Aerojet Rocketdyne Completes J-2X Testing

Total Page:16

File Type:pdf, Size:1020Kb

Aerojet Rocketdyne Completes J-2X Testing June 26, 2014 Aerojet Rocketdyne Completes J-2X Testing SACRAMENTO, Calif., June 26, 2014 (GLOBE NEWSWIRE) -- Aerojet Rocketdyne, a GenCorp (NYSE:GY) company, recently completed its final J-2X test series at NASA's Marshall Space Flight Center. Over a period of three years, Aerojet Rocketdyne teams manufactured, assembled and tested four newly developed engine test articles that achieved an accumulated duration of nearly five hours firing time and demonstrated full power operation for twice its designed life service. Delivering 30 percent more thrust and five percent more performance than the J-2 Apollo-era engine, upon which it is based, the J-2X is the highest performing human-rated upper-stage engine to be developed in nearly 40 years. "With J-2X, we were able to drive down the time needed to take a new rocket engine to 100 percent power level in testing, from 651 days to just 29, by integrating modern design, analysis and test practices with decades of experience gained on multiple engine development programs," said Aerojet Rocketdyne President Warren M. Boley, Jr. "That kind of knowledge isn't retained anywhere else in the industry and it demonstrates that we know how to design an engine that will work the first time." The J-2X is a liquid-oxygen/liquid-hydrogen fueled engine that is designed to start at altitude and re-start in space as part of a second or third stage of a large, multi-stage launch vehicle. With its full nozzle extension installed, the J-2X measures more than 15 feet tall and 10 feet in diameter at its base and weighs approximately 5,400 pounds. With a vacuum thrust of 294,000 lbs., the engine is designed to help loft heavy payloads—such as habitats, landers and in-space modules—beyond low-Earth orbit. "We had to modernize the J-2 engine to increase its power level and performance, so we had a good challenge on our hands," said Aerojet Rocketdyne's J-2X Director and Program Manager, Walt Janowski. "No part of this engine went untouched. We looked closely at each part to make sure it met modern standards and human-rated requirements." The completed J-2X testing provides direct benefits to Aerojet Rocketdyne's RS-25 test program, including understanding performance of the test stands and implementing new methods to record and interpret engine performance data. The RS-25 engines also feature a modernized engine controller, successfully demonstrated on J-2X, for controlling start and shutdown valve sequencing and health monitoring control functions. The J-2X engine is one of several options being considered to power the upper stage of NASA's future 130-metric-ton Space Launch System (SLS). The only vehicle with the mass, volume and speed required for human missions beyond low-Earth orbit, SLS will launch crew and cargo to deep space destinations. Capable of accomplishing these missions in fewer launches than any current or planned vehicle, NASA's SLS and Orion spacecraft programs are gearing up for major accomplishments this year. Orion's first flight test on a United Launch Alliance Delta IV Heavy, scheduled for December 2014, will take a human-rated spacecraft farther into space than one has been in 40 years. The mission will travel 15 times farther than the International Space Station and perform two Earth orbits to validate key functions including high velocity re-entry and recovery. Test firings of the RS-25 engine and SLS booster will demonstrate the performance of the vehicle's main propulsion systems, and the opening of the SLS Vertical Assembly Center will support welding of the vehicle's fuel tank - all important steps in preparing for deep space human explorations missions. A propulsion provider for all NASA human spaceflight programs and the Evolved Expendable Launch Vehicles, Aerojet Rocketdyne has delivered reliable propulsion solutions for more than 70 years. No other company has the experience and proven track record required to build these critical national assets. "Aerojet Rocketdyne is a propulsion innovator," said Boley. "We are redefining what the standards are for engine performance and we're ready to meet the propulsion needs of our nation." Aerojet Rocketdyne is a world-recognized aerospace and defense leader providing propulsion and energetics to the space, missile defense and strategic systems, tactical systems and armaments areas, in support of domestic and international markets. GenCorp is a diversified company that provides innovative solutions that create value for its customers in the aerospace and defense, and real estate markets. Additional information about Aerojet Rocketdyne and GenCorp can be obtained by visiting the companies' websites at www.Rocket.com and www.GenCorp.com. CONTACT: Glenn Mahone, Aerojet Rocketdyne, 202.302.9941 [email protected] Erin Dick, Aerojet Rocketdyne, 818-586-4977 [email protected] Source: Aerojet Rocketdyne News Provided by Acquire Media.
Recommended publications
  • Constellation Program Overview
    Constellation Program Overview October 2008 hris Culbert anager, Lunar Surface Systems Project Office ASA/Johnson Space Center Constellation Program EarthEarth DepartureDeparture OrionOrion -- StageStage CrewCrew ExplorationExploration VehicleVehicle AresAres VV -- HeavyHeavy LiftLift LaunchLaunch VehicleVehicle AltairAltair LunarLunar LanderLander AresAres II -- CrewCrew LaunchLaunch VehicleVehicle Lunar Capabilities Concept Review EstablishedEstablished Lunar Lunar Transportation Transportation EstablishEstablish Lunar Lunar Surface SurfaceArchitecturesArchitectures ArchitectureArchitecture Point Point of of Departure: Departure: StrategiesStrategies which: which: Satisfy NASA NGO’s to acceptable degree ProvidesProvides crew crew & & cargo cargo delivery delivery to to & & from from the the Satisfy NASA NGO’s to acceptable degree within acceptable schedule moonmoon within acceptable schedule Are consistent with capacity and capabilities ProvidesProvides capacity capacity and and ca capabilitiespabilities consistent consistent Are consistent with capacity and capabilities withwith candidate candidate surface surface architectures architectures ofof the the transportation transportation systems systems ProvidesProvides sufficient sufficient performance performance margins margins IncludeInclude set set of of options options fo for rvarious various prioritizations prioritizations of cost, schedule & risk RemainsRemains within within programmatic programmatic constraints constraints of cost, schedule & risk ResultsResults in in acceptable
    [Show full text]
  • Privacy Statement Link at the Bottom of Aerojet Rocketdyne Websites
    Privacy Notice Aerojet Rocketdyne – For external use Contents Introduction ...................................................................................................................... 3 Why we collect personal information? ............................................................................. 3 How we collect personal information? ............................................................................. 3 How we use information we collect? ............................................................................... 4 How we share your information? .................................................................................... 4 How we protect your personal information? ..................................................................... 4 How we collect consent? .............................................................................................. 4 How we provide you access? ........................................................................................ 4 How to contact Aerojet Rocketdyne privacy?.................................................................... 5 Collection of personal information .................................................................................. 5 Disclosure of personal information.................................................................................. 5 Sale of personal information .......................................................................................... 6 Children’s online privacy ..............................................................................................
    [Show full text]
  • 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.
    [Show full text]
  • Silencing Nasa's Space Shuttle Crawler
    SILENCING NASA’S SPACE SHUTTLE CRAWLER TRANSPORTER R. MacDonalda, C. Faszerb, and R. Margasahayamc aNoise Solutions Inc., #310 605 – 1st Street SW, Calgary, Alberta, Canada T2P 3S9 bFaszer Farquharson & Associates, #304 605 – 1st Street SW, Calgary, Alberta, Canada T2P 3S9 cNASA, John F. Kennedy Space Center, Florida, United States of America 32899 [email protected]; [email protected]; [email protected] Abstract. The crawler transporter (CT) is the world’s second largest known tracked vehicle, weighing 6 million pounds with a length of 131 feet and a width of 113 feet. The Kennedy Space Center (KSC) has two CTs that were designed and built for the Apollo program in the 1960’s, maintained and retrofitted for use in the Space Shuttle program. As a key element of the Space Shuttle ground systems, the crawler transports the entire 12-million-pound stack comprising the orbiter, the mobile launch platform (MLP), the external tank (ET), and the solid rocket boosters (SRB) from the Vehicle Assembly Building (VAB) to the launch pad. This rollout, constituting a 3.5 to 5.0 mile journey at a top speed of 0.9 miles-per-hour, requires over 8 hours to reach either Launch Complex 39A or B. This activity is only a prelude to the spectacle of sound and fury of the Space Shuttle launch to orbit in less than 10 minutes and traveling at orbital velocities of Mach 24. This paper summarizes preliminary results from the Crawler Transporter Sound Attenuation Study, encompassing test and engineering analysis of significant sound sources to measure and record full frequency spectrum and intensity of the various noise sources and to analyze the potential for noise mitigation.
    [Show full text]
  • ADVANCED SPACE ENGINE N74-16489 PRELIINABY DESIGN (Rocketdyne) F5,-P HC CSCL 21H $27.25 Unclas G3/28 28289 1
    NASA CR-121236 R-9269 ADVANCED SPACE ENGINE PRELIMINARY DESIGN By A. T. Zachary ROCKETDYNE DIVISION C- ROCKWELL INTERNATIONAL Prepared for NATIONAL AERONAUTICS AND SPACE ADMINISTRATION NASA-Lewis Research Center Contract NAS3-16751 (NVSA-CR-121236) ADVANCED SPACE ENGINE N74-16489 PRELIINABY DESIGN (Rocketdyne) f5,-p HC CSCL 21H $27.25 Unclas G3/28 28289 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA CR-121236 4. Title and Subtitle 5. Report Date ADVANCED SPACE ENGINE PRELIMINARY DESIGN October 1973 6. Performing Organization Code 7. Author(s) 8. Performing Organization Report No. A.T. Zachary R-9269 10. Work Unit No. 9. Performing Organization Name and Address Rocketdyne Division, Rockwell International 11. Contract or Grant No. Canoga Park, California, 91304 NAS3-16751 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Contractor Report National Aeronautics and Space Administration Washington, D.C., 20546 14. Sponsoring Agency Code 15. Supplementary Notes Project Manager, D.D. Scheer, NASA-Lewis Research Center, Cleveland, Ohio 16. Abstract Analysis and design of an optimum LO2/LH2, combustion topping cycle, 88,964 N (20,000-pound) thrust, liquid rocket engine was conducted. The design selected is well suited to high-energy, upper-stage engine applications such as the Space Tug and embodies features directed toward optimization of vehicle performance. A configuration selection was conducted based on prior Air Force Contracts F04611-71-C0039, F04611-71-C-0040, and F04611-67-C-0016,.and additional criteria for optimum stage performance. Following configuration selection, analyses and design of the major components and engine systems were conducted to sufficient depth to provide layout drawings suitable for subsequent detailing.
    [Show full text]
  • Space Shuttle Main Engine Orientation
    BC98-04 Space Transportation System Training Data Space Shuttle Main Engine Orientation June 1998 Use this data for training purposes only Rocketdyne Propulsion & Power BOEING PROPRIETARY FORWARD This manual is the supporting handout material to a lecture presentation on the Space Shuttle Main Engine called the Abbreviated SSME Orientation Course. This course is a technically oriented discussion of the SSME, designed for personnel at any level who support SSME activities directly or indirectly. This manual is updated and improved as necessary by Betty McLaughlin. To request copies, or obtain information on classes, call Lori Circle at Rocketdyne (818) 586-2213 BOEING PROPRIETARY 1684-1a.ppt i BOEING PROPRIETARY TABLE OF CONTENT Acronyms and Abbreviations............................. v Low-Pressure Fuel Turbopump............................ 56 Shuttle Propulsion System................................. 2 HPOTP Pump Section............................................ 60 SSME Introduction............................................... 4 HPOTP Turbine Section......................................... 62 SSME Highlights................................................... 6 HPOTP Shaft Seals................................................. 64 Gimbal Bearing.................................................... 10 HPFTP Pump Section............................................ 68 Flexible Joints...................................................... 14 HPFTP Turbine Section......................................... 70 Powerhead...........................................................
    [Show full text]
  • AEHF-6 Launch Marks 500Th Flight of Aerojet Rocketdyne's RL10 Engine
    AEHF-6 Launch Marks 500th Flight of Aerojet Rocketdyne’s RL10 Engine March 27, 2020 CAPE CANAVERAL, Fla., March 26, 2020 (GLOBE NEWSWIRE) -- The successful March 26 launch of the U.S. Space Force’s sixth and final Advanced Extremely High Frequency (AEHF) military communications satellite aboard a United Launch Alliance (ULA) Atlas V rocket marked the 500th flight of Aerojet Rocketdyne’s RL10 upper-stage engine. The RL10, which powers the ULA Atlas V Centaur upper stage, is one of several Aerojet Rocketdyne propulsion products supporting the mission. Aerojet Rocketdyne propulsion can be found on both the rocket and the AEHF-6 satellite. Built by Lockheed Martin, the AEHF satellites provide secure, jam-proof communications, including nuclear command and control, to U.S. and allied forces. “This launch marks an important milestone for Aerojet Rocketdyne and for the country,” said Eileen Drake, Aerojet Rocketdyne’s CEO and president. “The RL10 has supported a majority of the nation’s most important national security and scientific missions, including all of the AEHF satellites which provide communication links that are critical to our warfighters.” The Atlas V in the 551 configuration is the most powerful vehicle in the Atlas V family, featuring five Aerojet Rocketdyne AJ-60A solid rocket strap-on motors, each generating 348,500 pounds of thrust. Designed specifically to provide extra lifting power to the Atlas V, the AJ-60A is the world’s largest monolithic solid rocket motor ever flown. The AEHF-6 satellite, meanwhile, is outfitted with three different types of Aerojet Rocketdyne thrusters for attitude control, orbital station keeping and maneuvering.
    [Show full text]
  • SLS Case Study
    CASE STUDY Supporting Space Flight History with the Space Launch System (SLS) Technetics Group is a proud sup- Boeing representatives held a sup- plier to NASA, Boeing and Aerojet plier recognition presentation for Rocketdyne, and proved instru- the Technetics team members, mental in working with these orga- citing outstanding performance nizations on the development of in providing hydraulic accumula- NASA’s Space Launch System (SLS). tors and reservoirs for the Thrust The SLS is an advanced, heavy-lift Vector Control hydraulic system, BELFAB Edge-Welded launch vehicle that will send astro- located within the Core Stage of Metal Bellows nauts into deep space and open the rocket. Technetics was one up the possibility for missions to of the first suppliers on the pro- Qualiseal Mechanical neighboring planets. The program gram to have provided all Flight 1 Seals is enabling humans to travel fur- requirements and subsystem test ther into space than ever before units. and paving the way for new sci- Aerojet Rocketdyne also rec- entific discoveries and knowledge ognized Technetics and stated that was once out of reach. that Technetics “has gone above Technetics has worked closely and beyond to produce quality with program design teams for hardware and support aggressive critical applications for the Core schedules,” and that “Technetics Stage and Upper Stage on the SLS. efforts and those of Technetics NAFLEX Seals Specifically, a number of preci- employees have not gone unno- sion sealing solutions and fluid ticed.” To express their appre- management components were ciation, Aerojet Rocketdyne needed for Aerojet Rocketdyne’s representatives visited the RS-25 and RL10 engines to ensure Technetics Deland, FL facility to the integrity of the overall system.
    [Show full text]
  • Apollo Rocket Propulsion Development
    REMEMBERING THE GIANTS APOLLO ROCKET PROPULSION DEVELOPMENT Editors: Steven C. Fisher Shamim A. Rahman John C. Stennis Space Center The NASA History Series National Aeronautics and Space Administration NASA History Division Office of External Relations Washington, DC December 2009 NASA SP-2009-4545 Library of Congress Cataloging-in-Publication Data Remembering the Giants: Apollo Rocket Propulsion Development / editors, Steven C. Fisher, Shamim A. Rahman. p. cm. -- (The NASA history series) Papers from a lecture series held April 25, 2006 at the John C. Stennis Space Center. Includes bibliographical references. 1. Saturn Project (U.S.)--Congresses. 2. Saturn launch vehicles--Congresses. 3. Project Apollo (U.S.)--Congresses. 4. Rocketry--Research--United States--History--20th century-- Congresses. I. Fisher, Steven C., 1949- II. Rahman, Shamim A., 1963- TL781.5.S3R46 2009 629.47’52--dc22 2009054178 Table of Contents Foreword ...............................................................................................................................7 Acknowledgments .................................................................................................................9 Welcome Remarks Richard Gilbrech ..........................................................................................................11 Steve Fisher ...................................................................................................................13 Chapter One - Robert Biggs, Rocketdyne - F-1 Saturn V First Stage Engine .......................15
    [Show full text]
  • Handout – Innovative Business Agreements and Related Cost
    MG-4 - Innovative Business Agreements and Related Cost & Pricing Methods at NASA in Support of New Commercial Programs Kennedy Space Center - CFO Business & Cost Assessment Office Innovative Business Agreements and Related Cost & Pricing Methods at NASA in Support of New Commercial Programs JIM ROBERTS & TERRY LAMBING NASA Kennedy Space Center Office of the CFO ICEAA National Conference June 2014 Kennedy Space Center - CFO Business & Cost Assessment Office Background.. • Immediately after Shuttle retirement decision in 2004, transition planning for NASA’s facilities was begun. • In April 2010 President Obama delivered a speech at Kennedy Space Center in which he outlined his new vision for the U.S. space program. Emphasis was placed on enabling the exploration of Space by Commercial entities instead of by Government. • The Constellation Program - which was to fill the void of the retiring Space Shuttle Program - was cancelled. • Facilities no longer needed for remaining NASA programs were identified, and NASA Centers were charged with leveraging value of underutilized property through initiatives such as out-leasing. • Focus was placed on development of Commercial Business Partnerships to enable commercial space activities using unused or available facilities and launch infrastructure. 5/23/2014 2 1 ICEAA 2014 Professional Development & Training Workshop MG-4 - Innovative Business Agreements and Related Cost & Pricing Methods at NASA in Support of New Commercial Programs Kennedy Space Center - CFO Business & Cost Assessment Office Kennedy
    [Show full text]
  • Rocketdyne R-6636-L FINAL RE PORT FLUORINE-HYDROGEN
    (THRU) ° %/ / (PAGES) (CODE:) NASA CR-5497_ _-_ (NASA CR OR TMX OR AD NUMBER) (CATEGORY) Rocketdyne R-6636-l FINAL RE PORT FLUORINE-HYDROGEN PERFORMANCE EVALUATION .J PHASE I, PART I : ANALYSIS, DESIGN, AND DEMONSTRATION HIGH-PERFORMANCE INJECTORS FOR THE LIQUID F LUORINE- GASE OUS HYDROGEN PROPE L LANT C OMBINATION By GPO PRICE $ i{ H. A. Arbit CFSTI PRICE(S)•$ So Do Clapp Hard copy (HC) Microfiche (M F) ff 653 July 65 prepared for NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Contract NASw- 1229 ROCKETDYNE RESEARCH DEPARTMENT North American Aviation, Inc. 6633 Canoga Avenue, Canoga Park, California NOTI CE This report was prepared as an account of Government sponsored Work. Neither the United States, nor the National Aeronautics and Space Administration (NASA), nor any person acting on be- half of NASA: A.) Makes any warranty or representation, expressed or implied, with respect to the accuracy, completeness, or usefulness of the information contained in this report, or that the use of any information, apparatus, method, or process disclosed in this report may not infringe privately owned rights; or B.) Assumes any liabilities with respect to the use of, ¢ or for damages resulting from the use of any infor- mation, apparatus, method or process disclosed in this report. As used above, "person acting on behalf of NASA" includes any employee or contractor of NASA, or employee of such contractor, to the extent that such employee or contractor of NASA or employee of such contractor prepares, disseminates, or provides access to, any information pursuant to his employment or contractor with NASA, or his employment with such contractor.
    [Show full text]
  • NASA Begins Engine Test Project for Space Launch System Rocket 21 July 2014, by Rachel Kraft
    NASA begins engine test project for space launch system rocket 21 July 2014, by Rachel Kraft shuttle," said Steve Wofford, SLS Liquid Engines Element manager. "This testing will confirm the RS-25 will be successful at powering SLS." Early tests on the engine will collect data on the performance of its new advanced engine controller and other modifications. The controller regulates valves that direct the flow of propellant to the engine, which determines the amount of thrust generated during an engine test, known as a hotfire test. In flight, propellant flow and engine thrust determine the speed and trajectory of a spacecraft. The controller also regulates the engine startup sequence, which is especially important on an engine as sophisticated as the RS-25. Likewise, the controller determines the engine shutdown sequence, ensuring it will proceed properly under RS-25 rocket engine No. 0525 is positioned onto the A-1 both normal and emergency conditions. Test Stand at NASA’s Stennis Space Center in Mississippi in preparation for a series of developmental "Installation of RS-25 engine No. 0525 signals the tests. Credit: NASA launch of another major rocket engine test project for human space exploration on the A-1 Test Stand," said Gary Benton, RS-25 rocket engine test project manager at Stennis. (Phys.org) —Engineers have taken a crucial step in preparing to test parts of NASA's Space Launch The SLS is designed to carry astronauts in NASA's System (SLS) rocket that will send humans to new Orion spacecraft deeper into space than ever destinations in the solar system.
    [Show full text]