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May 29, 2011
05/11
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Klipstein, W. M.; Thompson, R. J.; Seidel, D. J.; Kohel, J.; Maleki, L
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The Time and Frequency Sciences and Technology Group at Jet Propulsion Laboratory (JPL) has developed a laser cooling capability for flight and has been selected by NASA to support the Laser-Cooling and Atomic Physics (LCAP) program. Current work in the group includes design and development for tee two laser-cooled atomic clock experiments which have been selected for flight on the International Space Station.
Topics: CLOCKS, SKEWNESS, ACCURACY, MODULES, HIGH SPEED, COMPUTERS, X-33 REUSABLE LAUNCH VEHICLE
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May 31, 2011
05/11
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Queen, Eric M.; Striepe, Scott A.; Powell, Richard W
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A ''Monte Carlo-like'' design analysis tool is developed and applied to an aeromaneuvering Mars entry vehicle. This tool provides realistic but challenging design cases using many fewer cases than a full Monte Carlo analysis. The problem of random input variables that are provided a priori (as opposed to being drawn from a given distribution) is addressed and a solution is found that shows prospects for future improvement.
Topics: AEROSPIKE ENGINES, PLUMES, X-33 REUSABLE LAUNCH VEHICLE, HEAT FLUX, SEA LEVEL, THRUST
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Jun 2, 2011
06/11
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Prinzel, Lawrence J., III; Arthur, Jarvis J., III; Kramer, Lynda J.; Bailey, Randall E
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Eight 757 commercial airline captains flew 22 approaches using the Reno Sparks 16R Visual Arrival under simulated Category I conditions. Approaches were flown using a head-down synthetic vision display to evaluate four tunnel (''minimal'', ''box'', ''dynamic pathway'', ''dynamic crow s feet'') and three guidance (''ball'', ''tadpole'', ''follow-me aircraft'') concepts and compare their efficacy to a baseline condition (i.e., no tunnel, ball guidance). The results showed that the tunnel concepts...
Topics: AEROTHERMODYNAMICS, X-33 REUSABLE LAUNCH VEHICLE, COMPUTATIONAL FLUID DYNAMICS, THERMAL PROTECTION,...
In response to the Cooperative Agreement, Lockheed Martin Skunk Works has compiled an Annual Performance Report of the X-33/RLV Program. This report consists of individual reports from all industry team members, as well as NASA team centers. The first milestone was hand delivered to NASA MSFC. The second year has been one of significant accomplishment in which team members have demonstrated their ability to meet vital benchmarks while continuing on the technical adventure of the 20th century.
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, REUSABLE SPACECRAFT,...
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May 30, 2011
05/11
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Pfister, Robin; Ullman, Richard; Wichmann, Keit
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Over the past decade NASA has designed, built, evolved, and operated the Earth Observing System Data and Information System (EOSDIS) Information Management System (IMS) in order to provide user access to NASA's Earth Science data holdings. During this time revolutionary advances in technology have driven changes in NASA's approach to providing an IMS service. This paper will describe NASA's strategic planning and approach to build and evolve the EOSDIS IMS and to serve the evolving needs of...
Topics: THERMOGRAPHY, VOIDS, JOINTS (JUNCTIONS), INFRARED INSPECTION, NONDESTRUCTIVE TESTS, X-33 REUSABLE...
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487
May 29, 2011
05/11
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Rubincam, David Parr
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Bell's theorem can be proved through simple geometrical reasoning, without the need for the Psi function, probability distributions, or calculus. The proof is based on N. David Mermin's explication of the Einstein-Podolsky-Rosen-Bohm experiment, which involves Stern-Gerlach detectors which flash red or green lights when detecting spin-up or spin-down. The statistics of local hidden variable theories for this experiment can be arranged in colored strips from which simple inequalities can be...
Topics: X-33 REUSABLE LAUNCH VEHICLE, REUSABLE SPACECRAFT, VENTURESTAR LAUNCH VEHICLE, LAUNCHING SITES,...
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May 31, 2011
05/11
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Arthun, Daniel; Schachner, Christia
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The spinning rocket simulator (SRS) is an ongoing project at Oral Roberts University. The goal of the SRS is to gather crucial data concerning a spinning rocket under thrust for the purpose of analysis and correction of the coning motion experienced by this type of spacecraft maneuver. The computer animation simulates a virtual, scale model of the component of the SRS that represents the spacecraft itself. This component is known as the (VSM), or virtual spacecraft model. During actual physical...
Topics: COMPUTERIZED SIMULATION, MONTE CARLO METHOD, COMPUTER PROGRAMS, SOFTWARE DEVELOPMENT TOOLS,...
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154
May 31, 2011
05/11
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Sauvageau, Donald R
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As part of the continuing effort to identify approaches to improve the safety and reliability of the Space Shuttle system, a Five-Segment Booster (FSB) design was conceptualized as a replacement for the current Space Shuttle boosters. The FSB offers a simple, unique approach to improve astronaut safety and increase performance margin. To determine the feasibility of the FSB, a Phase A study effort was sponsored by NASA and directed by the Marshall Space Flight Center. This study was initiated...
Topics: BOLTS, X-33 REUSABLE LAUNCH VEHICLE, DEBONDING (MATERIALS), DEFECTS, JOINTS (JUNCTIONS), SANDWICH...
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Jun 2, 2011
06/11
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Airiau, Stephane; Wolpert, David H
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Product Distribution (PD) theory is a new framework for doing distributed adaptive control of a multiagent system (MAS). We introduce the technique of ''coordinate transformations'' in PD theory gradient descent. These transformations selectively couple a few agents with each other into ''meta-agents''. Intuitively, this can be viewed as a generalization of forming binding contracts between those agents. Doing this sacrifices a bit of the distributed nature of the MAS, in that there must now be...
Topics: AEROTHERMODYNAMICS, PROTUBERANCES, THERMAL PROTECTION, CONSTRUCTION, ELEVONS, HEAT TRANSFER, X-33...
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May 27, 2011
05/11
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Han, Samuel S
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An RBCC engine combines air breathing and rocket engines into a single engine to increase the specific impulse over an entire flight trajectory. Considerable research pertaining to RBCC propulsion was performed during the 1960's and these engines were revisited recently as a candidate propulsion system for either a single-stage-to-orbit (SSTO) or two-stage-to-orbit (TSTO) launch vehicle. There are a variety of RBCC configurations that had been evaluated and new designs are currently under...
Topics: WIND TUNNEL TESTS, DESIGN ANALYSIS, X-33 REUSABLE LAUNCH VEHICLE, PREDICTION ANALYSIS TECHNIQUES,...
This viewgraph presentation gives an overview of the X-33 program update, including details on program objectives and plans, the X-33 configuration, technologies used, and X-33 assembly and test status.
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, PROJECT PLANNING, ASSEMBLING,...
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462
May 29, 2011
05/11
by
NON
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This report summarizes the management of the National General Aviation Design Competition on behalf of NASA, the FAA and the Air Force by the Virginia Space Grant Consortium (VSGC) for the time period October 1, 1999 through September 30, 2000. This was the VSGC's sixth year of managing the Competition, which the Consortium originally designed, developed and implemented for NASA and the FAA. The seventh year of the Competition was announced in July 2000. Awards to winning university teams were...
Topics: WIND TUNNEL TESTS, AERODYNAMIC DRAG, BASE FLOW, DRAG REDUCTION, X-33 REUSABLE LAUNCH VEHICLE,...
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146
May 29, 2011
05/11
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Gray, Andrew; Srinivasan, Meera; Simon, Marvin; Yan, Tsun-Ye
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An all-digital high data rate parallel receiver architecture developed jointly by Goddard Space Flight Center and the Jet Propulsion Laboratory is presented. This receiver utilizes only a small number of high speed components along with a majority of lower speed components operating in a parallel frequency domain structure implementable in CMOS, and can currently process up to 600 Mbps with standard QPSK modulation. Performance results for this receiver for bandwidth efficient QPSK modulation...
Topics: REUSABLE LAUNCH VEHICLES, EIGENVALUES, OPTIMAL CONTROL, STABILITY, DECOUPLING, ANGULAR VELOCITY,...
The X-33 liquid hydrogen tank failure investigation found the following: (1) The inner skin microcracked and hydrogen infiltrated into it; (2) The cracks grew larger under pressure; (3) When pressure was removed, the cracks closed slightly; (4) When the tank was drained and warmed, the cracks closed and blocked the leak path; (5) Foreign object debris (FOD) and debond areas provided an opportunity for a leak path; and (6) There is still hydrogen in the other three lobes today.
Topics: NASA Technical Reports Server (NTRS), MICROCRACKS, X-33 REUSABLE LAUNCH VEHICLE, ACCIDENT...
This viewgraph presentation gives an overview of the X-33 LH2 tank failure investigation findings. The conclusions of the investigation include the following: (1) the inner skin microcracked and hydrogen infiltrated; (2) the cracks grew larger under pressure; (3) when pressure was removed, the cracks closed slightly; (4) when the tank was drained and warmed, the cracks closed and blocked the leak path; (5) FOD and debond areas provided an opportunity for a leak path; and (6) there is still...
Topics: NASA Technical Reports Server (NTRS), FAILURE ANALYSIS, LEAKAGE, MICROCRACKS, X-33 REUSABLE LAUNCH...
This paper will present several methods for adjusting clock skew variations that occur in a n accumulative z-axis interconnect system. In such a system, delay between modules in a function of their distance from one another. Clock distribution in a high-speed system, where clock skew must be kept to a minimum, becomes more challenging when module order is variable before design.
Topics: NASA Technical Reports Server (NTRS), CLOCKS, SKEWNESS, ACCURACY, MODULES, HIGH SPEED, COMPUTERS,...
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261
Jun 2, 2011
06/11
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Edward, Bernard L.; Burnside, Jamie W., et al; Townes, Stephen A.; Bondurant, Roy S.; Scozzafava, Joseph J.; Boroson, Don M.; Parvin, Ben A.; Biswas, Abhijit; Pillsbury, Alan D.; Khatri, Farzana I.
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This paper provides an overview of the Mars Laser Communications Demonstration Project, a joint project between NASA s Goddard Space Flight Center (GSFC), the Jet Propulsion Laboratory, California Institute of Technology (JPL), and the Massachusetts Institute of Technology Lincoln Laboratory (MIT/LL). It reviews the strawman designs for the flight and ground segments, the critical technologies required, and the concept of operations. It reports preliminary conclusions from the Mars Lasercom...
Topics: AIRCRAFT DESIGN, DESIGN ANALYSIS, FLIGHT CHARACTERISTICS, FLIGHT CONTROL, NEURAL NETS, X-33...
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Jun 9, 2011
06/11
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Deur, J. M.; Cline, M. C
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Requirements to limit pollutant emissions from the gas turbine engines for the future High-Speed Civil Transport (HSCT) have led to consideration of various low-emission combustor concepts. One such concept is the Integrated Mixer-Flame Holder (IMFH). This report describes a series of IMFH analyses performed with KIVA-II, a multi-dimensional CFD code for problems involving sprays, turbulence, and combustion. To meet the needs of this study, KIVA-II's boundary condition and chemistry treatments...
Topics: AERODYNAMIC HEATING, BOUNDARY LAYER TRANSITION, HYPERSONIC BOUNDARY LAYER, X-33 REUSABLE LAUNCH...
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340
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The Sea-viewing Wide Field-of-view Sensor (SeaWiFS) is the follow-on ocean color instrument to the Coastal Zone Color Scanner (CZCS), which ceased operations in 1986, after an eight-year mission. SeaWiFS was launched on 1 August 1997, onboard the OrbView-2 satellite, built by Orbital Sciences Corporation (OSC). The SeaWiFS Project at the National Aeronautics and Space Administration (NASA) Goddard Space Flight Center (GSFC), undertook the responsibility of documenting all aspects of this...
Topics: ENGINE TESTS, FULL SCALE TESTS, PROPELLANT TESTS, TEST FACILITIES, X-33 REUSABLE LAUNCH VEHICLE,...
Control of the X33 reusable launch vehicle is considered. The launch control problem consists of automatic tracking of the launch trajectory which is assumed to be optimally precalculated. It requires development of a reliable, robust control algorithm that can automatically adjust to some changes in mission specifications (mass of payload, target orbit) and the operating environment (atmospheric perturbations, interconnection perturbations from the other subsystems of the vehicle, thrust...
Topics: NASA Technical Reports Server (NTRS), CONTROL SYSTEMS DESIGN, X-33 REUSABLE LAUNCH VEHICLE,...
The NASA Lewis Research Center, in cooperation with Rocketdyne, the Boeing Company, tested a novel rocket engine ignition system, called the combustion-wave ignition system, in its Research Combustion Laboratory. This ignition system greatly simplifies ignition in rocket engines that have a large number of combustors. The particular system tested was designed and fabricated by Rocketdyne for the national experimental spacecraft, X-33, which uses Rocketdyne s aerospike rocket engines. The goal...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, IGNITION SYSTEMS, FLAME...
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224
May 30, 2011
05/11
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Russell, S. S.; Walker, J. L.; Lansing, M. D
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During the manufacture of the X-33 liquid hydrogen (LH2) Tank 2, a total of 36 reinforcing caps were inspected thermographically. The cured reinforcing sheets of graphite/epoxy were bonded to the tank using a wet cobond process with vacuum bagging and low temperature curing. A foam filler material wedge separated the reinforcing caps from the outer skin of the tank. Manufacturing difficulties caused by a combination of the size of the reinforcing caps and their complex geometry lead to a...
Topics: FLIGHT CONTROL, TRACKING PROBLEM, SERVOMECHANISMS, PROPORTIONAL CONTROL, MIMO (CONTROL SYSTEMS),...
The NASA Glenn Research Center at Lewis Field, in cooperation with Rocketdyne, has designed, developed, and implemented an automated Post-Test Diagnostic System (PTDS) for the X-33 linear aerospike engine. The PTDS was developed to reduce analysis time and to increase the accuracy and repeatability of rocket engine ground test fire and flight data analysis. This diagnostic system provides a fast, consistent, first-pass data analysis, thereby aiding engineers who are responsible for detecting...
Topics: NASA Technical Reports Server (NTRS), AEROSPIKE ENGINES, ROCKET ENGINES, ROCKET ENGINE DESIGN, X-33...
The X-33 experimental program is a cooperative program between industry and NASA, managed by Lockheed-Martin Skunk Works to develop an experimental vehicle to demonstrate new technologies for a single-stage-to-orbit, fully reusable launch vehicle (RLV). One of the new technologies to be demonstrated is an advanced Thermal Protection System (TPS) being designed by BF Goodrich (formerly Rohr, Inc.) with support from NASA. The calculation of an aerothermal database is crucial to identifying the...
Topics: NASA Technical Reports Server (NTRS), AEROTHERMODYNAMICS, X-33 REUSABLE LAUNCH VEHICLE,...
A methodology for very fast design of 3DOF entry trajectories subject to all common inequality and equality constraints is developed. The approach make novel use of the well known quasi-equilibrium glide phenomenon in lifting entry as a center piece for conveniently enforcing the inequality constraints which are otherwise difficulty to handle. The algorithm is able to generate a complete feasible 3DOF entry trajectory, given the entry conditions, values of constraint parameters, and final...
Topics: NASA Technical Reports Server (NTRS), TRAJECTORIES, ALGORITHMS, THREE DIMENSIONAL MODELS,...
This paper presents radiation data for the linear aerospike engine.
Topics: NASA Technical Reports Server (NTRS), AEROSPIKE ENGINES, PLUMES, X-33 REUSABLE LAUNCH VEHICLE, SEA...
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May 28, 2011
05/11
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Mackall, Dale; McBride, David; Cohen, Dorothe
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The Integrated Test Facility (ITF), being built at the NASA Ames Research Center's Dryden Flight Research Facility (ADFRF), will provide new real-time test capabilities for emerging research aircraft. An overview of the ITF and the real-time systems being developed to operate this unique facility are outlined in this paper. The ITF will reduce flight test risk by minimizing the difference between the flight- and ground-test environments. The ground-test environment is provided by combining...
Topics: SPACECRAFT LAUNCHING, DATA ACQUISITION, ROCKET NOZZLES, X-33 REUSABLE LAUNCH VEHICLE, BASE HEATING,...
In response to Clause 17 of the Cooperative Agreement NCC8-115, Lockheed Martin Skunk Works has compiled an Annual Performance Report of the X-33/RLV Program. This report consists of individual reports from all industry team members, as well as NASA team centers. Contract award was announced on July 2, 1996 and the first milestone was hand delivered to NASA MSFC on July 17, 1996. The first year has been one of growth and progress as all team members staffed up and embarked on the technical...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, SINGLE STAGE TO ORBIT VEHICLES,...
A viewgraph presentation outlines the design and testing of the single stage to orbit vehicle, the X-33. The history and objectives of the program to build the X-33 are discussed, as well as the specifications for the spacecraft. Flight test results are given and future plans for a spaceport are discussed.
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, SINGLE STAGE TO ORBIT VEHICLES,...
The presentation "NASA Experience with Launch Vehicles" is a compilation of Mr. Dumbacher's career experiences with the Space Shuttle Program, the Delta - Clipper Experimental flight test project, the X-33 demonstrator project, and recent experiences with the Orbital Spaceplane Program agd the current NASA effort on Exploration Launch Systems. Mr. Dumbacher will discuss his personal experiences and provide lessons learned from each program. The accounts provided by Mr. Dumbacher are...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, DELTA CLIPPER, LAUNCH VEHICLES,...
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283
May 29, 2011
05/11
by
Kao, Hsiao C
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The topic of stationary configurations of point vortices, also known as vortex equilibrium, has received considerable attention in recent years. By observing numerical results, it is found that a ''counterpart'' of this system also exists, in which moving vortices may be ''trapped'' by an inlet-like device to form a stationary pattern with no translational motion. After an intuitive explanation for the process, vortex trajectory maps based on numerical results are presented. These maps exhibit...
Topics: FLIGHT CONTROL, DIFFERENTIAL EQUATIONS, COST REDUCTION, X-33 REUSABLE LAUNCH VEHICLE, ENGINE...
The X-33 vehicle is an advanced technology demonstrator sponsored by NASA. For the past three years the Structural Dynamics & Loads Group of NASA's Marshall Space Flight Center has had the task of integrating the X-33 vehicle structural finite element model. In that time, five versions of the integrated vehicle model have been produced and a strategy has evolved that would benefit anyone given the task of integrating structural finite element models that have been generated by various...
Topics: NASA Technical Reports Server (NTRS), STRATEGY, FINITE ELEMENT METHOD, MODELS, X-33 REUSABLE LAUNCH...
To enable low-cost space access for advanced exploration vehicles, researchers from NASA's Ames Research Center invented and patented a protective coating for ceramic materials (PCCM) in 1994. The technology, originally intended to coat the heat shields of the X-33 and X-34 next-generation vehicles for optimum protection during atmospheric reentry, greatly reduces surface temperature of a thermal control structure while it reradiates absorbed energy to a cooler surface or body, thus preventing...
Topics: NASA Technical Reports Server (NTRS), PROTECTIVE COATINGS, X-33 REUSABLE LAUNCH VEHICLE, X-34...
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540
May 31, 2011
05/11
by
Patnaik, Surya N.; Hopkins, Dale A
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The theory of elasticity evolved over centuries through the contributions of eminent scientists like Cauchy, Navier, Hooke Saint Venant, and others. It was deemed complete when Saint Venant provided the strain formulation in 1860. However, unlike Cauchy, who addressed equilibrium in the field and on the boundary, the strain formulation was confined only to the field. Saint Venant overlooked the compatibility on the boundary. Because of this deficiency, a direct stress formulation could not be...
Topics: X-33 REUSABLE LAUNCH VEHICLE, ACTUATORS, STABILITY, CONFIGURATION MANAGEMENT, CONTROL SYSTEMS...
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172
May 26, 2011
05/11
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DeLand, Matthew T.; Cebula, Richard P.; Hilsenrath, Ernes
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The Shuttle SBUV (SSBUV) and NOAA-11 SBUV/2 instruments measured solar spectral UV irradiance during the maximum and declining phase of solar cycle 22. The SSB UV data accurately represent the absolute solar UV irradiance between 200-405 nm, and also show the long-term variations during eight flights between October 1989 and January 1996. These data have been used to correct long-term sensitivity changes in the NOAA-11 SBUV/2 data, which provide a near-daily record of solar UV variations over...
Topics: X-33 REUSABLE LAUNCH VEHICLE, MAINTENANCE, DECISION MAKING, SMART STRUCTURES, COST REDUCTION,...
The X-33, NASA's flagship for reusable space plane technology demonstration, is on course to permit a crucial decision for the nation by the end of this decade. Lockheed Martin Skunk Works, NASA's partner in this effort, has led a dedicated and talented industry and government team that have met and solved numerous challenges within the first 26 months. This program began by accepting the mandate that included two unprecedented and highly challenging goals: 1) demonstrate single stage to orbit...
Topics: NASA Technical Reports Server (NTRS), TECHNOLOGY ASSESSMENT, X-33 REUSABLE LAUNCH VEHICLE,...
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170
Jun 9, 2011
06/11
by
Glaessgen, E. H.; Riddell, W. T.; Raju, I. S
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The effects of several critical assumptions and parameters on the computation of strain energy release rates for delamination and debond configurations modeled with plate elements have been quantified. The method of calculation is based on the virtual crack closure technique (VCCT), and models that model the upper and lower surface of the delamination or debond with two-dimensional (2D) plate elements rather than three-dimensional (3D) solid elements. The major advantages of the plate element...
Topics: AERODYNAMIC CHARACTERISTICS, AERODYNAMIC HEATING, COMPUTATIONAL FLUID DYNAMICS, FLIGHT CONDITIONS,...
The X-33 Guidance, Navigation, and Control (GN&C) Peer Review Team (PRT) was formed to assess the integrated X-33 vehicle GN&C system in order to identify any areas of disproportionate risk for initial flight. The eventual scope of the PRT assessment encompasses the GN&C algorithms, software, avionics, control effectors, applicable models, and testing. The initial (phase 1) focus of the PRT was on the GN&C algorithms and the Flight Control Actuation Subsystem (FCAS). The PRT...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, GUIDANCE (MOTION), FLIGHT...
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May 30, 2011
05/11
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Choi, Sung R.; Powers, Lynn M.; Holland, Frederic A.; Gyekenyesi, John P
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Extensive creep testing of a hot-pressed silicon nitride (NC132) was performed at 1300 C in air using five different specimen/loading configurations, including pure tension, pure compression, four-point uniaxial flexure, ball-on-ring biaxial flexure, and ring-on-ring biaxial flexure. Nominal creep strain and its rate for a given nominal applied stress were greatest in tension, least in compression, and intermediate in uniaxial and biaxial flexure. Except for the case of compressive loading,...
Topics: AEROSPACE SAFETY, MANAGEMENT PLANNING, RISK, SPACE SHUTTLES, MISSION PLANNING, X-33 REUSABLE LAUNCH...
The Primary activities of Lee & Associates for the referenced Purchase Order has been in direct support of the X-33/Reusable Launch Vehicle Technology Program. An independent review to evaluate the X-33 liquid hydrogen fuel tank failure, which recently occurred after-test of the starboard tank has been provided. The purpose of the Investigation team was to assess the tank design modifications, provide an assessment of the testing approach used by MSFC (Marshall Space Flight Center) in...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, FUEL TANKS, TECHNOLOGY...
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224
May 29, 2011
05/11
by
Choi, Michael K
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Landsat-7 was successfully launched into orbit on April 15, 1999. After devoting three months to the t bakeout and cool-down of the radiative cooler, and on- t orbit checkout, the Enhanced Thematic Mapper Plus (ETM) began the normal imaging phase of the mission in mid-July 1999. This paper presents the thermal performance of the ETM from mid-July 1999 to mid-May 2000. The flight temperatures are compared to the yellow temperature limits, and worst cold case and worst hot case flight temperature...
Topics: SPACECRAFT GUIDANCE, FLIGHT SAFETY, RISK, CONTROL SYSTEMS DESIGN, SPACECRAFT CONTROL, X-33 REUSABLE...
This research report is divided into four sections. The first section is related to participation on the team that evaluated the proposals for the X-33 project and the Reusable Launch Vehicle (RLV) during mid-May; prior to beginning the 1996 Summer Faculty Fellowship. The second section discusses the various meetings attended related to the technology evaluation process. The third section is related to various research and evaluation activities engaged in by this researcher. The final section...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, NASA PROGRAMS, RESEARCH AND...
In 1996, Systems and Processes Engineering Corporation (SPEC), of Austin, Texas, undertook a NASA Small Business Innovation Research (SBIR) contract with Langley Research Center to develop a compact and lightweight digital thermal sensing (DTS) system for monitoring the cryogenic tanks on the X-33 prototype aircraft. That technology, along with a processor developed by SPEC for Goddard Space Flight Center, was space-qualified and integrated into several NASA missions. SPEC formed an ancillary...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, TEMPERATURE SENSORS,...
A Monte Carlo dispersion analysis has been completed on the X-33 software simulation. The simulation is based on a preliminary version of the software and is primarily used in an effort to define and refine how a Monte Carlo dispersion analysis would have been done on the final flight-ready version of the software. This report gives an overview of the processes used in the implementation of the dispersions and describes the methods used to accomplish the Monte Carlo analysis. Selected results...
Topics: NASA Technical Reports Server (NTRS), COMPUTERIZED SIMULATION, MONTE CARLO METHOD, COMPUTER...
In response to the Access to Space Study, which was conducted in 1993 through the Office of Space Systems Development, an advanced technology Reusable Launch Vehicle (RLV) was selected for demonstration. The X-33 was advanced as an demonstration project, to build and test a 53-percent scale prototype of an operational RLV, it would also demonstrate new technologies which would be required to assure the operation of the new RLV. This presentation reviews the progress of the X-33 development and...
Topics: NASA Technical Reports Server (NTRS), X-33 REUSABLE LAUNCH VEHICLE, REUSABLE SPACECRAFT,...
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440
Jun 1, 2011
06/11
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Koelfgen, Syri J.; Hawk, Clark W.; Eskridge, Richard; Smith, James W.; Martin, Adam K
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There are a number of possible advantages to using accelerated plasmoids for in-space propulsion. A plasmoid is a compact plasma structure with an integral magnetic field. They have been studied extensively in controlled fusion research and are classified according to the relative strength of the poloidal and toroidal magnetic field (B(sub p), and B(sub t), respectively). An object with B(sub p), / B(sub t) much greater than 1 is classified as a Field Reversed Configuration (FRC); if B(sub p)...
Topics: X-33 REUSABLE LAUNCH VEHICLE, BRAGG GRATINGS, SYSTEMS HEALTH MONITORING, MANAGEMENT SYSTEMS,...
The state-of-the-art development of several Metal Matrix Composites (MMC) for NASA's advanced propulsion systems will be presented. The goal is to provide an overview of NASA-Marshall Space Flight Center's on-going activities in MMC components for advanced liquid rocket engines such as the X-33 vehicle's Aerospike engine and X-34's Fastrac engine. The focus will be on lightweight, low cost, and environmental compatibility with oxygen and hydrogen of key MMC materials, within each of NASA's new...
Topics: NASA Technical Reports Server (NTRS), METAL MATRIX COMPOSITES, WELDING, JOINTS (JUNCTIONS), LIQUID...
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760
May 27, 2011
05/11
by
Scialdone, John J
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At various time concerns have been expressed that rapid decompressions of compartments of gas pockets and thermal blankets during spacecraft launches may have caused pressure differentials across their walls sufficient to cause minor structural failures, separations of adhesively-joined parts, ballooning, and flapping of blankets. This paper presents a close form equation expressing the expected pressure differentials across the walls of a compartment as a function of the external to the volume...
Topics: X-33 REUSABLE LAUNCH VEHICLE, TRANSITION FLIGHT, CONTROL ROCKETS, GUIDANCE SENSORS,...
This paper presents viewgraphs of the RS-68 and Linear Aerospike engines. The topics include: 1) The mission; 2) Design and Development Strategies; 3) Cost Driven Design Trades; 4) Moderate Pressure Requirements Enable Reduced Complexity; 5) Experience Based Design; 6) Development Costs Dominated by Cost of Eliminating Failure Modes; and 7) Reducing Development Costs. This paper also includes the design of the RS-68 Engine and the engine performance.
Topics: NASA Technical Reports Server (NTRS), AEROSPIKE ENGINES, LIQUID PROPELLANT ROCKET ENGINES, DESIGN...
In this paper, the development history for the first cryogenic pressurized fuel tank coverplates is presented along with a synopsis of the development strategy and technologies which led to success on this program. Coverplates are the large access panels used to access launch vehicle fuel tanks. These structures incorporate all of the requirements for a pressure vessel as well as the added requirement to mount all of the miscellaneous access points required for a fuel management system. The...
Topics: NASA Technical Reports Server (NTRS), CRYOGENIC FLUID STORAGE, FUEL TANKS, PANELS, X-33 REUSABLE...
