B-167838 Overstatement of Contract Target Costs for F-1 Rocket
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
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 .............................................................................................. -
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. -
Assessing the Evolution of the Airborne Generation of Thermal Lift in Aerostats 1783 to 1883
Journal of Aviation/Aerospace Education & Research Volume 13 Number 1 JAAER Fall 2003 Article 1 Fall 2003 Assessing the Evolution of the Airborne Generation of Thermal Lift in Aerostats 1783 to 1883 Thomas Forenz Follow this and additional works at: https://commons.erau.edu/jaaer Scholarly Commons Citation Forenz, T. (2003). Assessing the Evolution of the Airborne Generation of Thermal Lift in Aerostats 1783 to 1883. Journal of Aviation/Aerospace Education & Research, 13(1). https://doi.org/10.15394/ jaaer.2003.1559 This Article is brought to you for free and open access by the Journals at Scholarly Commons. It has been accepted for inclusion in Journal of Aviation/Aerospace Education & Research by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. Forenz: Assessing the Evolution of the Airborne Generation of Thermal Lif Thermal Lift ASSESSING THE EVOLUTION OF THE AIRBORNE GENERATION OF THERMAL LIFT IN AEROSTATS 1783 TO 1883 Thomas Forenz ABSTRACT Lift has been generated thermally in aerostats for 219 years making this the most enduring form of lift generation in lighter-than-air aviation. In the United States over 3000 thermally lifted aerostats, commonly referred to as hot air balloons, were built and flown by an estimated 12,000 licensed balloon pilots in the last decade. The evolution of controlling fire in hot air balloons during the first century of ballooning is the subject of this article. The purpose of this assessment is to separate the development of thermally lifted aerostats from the general history of aerostatics which includes all gas balloons such as hydrogen and helium lifted balloons as well as thermally lifted balloons. -
The Rotating Wing Aircraft Meetings of 1938 and 1939 Were the First
The Rotating Wing Aircraft Meetings of 1938 and 1939 This advertisement showing Pitcairn’s 1932 Tandem landing at an were the first national conferences on rotorcraft. They marked estate was typical of their strategy to market to the wealthy. “If yours a transition from a technological focus on the Autogiro to the is such an estate or if you will select a neighboring field, a Pitcairn representative will gladly demonstrate the complete practicality of helicopter. In addition, these important meetings helped to this modern American scene.” With the Great Depression wearing lay the groundwork for the founding of the American Heli- on, however, the Autogiro business was moribund by the late 1930s. copter Society. – Ed. he Rotating Wing Aircraft Meeting of October 28 This was a significant gathering for the future of – 29, 1938 at the Franklin Institute in Philadel- rotary wing flight in America, coming at a time when T phia, PA, sponsored by the Philadelphia Chapter the Autogiro movement was moribund and helicopter of the Institute of the Aeronautical Sciences (IAS, the development was just about to receive a boost with forerunner of the American Institute of Aeronautics and commencement of the just-passed Dorsey-Logan Bill. Astronautics, or AIAA), was an historic gathering of And, perhaps of greater importance, those attending – those involved, committed to and researching Autogiro, including many of the leading developers of rotary wing convertiplane and helicopter flight. It was, as described flight – were actively speculating as to the future that in the preface to the conference proceedings, “the first rotary wing flight might take. -
1 American Institute of Aeronautics and Astronautics EXTENDED
EXTENDED CAPABILITIES OF ZERO-PRESSURE AND SUPERPRESSURE SCIENTIFIC BALLOONING PLATFORMS E. Lee Rainwater*, Raven Industries, Inc., Sulphur Springs, Texas USA Debora A. Fairbrother†, NASA Wallops Flight Facility, Wallops Island, Virginia USA Michael S. Smith‡, Raven Industries, Inc., Sulphur Springs, Texas USA ABSTRACT Updated Heavy Lift Designs Balloons with maximum payloads of up to 3625 kg The 1.7 million cubic meter (60 million cubic foot) (8000 lb) have been available for many years. However, scientific balloon platform, designed and manufactured the reliability of such balloons is compromised when by Raven Industries, Inc. and funded by NASA, has flown at the maximum payload. Raven Industries, in successfully flown a payload of 680 kg (1500 lb) to a cooperation with NASA and the National Scientific float altitude of over 48.7 km (160 kft). This record- Balloon Facility (NSBF), has developed a new 1 MCM breaking flight, performed in August, 2002, greatly (36.7 MCF) heavy-load balloon design which utilizes extended the performance envelope of scientific bal- three-layer co-extruded film technologies developed for looning platforms with regard to its ability to lift sig- the ULDB program. This balloon promises to utilize the nificant payloads to extreme altitudes. This has, in turn, full gross inflation capacity of NSBF’s launch equip- generated significant interest from the scientific com- ment, while delivering the near-100% reliability associ- munity regarding the increased altitude and duration ated with existing medium-capacity balloons. capabilities of scientific ballooning platforms. Zero-pressure Ultra-high Altitude Balloons (UHABs) In order to explore future capabilities and establish a ULDB film technology also found practical application future direction for ultra high-altitude platforms, NASA 1 and Raven have partnered in a study to determine the in the 60 MCF “Big 60” balloon . -
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. -
Subsonic Fixed Wing Project Reference Document
Fundamental Aeronautics Program Subsonic Fixed Wing Project Reference Document Principal Investigator: Dr. Fay Collier Project Manager: Eddie Zavala Project Scientist: Dennis Huff This document was developed over the past several months by NASA to define the rationale, scope and detailed content of a comprehensive Fundamental Aeronautics Subsonic Fixed-Wing research project. It contains reference to past work and an approach to accomplish planned work with applicable milestones, metrics and deliverables. The document also references potential opportunities for cooperation with external organizations in areas that are currently considered to be of common interest or benefit to NASA. This document should be considered a reference document and not a completed research plan. Technical Plan standards for noise and emissions, a “clean sheet” design effort exploring novel commercial 1.1 Relevance transport configurations optimized for low noise Problem Statement: This document is focused and emissions is envisioned. These concepts have on meeting the challenge to "re-establish our the potential to be radically different from today’s dedication to the mastery of the core conventional commercial transport competencies of aeronautics to develop multi- configurations. This design problem is an ideal disciplinary capabilities that will enable both application for the products of this proposal. civilian and military communities to build In response to the National Energy Policy Act of platforms that meet their specific needs." 2005, Michael Wynne (Secretary of the Air ("Reshaping NASA's Aeronautics Research Force) has created an Energy IPT chartered to Program", October 17, 2005, Dr. Lisa Porter). take a broad based approach to reduce the Air Research directed towards this challenge is Force’s energy costs through technology. -
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........................................................... -
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. -
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. -
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 -
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.