Interim Cryogenic Propulsion Stage
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Master Layout 071013
3RD annual GULF COAST AEROSPACE CORRIDOR Louisiana Mississippi Alabama Florida 2013-2014 June 2013 Gulf Coast Aerospace Corridor 2013-2014 – 1 Researched, written and prepared by the Gulf Coast Reporters’ League, an independent team of current and former journalists. Support for this project was provided by our underwriters. Findings detailed in this publication are those of the authors and do not necessarily reflect views of the organizations or agencies that appear in this publication or provide support. This book is available as a free PDF download. Printed versions and an eBook edition are available from Lulu.com, a print-on-demand service based in Raleigh, N.C. All rights reserved. Cover photos, clockwise from upper left: U.S. Navy Triton unmanned surveillance aircraft flying over the clouds (Northrop Grumman illustration); U.S. Air Force F-35 Joint Strike Fighters flying in formation (U.S. Air Force photo); portion of the popular Airbus A320 (Airbus photo); NASA’s Space Launch System taking off from the launch pad (NASA illustration). Version 3, 07/10/2013 Copyright © 2013-2014 by Tortorano Commissioned Publications/Gulf Coast Reporters’ League Gulf Coast Aerospace Corridor 2013-2014 – 2 Acknowledgements The Gulf Coast Reporters’ League and Okaloosa STEMM Center of Valparaiso, Fla., would like to thank Quint & Rishy Studer of Pensacola, Fla., for providing printed copies of this book to teachers with aviation-related courses in Okaloosa County, Fla. Support for the research, writing and compilation of this aerospace report was provided -
Mini Models Fire up for SLS Base Heating Tests the State of the Center
Serving the Marshall Space Flight Center Community www.nasa.gov/centers/marshall/about/star/index.html February 4, 2015 Inside This Issue: The State of the Center Four Marshall Center Marshall Space Flight Center Deputy Director Engineers Receive NASA Teresa Vanhooser talks about NASA’s $18.5 Innovation Award page 4 billion fiscal year 2016 proposed budget as Marshall Director Patrick Scheuermann, center, and Johnny Stephenson, acting director of the center’s Office of Strategic Analysis and Alabama and Washington Communications, look on during an all-hands Students Selected for meeting with employees Feb. 2. The proposed Winning Designs of 3-D budget includes $2.09 billion for Marshall. “This is a strong budget for Marshall,” Printed Tools for Astronauts Scheuermann said. “It provides stability for page 7 our workforce and the resources necessary to advance our deep space exploration programs.” (NASA/MSFC/Emmett Given) See State of the Center on page 2 Turning up the Temperature: Mini Models Fire Up for SLS Base Heating Tests By Megan Davidson Check us It may be cold in upstate New of the SLS propulsion system. That out online! York, but NASA engineers are includes two five-segment solid Scan the turning up the temperature in rocket boosters and four core stage QR code Buffalo for a series of tests that will RS-25 engines, and a 2 percent, or provide critical data on the heating 6.5-foot-tall, scale model of the conditions at the base of NASA’s new entire rocket. The models are fired Marshall Space Flight Center, Alabama 35812 rocket, the Space Launch System. -
Orion Capsule Launch Abort System Analysis
Orion Capsule Launch Abort System Analysis Assignment 2 AE 4802 Spring 2016 – Digital Design and Manufacturing Georgia Institute of Technology Authors: Tyler Scogin Michel Lacerda Jordan Marshall Table of Contents 1. Introduction ......................................................................................................................................... 4 1.1 Mission Profile ............................................................................................................................. 7 1.2 Literature Review ........................................................................................................................ 8 2. Conceptual Design ............................................................................................................................. 13 2.1 Design Process ........................................................................................................................... 13 2.2 Vehicle Performance Characteristics ......................................................................................... 15 2.3 Vehicle/Sub-Component Sizing ................................................................................................. 15 3. Vehicle 3D Model in CATIA ................................................................................................................ 22 3.1 3D Modeling Roles and Responsibilities: .................................................................................. 22 3.2 Design Parameters and Relations:............................................................................................ -
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. -
Interstellar Probe on Space Launch System (Sls)
INTERSTELLAR PROBE ON SPACE LAUNCH SYSTEM (SLS) David Alan Smith SLS Spacecraft/Payload Integration & Evolution (SPIE) NASA-MSFC December 13, 2019 0497 SLS EVOLVABILITY FOUNDATION FOR A GENERATION OF DEEP SPACE EXPLORATION 322 ft. Up to 313ft. 365 ft. 325 ft. 365 ft. 355 ft. Universal Universal Launch Abort System Stage Adapter 5m Class Stage Adapter Orion 8.4m Fairing 8.4m Fairing Fairing Long (Up to 90’) (up to 63’) Short (Up to 63’) Interim Cryogenic Exploration Exploration Exploration Propulsion Stage Upper Stage Upper Stage Upper Stage Launch Vehicle Interstage Interstage Interstage Stage Adapter Core Stage Core Stage Core Stage Solid Solid Evolved Rocket Rocket Boosters Boosters Boosters RS-25 RS-25 Engines Engines SLS Block 1 SLS Block 1 Cargo SLS Block 1B Crew SLS Block 1B Cargo SLS Block 2 Crew SLS Block 2 Cargo > 26 t (57k lbs) > 26 t (57k lbs) 38–41 t (84k-90k lbs) 41-44 t (90k–97k lbs) > 45 t (99k lbs) > 45 t (99k lbs) Payload to TLI/Moon Launch in the late 2020s and early 2030s 0497 IS THIS ROCKET REAL? 0497 SLS BLOCK 1 CONFIGURATION Launch Abort System (LAS) Utah, Alabama, Florida Orion Stage Adapter, California, Alabama Orion Multi-Purpose Crew Vehicle RL10 Engine Lockheed Martin, 5 Segment Solid Rocket Aerojet Rocketdyne, Louisiana, KSC Florida Booster (2) Interim Cryogenic Northrop Grumman, Propulsion Stage (ICPS) Utah, KSC Boeing/United Launch Alliance, California, Alabama Launch Vehicle Stage Adapter Teledyne Brown Engineering, California, Alabama Core Stage & Avionics Boeing Louisiana, Alabama RS-25 Engine (4) -
January 10 Color.Indd
Volume 5 Issue 1 www.nasa.gov/centers/stennis January 2010 Stennis hosts NASA Day at the Capitol Astronaut Danny Olivas addresses members of the Mississippi Senate Stennis exceeds during NASA Day at the Capitol activities 2009 campaign Jan. 6. He is joined by Mississippi Lt. Gov. Phil giving goal Bryant (at left rear), Stennis Space Center tennis Space Center Deputy Director Patrick employees closed 2009 by Scheuermann (left) and exceeding their Combined a pair of Gulf Coast S Federal Campaign giving goal delegation members. Olivas also spoke to the of $200,000 by 16.5 percent. Mississippi House of Representatives during Employees contributed Jan. 6 activities. $233,016 through the 2009 campaign. In addition to epresentatives from John C. “These are exciting days for NASA exceeding the giving goal, the Stennis Space Center visited and Stennis Space Center,” Stennis 2009 total also surpassed the RJackson on Jan. 6, to meet Director Gene Goldman said. “Sten- 2008 giving total by almost with Mississippi legislators as part of nis is making continued progress, $35,000 (17.3 percent). NASA Day at the Capitol. readying for testing of the engines that will replace the space shuttle The CFC is the largest annual Astronaut Danny Olivas, who has main engine. In addition, we are workplace charity effort. Each logged more than 668 hours in space involved in science projects related to year, its gifts support organiza- and 34-plus spacewalk hours during a the Gulf of Mexico and benefi cial to tions providing health and hu- pair of space shuttle missions, joined this region. -
Delta IV Parker Solar Probe Mission Booklet
A United Launch Alliance (ULA) Delta IV Heavy what is the source of high-energy solar particles. MISSION rocket will deliver NASA’s Parker Solar Probe to Parker Solar Probe will make 24 elliptical orbits an interplanetary trajectory to the sun. Liftoff of the sun and use seven flybys of Venus to will occur from Space Launch Complex-37 at shrink the orbit closer to the sun during the Cape Canaveral Air Force Station, Florida. NASA seven-year mission. selected ULA’s Delta IV Heavy for its unique MISSION ability to deliver the necessary energy to begin The probe will fly seven times closer to the the Parker Solar Probe’s journey to the sun. sun than any spacecraft before, a mere 3.9 million miles above the surface which is about 4 OVERVIEW The Parker percent the distance from the sun to the Earth. Solar Probe will At its closest approach, Parker Solar Probe will make repeated reach a top speed of 430,000 miles per hour journeys into the or 120 miles per second, making it the fastest sun’s corona and spacecraft in history. The incredible velocity trace the flow of is necessary so that the spacecraft does not energy to answer fall into the sun during the close approaches. fundamental Temperatures will climb to 2,500 degrees questions such Fahrenheit, but the science instruments will as why the solar remain at room temperature behind a 4.5-inch- atmosphere is thick carbon composite shield. dramatically Image courtesy of NASA hotter than the The mission was named in honor of Dr. -
Marshall Space Flight Center Marshall Overview Marshall
https://ntrs.nasa.gov/search.jsp?R=20150002594 2019-08-31T11:48:14+00:00Z National Aeronautics and Space Administration Marshall Space Flight Center Marshall Overview marshall Dr. Daniel Schumacher www.nasa.gov Director, Science and Technology Office NASA Around the Country Glenn Research Center Aeronautics and Spacecraft Technology Cleveland, Ohio Ames Research Center Goddard Space Aerospace and Flight Center Small Spacecraft Science Missions Moffett Field, Calif. and Telescopes Greenbelt, Md. Dryden Flight NASA Headquarters Washington, D.C. Research Center Atmospheric Research and Testing Edwards, Calif. Langley Research Center Aviation and Space Research Hampton, Va. Jet Propulsion Laboratory Deep Space Robotic Rovers and Networks Pasadena, Calif. Kennedy Space Center Space Vehicle Launch and Johnson Space Center Landing Cape Canaveral, Fla. Human Space Flight Marshall Space Operations Michoud Flight Center Houston, Texas Assembly Facility Space Transportation, Stennis Space Center Large Vehicle Propulsion Systems, Vehicle Engine Testing Manufacturing Space Systems, and Bay St. Louis, Miss. New Orleans, La. Science Huntsville, Ala. Supporting NASA’s mission with unique engineering expertise. 2 Marshall Profile $2B expenditures 6,000 employees 3rd largest employer 4 core product lines nationally (FY13: 2,446 civil service) in the Huntsville – supported by more than ($1.2B in Alabama) Madison County area 125 unique and specialized facilities Part of an Aerospace/Defense/Commercial Technical Community • Redstone Arsenal – home to 18 primary -
Development of a 10 Kn LOX/HTPB Hybrid Rocket Engine Through Successive Development and Testing of Scaled Prototypes
DOI: 10.13009/EUCASS2017-334 7TH EUROPEAN CONFERENCE FOR AERONAUTICS AND AEROSPACE SCIENCES (EUCASS) Development of a 10 kN LOX/HTPB Hybrid Rocket Engine through Successive Development and Testing of Scaled Prototypes Maximilian Bambauer and Markus Brandl WARR (TUM) c/o TUM Lehrstuhl für Raumfahrttechnik Boltzmannstraße 15 D-85748 Garching bei München [email protected] [email protected] · Abstract The development of a hybrid flight engine for a sounding rocket requires intensive preparation work and pretests. To obtain better understanding of the difficulties in design and operation that occur with LOX/HTPB rocket engines, four rocket engines with increasing size and thrust level are successively developed and manufactured. Listed chronologically, those engines are the demonstrator engine, the sub- scale engine with a cylindrical grain geometry and later a star shaped geometry, the full-scale test engine and the full-scale flight version. At first a small-scale technology demonstrator was developed. It pro- duced a mean thrust of 160N for 5s and had the purpose to validate the design calculations and to gain first experiences with the use of cryogenic propellants, especially regarding cooldown procedures. Based on this test results the so-called sub-scale engine was developed and tested. The engine can be operated with two grain configurations, using either a cylindrical grain or a star shaped grain. The star shaped grain geometries are realized, using an additive manufactured core, outside of which the HTPB is casted. In the low thrust configuration, the engine is operated using a cylindrical single port HTPB grain and it produces a thrust of about 540 N for a duration of 10 s. -
The Delta Launch Vehicle- Past, Present, and Future
The Space Congress® Proceedings 1981 (18th) The Year of the Shuttle Apr 1st, 8:00 AM The Delta Launch Vehicle- Past, Present, and Future J. K. Ganoung Manager Spacecraft Integration, McDonnell Douglas Astronautics Co. H. Eaton Delta Launch Program, McDonnell Douglas Astronautics Co. Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Ganoung, J. K. and Eaton, H., "The Delta Launch Vehicle- Past, Present, and Future" (1981). The Space Congress® Proceedings. 7. https://commons.erau.edu/space-congress-proceedings/proceedings-1981-18th/session-6/7 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. THE DELTA LAUNCH VEHICLE - PAST, PRESENT AND FUTURE J. K. Ganoung, Manager H. Eaton, Jr., Director Spacecraft Integration Delta Launch Program McDonnell Douglas Astronautics Co. McDonnell Douglas Astronautics Co. INTRODUCTION an "interim space launch vehicle." The THOR was to be modified for use as the first stage, the The Delta launch vehicle is a medium class Vanguard second stage propulsion system, was used expendable booster managed by the NASA Goddard as the Delta second stage and the Vanguard solid Space Flight Center and used by the U.S. rocket motor became Delta's third stage. Government, private industry and foreign coun Following the eighteen month development program tries to launch scientific, meteorological, and failure to launch its first payload into or applications and communications satellites. -
ITEM 2 Complete Subsystems Complete
ITEM 2 Complete Subsystems Complete CATEGORY I ~ ITEM 2 CATEGORY Subsystems Complete subsystems usable in the systems in Item 1, as follows, as well Produced by as the specially designed “production facilities” and “production equip- companies in ment” therefor: (a) Individual rocket stages; • Brazil • China Nature and Purpose: A rocket stage generally consists of structure, engine/ • Egypt motor, propellant, and some elements of a control system. Rocket engines or • France motors produce propulsive thrust to make the rocket fly by using either solid • Germany propellants, which burn to exhaustion once ignited, or liquid propellants • India burned in a combustion chamber fed by pressure tanks or pumps. • Iran • Iraq Method of Operation: A launch signal either fires an igniter in the solid • Israel propellant inside the lowermost (first stage) rocket motor, or tank pressure • Italy or a pump forces liquid propellants into the combustion chamber of a • Japan rocket engine where they react. Expanding, high-temperature gases escape • Libya at high speeds through a nozzle at the rear of the rocket stage. The mo- • North Korea mentum of the exhausting gases provides the thrust for the missile. Multi- • Pakistan stage rocket systems discard the lower stages as they burn up their propel- • Russia lant and progressively lose weight, thereby achieving greater range than • South Korea comparably sized, single-stage rocket systems. • Syria • Ukraine Typical Missile-Related Uses: Rocket stages are necessary components of any • United Kingdom rocket system. Rocket stages also are used in missile and missile-component • United States testing applications. Photo Credit: Chemical Propulsion Information Agency Other Uses: N/A Appearance (as manufactured): Solid propellant rocket motor stages are cylinders usually ranging from 4 to 10 m in length and 0.5 to 4 m in diame- ter, and capped at each end with hemispherical domes as shown in Figure 2-1. -
3Rd Wernher Von Braun Memorial Symposium
6th Wernher von Braun Memorial Symposium - Bringing Exploration Forward - October 7-10, 2013 Chan Auditorium Business Administration Building The University of Alabama in Huntsville 301 Sparkman Drive Huntsville, AL 35899 An AAS Symposium organized in conjunction with The University of Alabama in Huntsville NASA Marshall Space Flight Center Huntsville National Space Club Media Sponsor – SpaceNews Education Sponsor – Aerojet Rocketdyne Co-sponsored by: Boeing Lockheed Martin Northrop Grumman Orbital Sciences Corporation SpaceX United Launch Alliance - Program - Monday, October 7 5:30 pm Kick-off Networking Reception University Center, Exhibit Hall - sponsored by Orbital Sciences Corporation Tuesday, October 8 7:15 am AAS Corporate Members Breakfast (Invitation Only) 7:30 am Registration Opens / Networking / Continental Breakfast Business Administration Building, Lobby - sponsored by SpaceX 8:30 am Welcome to Campus - Chan Auditorium Dr. Robert Altenkirch, President, The University of Alabama in Huntsville Remarks by AAS Executive Vice President Walt Faulconer, President, Strategic Space Solutions, LLC 8:45 am Marshall Space Flight Center Update Patrick Scheuermann, Director, NASA Marshall Space Flight Center 9:00 am Keynote Charlie Bolden, NASA Administrator 9:45 am Break - sponsored by SpaceX 10:00 am Roundtable: Exploration Going Forward with SLS and Orion – 2020 and Beyond Moderator: Mary Lynne Dittmar, CEO, Dittmar Associates, Inc. Panelists: Dan Dumbacher, Deputy Associate Administrator for Exploration Systems Development, NASA Headquarters