Browse Topic: Booster rocket engines

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Phase-Change Coating Absorbs Heat from Rockets, Pipes, and BeerTBMG-3544611/1/2019
Spinoff is NASA's annual publication featuring successfully commercialized NASA technology. This commercialization has contributed to the development of products and services in the fields of health and medicine, consumer goods, transportation, public safety, computer technology, and environmental resources.
Celebrating the 50th Anniversary of Apollo 11: Getting There, To a New Era of Space ExplorationTBMG-347457/1/2019
For the first time in a generation, NASA is building a human spacecraft for deep-space missions that will usher in a new era of space exploration. A series of increasingly challenging missions awaits, and this new spacecraft will take astronauts farther than they’ve gone before, including to the Moon and Mars.
Hermetic Seal Leak Detection Apparatus with Variable Size Test ChamberTBMG-249287/1/2016
NASA’s Marshall Space Flight Center has developed a unique apparatus ideal for use in nondestructive testing (NDT) of hermetic seals of containers or instrumentation. The device is capable of detecting both large and small leaks and can be calibrated to characterize the relative leak rate. Its simple design does not require specialized gases for pressurization and detection, and eliminates the need for expensive instrumentation such as a mass spectrometer to analyze leaks and achieve high sensitivity. Low in cost and simple to manufacture, the patent-pending technology is ideal for use in many industries, from aerospace applications to food packaging and commercial goods.
The Future of Exploration Starts With 3D PrintingTBMG-246595/1/2016
Last year, engineers at NASA’s Marshall Space Flight Center in Huntsville, AL, tested an additive manufacturing process that is being used to make some of the parts for NASA’s new rocket, the Space Launch System (SLS), more efficiently and affordably without compromising performance and safety. Selective laser melting (SLM) is a 3D printing process used to create complex parts for the engine and other components of the rocket. Four RS-25 engines and two solid rocket boosters will power the core stage of the SLS.
Aerodynamics Model for a Solid Rocket BoosterTBMG-224167/1/2015
NASA required an aerodynamics model of a spent solid rocket booster (SRB) to predict trajectory and impact location of the Ares I first stage after separation. The software needed to be integrated into new simulations written in C. Marshall Space Flight Center (MSFC) had previously developed a solid rocket booster re-entry simulation for the Space Transportation System (the Space Shuttle). The simulation was written in Fortran, and the aerodynamics model was embedded in a single function with other parts of the flight dynamics model. It could not be extracted easily for reuse in another simulation.
Cameras Provide Critical Data for NASA Rocket’s First FlightTBMG-222646/1/2015
On March 11, NASA tested the powerful five-segment booster for NASA’s new rocket, the Space Launch System. To provide critical data for the rocket’s first flight, eight cameras with more than 40 different settings — including varying exposures — were set up near the forward portion of the booster. During the two-minute test, the cameras were computer-controlled and cycled through pre-programmed settings.
Hovercraft Landing SystemTBMG-2070910/1/2014
A concept for recovering reusable spacecraft or capsules, or reusable rocket boosters, has them land on an airbag-based, cushioned platform positioned on a highly maneuverable hovercraft. This landing method would have performance advantages over conventional approaches to reusability by placing most of the landing function on the hovercraft while maintaining the safety benefit of an open ocean landing away from populated areas; however, it would be similar to a dry landing as the spacecraft or booster would not enter the water.
The Semantic Web and Space Operations2011-01-250610/18/2011
In this paper, we introduce the use of ontologies to implement the information developed and organized by resource planning tools into standard project management documents covering integrated cost, resource modeling and analysis, and visualization. The basic upper ontology used for NASA Space Operations is explained and the results obtained are discussed. This ontology-centered approach is looking for tighter connections between software, hardware, and systems engineering.
Rabelo, Luis, Marin, Mario, Fishwick PhD, Paul, Ezzell, Zach
NASA Announces New Launch SystemTBMG-112259/14/2011
Today, NASA announced the new Space Launch System (SLS), an advanced heavy-lift launch vehicle that will provide an entirely new national capability for human exploration beyond Earth's orbit.
The Art and Science of Systems Engineering Tightly Coupled Programs2010-01-232110/19/2010
This paper discusses the fundamentals of architecting a major human spaceflight program and some of the lessons that can be learned from NASA's Constellation Program. This paper describes the Constellation program, whose primary objective focuses on development of a new generation of vehicles and systems to enable human exploration beyond Earth orbit. Constellation is made up of seven projects that are highly interdependent and is referred to in the NASA management system as a “tightly coupled” program. This paper will discuss the driving architectural priorities and characteristics for human exploration missions beyond earth orbit and how its building blocks are developed through initial capability missions to the International Space Station. The systems engineering challenges of simultaneously defining and developing systems that are interdependent will be discussed.
Muirhead, Brian K., Thomas, Dale
Data Mining and Complex Problems: Case Study in Composite Materials2009-01-318211/10/2009
Data mining is defined as the discovery of useful, possibly unexpected, patterns and relationships in data using statistical and non-statistical techniques in order to develop schemes for decision and policy making. Data mining can be used to discover the sources and causes of problems in complex systems. In addition, data mining can support simulation strategies by finding the different constants and parameters to be used in the development of simulation models. This paper introduces a framework for data mining and its application to complex problems. To further explain some of the concepts outlined in this paper, the potential application to the NASA Shuttle Reinforced Carbon-Carbon structures and genetic programming is used as an illustration.
Rabelo, Luis, Marin, Mario, Huddleston, Lisa
Prediction of Launch Vehicle Ignition Overpressure and Liftoff AcousticsTBMG-56869/1/2009
The LAIOP (Launch Vehicle Ignition Overpressure and Liftoff Acoustic Environments) program predicts the external pressure environment generated during liftoff for a large variety of rocket types. These environments include ignition overpressure, produced by the rapid acceleration of exhaust gases during rocket-engine start transient, and launch acoustics, produced by turbulence in the rocket plume. The ignition overpressure predictions are time-based, and the launch acoustic predictions are frequency-based. Add itionally, the software can predict ignition overpressure mitigation, using water-spray injection into the rocket exhaust stream, for a limited number of configurations.
Laser Tracker Ensures Accurate Alignment of Ares I ComponentsTBMG-54527/1/2009
FARO® Laser Tracker FARO Technologies Lake Mary, FL 800-736-0234 www.faro.com
The Future of Space PropulsionTBMG-489410/1/2008
Significant challenges and advances in space propulsion have occurred over the past ten years. The end of the Cold War had significant impacts, both positive and negative. Operational systems now have to operate well beyond their design life. Parts and technology obsolescence are having a significant impact, as are an aging workforce and limited opportunities to develop new systems. The advent of asymmetric warfare is fully upon us. The military has to pro - ject power anywhere on the globe. In addition, there is concern that U.S. space assets are vulnerable in this new world. Furthermore, changes in acquisition policy driven by incredible cost and schedule overruns on nearly every space acquisition program will have significant impacts on the future of propulsion.
The First Development of Human Factors Engineering Requirements for Application to Ground Task Design for a NASA Flight Program2008-01-21036/29/2008
The National Aeronautics and Space Administration has long applied standards-derived human engineering requirements to the development of hardware and software for use by astronauts while in flight. The most important source of these requirements has been NASA-STD-3000. While there have been several ground systems human engineering requirements documents, none has been applicable to the flight system as handled at NASA's launch facility at Kennedy Space Center. At the time of the development of previous human launch systems, there were other considerations that were deemed more important than developing worksites for ground crews; e.g., hardware development schedule and vehicle performance. However, experience with these systems has shown that failure to design for ground tasks has resulted in launch schedule delays, ground operations that are more costly than they might be, and threats to flight safety. As the Agency begins the development of new systems to return humans to the moon, the new Constellation Program is addressing this issue with a new set of human engineering requirements. Among these requirements is a subset that will apply to the design of the flight components and that is intended to assure ground crew success in vehicle assembly and maintenance tasks. These requirements address worksite design for usability and for ground crew safety.
Dischinger, H. Charles, Stambolian, Damon B., Miller, Darcy H.
Explaining Space Project Failures2008-01-21556/29/2008
Space projects are spectacular, costly, and highly visible. Their occasional failures receive extensive analysis and explanation. This paper reviews studies of failures of crewed and uncrewed missions. The explanations of these space project failures include simple oversight errors, poor project management, complex combinations of unforeseen events, and conceptual flaws that prohibited success. Failures are usually found to be caused by project management errors, based on the reasoning that the project manager and team members had the capability and responsibility to avoid them. These failure causes are well known. Why do so many projects make the same mistakes?
Jones, Harry
Simulated Models Test Design of Space Shuttles and Rocket EnginesTBMG-28115/1/2008
Finite element modeling and analysis Dynamic Concepts Huntsville, AL 256-922-9888 www.dynamic-concepts.com
The Multiplier Effect2007-01-30667/9/2007
As a school teacher, I immersed myself into NASA's Johnson Space Center world and in this paper I document my experiences with scientists, engineers, astronauts, trainers, flight directors, educators, doctors, researchers, chemists, public affairs personnel, managers, college co-ops, and other professionals. I describe how my experiences can be used as a model for bridging NASA and school communities.
Forman, Kenneth S.
Thrust-Augmented Nozzles for Rocket EnginesTBMG-45532/1/2007
The thrust-augmented nozzle (TAN) has been invented as a means of obtaining high performance from a rocket engine both during liftoff at sea-level atmospheric pressure and later during flight under near-vacuum conditions. In effect, the TAN rocket engine amounts to a booster rocket engine contained entirely within a sustainer rocket engine, and very little weight is associated with the incorporation of the TAN portion. Heretofore, it has been difficult or impossible to design the same rocket engine to perform well at both extremes of ambient pressure.
Evaluation of Coatings and Materials for Future Radiators2006-01-20327/17/2006
NASA's current vision for exploration dictates that radiators for a Crew Exploration Vehicle (CEV), a Lunar Surface Access Module (LSAM), and a lunar base will need to be developed. These applications present new challenges when compared to previous radiators on the Space Shuttle and International Space Station (ISS). In addition, many technological advances have been made that could positively impact future radiator design. This paper outlines new requirements for future radiators and documents a trade study performed to select some promising technologies for further evaluation. These technologies include carbon composites substrates as well as Optical Solar Reflectors (OSRs), a lithium based white paint, and electrochromic thin films for optical coatings.
Tuan, George C., Westheimer, David T., Birur, Gajanana C., Beach, Duane E., Jaworske, Donald A., Peters, Wanda C., Triolo, Jack J.
Simulation of Dropping of Cargo With ParachutesTBMG-16885/1/2006
Decelerator System Simulation (DSS) is a computer program for predicting and analyzing the dynamics of a load of cargo dropped with parachutes from an aircraft. A DSS simulation runs from the first motion in the aircraft until the payload reaches the ground. Intended for use in support of airdrop tests for the X- 38 program, DSS was developed by modifying and augmenting an older program, denoted UD233A, used for simulating the dynamics of a space-shuttle solid rocket booster falling with a parachute. The main effort in converting UD233A into DSS involved development of computational models for simulating the inflation of one or more parachute( s), the dynamics of the payload and the slings connecting the parachute( s) with the payload, and the extraction of the payload and parachutes from the aircraft.
On the Development of a Comprehensive Hazard Modeling Tool through Distributed Simulation: Learning from the Columbia Space Shuttle Accident2005-01-336810/3/2005
The tragic loss of the space shuttle Columbia on February 1, 2003 during its reentry phase raised legitimate concerns on the safety of the public on the ground associated with the operation of launch vehicles. Although there was no human casualty reported, the outcome of this accident could have been much different. In this paper, we investigate the use of distributed simulation and information fusion to better predict the effects, in terms of expectations of casualties (EC), of the different hazards produced by an accidental or instructed loss of such a vehicle. A prototype is described.
Sala-Diakanda, Serge N., Rabelo, Luis C., Sepúlveda, José A.
A Distributed Environment for Spaceports2004-01-309411/2/2004
This paper describes the development of a distributed environment for spaceport simulation modeling. This distributed environment is the result of the applications of the High-Level Architecture (HLA) and integration frameworks based on software agents and XML. This distributed environment is called the Virtual Test Bed (VTB). A distributed environment is needed due to the nature of the different models needed to represent a spaceport. This paper provides two case studies: one related to the translation of a model from its native environment and the other one related to the integration of real-time weather.
Rabelo, Luis, Sepulveda, Jose, Marin, Mario, Park, Jaebok
Airborne Multichannel Swept-Tuned Spectrum AnalyzerTBMG-69319/1/2000
Two airborne spectrum analyzers were developed for acquiring dynamic data, characterized by frequencies up to 25 kHz, from a hypersonic-crossflow-transition experiment aboard the air-launched Pegasus® space booster rocket (see Figure 1). Real-time transmission of time histories of the dynamic data via a pulse-code modulation (PCM) telemetry encoder would have required sample rates of at least 50,000 s -1. The telemetry bandwidth necessary to support rates as high as this was not available; however, conversion of the data to the frequency domain aboard the rocket would make it possible to trade frequency resolution for a reduction in telemetry bandwidth. The two airborne spectrum analyzers implement this type of conversion. One spectrum analyzer is based on a swept-tuned receiver; the other is based on digital signal processing technology. The remainder of this article describes the swept-tuned spectrum analyzer.
Durability Studies on the F-15B Flight-Test FixtureTBMG-299127/1/1999
NASA's F-15B #836 is a two-seat version of the F-15, which is a high-performance, supersonic, all-weather fighter airplane. The F-15B is used as a test-bed aircraft for a wide variety of flight experiments. In support of this use, a flight-test fixture (FTF) (see Figure 1) was developed to provide a space for flight experiments in a region with known aerodynamic conditions.
Ariane 5 Lightning Verification Plan1999-01-23346/22/1999
The ARIANE 5 launcher shall withstand an on-ground direct lightning stroke of 5 kA or an indirect stroke of 200 kA arising on its launch pad protection system. The definition of indirect effects protections has been performed on the basis of a simplified modelisation of electromagnetic coupling. The lightning qualification has been achieved by both theoretical analysis, based on a very accurate modelisation, and various tests performed at unit and subassembly levels. This process has shown that global compatibility is ensured.
Gobin, V., Bertuol, S.
Automation of the Space Shuttle Solid Rocket Motor Assembly Process9722346/3/1997
The Space Shuttle's Solid Rocket Motor (SRM) processing equipment for motor assembly at NASA's John F. Kennedy Space Center, was designed in the mid 1980's. Consequently, the data acquisition systems (DAS) and associated processors are obsolete and unreliable. The SRM Stacking Enhancement Tool (SSET) project was initiated to update and automate the motor assembly process. The SSET project is replacing the existing segment processing data acquisition panels and incorporating the Segment Shape Prediction Program (SSPP) into a single panel providing updated processors and an intuitive “smart” graphical user interface with the capability of recording all data. The SSET project is also providing a Calibration Confirmation Control System (CCCS) that will electronically retain the instruments calibration information with the instrument.
Henderson, Paul G., Bradley, Andy J.
Spearheading Machining Technology for Aerospace9722266/3/1997
The aerospace industry is faced with ever more demands on quality, variety and complexity of their products. The spectrum of part materials certainly encompasses a much wider range than any industrial manufacturing while the cost of parts and components by design, function and machining are highest, too. Hence aerospace manufacturing's perpetual quest for new, advanced machining processes that: yield predictable, consistent results. lower the machining cost per part. decrease main machining times. increase flexibility and adaptability. improve produced quality. minimize operations. The three advanced processes that can accommodate these demands best are one-pass finish-machining, (near) dry-machining and high-speed machining. ONE-PASS FINISH-MACHINING - The key is to finish-machine given part castings with one operation at high precision, instead of step by step machining. The one-pass approach is to include even complicated part configurations and contours. Foregoing premachining and post-machining processes, dramatically lowers manufacturing cost and markedly increases productivity. HIGH-SPEED MACHINING - Geared toward shortening main machining times and minimizing non-cutting times, high-speed machining is very promising. However, it is not just a matter of revving up machine spindle speeds, but to design cutting tools and tooling interfaces that as a whole system secure productivity and precision machining. (NEAR) DRY-MACHINING - A study by Daimler Benz revealed that up to 16% of overall production cost is related to the use of cutting fluids. Cost considerations and OSHA requirements spur efforts to implement (near) dry-machining processes. New technical developments are quite encouraging.
Erdel, Bert P.
Shunt Filter Design for a DC Resonant Link Based Vector Controlled Induction Motor Drive9514265/1/1995
This paper considers the performance of a resonant dc link based vector controlled induction motor drive to be used in aerospace applications. In particular, it was found that resonant dc link based drives may suffer from unacceptably large current ripple when being used with extremely high speed machines. A filter design and alternate control algorithm are set forth which alleviate the current ripple concern while at the same time ensuring ideal steady-state performance.
Sudhoff, Scott, Schreiner, Ken
Automatic Fastening of Space Vehicle Subassemblies94183910/1/1994
Space launch vehicles offer some unique challenges to automatic riveting. In most cases the assemblies are only used once and have one chance to perform. This requires a high degree of reliability for each assembly. The equipment used must be capable of producing high quality fastener installations. The automatic riveting machine used at the Harlingen Facility of Martin-Marietta Aeronautics Group meets this challenge. This paper describes the equipment, tooling, and controller used to automatically fasten the subassemblies of the Payload Fairing (lower cone and cylinder), Interstage Adapter and Thrust Cylinder of the Atlas/Centaur space vehicle. It will discuss the unique features of the automatic riveting machine and the tooling required to fasten the individual subassemblies. It will discuss the tooling requirements for the individual subassemblies and their part positioner requirements.
Stiles, Oscar B., Clifton, James E.
Computer and Experimental Simulation of Fluid Flow Through Varying-Constricted Tubes9400193/1/1994
Flow fields in the neighbourhood of constrictions in a tube were studied numerically. Flow seperation and reattachment as the flow passes through the constrictions in the tube were studied for Reynolds number to the order of 200. Constrictions with constriction spacing ratios of 1, 2, 3 and ∞ were studied for diameter constriction ratios of 0.2 to 0.6. Experimental flow visualizations were performed for similar double constrictions.
Lee, T. S., Low, H. T.
Computer Simulation of a 20-kHz Power System for Advanced Launch Systems9314254/1/1993
The performance of two 20-kHz actuator power systems being built for an advanced launch system are evaluated for a typical launch scenario using an end-to-end system simulation. Aspects of system performance ranging from the switching of the power electronic devices to the vehicle aerodynamics are represented in the simulation. It is shown that both systems adequately stabilize the vehicle against a wind gust during a launch. However, it is also shown that in both cases there are bus voltage and current fluctuations which make system power quality a concern.
Kenny, B. H., Sudhoff, S. D., Wasynczuk, O., Krause, P. C.
Computer Simulation of a Resonant DC Link for Advanced Launch Systems9314244/1/1993
The performance of a resonant dc link based actuator power system being built for an advanced launch system application is evaluated for a typical launch scenario using two end-to-end system simulations, one using a digital computer and the other using a hybrid computer. Aspects of system performance from the switching of the power electronic devices to the vehicle aerodynamics are addressed. Using these simulations, it is shown that the resonant dc link actuator adequately stabilize the vehicle against a wind gust during a launch.
Sudhoff, S.D., Wasynczuk, O., Krause, P.C.
Rocket Propulsion Experimental Facilities at the Phillips Laboratory, Edwards Air Force Base, California9314464/1/1993
The Phillips Laboratory has extensive rocket propulsion facilities at Edwards Air Force Base, California. These facilities range from small scale cells capable of firing liquid rocket engines as small as 0.01 lbf (0.04 Newtons (N)) thrust up to very large liquid/solid test stands designed for firings up to 10 million lbf (44.5 million N) thrust. This paper gives a review of the variety and capabilities of the numerous facilities at Edwards Air Force Base, as well as an overview of current projects. Emphasis is placed on the general capabilities of these facilities; specifics are available upon request to the author. Trends in the evolution of rocket test facilities are discussed.
Beckmann, Joel W., Kalliomaa, Wayne M.
An Electromechanical Actuation System for an Expendable Launch Vehicle9291128/3/1992
A major effort at the NASA Lewis Research Center in recent years has been to develop electromechanical actuators (EMA's) to replace the hydraulic systems used for thrust vector control (TVC) on launch vehicles. This is an attempt to overcome the inherent inefficiencies and costs associated with the existing hydraulic structures. General Dynamics Space Systems Division, under contract to NASA Lewis, is developing 18.6 kW (25 hp), 29.8 kW (40 hp), and 52.2 kW (70 hp) peak EMA systems to meet the power demands for TVC on a family of vehicles developed for the National Launch System. These systems utilize a pulse population modulated converter and field-oriented control scheme to obtain independent control of both the voltage and frequency. These techniques allow an induction motor to be operated at its maximum torque at all times. At NASA Lewis, we are building on this technology to develop our own in-house system capable of meeting the peak power requirements for an expendable launch vehicle (ELV) such as the Atlas. Our EMA will be capable of delivering 22.4 kW (30 hp) peak power with a nominal of 6.0 kW (8 hp). This system differs from the previous ones in two areas: 1) the use of advanced control methods, and 2) the incorporation of built-in-test. The advanced controls are essential for minimizing the controller size, while the built-in-test is necessary to enhance the system reliability and vehicle health monitoring. The ultimate goal of this program is to demonstrate an EMA which will be capable of self-test and easy integration into other projects. This paper will describe the effort underway at NASA Lewis to develop an EMA for an Atlas class ELV. An explanation will be given for each major technology block, and the status of the overall program will be reported.
Burrows, Linda M., Roth, Mary Ellen
Electromechanical Systems with Transient High Power Response Operating from a Resonant AC Link9291138/3/1992
The combination of an inherently robust asynchronous (induction) electrical machine with the rapid control of energy provided by a high frequency resonant ac link enables the efficient management of higher power levels with greater versatility. This could have a variety of applications from launch vehicles to all-electric automobiles. These types of systems utilize a machine which is operated by independent control of both the voltage and frequency. This is made possible by using an indirect field-oriented control method which allows instantaneous torque control in all four operating quadrants. Incorporating the ac link allows the converter in these systems to switch at the zero crossing of every half cycle of the ac waveform. This “zero loss” switching of the link allows rapid energy variations to be achieved without the usual frequency proportional switching loss. Several field-oriented control systems have been developed by NASA Lewis and General Dynamics Space Systems Division under contract to NASA. This paper will begin with a description of a single motor, electromechanical actuation system and then focus on a conceptual design for an AC electric vehicle. This design will incorporate an induction motor/generator together with a flywheel for peak energy storage. System operation and implications along with the associated circuitry will be addressed. Such a system would greatly improve all-electric vehicle ranges over the Federal Urban Driving Cycle (FUD).
Burrows, Linda M., Hansen, Irving G.
EB Welding of Launch Vehicles9121319/1/1991
The Electron Beam (EB) welding process has gained widespread acceptance in the aerospace industry as an efficient, precise, high quality joining process. Because its optimum performance is realized in a vacuum environment, its use has been limited to welding of fairly small components, where Xray quality, high strength welds are required with minimal part distortion. Larger components can be welded; however, the equipment and operating costs increase with the correspondingly larger vaccum chambers used to house the parts to be welded.
Szabo, Attila
Assessment of Aerospace Technology in Japan Viewed from an American Perspective9119689/1/1991
This is an assessment of Aerospace Technology in Japan, the national vision supporting it and the strategy underlies it's ultimate purpose. It includes a comparison of the organizations and missions of the two principle aerospace agencies: One, the Institute of Space and Astronautical Science (ISAS); and, two, the National Space Development Agency (NASDA). Included are the launch capabilities and deep space facilities of ISAS, at Kagoshima Space Center (KSC) in Uchinoura on Kyushu island; and the NASDA Tanegashima Space Center (TSC) on Tanegashima Island. Also included are the design and development history of domestic Nippon launch and space vehicles, beginning with the licensing of the United States Thor-Delta rocket technology and including the design of the domestic H-I second and third stages and the all domestic H-II vehicles. Included in this essay are overviews of H-I and H-II launch vehicles during assembly at the Oye and Oye West Plants of Nagoya Aircraft Works, Mitsubishi Heavy Industries. ISAS and NASDA have placed more than 40 satellites in orbit since the start of the Japanese space program.
Wyczalek, Floyd A.
Space Shuttle Launch Pad Rescue Plan9115697/1/1991
The final preparation of the Space Shuttle Orbiter for flight involves the loading of large quantities of hazardous propellants. Additionally, many pyrotechnically operated mechanical joints are armed and ready for flight. The personnel manning at the pad is minimized during these operations to reduce the risk. Upon completition of propellant loading, the flight crew must be boarded onto the vehicle which at this point has tremendous potential energy. Plans have been made to safely and quickly evacuate the crew should some unforeseen contigency occur. Both aided and unaided egress scenarios have been planned. Personnel protective equipment is an important consideration to assure the highest chance for survival. Rapid movement of personnel is enhanced by the use of the slidewire system and specially prepared armored personnel carriers. The end result, as will be discussed in this paper, is a system that provides a reasonable chance of survival should an emergency occur during late countdown at the pad.
Doerr, Donald F.
Detecting Entrapped Plastic Blast Media Through the Use of Fluorescent Media9009624/1/1990
The use of Plastic Media Blasting (PMB) for the removal of organic coatings is increasing. This method has many advantages over chemical stripping and other conventional organic media, but the user should be aware that the media could become embedded in cracks, defects, seams, and joints. To address media embedment, a fluorescent media has been developed and patented. Data will be presented concerning the ability of the fluorescent media to detect crack defects.
Zook, Lee M., Novak, Howard L.
Plastic Media Blasting an Alternative for Coating Removal8909174/1/1989
Plastic Media Blasting (“PMB”) is a revolutionary method for the rapid and safe removal of primer, paint and even powder and other chemically resistant coatings from a vast range of products without the use of toxic chemicals or pneumatic blasting with hard abrasives. Although resembling sandblasting, PMB does not use the hard abrasives or high pressures of that process. Instead, PMB uses reusable-plastic particles which are applied at pressures of 20 to 40 psi. The unique abrasive blast media not only replaces potentially hazardous abrasives such as silica sand, but since it is reusable it also generates less overall waste material.
Abbott, Kenneth E.
Using Shuttle-C for Space Station Freedom Assembly88154610/1/1988
The transition from the current Shuttle Space Transportation System (STS) payload delivery capability to an advanced launch system has been the topic of several studies and proposals. The need for an early, reliable, low cost heavy lift vehicle has been identified and supported by NASA as a response to that need. This paper will provide a brief background and description of the Shuttle-C, and will primarily focus on cargo bay sizing and manifesting for one of the three identified design reference missions: Space Station Freedom assembly.
McCormick, Robert, Yetter, Bret
HOTOL: An Advanced European Space Transporter8713447/1/1987
The origins of the HOTOL Project and its primary design objectives, aimed at reducing satellite launch costs, are defined. Primary structural, aerodynamics and systems design features are described. Operational procedures are explained and support facilities illustrated. A possible future development programme is outlined.
Burns, B.R.A.
Thermal Protection: The Process of Gas Injection Molding86175310/1/1986
Gas Injection Molding (GIM) is a process by which External Tank (ET) components receive Super Light Ablator (SLA) through pressurized injection of ablator into a vented mold assembly. Component surfaces are cleaned and coated with a silicone primer. Each part is transferred to the adhesive work station where a pre-mixed batch of adhesive is obtained and applied to the primer substrate in a smooth continuous coating. After injection is complete, the mold is processed through a heat cycle, the panel representative of the component is scrutinized for acceptable density and tensile strength values. The component is inspected for dimensional tolerances and visual inspection is performed.
Moffett, James L.
MOVER II - A Computer Program for Verifying Reduced-Order Models of Large Dynamic Systems86179010/1/1986
This paper introduces a computer code for model verification of linear dynamic systems. Presentation is made within the broader context of system identification, and the many alternatives available for implementing a code. Practical considerations of the system identification process are discussed first. Alternative methods are reviewed and a classification system for existing as well as nonexisting methods is proposed. Finally, a rationale for the selection of a particular modeling approach, type of measurement data, and estimation algorithm is discussed. Although MOVER II was not specifically designed for large space structures, its capabilities fulfill many of the needs now recognized as important in the verification of reduced-order models. Prior application involving extensive use of substructuring and coordinate reduction is discussed.
Chrostowski, J. D., Hasselman, T. K.
Recent Shuttle EVA Operations and Experience8513287/1/1985
This paper describes the hardware used and the experience gained during the Space Shuttle extravehicular activities (EVAs) or “spacewalks” of 1984. Seven EVAs on four missions were conducted with objectives including hardware verification, satellite repair, hydrazine transfer, and satellite retrieval. The hardware used on these flights falls into two categories - general EVA hardware (e.g. the Manned Maneuvering Unit) and mission-unique hardware (e.g. apogee kick motor capture device, used to retrieve the WESTAR VI and PALAPA B-2 satellites). The successful completion of the mission objectives resulted in an increased knowledge of EVA operations and a broader base of Space Shuttle capabilities which are applicable to future operations.
Rogers, Leslie J. A., Whitsett, C. Ed, Rodriguez, Manuel
Federal Funding For Transportation Safety8512266/1/1985
Federal regulations promoting safety in transportation have existed for more than 100 years, but federal spending supporting research, standard setting, enforcement and capital programs are modern phenomena. Before the 1966 highway and motor carrier safety Acts, federal safety spending was less than $700, 000 a year, and largely confined to aviation and marine modes where there was federal responsibility for certain transport operations. Federal spending for safety programs is now around $3 billion a year, and predominantly for highway and motor vehicle programs. Around $200 million a year is spent on rulemaking and enforcement in each of road, air and water modes, with about one-tenth of that on rail safety. But federal responsibilities vis-avis state and private transport interests differ so that modal comparisons of spending will not reflect overall spending or relative priorities for safety issues amongst modes.
Wishart, Jenifer
Advanced Launch Vehicles84162310/1/1984
Vehicles capable of lifting very large and heavy payloads into low earth orbit (LEO) will be needed to support certain large-scale space missions being considered for the late 1990-2000 time period. These missions include the support of strategic national commitments, large space power systems, and interplanetary and lunar exploration. Nearer term missions will utilize the Space Shuttle and its direct derivatives, the Shuttle-Derived Vehicles (SDV), currently being defined under NASA and DOD sponsored studies. A conceptual design of a Heavy Lift Launch Vehicle (HLLV) that will lift a half million pounds to low earth orbit is presented. Design alternatives and key system design problems and issues are discussed. The new developments required, such as a new large liquid booster engine and Space Shuttle Main Engine (SSME) modifications, are identified. New candidate launch locations and launch facility requirements are also discussed. The commonality and utilization of the booster stage “elements” as a liquid booster for a “growth” Space Shuttle are conceptually defined.
Marshall, William R., Shelton, Billy W.
Steel, Maraging, Sheet, Strip, and Plate, 18Ni - 7.8Co - 4.9Mo - 0.40Ti - 0.10Al, Consumable Electrode Melted, Solution Heat TreatedAMS6520A (Historical)4/1/1982
This specification covers a premium aircraft-quality, maraging steel in the form of sheet, strip, and plate. These products have been used typically for large booster rocket applications, pressure vessels, and other components requiring through-hardening, without quenching, to a yield strength of 245 ksi (1689 MPa) or higher, but usage is not limited to such applications.
AMS E Carbon and Low Alloy Steels Committee
The Space Transportation Company Inc.8213682/1/1982
The Space Transportation Company Inc. was formed in 1979 to seek private funding for a fifth space shuttle. In early 1982, the Company made a formal proposal to NASA to acquire the fifth Orbiter and indicated that funding for this acquisition was available. This presentation will discuss the current organization of The Space Transportation Company, its relationship with NASA, and the funding arrangements it has in place to carry out its intended plans.
Stear, Adrian N.
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