 Sun Picture 16 Moon Picture 17 Earth Spin Demonstration 18 Moon Orbit Demonstration 19 Extensions and Adaptations 21 Standards Addressed, detailed 22 Background: Sun The Sun is the center of our Solar System, both literally—as all of the planets orbit around it, and figuratively—as its rays warm our planet and sustain life as we know it. The Sun is very hot compared to temperatures we usually encounter. Its mean surface temperature is about 9980° Fahrenheit (5800 Kelvin) and its interior temperature is as high as about 28 million° F (15,500,000 Kelvin). -
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…………….. .................................................................................................................................. -
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