NSIAD-87-215 NASA Procurement: the 1973 Space Shuttle Solid
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Nasa X-15 Program
5 24,132 6 9 NASA X-15 PROGRAM By: T.D. Barnes - NASA Contractor - 1960s NASA contractors for the X-15 program were Bendix Field Engineering followed by Unitec, Inc. The NASA High Range Tracking stations were located at Ely and Beatty Nevada with main control being at Dryden/Edwards AFB in California. Personnel at the tracking stations consisted of a Station Manager, a Technical Advisor, and field engineers for the Mod-2 Radar, Data Transmission System, Communications, Telemetry, and Plant Maintenance/Generators. NASA had a site monitor at each tracking station to monitor our contractor operations. Though supporting flights of the X-15 was their main objective, they also participated in flights of the XB-70, the three Lifting Bodies, experimental Lunar Landing vehicles, and an occasional A-12/YF-12/SR-71 Blackbird flight. On mission days a NASA van picked up each member of the crew at their residence for the 4:20 a.m. trip to the tracking station 18 miles North of Beatty on the Tonopah Highway. Upon arrival each performed preflight calibrations and setup of their various systems. The liftoff of the B-52, with the X-15 tucked beneath its wing, seldom occurred after 9:00 a.m. due to the heat effect of the Mojave Desert making it difficult for the planes to acquire altitude. At approximately 0800 hours two pilots from Dryden would proceed uprange to evaluate the condition of the dry lake beds in the event of an emergency landing of the X-15 (always buzzing our station on the way up and back). -
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 .............................................................................................. -
1 American Institute of Aeronautics and Astronautics from Air Bubbles Cast in the Fuel (Voids) Can Cause Problems During Hot-Fire Operations
Genetic Algorithm Optimization of a Cost Competitive Hybrid Rocket Booster George Story1 NASA MSFC Huntsville, Al Performance, reliability and cost have always been drivers in the rocket business. Hybrid rockets have been late entries into the launch business due to substantial early development work on liquid rockets and solid rockets. Slowly the technology readiness level of hybrids has been increasing due to various large scale testing and flight tests of hybrid rockets. One remaining issue is the cost of hybrids vs the existing launch propulsion systems. This paper will review the known state-of-the-art hybrid development work to date and incorporate it into a genetic algorithm to optimize the configuration based on various parameters. A cost module will be incorporated to the code based on the weights of the components. The design will be optimized on meeting the performance requirements at the lowest cost. I. Introduction Hybrids, considered part solid and part liquid propulsion system, have been caught in the middle of development goals of the various NASA and military programs. Solid rocket motor technology has matured due to the design simplicity, on-demand operational characteristics and low cost. The reliability of solids, given minimal maintenance requirements, made them the ideal system for military applications. On the other hand, liquid rocket engine technology has matured due to their higher specific impulse (ISP) over solids and variable control thrust capability. Hybrid Rockets have been used in only one flight-production application (Teledyne Ryan AQM-81A ‘Firebolt Supersonic Aerial Target) and one series of recent manned flight demonstrations (Burt Rutan’s SpaceshipOne), suggesting that advantages have been overlooked in some potential applications. -
Gallery of USAF Weapons Note: Inventory Numbers Are Total Active Inventory Figures As of Sept
Gallery of USAF Weapons Note: Inventory numbers are total active inventory figures as of Sept. 30, 2011. ■ 2012 USAF Almanac Bombers B-1 Lancer Brief: A long-range, air refuelable multirole bomber capable of flying intercontinental missions and penetrating enemy defenses with the largest payload of guided and unguided weapons in the Air Force inventory. Function: Long-range conventional bomber. Operator: ACC, AFMC. First Flight: Dec. 23, 1974 (B-1A); Oct. 18, 1984 (B-1B). Delivered: June 1985-May 1988. IOC: Oct. 1, 1986, Dyess AFB, Tex. (B-1B). Production: 104. Inventory: 66. Aircraft Location: Dyess AFB, Tex.; Edwards AFB, Calif.; Eglin AFB, Fla.; Ellsworth AFB, S.D. Contractor: Boeing, AIL Systems, General Electric. Power Plant: four General Electric F101-GE-102 turbofans, each 30,780 lb thrust. Accommodation: pilot, copilot, and two WSOs (offensive and defensive), on zero/zero ACES II ejection seats. Dimensions: span 137 ft (spread forward) to 79 ft (swept aft), length 146 ft, height 34 ft. B-1B Lancer (SSgt. Brian Ferguson) Weight: max T-O 477,000 lb. Ceiling: more than 30,000 ft. carriage, improved onboard computers, improved B-2 Spirit Performance: speed 900+ mph at S-L, range communications. Sniper targeting pod added in Brief: Stealthy, long-range multirole bomber that intercontinental. mid-2008. Receiving Fully Integrated Data Link can deliver nuclear and conventional munitions Armament: three internal weapons bays capable of (FIDL) upgrade to include Link 16 and Joint Range anywhere on the globe. accommodating a wide range of weapons incl up to Extension data link, enabling permanent LOS and Function: Long-range heavy bomber. -
Environmental, Social & Governance Report
ESG Environmental, Social & Governance Report Aerojet Rocketdyne 2020 ESG Report Table of Contents About Us Aerojet Rocketdyne is a world-recognized supports our business and our efforts to meet Section One - Social Responsibility technology-based engineering and or exceed the expectations of our customers, Aerojet Rocketdyne Foundation .......................................................... 7 manufacturing company that develops and deliver best-in-class products and services, Employee Volunteer and Giving .......................................................... 8 produces specialized power and propulsion and uphold our high ethical standards while Sponsorship and Donations ................................................................ 8 systems, as well as armament systems. We conducting business with a regard for the develop and manufacture liquid and solid rocket preservation and protection of human safety, Employees and Community ................................................................. 9 propulsion, air-breathing hypersonic engines, health, and the natural environment. Human Resources and electric power and propulsion for space, Section Two - Our Shared Values of Accountability, defense, civil and commercial applications. Tuition Assistance Program ............................................................... 13 Adaptability, Excellence, Integrity and In addition, we are engaged in the rezoning, Scholarship Program ......................................................................... 14 Teamwork are intended -
The Challenger Disaster
Engineering Ethics Case Study: The Challenger Disaster Course No: LE3-001 Credit: 3 PDH Mark Rossow, PhD, PE, Retired Continuing Education and Development, Inc. 22 Stonewall Court Woodcliff Lake, NJ 07677 P: (877) 322-5800 [email protected] Engineering Ethics Case Study: The Challenger Disaster Mark P. Rossow, P.E., Ph.D. © 2015 Mark P. Rossow All rights reserved. No part of this work may be reproduced in any manner without the written permission of the author. 2 Preface On January 28, 1986, the Space Shuttle Challenger was destroyed in a disastrous fire shortly after liftoff. All passengers aboard the vehicle were killed. A presidential commission was formed to investigate the cause of the accident and found that the O-ring seals had failed, and, furthermore, that the seals had been recognized as a potential hazard for several years prior to the disaster. The commission’s report, Report to the President by the Presidential Commission on the Space Shuttle Challenger Accident, stated that because managers and engineers had known in advance of the O-ring danger, the accident was principally caused by a lack of communication between engineers and management and by poor management practices. This became the standard interpretation of the cause of the Challenger disaster and routinely appears in popular articles and books about engineering, management, and ethical issues. But the interpretation ignores much of the history of how NASA and the contractor’s engineers had actually recognized and dealt with the O-ring problems in advance of the disaster. When this history is considered in more detail, the conclusions of the Report to the President become far less convincing. -
RS-25 for NASA's Space Launch System
AEROJET ROCKETDYNE PROPRIETARY 0 THIS DOCUMENT CONTAINS NO EXPORT CONTROLLED – ITAR/USML CATEGORY IV September 2016 Aerojet Rocketdyne Footprint International Offices: Redmond, WA Moscow Tokyo London Belfast UAE Picatinny Arsenal, NJ Sacramento, CA Clearfield, UT ARDÉ, NJ Headquarters Washington, D.C. Denver, CO Gainesville, VA Orange, VA Los Angeles, CA Jonesboro, TN Vernon, CA Camden, AR Socorro, NM Tucson, AZ Huntsville, AL Headquarters Dallas, TX Orlando, FL Operating Locations Stennis, MS Eglin AFB, FL Field Offices West Palm Beach, FL Nearly 5,000 Employees Across 14 States 140 and Growing at NASA Stennis Space Center Aerojet Rocketdyne Proprietary 1 Aerojet Rocketdyne & NASA Stennis Space Center (SSC): A Fifty Year Partnership • NASA-SSC is the nation’s Center of Excellence for large space transportation propulsion systems testing • Tested each of the F-1 rocket engines that powered the first stage of the Saturn V launch vehicle for the Apollo missions • Early 1970s, SSC’s facilities were modified to test the space shuttle's main engines (SSMEs) • All the 405 flown engines supporting 135 shuttle flights tested and proven flight-worthy at SSC • SSC’s state-of-the-art facilities continues to assemble and test components and engines for future Space Launch System (SLS) missions (RS-25 and J-2X) • RS-68/A engines supporting the Delta IV program launching national security satellites and recently the Orion Capsule for NASA’s Exploration Flight Test-1 Aerojet Rocketdyne Proprietary 2 SSC Facilities Occupied by Aerojet Rocketdyne • A1 Test Stand– RS-25 (1st Stage booster for SLS) • Primary Customer – NASA • Aerojet Rocketdyne Test Article Contractor • B Test Stand • B1 - RS-68 (1st Stage booster for Delta-IV) • Primary Customer – Air Force (ULA) • Test Stand is operated under a Space Act Agreement • B2 (RS-25 Space Launch System Stage Testing) • B Complex Test Control Center (BTCC) • Engine Assembly Facility (EAF – Bldg. -
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. -
Round Trip to Orbit: Human Spaceflight Alternatives
Round Trip to Orbit: Human Spaceflight Alternatives August 1989 NTIS order #PB89-224661 Recommended Citation: U.S. Congress, Office of Technology Assessment, Round Trip to Orbit: Human Spaceflight Alternatives Special Report, OTA-ISC-419 (Washington, DC: U.S. Government Printing Office, August 1989). Library of Congress Catalog Card Number 89-600744 For sale by the Superintendent of Documents U.S. Government Printing Office, Washington, DC 20402-9325 (order form can be found in the back of this special report) Foreword In the 20 years since the first Apollo moon landing, the Nation has moved well beyond the Saturn 5 expendable launch vehicle that put men on the moon. First launched in 1981, the Space Shuttle, the world’s first partially reusable launch system, has made possible an array of space achievements, including the recovery and repair of ailing satellites, and shirtsleeve research in Spacelab. However, the tragic loss of the orbiter Challenger and its crew three and a half years ago reminded us that space travel also carries with it a high element of risk-both to spacecraft and to people. Continued human exploration and exploitation of space will depend on a fleet of versatile and reliable launch vehicles. As this special report points out, the United States can look forward to continued improvements in safety, reliability, and performance of the Shuttle system. Yet, early in the next century, the Nation will need a replacement for the Shuttle. To prepare for that eventuality, NASA and the Air Force have begun to explore the potential for advanced launch systems, such as the Advanced Manned Launch System and the National Aerospace Plane, which could revolutionize human access to space. -
Shuttle Fact Sheet
NASA Facts National Aeronautics and Space Administration Marshall Space Flight Center Huntsville, Alabama 35812 FS-2003-06-62-MSFC June 2003 Space Shuttle Propulsion Systems managed by the Marshall Space Flight Center The Space Shuttle is NASA’s reusable space vehicle designed for transport of people, spacecraft and equipment to and from Earth orbit. The propulsion elements of the Space Shuttle, including the Main Engine, External Tank and Solid Rocket Boosters that propel the Space Shuttle into orbit are managed at the Marshall Space Flight Center in Huntsville, Alabama. The Space Shuttle Main Engines number of flights between required overhauls. The Space The three Space Shuttle Main Engines are clustered Shuttle Main Engines are built by Rocketdyne Propulsion at the aft end of the orbiter and have a combined thrust and Power Division of the Boeing Company in Canoga of more than 1.2 million pounds (5.4 million newtons) Park, Calif. The engine turbopump is built by Pratt and at sea level. They are high performance, liquid propel- Whitney of West Palm Beach, Fla. The turbopumps are lant rocket engines whose thrust can be varied over made by Pratt and Whitney of West Palm Beach, Fla. a range of 65 to 109 percent of their rated The External Tank Low-Pressure power level. They are Oxidizer Oxidizer The External Tank the world’s first reus- Preburner Turbopump is a giant cylinder High-Pressure able rocket engines Main Injector container with a Oxidizer Turbopump and are 14 feet long Fuel rounded, or ogive, (4.3 meters) and 7.5 Preburner top -- higher than a Low-Pressure feet (2.3 meters) in Fuel Turbopump Hot Gas 15-story building, with diameter at the nozzle Manifold a length of 154 feet exit. -
The Evolution of Commercial Launch Vehicles
Fourth Quarter 2001 Quarterly Launch Report 8 The Evolution of Commercial Launch Vehicles INTRODUCTION LAUNCH VEHICLE ORIGINS On February 14, 1963, a Delta launch vehi- The initial development of launch vehicles cle placed the Syncom 1 communications was an arduous and expensive process that satellite into geosynchronous orbit (GEO). occurred simultaneously with military Thirty-five years later, another Delta weapons programs; launch vehicle and launched the Bonum 1 communications missile developers shared a large portion of satellite to GEO. Both launches originated the expenses and technology. The initial from Launch Complex 17, Pad B, at Cape generation of operational launch vehicles in Canaveral Air Force Station in Florida. both the United States and the Soviet Union Bonum 1 weighed 21 times as much as the was derived and developed from the oper- earlier Syncom 1 and the Delta launch vehicle ating country's military ballistic missile that carried it had a maximum geosynchro- programs. The Russian Soyuz launch vehicle nous transfer orbit (GTO) capacity 26.5 is a derivative of the first Soviet interconti- times greater than that of the earlier vehicle. nental ballistic missile (ICBM) and the NATO-designated SS-6 Sapwood. The Launch vehicle performance continues to United States' Atlas and Titan launch vehicles constantly improve, in large part to meet the were developed from U.S. Air Force's first demands of an increasing number of larger two ICBMs of the same names, while the satellites. Current vehicles are very likely to initial Delta (referred to in its earliest be changed from last year's versions and are versions as Thor Delta) was developed certainly not the same as ones from five from the Thor intermediate range ballistic years ago.