Final Environmental Assessment for Launch of Nasa Routine Payloads on Expendable Launch Vehicles
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Spacex Launch Manifest - a List of Upcoming Missions 25 Spacex Facilities 27 Dragon Overview 29 Falcon 9 Overview 31 45Th Space Wing Fact Sheet
COTS 2 Mission Press Kit SpaceX/NASA Launch and Mission to Space Station CONTENTS 3 Mission Highlights 4 Mission Overview 6 Dragon Recovery Operations 7 Mission Objectives 9 Mission Timeline 11 Dragon Cargo Manifest 13 NASA Slides – Mission Profile, Rendezvous, Maneuvers, Re-Entry and Recovery 15 Overview of the International Space Station 17 Overview of NASA’s COTS Program 19 SpaceX Company Overview 21 SpaceX Leadership – Musk & Shotwell Bios 23 SpaceX Launch Manifest - A list of upcoming missions 25 SpaceX Facilities 27 Dragon Overview 29 Falcon 9 Overview 31 45th Space Wing Fact Sheet HIGH-RESOLUTION PHOTOS AND VIDEO SpaceX will post photos and video throughout the mission. High-Resolution photographs can be downloaded from: http://spacexlaunch.zenfolio.com Broadcast quality video can be downloaded from: https://vimeo.com/spacexlaunch/videos MORE RESOURCES ON THE WEB Mission updates will be posted to: For NASA coverage, visit: www.SpaceX.com http://www.nasa.gov/spacex www.twitter.com/elonmusk http://www.nasa.gov/nasatv www.twitter.com/spacex http://www.nasa.gov/station www.facebook.com/spacex www.youtube.com/spacex 1 WEBCAST INFORMATION The launch will be webcast live, with commentary from SpaceX corporate headquarters in Hawthorne, CA, at www.spacex.com. The webcast will begin approximately 40 minutes before launch. SpaceX hosts will provide information specific to the flight, an overview of the Falcon 9 rocket and Dragon spacecraft, and commentary on the launch and flight sequences. It will end when the Dragon spacecraft separates -
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. -
Rocket Propulsion Fundamentals 2
https://ntrs.nasa.gov/search.jsp?R=20140002716 2019-08-29T14:36:45+00:00Z Liquid Propulsion Systems – Evolution & Advancements Launch Vehicle Propulsion & Systems LPTC Liquid Propulsion Technical Committee Rick Ballard Liquid Engine Systems Lead SLS Liquid Engines Office NASA / MSFC All rights reserved. No part of this publication may be reproduced, distributed, or transmitted, unless for course participation and to a paid course student, in any form or by any means, or stored in a database or retrieval system, without the prior written permission of AIAA and/or course instructor. Contact the American Institute of Aeronautics and Astronautics, Professional Development Program, Suite 500, 1801 Alexander Bell Drive, Reston, VA 20191-4344 Modules 1. Rocket Propulsion Fundamentals 2. LRE Applications 3. Liquid Propellants 4. Engine Power Cycles 5. Engine Components Module 1: Rocket Propulsion TOPICS Fundamentals • Thrust • Specific Impulse • Mixture Ratio • Isp vs. MR • Density vs. Isp • Propellant Mass vs. Volume Warning: Contents deal with math, • Area Ratio physics and thermodynamics. Be afraid…be very afraid… Terms A Area a Acceleration F Force (thrust) g Gravity constant (32.2 ft/sec2) I Impulse m Mass P Pressure Subscripts t Time a Ambient T Temperature c Chamber e Exit V Velocity o Initial state r Reaction ∆ Delta / Difference s Stagnation sp Specific ε Area Ratio t Throat or Total γ Ratio of specific heats Thrust (1/3) Rocket thrust can be explained using Newton’s 2nd and 3rd laws of motion. 2nd Law: a force applied to a body is equal to the mass of the body and its acceleration in the direction of the force. -
Commercial Space Transportation Developments and Concepts: Vehicles, Technologies and Spaceports
Commercial Space Transportation 2006 Commercial Space Transportation Developments and Concepts: Vehicles, Technologies and Spaceports January 2006 HQ003606.INDD 2006 U.S. Commercial Space Transportation Developments and Concepts About FAA/AST About the 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 49 United States Code, Subtitle IX, Chapter 701 (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 encour- age, facilitate, and promote commercial space launches and reentries. Additional information concerning commercial space transportation can be found on FAA/AST’s web site at http://ast.faa.gov. Federal Aviation Administration Office of Commercial Space Transportation i About FAA/AST 2006 U.S. Commercial Space Transportation Developments and Concepts 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 Federal Aviation Administration Office of Commercial Space Transportation 2006 U.S. Commercial Space Transportation Developments and Concepts Contents Table of Contents Introduction . .1 Significant 2005 Events . .4 Space Competitions . .6 Expendable Launch Vehicles . .9 Current Expendable Launch Vehicle Systems . .9 Atlas 5 - Lockheed Martin Corporation . -
Indigenous Encounters
From Islands to Atoll: Relating Reefs of History at Kwajalein Greg Dvorak 1. Atollism Islands of starvation, islands of abundance, islands of connectedness: the nearly one hundred flat coral islets that form Kwajalein in the Marshall Islands, the largest atoll on earth, are a gigantic ring on the water, strung together by a dynamic reef. The lagoon it encloses—indeed the entire atoll—is a microcosm of Oceania, a metaphor for the contradictory and interconnected histories of the contemporary world. I choose Kwajalein to explore the idea of “encounter” not only because it was the site of a major battle of the Pacific War and a place of unfathomable change throughout the twentieth century between Marshall Islanders, Japanese, and Americans; I focus on Kwajalein also because it was my childhood hometown, where I spent the first decade of my life. Because the main island of the atoll is leased to the US Army as a missile-testing base, my early years in American suburbia there provided my first taste of the ways in which huge nations and small localities intersect. Haunted by the ghosts of Japanese soldiers and the lullabies of our Marshallese housekeeper, I knew that this atoll had been home to many others before me, yet I felt linked to those other people through the common idea of home, and through the genealogy of the atoll itself. Coral colonizes: Polyps voyage in the ocean currents, joining with other coral communities atop subaquatic volcanoes that rise miles from the sea floor to break the surface. Their migrations are based on the flows of the sea, and their settlements are serendipitous. -
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. -
United States Army Garrison- Kwajalein Atoll Information Handbook
United States Army Garrison- Kwajalein Atoll Information Handbook Produced by DYNCORP INTERNATIONAL LLC Last updated: 4 September 2019 U.S. ARMY GARRISON KWAJALEIN ATOLL/ REAGAN TEST SITE U.S. ARMY INSTALLATION MANAGEMENT COMMAND KWAJALEIN ATOLL, MARSHALL ISLANDS I. INSTALLATION DATA Name of Site: The installation is currently called “United States Army Garrison - Kwajalein Atoll/ Ronald Reagan Ballistic Missile Defense Test Site” (USAG-KA/RTS) effective 01 October 2013. The installation has undergone multiple name changes since its inception: U.S. Army Kwajalein Atoll/ Ronald Reagan Ballistic Missile Defense Test Site (USAKA/RTS) from 15 June 2001 to 01 October 2013; U.S. Army Kwajalein Atoll/ Kwajalein Missile Range (USAKA/KMR) from 01 March 1998 to 15 June 2001; U.S. Army Kwajalein Atoll (USAKA) from 14 November 1986 to 30 September 1997; Kwajalein Missile Range (KMR) from 15 April 1968 to 13 November 1986; Kwajalein Test Site from 1 July 1964 to 14 April 1968. Between 1945 and 30 June 1964, while under the command of the United States Navy, the installation was referred to at various times as the Navy Operating Base Kwajalein, Naval Air Station Kwajalein, Naval Station Kwajalein and Pacific Missile Range Facility (PMRF) Kwajalein. Site Number: NQ100 [for Military Real Property Inventory purposes, assigned by the U.S. Army Chief of Engineers per paragraph 2.2.1 (3) of AR 405-45] U.S. Mail Address: PSC 701-PO Box 26, APO AP 96555-0001 Status: USAG-KA/RTS is a Class II site (Active) of the United States Army and is designated a subordinate activity of the U.S. -
Out There Somewhere Could Be a PLANET LIKE OURS the Breakthroughs We’Ll Need to find Earth 2.0 Page 30
September 2014 Out there somewhere could be A PLANET LIKE OURS The breakthroughs we’ll need to find Earth 2.0 Page 30 Faster comms with lasers/16 Real fallout from Ukraine crisis/36 NASA Glenn chief talks tech/18 A PUBLICATION OF THE AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS Engineering the future Advanced Composites Research The Wizarding World of Harry Potter TM Bloodhound Supersonic Car Whether it’s the world’s fastest car With over 17,500 staff worldwide, and 2,800 in or the next generation of composite North America, we have the breadth and depth of capability to respond to the world’s most materials, Atkins is at the forefront of challenging engineering projects. engineering innovation. www.na.atkinsglobal.com September 2014 Page 30 DEPARTMENTS EDITOR’S NOTEBOOK 2 New strategy, new era LETTER TO THE EDITOR 3 Skeptical about the SABRE engine INTERNATIONAL BEAT 4 Now trending: passive radars IN BRIEF 8 A question mark in doomsday comms Page 12 THE VIEW FROM HERE 12 Surviving a bad day ENGINEERING NOTEBOOK 16 Demonstrating laser comms CONVERSATION 18 Optimist-in-chief TECH HISTORY 22 Reflecting on radars PROPULSION & ENERGY 2014 FORUM 26 Electric planes; additive manufacturing; best quotes Page 38 SPACE 2014 FORUM 28 Comet encounter; MILSATCOM; best quotes OUT OF THE PAST 44 CAREER OPPORTUNITIES 46 Page 16 FEATURES FINDING EARTH 2.0 30 Beaming home a photo of a planet like ours will require money, some luck and a giant telescope rich with technical advances. by Erik Schechter COLLATERAL DAMAGE 36 Page 22 The impact of the Russia-Ukrainian conflict extends beyond the here and now. -
6. Chemical-Nuclear Propulsion MAE 342 2016
2/12/20 Chemical/Nuclear Propulsion Space System Design, MAE 342, Princeton University Robert Stengel • Thermal rockets • Performance parameters • Propellants and propellant storage Copyright 2016 by Robert Stengel. All rights reserved. For educational use only. http://www.princeton.edu/~stengel/MAE342.html 1 1 Chemical (Thermal) Rockets • Liquid/Gas Propellant –Monopropellant • Cold gas • Catalytic decomposition –Bipropellant • Separate oxidizer and fuel • Hypergolic (spontaneous) • Solid Propellant ignition –Mixed oxidizer and fuel • External ignition –External ignition • Storage –Burn to completion – Ambient temperature and pressure • Hybrid Propellant – Cryogenic –Liquid oxidizer, solid fuel – Pressurized tank –Throttlable –Throttlable –Start/stop cycling –Start/stop cycling 2 2 1 2/12/20 Cold Gas Thruster (used with inert gas) Moog Divert/Attitude Thruster and Valve 3 3 Monopropellant Hydrazine Thruster Aerojet Rocketdyne • Catalytic decomposition produces thrust • Reliable • Low performance • Toxic 4 4 2 2/12/20 Bi-Propellant Rocket Motor Thrust / Motor Weight ~ 70:1 5 5 Hypergolic, Storable Liquid- Propellant Thruster Titan 2 • Spontaneous combustion • Reliable • Corrosive, toxic 6 6 3 2/12/20 Pressure-Fed and Turbopump Engine Cycles Pressure-Fed Gas-Generator Rocket Rocket Cycle Cycle, with Nozzle Cooling 7 7 Staged Combustion Engine Cycles Staged Combustion Full-Flow Staged Rocket Cycle Combustion Rocket Cycle 8 8 4 2/12/20 German V-2 Rocket Motor, Fuel Injectors, and Turbopump 9 9 Combustion Chamber Injectors 10 10 5 2/12/20 -
Materials for Liquid Propulsion Systems
https://ntrs.nasa.gov/search.jsp?R=20160008869 2019-08-29T17:47:59+00:00Z CHAPTER 12 Materials for Liquid Propulsion Systems John A. Halchak Consultant, Los Angeles, California James L. Cannon NASA Marshall Space Flight Center, Huntsville, Alabama Corey Brown Aerojet-Rocketdyne, West Palm Beach, Florida 12.1 Introduction Earth to orbit launch vehicles are propelled by rocket engines and motors, both liquid and solid. This chapter will discuss liquid engines. The heart of a launch vehicle is its engine. The remainder of the vehicle (with the notable exceptions of the payload and guidance system) is an aero structure to support the propellant tanks which provide the fuel and oxidizer to feed the engine or engines. The basic principle behind a rocket engine is straightforward. The engine is a means to convert potential thermochemical energy of one or more propellants into exhaust jet kinetic energy. Fuel and oxidizer are burned in a combustion chamber where they create hot gases under high pressure. These hot gases are allowed to expand through a nozzle. The molecules of hot gas are first constricted by the throat of the nozzle (de-Laval nozzle) which forces them to accelerate; then as the nozzle flares outwards, they expand and further accelerate. It is the mass of the combustion gases times their velocity, reacting against the walls of the combustion chamber and nozzle, which produce thrust according to Newton’s third law: for every action there is an equal and opposite reaction. [1] Solid rocket motors are cheaper to manufacture and offer good values for their cost. -
Year in Review 2013
SM_Dec_2013 cover Worldwide Satellite Magazine December 2013 SatMagazine 2013 YEAR IN REVIEW SatMagazine December 2013—Year In Review Publishing Operations Senior Contributors This Issue’s Authors Silvano Payne, Publisher + Writer Mike Antonovich, ATEME Mike Antonovich Robert Kubbernus Hartley G. Lesser, Editorial Director Tony Bardo, Hughes Eran Avni Dr. Ajey Lele Richard Dutchik Dave Bettinger Tom Leech Pattie Waldt, Executive Editor Chris Forrester, Broadgate Publications Don Buchman Hartley Lesser Jill Durfee, Sales Director, Editorial Assistant Karl Fuchs, iDirect Government Services Eyal Copitt Timothy Logue Simon Payne, Development Director Bob Gough, 21 Carrick Communications Rich Currier Jay Monroe Jos Heyman, TIROS Space Information Tommy Konkol Dybvad Tore Morten Olsen Donald McGee, Production Manager David Leichner, Gilat Satellite Networks Chris Forrester Kurt Peterhans Dan Makinster, Technical Advisor Giles Peeters, Track24 Defence Sima Fishman Jorge Potti Bert Sadtler, Boxwood Executive Search Simen K. Frostad Sally-Anne Ray David Gelerman Susan Sadaat Samer Halawi Bert Sadtler Jos Heyman Patrick Shay Jack Jacobs Mike Towner Casper Jensen Serge Van Herck Alexandre Joint Pattie Waldt Pradman Kaul Ali Zarkesh Published 11 times a year by SatNews Publishers 800 Siesta Way Sonoma, CA 95476 USA Phone: (707) 939-9306 Fax: (707) 838-9235 © 2013 SatNews Publishers We reserve the right to edit all submitted materials to meet our content guidelines, as well as for grammar or to move articles to an alternative issue to accommodate publication space requirements, or removed due to space restrictions. Submission of content does not constitute acceptance of said material by SatNews Publishers. Edited materials may, or may not, be returned to author and/or company for review prior to publication. -
NYC Aerospace Rocket Program
NYC Aerospace Rocket Program NYC Aerospace’s 100,000ft rocket program is committed to designing and manufacturing a sounding rocket to reach 100,000ft, above 99% of the atmosphere. The purpose of this mission is to research the applications of ammonium perchlorate composite propellant (APCP) to large rockets. Many future aerospace engineers have learned a great deal about rocketry from participating in this project, which is one of NYC Aerospace’s many projects involving students citywide. Rocket details Our goal is to send a single-stage rocket to 100,000ft using ammonium perchlorate composite propellant (APCP). In order to reach this altitude, the rocket will likely need to maintain structural integrity at velocities on the order of Mach 2 and above. Therefore, the rocket body will need to be made of a light metal such as aluminum or titanium. A metal body necessitates the capacity of the rocket motor to be in the O range of near 30,000Ns of impulse. Assuming a perfectly efficient motor, this requires around 30lb of propellant. We can calculate fuel fraction by first establishing our delta v budget. Δv = √2gz = √2(9.8m/s2)(30480m) =772m/s= mach 2.25 Using the delta v necessary, we can calculate the minimum fuel fraction using Tsiolkovsky’s ideal rocket equation. Assuming the specific impulse of our motor is 228s: m final Δv =− v eln m initial m final = exp(− 772/2280) = 0.71 m initial Thus, we only need 29% of our rocket to be fuel. This brings the max mass of our rocket to 103lb.