Sample records for hellyer stringer zone

  1. Hydrothermal and metamorphic berthierine from the Kidd Creek volcanogenic massive sulfide deposit, Timmins, Ontario

    USGS Publications Warehouse

    Slack, J.F.; Wei-Teh, Jiang; Peacor, D.R.; Okita, P.M.

    1992-01-01

    Berthierine, a 7 A?? Fe-Al member of the serpentine group, occurs in the footwall stringer zone of the Archean Kidd Creek massive sulfide deposit, associated with quartz, muscovite, chlorite, pyrite, sphalerite, chalcopyrite, and local tourmaline, cassiterite, and halloysite. Petrographic and scanning electron microscopic (SEM) studies reveal different types of berthierine occurrences, including interlayers within the rims on deformed chlorite, intergrowths with muscovite and halloysite, and discrete coarse grains. This is the first reported occurrence of berthierine from volcanogenic massive sulfide deposits. Textural relations suggest that most of the berthierine formed as a primary hydrothermal mineral at relatively high temperatures (~350??C) in the footwall stringer zone, probably by the replacement of a pre-existing aluminous phase such as muscovite or chlorite. However, the intergrowth textures observed by SEM and TEM suggest that some of the berthierine originated by syn- or post-metamorphic replacement of chlorite. -from Authors

  2. How rheological heterogeneities control the internal deformation of salt giants.

    NASA Astrophysics Data System (ADS)

    Raith, Alexander; Urai, Janos L.

    2017-04-01

    Salt giants, like the North European Zechstein, consist of several evaporation cycles of different evaporites with highly diverse rheologies. Common Potassium and Magnesium (K-Mg) salt are typically 10 to 100 times less viscous as halite while stringers consisting of anhydrite and carbonates are about 100 times more viscous. In most parts, these mechanically layered bodies experienced complex deformation, resulting in large scale internal folding with ruptured stringers and shear zones, as observed in seismic images. Furthermore, locally varying evaporation history produced different mechanical stratigraphies across the salt basin. Although most of these extraordinary soft or strong layers are rather thin (<100 m) compared to the dominating halite, we propose they have first order control on the deformation and the resulting structures inside salt bodies. Numerical models representing different mechanical stratigraphies of hard and soft layers inside a salt body were performed to analyze their influence on the internal deformation during lateral salt flow. The results show that a continuous or fractured stringer is folded and thrusted during salt contraction while soft K-Mg salt layers act as internal décollement. Depending on the viscosity of the fractured stringers, the shortening is mostly compensated by either folding or thrusting. This folding has large control over the internal structure of the salt body imposing a dominating wavelength to the whole structure during early deformation. Beside strong stringers, K-Mg salt layers also influence the deformation and salt flow inside the salt pillow. Strain is accumulated in the soft layers leading to stronger salt flow near these layers and extensive deformation inside of them. Thus, if a soft layer is present near a stringer, it will experience more deformation. Additionally, the strong strain concentration in the soft layers could decouple parts of the salt body from the main deformation.

  3. A remediation performance model for enhanced metabolic reductive dechlorination of chloroethenes in fractured clay till

    NASA Astrophysics Data System (ADS)

    Manoli, Gabriele; Chambon, Julie C.; Bjerg, Poul L.; Scheutz, Charlotte; Binning, Philip J.; Broholm, Mette M.

    2012-04-01

    A numerical model of metabolic reductive dechlorination is used to describe the performance of enhanced bioremediation in fractured clay till. The model is developed to simulate field observations of a full scale bioremediation scheme in a fractured clay till and thereby to assess remediation efficiency and timeframe. A relatively simple approach is used to link the fermentation of the electron donor soybean oil to the sequential dechlorination of trichloroethene (TCE) while considering redox conditions and the heterogeneous clay till system (clay till matrix, fractures and sand stringers). The model is tested on lab batch experiments and applied to describe sediment core samples from a TCE-contaminated site. Model simulations compare favorably to field observations and demonstrate that dechlorination may be limited to narrow bioactive zones in the clay matrix around fractures and sand stringers. Field scale simulations show that the injected donor is expected to be depleted after 5 years, and that without donor re-injection contaminant rebound will occur in the high permeability zones and the mass removal will stall at 18%. Long remediation timeframes, if dechlorination is limited to narrow bioactive zones, and the need for additional donor injections to maintain dechlorination activity may limit the efficiency of ERD in low-permeability media. Future work should address the dynamics of the bioactive zones, which is essential to understand for predictions of long term mass removal.

  4. The effect of broken stringers on the stress intensity factor for a uniformly stiffened sheet containing a crack

    NASA Technical Reports Server (NTRS)

    Poe, C. C., Jr.

    1973-01-01

    A linear elastic stress analysis was made of a centrally cracked sheet stiffened by riveted, uniformly spaced and sized stringers. The stress intensity factor for the sheet and the load concentration factor for the most highly loaded stringer were determined for various numbers of broken stringers. A broken stringer causes the stress intensity factor to be very high when the crack tip is near the broken stringer, but causes little effect when the crack tip extends beyond several intact stringers. A broken stringer also causes an increase in the load concentration factor of the adjacent stringers. The calculated residual strengths and fatigue-crack-growth lives of a stiffened aluminum sheet with a broken stringer were only slightly less than a sheet with all intact stringers, and were still much higher than those of an unstiffened sheet.

  5. Repaired Pallets May Be Stronger Than the Original

    Treesearch

    John W. Clarke; Marshall S. White; T.E. McLain; Philip A. Araman

    1995-01-01

    Stringer-style pallets are often notched to permit 4-way entry with forklift tines. Splits often occur around these stringer notches, significantly reducing the strength and durability of the pallet. Pallet stringer repair has traditionally involved replacement of the damaged stringer with a new stringer or support of the damaged stringer with various size companion...

  6. The large scale structures of the Late Permian Zechstein 3 intra-salt stringer, northern Netherlands

    NASA Astrophysics Data System (ADS)

    van Gent, H.; Strozyk, F.; Urai, J. L.; de Keijzer, M.; Kukla, P. A.

    2012-04-01

    The three dimensional study of the internal structure of salt structures on the several different scales is of fundamental importance to understand mechanisms of salt tectonics, for intra-salt storage cavern stability, and for drilling in salt-prone petroleum systems with associated problems like borehole instability and overpressured fluids. While most salt-related studies depict salt as structureless bodies, detailed field-, well- and mining gallery mapping have shown an amazing spectrum of brittle, complexly folded, faulted and boudinaged intra-salt layers ("stringers"), but mostly on a very local scale. First detailed insights into these three-dimensionally heterogeneous and very complex structures of the layered evaporites were provided by observations in modern high-resolution 3D seismic data, such as across the Late Permian Zechstein in the Southern Permian Basin (SPB). In the northern Dutch onshore part of the SPB, the Z2 and Z3 halite interface is characterized by the seismically visible reflections of the 30-150 m thick Z3 anhydrite-carbonate layer that clearly resolves the complex intra-salt structure. This stringer shows a high fragmentation into blocks of several tens of meters to kilometres diameter with complexly folded and faulted structures that correlate to the regionally varying deformation stages of the Zechstein, as it is implied by the shape of Top Salt. After an extensive seismic mapping over the entire northern Netherlands, structures observed include an extensive network of thicker zones, inferred to result from early karstification. Later, this template of relatively strong zones was deformed into large scale folds and boudins as the result of salt tectonics. Non-plane-strain salt flow produced complex fold and boudin geometries that overprint each other. There are some indications of a feedback between the early internal evolution of this salt giant and the position of later salt structures. The stringer has a higher density then the surrounding halite, and in the literature there is some controversy concerning the sinking rates of single stringer fragments. We observed no structures indicative of sinking, but conclude that the present-day position of the blocks can be explained by internal folding of the entire salt section. In the end, this study aims at (i) improving the understanding of the development and dynamics of Zechstein halokinesis, (ii) gaining new insights into the 3D internal deformation in salt, and (iii) a linkage of processes in the layered evaporites with the deformation of the enclosing sub- and supra-salt sediments.

  7. Elastic-Plastic Nonlinear Response of a Space Shuttle External Tank Stringer. Part 1; Stringer-Feet Imperfections and Assembly

    NASA Technical Reports Server (NTRS)

    Knight, Norman F., Jr.; Song, Kyongchan; Elliott, Kenny B.; Raju, Ivatury S.; Warren, Jerry E.

    2012-01-01

    Elastic-plastic, large-deflection nonlinear stress analyses are performed for the external hat-shaped stringers (or stiffeners) on the intertank portion of the Space Shuttle s external tank. These stringers are subjected to assembly strains when the stringers are initially installed on an intertank panel. Four different stringer-feet configurations including the baseline flat-feet, the heels-up, the diving-board, and the toes-up configurations are considered. The assembly procedure is analytically simulated for each of these stringer configurations. The location, size, and amplitude of the strain field associated with the stringer assembly are sensitive to the assumed geometry and assembly procedure. The von Mises stress distributions from these simulations indicate that localized plasticity will develop around the first eight fasteners for each stringer-feet configuration examined. However, only the toes-up configuration resulted in high assembly hoop strains.

  8. 27. PLAN OF STRINGERS TO BE REPLACED (with 'Present Stringers' ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    27. PLAN OF STRINGERS TO BE REPLACED (with 'Present Stringers' written over the word 'stringers' in the original) SOUTH HADLEY FALLS BRIDGE, HOLYOKE, MASS. Scale 11/2' = 1' 1/1/23 P.E. Bond City Engr. - Holyoke Bridge, Spanning Connecticut River, between Holyoke & South Hadley Falls, Holyoke, Hampden County, MA

  9. Defining perennial, intermittent and ephemeral channels in eastern Kentucky: application to forestry best management practices

    Treesearch

    J. R. Svec; R. K. Kolka; J. W. Stringer

    2003-01-01

    In Kentucky stream classification is used to determine which forestry best management practice (BMP) to apply in riparian zones. Kentucky defines stream classes as follows (Stringer and others 1998): a) perennial streams that hold water throughout the year, b) intermittent streams that hold water during wet portions of the year, and c) ephemeral channels that hold...

  10. Test Analysis Correlation of the Single Stringer Bending Tests for the Space Shuttle ET-137 Intertank Stringer Crack Investigation

    NASA Technical Reports Server (NTRS)

    Phillips, Dawn R.; Saxon, Joseph B.; Wingate, Robert J.

    2012-01-01

    On November 5, 2010, Space Shuttle mission STS-133 was scrubbed due to a hydrogen leak at the Ground Umbilical Carrier Plate (GUCP). After the scrub, a crack in the foam thermal protection system (TPS) was observed on the External Tank (ET) near the interface between the liquid oxygen (LOX) tank and the Intertank. When the damaged foam was removed, two 9-in. long cracks were found on the feet of Intertank stringer S7-2, and the stringer failure was the cause of the TPS crack. An investigation was conducted to determine the root cause of the cracks, establish a remedy/repair for the stringers, and provide flight rationale for the damaged tank, ET-137. The Space Transportation System (STS) Super Lightweight ET (SLWT) is comprised of two propellant tanks (an aft liquid hydrogen (LH2) tank and a forward LOX tank) and an Intertank. The Intertank serves as the structural connection between the two propellant tanks and also functions to receive and distribute all thrust loads from the solid rocket boosters . The Intertank is a stiffened cylinder structure consisting of eight mechanically joined panels (two integrally-stiffened, machined thrust panels to react the booster loads and six stringer-stiffened skin panels). There are one main ring frame, four intermediate ring frames, and forward and aft flange chords that mate to the respective propellant tanks.. The skin/stringer panels utilize external hat-section stringers that are mechanically attached with rivets along most of their length and with specialty fasteners, such as GP Lockbolts and Hi-Loks, at the forward and aft ends where the stringers attach to the flange chords. During the STS-133 Intertank stringer crack investigation, cracks were found on a total of five stringers. All of the cracks were at the LOX end, in the feet of the stringers, and near the forward fasteners (GP Lockbolts). Video of tanking for the November 5 launch attempt was used to determine that the TPS failure, and thus the stringer failure, occurred as the LOX liquid level crossed the LOX tank / Intertank interface ring frame. Hence, cryogenically-induced displacements were suspected as a contributing cause of the stringer cracks. To study the behavior of Intertank stringers subjected to similar displacements, static load tests of individual stringers, colloquially known as "single stringer bending tests" were performed. Approximately thirty stringers were tested, many of which were cut from the partially completed Intertank for what would have been ET-139. In addition to the tests, finite element (FE) analyses of the test configuration were also performed. In this paper, the FE analyses and test-analysis correlation for stringer test S6-8 are presented. Stringer S6-8 is a "short chord" configuration with no doubler panels.

  11. Lessons Learned on Bioaugmentation of DNAPL Source Zone Areas

    DTIC Science & Technology

    2007-10-01

    but rather have stringers, ganglia or blobs that can create an “effective pool length”. As the leading edge of these discontinuous DNAPL free-phases...terminal restriction fragment length polymorphism (T-RFLP), denaturing gradient gel electrophoresis (DGGE), and fluorescent in situ hybridization ( FISH ...question of interest (e.g. PCR, FISH , DGGE); (ii) sampling location(s); (iii) an appropriate sampling procedure; and (iv) an appropriate sample handling

  12. Surgical Nondestructive Evaluation (SuNDE)

    DTIC Science & Technology

    2011-07-01

    Primary selected A-10 wing inspection area, on the stringer runouts opposite the front spar access hole...at Stringer Doubler Runout . .........................................11 Figure 6. A-10 Inspection Required Under Stringer Flange...volume. ................................................14 Figure 9. CAD view of the A10 cavity showing the inspection areas on the stringer runouts

  13. Caul and method for bonding and curing intricate composite structures

    NASA Technical Reports Server (NTRS)

    Willden, Kurtis S. (Inventor); Goodno, Kenneth N. (Inventor)

    1993-01-01

    The invention disclosed here is a method for forming and curing an intricate structure of criss-crossing composite stringers and frames that are bonded to a skin panel. A structure constructed in accordance with the invention would be well-suited for use as a portion of an aircraft fuselage, a boat hull, or the like. The method is preferably practiced by applying uncured composite stringers to an uncured composite sheet panel. This is followed by placing cured frames crosswise over the stringers. The frames have openings at the locations where they intersect with the stringers which enables the frames to come into direct contact with the skin along most of their length. During the forming and curing process, the stringers are covered with a plurality of cauls, and the entire assembly of skin panel, stringers, frames and cauls is subjected to a vacuum bagging and curing process. The cauls serve to maintain both part shape and to control the flow of resin within the stringers as they are cured. Further, they probably eliminate the need for intermediate protective materials between the vacuum bag and the stringers.

  14. Universal connectors for joining stringers

    NASA Technical Reports Server (NTRS)

    Harrison, Jr., Ernest (Inventor)

    1987-01-01

    This invention is a lightweight, universal connector that joins stringers at various angles. The connectors 10 are fabricated from fiber-epoxy resin strips that wrap around stringers 30 and have ends, tabs 16 and 18, which extend in one general direction. The inside surface of the first tab 16 lies on a plane defined by the stringers being joined, and the second tab 18 is separated from the first tab 16 by a distance equal to their thickness. Stringers 30 of different shapes and sizes are joined by alternately bonding the first tab 16 of one connector between the first 16 and second 18 tabs of another connector. Tee-joints are formed by using web elements 41 and 42 which each partially wrap around a stringer 3010 and have tabs 411 and 421 which are offset, and are bonded between tabs 16 and 18 of universal connectors 109 and 1010 bonded to another stringer 309. Sharp corners are trimmed from the tabs so that a gusset area remains between the stringers for support. Acute angle through obtuse angle joints are formed by trimming those edges of the tabs which lie against the stringers. A specific application of the invention is a Walker 60, utilized by handicapped individuals, fabricated from composite materials that is 40% lighter than similar metallic structures.

  15. Effect of stringer repair methods and repair frequency on GMA performance

    Treesearch

    John W. Clarke; Marshall S. White; Philip A. Araman

    2005-01-01

    Over 135 million wooden pallets were repaired for reuse in 1995. Notched stringers are one of the most commonly damaged components. Metal plates, half companion stringers, and full companion stringers are repair methods described in the U.S. industry standard published by the American Society of Mechanical Engineers. This study evaluated the effect of these three...

  16. A note on the effect of bending stiffness of stringers attached to a plate with a crack

    NASA Technical Reports Server (NTRS)

    Arin, K.

    1974-01-01

    An infinite stringer partially bonded to a plate through a layer of adhesive is considered. The stringer had bending as well as longitudinal stiffness. The effect of the stringer's bending rigidity on the stress intensity factor at the tip of the crack is illustrated. Shear stress distribution between the plate and the stringer and the stress intensity factors are obtained from the solution of a system of Fredholm integral equations. The continuity of displacements along the line of bond is represented by the equations.

  17. Pultruded Rod/Overwrap Testing for Various Stitched Stringer Configurations

    NASA Technical Reports Server (NTRS)

    Leone, Frank A., Jr.

    2016-01-01

    The unidirectional carbon pultruded rod running through the tops of the stringers is a key design feature of the Pultruded Rod Efficient Unitized Structure (PRSEUS) concept as applied to aircraft fuselage structure. Reported herein are the test methods and results from a test campaign in which the strength of the rod/overwrap interface of various PRSEUS stringer configurations were characterized. The different stringer configurations included different materials and stacking sequences for the stringer overwrap and whether or not an additional layer of adhesive was included between the rod and the overwrap.

  18. Effect of debond growth on stress-intensity factors in a cracked orthotropic sheet stiffened by a semi-infinite orthotropic sheet

    NASA Technical Reports Server (NTRS)

    Bigelow, C. A.

    1986-01-01

    Stress-intensity factors are determined for a cracked infinite sheet adhesively bonded to a stringer, and debonding of the adhesive layer is predicted. The stringer is modeled as a semi-infinite sheet. Adhesive nonlinearity is also included. Both the sheet and stringer are treated as homogeneous, orthotropic materials. A set of integral equations is formulated and solved to obtain the adhesive shear stresses and crack-tip stress-intensity factors. Adhesive debonding is predicted using a rupture criterion based on the combined adhesive stresses. When the crack is not under the stringer, the debond extends along the edge of the stringer. When the crack tip is beneath the stringer, the debond grows to the end of the crack, then along the edge of the stringer. Stress levels required for debond initiation decrease as the crack tip is moved beneath the stringer. With a nonlinear adhesive, the debond initiates at higher applied stress levels than in linear adhesive cases. Compared with the linear adhesive solution, modeling a nonlinear adhesive causes the stress-intensity factor to increase when the bond is assumed to remain intact but causes the stress-intensity factor to decrease when debonding is included.

  19. STS-133 Space Shuttle External Tank Intertank Stringer Crack Investigation Stress Analysis

    NASA Technical Reports Server (NTRS)

    Steeve, Brian E.

    2012-01-01

    The first attempt to launch the STS-133 Space Shuttle mission in the fall of 2010 was halted due to indications of a gaseous hydrogen leak at the External Tank ground umbilical carrier plate seal. Subsequent inspection of the external tank (figure 1) hardware and recorded video footage revealed that the foam insulation covering the forward end of the intertank near the liquid oxygen tank had cracked severely enough to have been cause for halting the launch attempt on its own (figure 2). An investigation into the cause of the insulation crack revealed that two adjacent hat-section sheet metal stringers (figure 3) had cracks up to nine inches long in the forward ends of the stringer flanges, or feet, near the fasteners that attach the stringer to the skin of the intertank (figure 4). A repair of those two stringers was implemented and the investigation effort widened to understand the root cause of the stringer cracks and to determine whether there was sufficient flight rationale to launch with the repairs and the other installed stringers.

  20. The Effect of Stringer Repair Methods and Repair Frequency on the Performance of GMA-Style 48x40-Inch Wood Pallets

    Treesearch

    John W. Clarke; Marshall S. White; Philip A. Araman

    2004-01-01

    Over 135 million wood pallets were repaired for reuse in 1995. One of the most commonly damaged components in a wood pallet is the notched stringer. Metal plates, half companion stringers, and full companion stringers are repair methods described in the U.S. industry standard published by the American Society of Mechanical Engineers. This study evaluated the effect of...

  1. Elastic-Plastic Nonlinear Response of a Space Shuttle External Tank Stringer. Part 2; Thermal and Mechanical Loadings

    NASA Technical Reports Server (NTRS)

    Knight, Norman F., Jr.; Warren, Jerry E.; Elliott, Kenny B.; Song, Kyongchan; Raju, Ivatury S.

    2012-01-01

    Elastic-plastic, large-deflection nonlinear thermo-mechanical stress analyses are performed for the Space Shuttle external tank s intertank stringers. Detailed threedimensional finite element models are developed and used to investigate the stringer s elastic-plastic response for different thermal and mechanical loading events from assembly through flight. Assembly strains caused by initial installation on an intertank panel are accounted for in the analyses. Thermal loading due to tanking was determined to be the bounding loading event. The cryogenic shrinkage caused by tanking resulted in a rotation of the intertank chord flange towards the center of the intertank, which in turn loaded the intertank stringer feet. The analyses suggest that the strain levels near the first three fasteners remain sufficiently high that a failure may occur. The analyses also confirmed that the installation of radius blocks on the stringer feet ends results in an increase in the stringer capability.

  2. Tensile strength of composite sheets with unidirectional stringers and crack-like damage: A brief report

    NASA Technical Reports Server (NTRS)

    Poe, C. C., Jr.

    1984-01-01

    The residual strength of composite sheets with bonded composite stringers loaded in tension was determined. The results are summarized. About 50 graphite/epoxy composite panels with crack-like slots were monotonically loaded in tension to failure. Both sheet layup and stringer configuration were varied. The composite panels have considerable damage tolerance. The stringers arrested cracks that ran from the crack-like slots, and the residual strengths were considerably greater than those of unstiffened composite sheets. A stress-intensity factor analysis was developed to predict the failing strains of the stiffened panels. Using the analysis, a single design curve was produced for composite sheets with bonded stringers of any configuration.

  3. Fatigue Life Methodology for Bonded Composite Skin/Stringer Configurations

    NASA Technical Reports Server (NTRS)

    Krueger, Ronald; Paris, Isabelle L.; OBrien, T. Kevin

    2000-01-01

    A methodology is presented for determining the fatigue life of bonded composite skin/stringer structures based on delamination fatigue characterization data and geometric nonlinear finite element analyses. Results were compared to fatigue tests on stringer flange/skin specimens to verify the approach.

  4. Compressive Testing of Stitched Frame and Stringer Alternate Configurations

    NASA Technical Reports Server (NTRS)

    Leone, Frank A., Jr.; Jegley, Dawn C.

    2016-01-01

    A series of single-frame and single-stringer compression tests were conducted at NASA Langley Research Center on specimens harvested from a large panel built using the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept. Different frame and stringer designs were used in fabrication of the PRSEUS panel. In this report, the details of the experimental testing of single-frame and single-stringer compression specimens are presented, as well as discussions on the performance of the various structural configurations included in the panel.

  5. Tensile strength of composite sheets with unidirectional stringers and crack-like damage

    NASA Technical Reports Server (NTRS)

    Poe, C. C., Jr.

    1984-01-01

    The damage tolerance characteristics of metal tension panels with riveted and bonded stringers are well known. The stringers arrest unstable cracks and retard propagation of fatigue cracks. Residual strengths and fatigue lives are considerably greater than those of unstiffened or integrally stiffened sheets. The damage tolerance of composite sheets with bonded composite stringers loaded in tension was determined. Cracks in composites do not readily propagate in fatigue, at least not through fibers. Moreover, the residual strength of notched composites is sometimes even increased by fatigue loading. Therefore, the residual strength aspect of damage tolerance, and not fatigue crack propagation, was investigated. About 50 graphite/epoxy composite panels were made with two sheet layups and several stringer configurations. Crack-like slots were cut in the middle of the panels to simulate damage. The panels were instrumented and monotonically loaded in tension to failure. The tests indicate that the composite panels have considerable damage tolerance, much like metal panels. The stringers arrested cracks that ran from the crack-like slots, and the residual strengths were considerably greater than those of unstiffened composite sheets. A stress intensity factor analysis was developed to predict the failing strains of the stiffened panels. Using the analysis, a single design curve was produced for composite sheets with bonded stringers of any configuration.

  6. Design of cryogenic tanks for launch vehicles

    NASA Technical Reports Server (NTRS)

    Copper, Charles; Pilkey, Walter D.; Haviland, John K.

    1990-01-01

    During the period since January 1990, work was concentrated on the problem of the buckling of the structure of an ALS (advanced launch systems) tank during the boost phase. The primary problem was to analyze a proposed hat stringer made by superplastic forming, and to compare it with an integrally stiffened stringer design. A secondary objective was to determine whether structural rings having the identical section to the stringers will provide adequate support against overall buckling. All of the analytical work was carried out with the TESTBED program on the CONVEX computer, using PATRAN programs to create models. Analyses of skin/stringer combinations have shown that the proposed stringer design is an adequate substitute for the integrally stiffened stringer. Using a highly refined mesh to represent the corrugations in the vertical webs of the hat stringers, effective values were obtained for cross-sectional area, moment of inertia, centroid height, and torsional constant. Not only can these values be used for comparison with experimental values, but they can also be used for beams to replace the stringers and frames in analytical models of complete sections of tank. The same highly refined model was used to represent a section of skin reinforced by a stringer and a ring segment in the configuration of a cross. It was intended that this would provide a baseline buckling analysis representing a basic mode, however, the analysis proved to be beyond the scope of the CONVEX computer. One quarter of this model was analyzed, however, to provide information on buckling between the spot welds. Models of large sections of the tank structure were made, using beam elements to model the stringers and frames. In order to represent the stiffening effects of pressure, stresses and deflections under pressure should first be obtained, and then the buckling analysis should be made on the structure so deflected. So far, uncharacteristic deflections under pressure were obtained from the TESTBED program using two types of structural elements. Similar results were obtained using the ANSYS program on a mainframe computer, although two finite element programs on microcomputers have yielded realistic results.

  7. The Factor Replicability of the Litwin and Stringer Organizational Climate Questionnaire: An Inter- and Intra-Organizational Assessment.

    ERIC Educational Resources Information Center

    Rogers, Evan D.; And Others

    1980-01-01

    Four recent factor analytic studies of the Litwin and Stringer Organizational Climate Questionnaire (LSOCQ) are compared. Although there is somewhat more intra- than inter-organizational replicability of factors, both comparisons raise considerable doubt about the validity of the Litwin and Stringer instrument. (Author)

  8. Space Transportation System (STS)-133/External Tank (ET)-137 Intertank (IT) Stringer Cracking Issue and Repair Assessment: Proximate Cause Determination and Material Characterization Study

    NASA Technical Reports Server (NTRS)

    Piascik, Robert S.

    2011-01-01

    Several cracks were detected in stringers located beneath the foam on the External Tank (ET) following the launch scrub of Space Transportation System (STS)-133 on November 5, 2010. The stringer material was aluminum-lithium (AL-Li) 2090-T83 fabricated from sheets that were nominally 0.064 inches thick. The mechanical properties of the stringer material were known to vary between different material lots, with the stringers from ET-137 (predominately lots 620853 and 620854) having the highest yield and ultimate stresses. Subsequent testing determined that these same lots also had the lowest fracture toughness properties. The NASA Engineering and Safety Center (NESC) supported the Space Shuttle Program (SSP)-led investigation. The objective of this investigation was to develop a database of test results to provide validation for structural analysis models, independently confirm test results obtained from other investigators, and determine the proximate cause of the anomalous low fracture toughness observed in stringer lots 620853 and 620854. This document contains the outcome of the investigation.

  9. Test and Analysis of Composite Hat Stringer Pull-off Test Specimens

    NASA Technical Reports Server (NTRS)

    Li, Jian; OBrien, T. Kevin; Rousseau, Carl Q.

    1996-01-01

    Hat stringer pull-off tests were performed to evaluate the delamination failure mechanisms in the flange region for a rod-reinforced hat stringer section. A special test fixture was used to pull the hat off the stringer while reacting the pull-off load through roller supports at both stringer flanges. Microscopic examinations of the failed specimens revealed that failure occurred at the ply termination in the flange area where the flange of the stiffener is built up by adding 45/-45 tape plies on the top surface. Test results indicated that the as-manufactured microstructure in the flange region has a strong influence on the delamination initiation and the associated pull-off loads. Finite element models were created for each specimen with a detailed mesh based on micrographs of the critical location. A fracture mechanics approach and a mixed mode delamination criterion were used to predict the onset of delamination and the pull-off load. By modeling the critical local details of each specimen from micrographs, the model was able to accurately predict the hat stringer pull-off loads and replicate the variability in the test results.

  10. On the contact interaction of two identical stringers with an elastic semi-infinite continuous or vertically cracked plate

    NASA Astrophysics Data System (ADS)

    Grigoryan, M. S.

    2018-04-01

    This paper considers two connected contact problems on the interaction of stringers with an elastic semi-infinite plate. In the first problem, an elastic half-infinite continuous plate is reinforced on its boundary by two identical stringers exposed to a tensile external force. In the second problem, in the presence of the same stringers, the plate contains a collinear system of cracks on its vertical axis. The solution of both problems is reduced to the solution of singular integral equations (SIE) that are solved by a known numerical-analytical method.

  11. A surface analytical examination of Stringer particles in Al-Li-Cu alloys

    NASA Technical Reports Server (NTRS)

    Larson, L. A.; Avalos-Borja, M.; Pizzo, P. P.

    1983-01-01

    A surface analytical examination of powder metallurgy processed Al-Li-Cu alloys was conducted. The oxide stringer particles often found in these alloys was characterized. Particle characterization is important to more fully understand their impact on the stress corrosion and fracture properties of the alloy. The techniques used were SIMS (Secondary Ion Mass Spectroscopy) and SAM (Scanning Auger Microscopy). The results indicate that the oxide stringer particles contain both Al and Li with relatively high Li content and the Li compounds may be associated with the stringer particles, thereby locally depleting the adjacent matrix of Li solute.

  12. A surface-analytical examination of stringer particles in aluminum-lithium-copper alloys

    NASA Technical Reports Server (NTRS)

    Larson, L. A.; Avalos-Borja, M.; Pizzo, P. P.

    1984-01-01

    A surface analytical examination of powder metallurgy processed Al-Li-Cu alloys was conducted. The oxide stringer particles often found in these alloys are characterized. Particle characterization is important to more fully understand their impact on the stress corrosion and fracture properties of the alloy. The techniques used where SIMS (Secondary Ion Mass Spectroscopy) and SAM (Scanning Auger Microscopy). The results indicate that the oxide stringer particles contain both Al and LI with relatively high Li content and the Li compounds may be associated with the stringer particles, thereby locally depleting the adjacent matrix of Li solute.

  13. Reinforcement of Wood Pallets with Metal Connector Plates

    Treesearch

    John W. Clarke; Thomas E. McLain; Marshall S. White; Philip A. Araman

    1993-01-01

    Reinforcement of the damage-prone areas of wood pallet stringers with metal connector plates (MCPs) may increase useful pallet life or permit use of less desirable wood species. This will improve the utilization of our timber resources and landfill space. Whole pallets and individual stringers, reinforced at the inner notches, were tested in static bending. Stringer...

  14. Evaluation of Metal Connector Plates for Repair of Wood Pallet Stringers

    Treesearch

    John W. Clarke; Thomas E. McLain; Marshall S. White; Philip A. Araman

    1993-01-01

    Repair of damaged pallets with metal connector plates (MCPs or plates) may reduce woodwaste while providing high quality, economical pallets. This study evaluated some effects of MCP repair on the performance of pallet components and some provisions of a preliminary standard for MCP repair of pallets. Whole pallet stringers and notched segments of stringers were tested...

  15. An automated technique for manufacturing thermoplastic stringers in continuous length

    NASA Astrophysics Data System (ADS)

    Pantelakis, Sp.; Baxevani, E.; Spelz, U.

    In the present work an automated Continuous Compression Moulding Technique for the manufacture of stringers in continuous length is presented. The method combines pultrusion and hot-pressing. The technique is utilized for the production of L-shape stringers which are widely applied in aerospace constructions. The investigation was carried out on carbon reinforced PEEK (C/PEEK), as well as, for comparison, on the thermoplastic composites carbon reinforced polyethersulfon (C/PES), glass and carbon reinforced polyphenylene-sulfide (G/PPS, C/PPS) and Kevlar reinforced Polyamide 6 (K/PA 6). For the materials investigated the optimized process parameters for manufacturing the L-shape stringers were derived experimentally. To achieve this goal, the quality of the produced parts was controlled by using non-destructive testing techniques. Parts providing satisfactory quality were also tested destructively to measure their mechanical properties. The investigation results have shown the suitability of the technique to produce continuous length stringers.

  16. Pallet Users State Their Preferences For Used Pallets - Companion Stringers Cited as Biggest

    Treesearch

    Robert J. Bush; Ronen Roudik; Philip A. Araman

    1995-01-01

    A study recently completed by VA Tech in Blacksburg, VA, found that half companion stringers have the greatest negative impact on purchasers of used pallets, followed by split deckboards, protruding nails, and full companion stringers. Repairs using metal plates had relatively little affect on the value of the pallet. The study provides new information concerning the...

  17. Broken Stringers Can Be Recovered By Splicing, Research By Pallet Lab Shows

    Treesearch

    Chaille Brindley

    1997-01-01

    With the increasing prices of lumber, pallet manufacturers and recyclers are looking to squeeze every dollar out of their operations. A recent study on stringer repair reveals another potential area of the business that may be squeezed. The study by Dr. Marshall White, director of the pallet and container research laboratory at Virginia Tech, shows broken stringers can...

  18. Method for homogenizing alloys susceptible to the formation of carbide stringers and alloys prepared thereby

    DOEpatents

    Braski, David N.; Leitnaker, James M.

    1980-01-01

    A novel fabrication procedure prevents or eliminates the reprecipitation of segregated metal carbides such as stringers in Ti-modified Hastelloy N and stainless steels to provide a novel alloy having carbides uniformly dispersed throughout the matrix. The fabrication procedure is applicable to other alloys prone to the formation of carbide stringers. The process comprises first annealing the alloy at a temperature above the single phase temperature for sufficient time to completely dissolve carbides and then annealing the single phase alloy for an additional time to prevent the formation of carbide stringers upon subsequent aging or thermomechanical treatment.

  19. Geology of the Huron River pitchblende occurrence, Baraga County, Michigan

    USGS Publications Warehouse

    Vickers, R.C.

    1955-01-01

    Pitchblende and secondary uranium minerals occur as very small, discontinuous stringers and pods in calcite and quartz cementing the breccia within a low-angle shear zone that dips about 10 degrees to the southwest. The shear zone has a thickness of 10 to 30 feet and cuts black, locally carbonaceous slates of the upper Huronian Precambrian Michigamme slate. Mineral deposition during two hypogene stages and one supergene stage was identified in polished sections. The first phase consisted of the introduction of quartz and minor hematite into the sheared slate. After fracturing of the quartz the second stage was initiated by deposition of calcite, pyrite, rutile, pitchblende, bornite, sphalerite, chalcopyrite, galena, and greenockite. The supergene stage consisted of the development of metatyuyamunite, chalcopyrite, chalcocite, covellite, cuprite, volborthite, malachite, and goethite.

  20. Life extension of Structural Repairs – A statistical approach towards efficiency improvement

    NASA Astrophysics Data System (ADS)

    Deepashri, N. V.; Kalaiyappan, Mohan

    2018-05-01

    The life extension program of aircraft is taken up whenever aircraft’s intended life reaches close to its DSG (Design Service Goal). The Extended Service Goal (ESG) of an aircraft, in general, and structural repairs, in particular, is arrived at on the basis of F&DT (Fatigue & Damage Tolerance) analysis. Life extension program of aircraft consists of assessment of remaining life of all parts of the aircrafts including structural, mechanical, and electrical and avionics equipment and structural repairs. For life extension of stringer repair, as an example, it is required to re-assess the fatigue life of stringer in the presence of coupling under modified load spectrum. This is achieved by assessing the fatigue life of Web and Outer Flange (OF) part of stringers separately as per F&DT justification philosophy. Assessment of the fatigue life requires determination of stress concentration factor (Kt) for different combination of width, pitch, stringer thickness, coupling thickness and pad-up thickness of all stringer profiles available in different sections of fuselage. Determination of stress concentration factor for Web and Outer Flange of stringer profile covering entire ranges involves substantial number of Finite Element (FE) analysis. In order to optimise the number of FE runs, stress concentration factor is determined under worst repair factors combination (max. plate width; max. thickness; max. pitch; min. rivet dia.; and min. No. of rivets) resulting in conservative value. A parametric study of Web and Outer Flange data across stringer profiles were carried out and proven statistical techniques were used to find the optimal equation to predict stress concentration factor. This in turn reduced number of FE runs substantially for a given range of width, pitch, stringer thickness and so on. The use of optimal equation obtained through regression analysis is able to predict Kt within reasonable accuracy for a given range of inputs.

  1. Experimental Study of Deformation and of Effective Width in Axially Loaded Sheet-stringer Panels

    NASA Technical Reports Server (NTRS)

    Ramberg, Walter; MCPHERSON ALBERT E; Levy, Sam

    1939-01-01

    The deformation of two sheet-stringer panels subjected to end compression under carefully controlled end conditions was measured at a number of points and at a number of loads, most of which were above the load at which the sheet had begun to buckle. The two panels were identical except for the sheet, which was 0.70-inch 24st alclad for specimen 1 and 0.025-inch 24st aluminum alloy for specimen 6. A technique was developed for attaching Tuckerman optical strain gauges to the sheet without disturbing the strain distribution in the sheet by the method of attachment. This technique was used to explore the strain distribution in the sheet at various loads. The twisting and the bending of the stringers was measured by means of pointers attached to the stringers. The shape of the buckles in the sheet of specimen 6 was recorded at two loads by means of plaster casts. The sheet and the stringer loads at failure are compared with the corresponding loads for five similar panels tested at the Navy Model Basin. A detailed comparison is made between the measured deformation of the buckled sheet and the deformation calculated from approximate theories for the deformation in a rectangular sheet with freely supported edges buckling under end compression advanced by Timoshenko, Frankland, and Marguerre. The measured effective width for the specimens is compared with the effective width given by nine different relations for effective width as a function of the edge stress divided by the buckling stress of the sheet. The analysis of the measured stringer deformation is confined to an application of Southwell's method of plotting deformation against deformation over load. It was concluded that the stringer failure in both specimens were due to an instability in which the stringer was simultaneously twisted and bent as a column.

  2. The structure of the Zechstein 3 stringer in the northern Netherlands, and its implications for salt kinematics and rheology

    NASA Astrophysics Data System (ADS)

    Strozyk, Frank; Urai, Janos; Li, Shiyuan; Schmatz, Joyce; Biehl, Bianca; Reuning, Lars; Raith, Alexander; Abe, Steffen; van Gent, Heijn; de Keijzer, Martin; Kukla, Peter

    2016-04-01

    The thick, late Permian Zechstein evaporites in the northern Netherlands are exceptionally well imaged in extensive 3D seismic and well datasets. The prominent seismic reflections of the thick, anhydrite-rich Zechstein 3 stringer, which is encased in thick layers of rock salt, provide a basin-scale view of the 3D internal structure of the Zechstein salt. The interpretation of the Z3 stringer was used as a strain marker for the different intra-salt deformation styles and salt flows. Furthermore, models of competing rheologies (pressure solution vs. dislocation creep, Newtonian vs. Power law) were tested in numerical simulations of the gravitational sinking of Z3 stringer fragments through the salt over geologic time in the Tertiary. The results show that several structural stringer styles can be linked to regional variation in salt kinematics. These mainly comprise local early syn-depositional gravitational movement, passive salt diapirism by differential loading in the Triassic, and reactive diapirism during contractions starting in the Cretaceous. The thickness and deformation degree of the individual salt layers thereby played a major role in the development of regionally distinctive styles of intra-salt structures, which can be linked to breaking and fold patterns in the stringer. When differential stresses in the salt relaxed across large parts of the northern Netherlands in the Tertiary, stringer fragments physically isolated in the salt did not significantly sink through the salt. The salt surrounding the fragments can not have deformed by Newtonian solution-precipitation creep, because the fragments would have sunk to base salt. Considering also results from geomechanical modelling and analysis of Zechstein salt samples, we conclude that this behaviour can only be explained by strong changes in salt rheology to non-Newtonian.

  3. American football and fatal exertional heat stroke: a case study of Korey Stringer.

    PubMed

    Grundstein, Andrew; Knox, John A; Vanos, Jennifer; Cooper, Earl R; Casa, Douglas J

    2017-08-01

    On August 1, 2001, Korey Stringer, a Pro Bowl offensive tackle for the Minnesota Vikings, became the first and to date the only professional American football player to die from exertional heat stroke (EHS). The death helped raise awareness of the dangers of exertional heat illnesses in athletes and prompted the development of heat safety policies at the professional, collegiate, and interscholastic levels. Despite the public awareness of this death, no published study has examined in detail the circumstances surrounding Stringer's fatal EHS. Using the well-documented details of the case, our study shows that Stringer's fatal EHS was the result of a combination of physiological limitations, organizational and treatment failings, and extreme environmental conditions. The COMfort FormulA (COMFA) energy budget model was used to assess the relative importance of several extrinsic factors on Stringer's EHS, including weather conditions, clothing insulation, and activity levels. We found that Stringer's high-intensity training in relation to the oppressive environmental conditions was the most prominent factor in producing dangerous, uncompensable heat stress conditions and that the full football uniform played a smaller role in influencing Stringer's energy budget. The extreme energy budget levels that led to the fatal EHS would have been avoided according to our modeling through a combination of reduced intensity and lower clothing insulation. Finally, a long delay in providing medical treatment made the EHS fatal. These results highlight the importance of modern heat safety guidelines that provide controls on extrinsic factors, such as the adjustment of duration and intensity of training along with protective equipment modifications based on environmental conditions and the presence of an emergency action plan focused on rapid recognition and immediate on-site aggressive cooling of EHS cases.

  4. American football and fatal exertional heat stroke: a case study of Korey Stringer

    NASA Astrophysics Data System (ADS)

    Grundstein, Andrew; Knox, John A.; Vanos, Jennifer; Cooper, Earl R.; Casa, Douglas J.

    2017-08-01

    On August 1, 2001, Korey Stringer, a Pro Bowl offensive tackle for the Minnesota Vikings, became the first and to date the only professional American football player to die from exertional heat stroke (EHS). The death helped raise awareness of the dangers of exertional heat illnesses in athletes and prompted the development of heat safety policies at the professional, collegiate, and interscholastic levels. Despite the public awareness of this death, no published study has examined in detail the circumstances surrounding Stringer's fatal EHS. Using the well-documented details of the case, our study shows that Stringer's fatal EHS was the result of a combination of physiological limitations, organizational and treatment failings, and extreme environmental conditions. The COMfort FormulA (COMFA) energy budget model was used to assess the relative importance of several extrinsic factors on Stringer's EHS, including weather conditions, clothing insulation, and activity levels. We found that Stringer's high-intensity training in relation to the oppressive environmental conditions was the most prominent factor in producing dangerous, uncompensable heat stress conditions and that the full football uniform played a smaller role in influencing Stringer's energy budget. The extreme energy budget levels that led to the fatal EHS would have been avoided according to our modeling through a combination of reduced intensity and lower clothing insulation. Finally, a long delay in providing medical treatment made the EHS fatal. These results highlight the importance of modern heat safety guidelines that provide controls on extrinsic factors, such as the adjustment of duration and intensity of training along with protective equipment modifications based on environmental conditions and the presence of an emergency action plan focused on rapid recognition and immediate on-site aggressive cooling of EHS cases.

  5. A theoretical analysis of the free vibrations of ring- and/or stringer-stiffened elliptical cylinders with arbitrary end conditions. Volume 1: Analytical derivation and applications

    NASA Technical Reports Server (NTRS)

    Boyd, D. E.; Rao, C. K. P.

    1973-01-01

    The derivation and application of a Rayleigh-Ritz modal vibration analysis are presented for ring and/or stringer stiffened noncircular cylindrical shells with arbitrary end conditions. Comparisons with previous results from experimental and analytical studies showed this method of analysis to be accurate for a variety of end conditions. Results indicate a greater effect of rings on natural frequencies than of stringers.

  6. Stress Analysis and Testing at the Marshall Space Flight Center to Study Cause and Corrective Action of Space Shuttle External Tank Stringer Failures

    NASA Technical Reports Server (NTRS)

    Wingate, Robert J.

    2012-01-01

    After the launch scrub of Space Shuttle mission STS-133 on November 5, 2010, large cracks were discovered in two of the External Tank intertank stringers. The NASA Marshall Space Flight Center, as managing center for the External Tank Project, coordinated the ensuing failure investigation and repair activities with several organizations, including the manufacturer, Lockheed Martin. To support the investigation, the Marshall Space Flight Center formed an ad-hoc stress analysis team to complement the efforts of Lockheed Martin. The team undertook six major efforts to analyze or test the structural behavior of the stringers. Extensive finite element modeling was performed to characterize the local stresses in the stringers near the region of failure. Data from a full-scale tanking test and from several subcomponent static load tests were used to confirm the analytical conclusions. The analysis and test activities of the team are summarized. The root cause of the stringer failures and the flight readiness rationale for the repairs that were implemented are discussed.

  7. Stringer Bending Test Helps Diagnose and Prevent Cracks in the Space Shuttle's External Tank

    NASA Technical Reports Server (NTRS)

    Saxon, Joseph B.; Swanson, Gregory R.; Ondocsin, William P.; Wingate, Robert J.

    2012-01-01

    Space Shuttle Discovery's last mission, STS-133, was scheduled to launch on November 5, 2010. Just hours before liftoff, a hydrogen leak at an umbilical connection scrubbed the launch attempt. After the scrub, further inspection revealed a large crack in the foam insulation covering the External Tank, ET-137. Video replay of the launch attempt confirmed the crack first appeared as cryogenic propellants were being loaded into the ET. When the cracked foam was removed, technicians found the underlying stringer had two 9-inch-long cracks. Further inspection revealed a total of 5 of the 108 ET stringers had cracked. NASA and Lockheed Martin immediately launched an aggressive campaign to understand the cracks and repair the stringers in ET-137, targeting February 2011 as the new launch date for STS-133. Responsibilities for the various aspects of the investigation were widely distributed among NASA centers and organizations. This paper will focus on lab testing at Marshall Space Flight Center (MSFC) in Huntsville, Alabama that was intended to replicate the stringer failure and gauge the effect of proposed countermeasures.

  8. Natural Fatigue Crack Initiation and Detection in High Quality Spur Gears

    DTIC Science & Technology

    2012-06-01

    Natural Fatigue Crack Initiation and Detection in High Quality Spur Gears by David “Blake” Stringer, Ph.D., Kelsen E. LaBerge, Ph.D., Cory...0383 June 2012 Natural Fatigue Crack Initiation and Detection in High Quality Spur Gears David “Blake” Stringer and Ph.D., Kelsen E. LaBerge...Quality Spur Gears 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) David “Blake” Stringer, Ph.D., Kelsen E

  9. Stresses Around Rectangular Cut-outs with Reinforced Coaming Stringers

    NASA Technical Reports Server (NTRS)

    Kuhn, Paul; Rafel, Norman; Griffith, George E

    1947-01-01

    Strain measurements and strength tests were made on six skin-stringer panels under axial load. Three of these panels had short rectangular cut-outs, and three a long one. The width of the cut-out was about one-half of the width of the panel. Three types of coating stringers were used: without reinforcement, with riveted-up reinforcement, or with integral reinforcement. The strain measurements were found to be in good agreement with a previously published theory adapted where necessary by making overlapping assumptions.

  10. Granite-hosted molybdenite mineralization from Archean Bundelkhand craton-molybdenite characterization, host rock mineralogy, petrology, and fluid inclusion characteristics of Mo-bearing quartz

    NASA Astrophysics Data System (ADS)

    Pati, J. K.; Panigrahi, M. K.; Chakarborty, M.

    2014-06-01

    The dominantly high-K, moderate to high SiO2 containing, variably fractionated, volcanic-arc granitoids (± sheared) from parts of Bundelkhand craton, northcentral India are observed to contain molybdenite (Mo) in widely separated 23 locations in the form of specks, pockets, clots and stringers along with quartz ± pyrite ± arsenopyrite ± chalcopyrite ± bornite ± covellite ± galena ± sphalerite and in invisible form as well. The molybdenite mineralization is predominantly associated with Bundelkhand Tectonic Zone, Raksa Shear Zone, and localized shear zones. The incidence of molybdenite is also observed within sheared quartz and tonalite-trondhjemite-granodiorite (TTG) gneisses. The fluid inclusion data show the presence of bi-phase (H2O-CO2), hypersaline and moderate temperature (100°-300°C) primary stretched fluid inclusions suggesting a possible hydrothermal origin for the Mo-bearing quartz occurring within variably deformed different granitoids variants of Archean Bundelkhand craton.

  11. Geology, ore facies and sulfur isotopes geochemistry of the Nudeh Besshi-type volcanogenic massive sulfide deposit, southwest Sabzevar basin, Iran

    NASA Astrophysics Data System (ADS)

    Maghfouri, Sajjad; Rastad, Ebrahim; Mousivand, Fardin; Lin, Ye; Zaw, Khin

    2016-08-01

    The southwest Sabzevar basin is placed in the southwestern part of a crustal domain known as the Sabzevar zone, at the north of Central Iranian microcontinent. This basin hosts abundant mineral deposits; particularly of the Mn exhalative and Cu-Zn volcanogenic massive sulfide (VMS) types. The evolution of this basin is governed by the Neo-tethys oceanic crust subduction beneath the Central Iranian microcontinent and by the resulting continental arc (Sanandaj-Sirjan) and back-arc (Sabzevar-Naien). This evolution followed two major sequences: (I) Lower Late Cretaceous Volcano-Sedimentary Sequence (LLCVSS), which is indicated by fine-grained siliciclastic sediments, gray basic coarse-grained different pyroclastic rocks and bimodal volcanism. During this stage, tuff-hosted stratiform, exhalative Mn deposits (Nudeh, Benesbourd, Ferizy and Goft), oxide Cu deposits (Garab and Ferizy) and Cu-Zn VMS (Nudeh, Chun and Lala) deposits formed. (II) Upper Late Cretaceous Sedimentary Dominated Sequence (ULCSS), including pelagic limestone, marly tuff, silty limestone and marl with minor andesitic tuff rocks. The economically most important Mn (Zakeri and Cheshmeh-sefid) deposits of Sabzevar zone occur within the marly tuff of this sequence. The Nudeh Cu-Zn volcanogenic massive sulfide (VMS) deposit is situated in the LLCVSS. The host-rock of deposits consists of alkali olivine basalt flow and tuffaceous silty sandstone. Mineralization occurs as stratiform blanket-like and tabular orebodies. Based on ore body structure, mineralogy, and ore fabric, we recognize three different ore facies in the Nudeh deposit: (1) a stringer zone, consisting of a discordant mineralization of sulfides forming a stockwork of sulfide-bearing quartz veins cutting the footwall volcano-sedimentary rocks; (2) a massive ore, consisting of massive replacement pyrite, chalcopyrite, sphalerite and Friedrichite with magnetite; (3) bedded ore, with laminated to disseminated pyrite, and chalcopyrite. Chloritization, silicification, sericitization and epidotization are the main wall-rock alterations; alteration intensity increases towards the stringer zone. The δ34S composition of the sulfides ranges from -1.5‰ to +3.69‰ with a general increase of δ34S ratios of massive ore facies to stockwork zone. The heavier values indicate that some of the sulfur was derived from seawater sulfate that was ultimately thermochemically reduced in deep hydrothermal reaction zones. Sulfur isotopes, along with sedimentological, textural, petrological, mineralogical, and geochemical evidences, suggest that this deposit should be classified as a Besshi-type VMS ore deposit.

  12. 12. View of bridge underside showing deck beams, stringers and ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    12. View of bridge underside showing deck beams, stringers and center pier. Jet Lowe, photographer, 1983 - Neshanic Station Lenticular Truss Bridge, State Route 567, spanning South Branch of Raritan River, Neshanic Station, Somerset County, NJ

  13. Iron Framing Axonometric, Stringer, IBeam, Channel, Composite TieBeam, and Small ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    Iron Framing Axonometric, Stringer, I-Beam, Channel, Composite Tie-Beam, and Small and Large Phoenix Columns - Washington Monument, High ground West of Fifteenth Street, Northwest, between Independence & Constitution Avenues, Washington, District of Columbia, DC

  14. Effect of Buckling Modes on the Fatigue Life and Damage Tolerance of Stiffened Structures

    NASA Technical Reports Server (NTRS)

    Davila, Carlos G.; Bisagni, Chiara; Rose, Cheryl A.

    2015-01-01

    The postbuckling response and the collapse of composite specimens with a co-cured hat stringer are investigated experimentally and numerically. These specimens are designed to evaluate the postbuckling response and the effect of an embedded defect on the collapse load and the mode of failure. Tests performed using controlled conditions and detailed instrumentation demonstrate that the damage tolerance, fatigue life, and collapse loads are closely tied with the mode of the postbuckling deformation, which can be different between two nominally identical specimens. Modes that tend to open skin/stringer defects are the most damaging to the structure. However, skin/stringer bond defects can also propagate under shearing modes. In the proposed paper, the effects of initial shape imperfections on the postbuckling modes and the interaction between different postbuckling deformations and the propagation of skin/stringer bond defects under quasi-static or fatigue loads will be examined.

  15. DETAIL OF FLOORBEAM CONNECTIONS AND STRINGERS FROM THE UNDERSIDE OF ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    DETAIL OF FLOORBEAM CONNECTIONS AND STRINGERS FROM THE UNDERSIDE OF THE BRIDGE; NOTE CABLES ADDED TO STRENGTHEN THE LOWER CHORDS OF THE TRUSS - Bedford County Bridge No. 4, Township Route 655 spanning Yellow Creek, Hopewell, Bedford County, PA

  16. Mission Command: Making it work at Battalion Level

    DTIC Science & Technology

    2013-04-01

    National Training Center, CA, February 2012. 29 Litwin , G.H., and R.A.Stringer, Motivation & Organizational Climate, Harvard University Press...for Joint Land Operations, Washington, DC: Joint Staff, 29 June 2010. Litwin , George H., and Robert A. Stringer Jr., Motivation & Organizational

  17. KSC-2011-1123

    NASA Image and Video Library

    2011-01-18

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank continues in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians are modifying 94 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges. After the modifications of the stringers are complete, foam insulation will be re-applied to the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is targeted for Feb. 24, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  18. KSC-2011-1124

    NASA Image and Video Library

    2011-01-18

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank continues in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians are modifying 94 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges. After modifications to the stringers are complete, foam insulation will be re-applied to the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is targeted for Feb. 24. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  19. KSC-2011-1121

    NASA Image and Video Library

    2011-01-18

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank continues in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians are modifying 94 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges. After the modifications of the stringers are complete, foam insulation will be re-applied to the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is targeted for Feb. 24, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  20. KSC-2011-1122

    NASA Image and Video Library

    2011-01-18

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank continues in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians are modifying 94 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges. After the modifications of the stringers are complete, foam insulation will be re-applied to the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is targeted for Feb. 24, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  1. KSC-2011-1120

    NASA Image and Video Library

    2011-01-18

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank continues in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians are modifying 94 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges. After the modifications of the stringers are complete, foam insulation will be re-applied to the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is targeted for Feb. 24, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  2. Fabrication and evaluation of brazed titanium-clad borsic/aluminum skin-stringer panels

    NASA Technical Reports Server (NTRS)

    Bales, T. T.; Royster, D. M.; Mcwithey, R. R.

    1980-01-01

    A successful brazing process was developed and evaluated for fabricating full-scale titanium-clad Borsic/aluminum skin-stringer panels. A panel design was developed consisting of a hybrid composite skin reinforced with capped honeycomb-core stringers. Six panels were fabricated for inclusion in the program which included laboratory testing of panels at ambient temperatures and 533 K (500 F) and flight service evaluation on the NASA Mach 3 YF-12 airplane. All panels tested met or exceeded stringent design requirements and no deleterious effects on panel properties were detected followng flight service evaluation on the YF-12 airplane.

  3. Assessment of the Damage Tolerance of Postbuckled Hat-Stiffened Panels Using Single-Stringer Specimens

    NASA Technical Reports Server (NTRS)

    Bisagni, Chiara; Vescovini, Riccardo; Davila, Carlos G.

    2010-01-01

    A procedure is proposed for the assessment of the damage tolerance and collapse of stiffened composite panels using a single-stringer compression specimen. The dimensions of the specimen are determined such that the specimen s nonlinear response and collapse are representative of an equivalent multi-stringer panel in compression. Experimental tests are conducted on specimens with and without an embedded delamination. A shell-based finite element model with intralaminar and interlaminar damage capabilities is developed to predict the postbuckling response as well as the damage evolution from initiation to collapse.

  4. Compressive Loading and Modeling of Stitched Composite Stiffeners

    NASA Technical Reports Server (NTRS)

    Leone, Frank A., Jr.; Jegley, Dawn C.; Linton, Kim A.

    2016-01-01

    A series of single-frame and single-stringer compression tests were conducted at NASA Langley Research Center on specimens harvested from a large panel built using the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept. Different frame and stringer designs were used in fabrication of the PRSEUS panel. In this paper, the details of the experimental testing of single-frame and single-stringer compression specimens are presented, as well as discussions on the performance of the various structural configurations included in the panel. Nonlinear finite element models were developed to further understand the failure processes observed during the experimental campaign.

  5. Membrane protection for steel stringer tops : Yaquina Bay Bridge, Newport, Oregon : construction report.

    DOT National Transportation Integrated Search

    1980-10-01

    The experimental feature of this project was to evaluate the application and performance of Chevron Industrial Membrane applied to the tops of steel deck stringers and other similar members as corrosion protection in conjunction with the deck replace...

  6. Trestle #1, detail of stringers and spacers on northeast end ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    Trestle #1, detail of stringers and spacers on northeast end of deck. View to southwest - Promontory Route Railroad Trestles, S.P. Trestle 779.91, One mile southwest of junction of State Highway 83 and Blue Creek, Corinne, Box Elder County, UT

  7. Live load rating of short span highway bridges as controlled by the exterior girder.

    DOT National Transportation Integrated Search

    1977-01-01

    The 1973 AASHTO Standard Specifications for Highway Bridge introduced the requirement that "In no case shall an exterior stringer have less carrying capacity than an interior stringer." This statement resulted from the concern that many original exte...

  8. 42. Fixed Span; General View of the Floor Beam, Stringer, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    42. Fixed Span; General View of the Floor Beam, Stringer, & Lateral Bracing System; looking S. (from near to far: 6L & R, 5L & R, 4 L & R). - Pacific Shortline Bridge, U.S. Route 20,spanning Missouri River, Sioux City, Woodbury County, IA

  9. Panel Stiffener Debonding Analysis using a Shell/3D Modeling Technique

    NASA Technical Reports Server (NTRS)

    Krueger, Ronald; Ratcliffe, James G.; Minguet, Pierre J.

    2008-01-01

    A shear loaded, stringer reinforced composite panel is analyzed to evaluate the fidelity of computational fracture mechanics analyses of complex structures. Shear loading causes the panel to buckle. The resulting out -of-plane deformations initiate skin/stringer separation at the location of an embedded defect. The panel and surrounding load fixture were modeled with shell elements. A small section of the stringer foot, web and noodle as well as the panel skin near the delamination front were modeled with a local 3D solid model. Across the width of the stringer fo to, the mixed-mode strain energy release rates were calculated using the virtual crack closure technique. A failure index was calculated by correlating the results with a mixed-mode failure criterion of the graphite/epoxy material. The objective was to study the effect of the fidelity of the local 3D finite element model on the computed mixed-mode strain energy release rates and the failure index.

  10. Panel-Stiffener Debonding and Analysis Using a Shell/3D Modeling Technique

    NASA Technical Reports Server (NTRS)

    Krueger, Ronald; Ratcliffe, James G.; Minguet, Pierre J.

    2007-01-01

    A shear loaded, stringer reinforced composite panel is analyzed to evaluate the fidelity of computational fracture mechanics analyses of complex structures. Shear loading causes the panel to buckle. The resulting out-of-plane deformations initiate skin/stringer separation at the location of an embedded defect. The panel and surrounding load fixture were modeled with shell elements. A small section of the stringer foot, web and noodle as well as the panel skin near the delamination front were modeled with a local 3D solid model. Across the width of the stringer foot, the mixed-mode strain energy release rates were calculated using the virtual crack closure technique. A failure index was calculated by correlating the results with a mixed-mode failure criterion of the graphite/epoxy material. The objective was to study the effect of the fidelity of the local 3D finite element model on the computed mixed-mode strain energy release rates and the failure index.

  11. Fuselage Versus Subcomponent Panel Response Correlation Based on ABAQUS Explicit Progressive Damage Analysis Tools

    NASA Technical Reports Server (NTRS)

    Gould, Kevin E.; Satyanarayana, Arunkumar; Bogert, Philip B.

    2016-01-01

    Analysis performed in this study substantiates the need for high fidelity vehicle level progressive damage analyses (PDA) structural models for use in the verification and validation of proposed sub-scale structural models and to support required full-scale vehicle level testing. PDA results are presented that capture and correlate the responses of sub-scale 3-stringer and 7-stringer panel models and an idealized 8-ft diameter fuselage model, which provides a vehicle level environment for the 7-stringer sub-scale panel model. Two unique skin-stringer attachment assumptions are considered and correlated in the models analyzed: the TIE constraint interface versus the cohesive element (COH3D8) interface. Evaluating different interfaces allows for assessing a range of predicted damage modes, including delamination and crack propagation responses. Damage models considered in this study are the ABAQUS built-in Hashin procedure and the COmplete STress Reduction (COSTR) damage procedure implemented through a VUMAT user subroutine using the ABAQUS/Explicit code.

  12. Preliminary report on the Comet area, Jefferson County, Montana

    USGS Publications Warehouse

    Becraft, George Earle

    1953-01-01

    Several radioactivity anomalies and a few specimens of sooty pitchblende and other uranium minerals have been found on the mine dumps of formerly productive base- and precious-metal mines along the Comet-Gray Eagle shear zone in the Comet area in southwestern Montana. The shear zone is from 50 to 200 feet wide and has been traced for at least 5? miles. It trends N. 80 ? W. across the northern part of the area and cuts the quartz monzonitic rocks of the Boulder batholith and younger silicic intrusive rocks, as well as prebatholithic volcanic rocks, and is in turn cut by dacite and andesite dikes. The youngest period of mineralization is represented by chalcedonic vein zones comprising one or more discontinuous stringers and veins of cryptocrystalline silica in silicified quartz monzonite and in alaskite that has not been appreciably silicified. In some places these zones contain no distinct chalcedonic veins but are represented only by silicified quartz monzonite. These zones locally contain uranium in association with very small amounts of pyrite, galena, ruby silver, arqentite, native silver, molybdenite, chalcopyrite, arsenopyrite, and barite. At the Free Enterprise mine, uranium has been produced from a narrow chalcedonic vein that contains disseminated secondary uranium minerals and local small pods of pitchblende and also from disseminated secondary uranium ,minerals in the adjacent quartz monzonite. Undiscovered deposits of uranium ore may occur spatially associated with the base- and precious-metal deposits along the Comet-Gray Eagle shear zone and with chalcedonic vein zones similar to the Free Enterprise.

  13. Repair & Reinforcing Pallet Stringers With Metal Plates

    Treesearch

    John W. Clarke; Thomas E. McLain; Marshall S. White; Philip A. Araman

    1993-01-01

    Notches significantly reduce the bending strength and life expectancy of stringer-class pallets with partial 4-way entry. Common failures include cracking between the notches (BN), bending failures in the region above the notch (AN) and splitting of end feet. In recent years, several suppliers and manufacturers of metal connector plates (MCPs) have developed equipment...

  14. 15. DETAIL OF UNDERSIDE OF BRIDGE, SHOWING LONGITUDINAL STRINGERS SUPPORTING ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    15. DETAIL OF UNDERSIDE OF BRIDGE, SHOWING LONGITUDINAL STRINGERS SUPPORTING WOODEN DECK AND RESTING ON TRANSVERSE FLOOR BEAMS. DIAGONAL EYE BARS FOR REINFORCEMENT ARE SEEN AT CENTER; VIEW FROM SOUTH BANK. - Mitchell's Mill Bridge, Spanning Winter's Run on Carrs Mill Road, west of Bel Air, Bel Air, Harford County, MD

  15. 20. Photocopy of drawing, Stringers for Bridge at So. Norwalk ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    20. Photocopy of drawing, Stringers for Bridge at So. Norwalk for the N.Y., N.H. and H.R.R., Contract No. 3000, Berlin Iron Bridge Company, dated July 8, 1895. Original on file with Metro North Commuter Railroad. - South Norwalk Railroad Bridge, South Main & Washington Streets, Norwalk, Fairfield County, CT

  16. Residual Strength Pressure Tests and Nonlinear Analyses of Stringer- and Frame-Stiffened Aluminum Fuselage Panels with Longitudinal Cracks

    NASA Technical Reports Server (NTRS)

    Young, Richard D.; Rouse, Marshall; Ambur, Damodar R.; Starnes, James H., Jr.

    1999-01-01

    The results of residual strength pressure tests and nonlinear analyses of stringer- and frame-stiffened aluminum fuselage panels with longitudinal cracks are presented. Two types of damage are considered: a longitudinal crack located midway between stringers, and a longitudinal crack adjacent to a stringer and along a row of fasteners in a lap joint that has multiple-site damage (MSD). In both cases, the longitudinal crack is centered on a severed frame. The panels are subjected to internal pressure plus axial tension loads. The axial tension loads are equivalent to a bulkhead pressure load. Nonlinear elastic-plastic residual strength analyses of the fuselage panels are conducted using a finite element program and the crack-tip-opening-angle (CTOA) fracture criterion. Predicted crack growth and residual strength results from nonlinear analyses of the stiffened fuselage panels are compared with experimental measurements and observations. Both the test and analysis results indicate that the presence of MSD affects crack growth stability and reduces the residual strength of stiffened fuselage shells with long cracks.

  17. Residual Strength Pressure Tests and Nonlinear Analyses of Stringer-and Frame-Stiffened Aluminum Fuselage Panels with Longitudinal Cracks

    NASA Technical Reports Server (NTRS)

    Young, Richard D.; Rouse, Marshall; Ambur, Damodar R.; Starnes, James H., Jr.

    1998-01-01

    The results of residual strength pressure tests and nonlinear analyses of stringer- and frame-stiffened aluminum fuselage panels with longitudinal cracks are presented. Two types of damage are considered: a longitudinal crack located midway between stringers, and a longitudinal crack adjacent to a stringer and along a row of fasteners in a lap joint that has multiple-site damage (MSD). In both cases, the longitudinal crack is centered on a severed frame. The panels are subjected to internal pressure plus axial tension loads. The axial tension loads are equivalent to a bulkhead pressure load. Nonlinear elastic-plastic residual strength analyses of the fuselage panels are conducted using a finite element program and the crack-tip-opening-angle (CTOA) fracture criterion. Predicted crack growth and residual strength results from nonlinear analyses of the stiffened fuselage panels are compared with experimental measurements and observations. Both the test and analysis results indicate that the presence of MSD affects crack growth stability and reduces the residual strength of stiffened fuselage shells with long cracks.

  18. Skin-Stiffener Debond Prediction Based on Computational Fracture Analysis

    NASA Technical Reports Server (NTRS)

    Krueger, Ronald; Minguet, Pierre J.; Gates, Tom (Technical Monitor)

    2005-01-01

    Interlaminar fracture mechanics has proven useful for characterizing the onset of delaminations in composites and has been used with limited success primarily to investigate onset in fracture toughness specimens and laboratory size coupon type specimens. Future acceptance of the methodology by industry and certification authorities however, requires the successful demonstration of the methodology on structural level. For this purpose a panel was selected that is reinforced with stringers. Shear loading causes the panel to buckle and the resulting out-of-plane deformations initiate skin/stringer separation at the location of an embedded defect. For finite element analysis, the panel and surrounding load fixture were modeled with shell elements. A small section of the stringer foot and the panel in the vicinity of the embedded defect were modeled with a local 3D solid model. Across the width of the stringer foot the mixed-mode strain energy release rates were calculated using the virtual crack closure technique. A failure index was calculated by correlating the results with the mixed-mode failure criterion of the graphite/epoxy material. For small applied loads the failure index is well below one across the entire width. With increasing load the failure index approaches one first near the edge of the stringer foot from which delamination is expected to grow. With increasing delamination lengths the buckling pattern of the panel changes and the failure index increases which suggests that rapid delamination growth from the initial defect is to be expected.

  19. 75 FR 1536 - Airworthiness Directives; The Boeing Company Model 737-600, -700, and -800 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-12

    ... stringers of the wing center section for drill starts, and applicable related investigative and corrective actions. This AD results from drill starts being found on the free flange of the lower stringers of the... this AD to prevent cracks from propagating from drill starts in the free flange, vertical web, and...

  20. Classifying defects in pallet stringers by ultrasonic scanning

    Treesearch

    Mohammed F. Kabir; Daniel L. Schmoldt; Philip A. Araman; Mark E. Schafer; Sang-Mook Lee

    2003-01-01

    Detecting and classifying defects are required to grade and sort pallet parts. Use of quality parts can extend the life cycle of pallets and can reduce long-term cost. An investigation has been carried out to detect and classify defects in yellow-poplar (Liriodendron tulipifera, L.) and red oak (Quercus rubra, L.) stringers using ultrasonic scanning. Data were...

  1. 19. Photocopy of drawing, typical floor beam and stringer, Bridge ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    19. Photocopy of drawing, typical floor beam and stringer, Bridge No. 79B, Main & Washington Sts., So. Norwalk, Ct., N. Y. Division, N.Y., N.H. and H.R.R., dated April 23, 1895. Original on file with Metro North Commuter Railroad. - South Norwalk Railroad Bridge, South Main & Washington Streets, Norwalk, Fairfield County, CT

  2. Modal analysis and dynamic stresses for acoustically excited shuttle insulation tiles

    NASA Technical Reports Server (NTRS)

    Ojalvo, I. U.; Ogilvie, P. L.

    1975-01-01

    Improvements and extensions to the RESIST computer program developed for determining the normalized modal stress response of shuttle insulation tiles are described. The new version of RESIST can accommodate primary structure panels with closed-cell stringers, in addition to the capability for treating open-cell stringers. In addition, the present version of RESIST numerically solves vibration problems several times faster than its predecessor. A new digital computer program, titled ARREST (Acoustic Response of Reusable Shuttle Tiles) is also described. Starting with modal information contained on output tapes from RESIST computer runs, ARREST determines RMS stresses, deflections and accelerations of shuttle panels with reusable surface insulation tiles. Both programs are applicable to stringer stiffened structural panels with or without reusable surface insulation titles.

  3. Geology of the Vienna Mineralized Area, Blaine and Camas Counties, Idaho

    USGS Publications Warehouse

    Mahoney, J. Brian; Horn, Michael C.

    2005-01-01

    The Vienna mineralized area of south-central Idaho was an important silver-lead-producing district in the late 1800s and has intermittently produced lead, silver, zinc, copper, and gold since that time. The district is underlain by biotite granodiorite of the Cretaceous Idaho batholith, and all mineral deposits are hosted by the biotite granodiorite. The granodiorite intrudes Paleozoic sedimentary rocks of the Sun Valley Group, is overlain by rocks of the Eocene Challis Volcanic Group, and is cut by numerous northeast-trending Eocene faults and dikes. Two mineralogically and texturally distinct vein types are present in a northwest- and east-trending conjugate shear-zone system. The shear zones postdate granodiorite emplacement and joint formation, but predate Eocene fault and dike formation. Ribbon veins consist of alternating bands of massive vein quartz and silver-sulfide (proustite and pyrargyrite) mineral stringers. The ribbon veins were sheared and brecciated during multiple phases of injection of mineralizing fluids. A quartz-sericite-pyrite-galena vein system was subsequently emplaced in the brecciated shear zones. Both vein systems are believed to be the product of mesothermal, multiphase mineralization. K-Ar dating of shear-zone sericite indicates that sericitization occurred at 80.7?2.8 Ma; thus mineralization in the Vienna mineralized area probably is Late Cretaceous in age.

  4. Methodology for Selection of Optimum Light Stringers in Functionally Graded Panels Designed for Prescribed Fundamental Frequency or Buckling Load

    NASA Astrophysics Data System (ADS)

    Birman, Victor; Byrd, Larry W.

    2008-02-01

    The interest to functionally graded materials (FGM) and structures has been generated by their potential advantages, including enhanced thermal properties, reduced or eliminated delamination concerns, a potential for an improved stress distribution, etc. Various aspects of the processing, design, micromechanics and analysis of FGM have been outlined in a number of reviews, mentioned here are [1-3]. In particular, functionally graded panels may be advantageous compared to their conventional counterparts in numerous applications. However, a typical FGM panel is asymmetric about its middle plane resulting in lower buckling loads and fundamental frequencies as well as higher stresses and deformations than the counterpart with a symmetric distribution of the same constituents. The reduced stiffness of FGM panels can be compensated by reinforcing them with stringers. For example, metallic stringers at the metal-rich surface of a FGM ceramic-metal panel may provide an efficient solution enabling a designer to increase both buckling loads as well as natural frequencies. The list of studies on optimization of FGM is extensive as could be anticipated for such tailored structural elements. For example, recent papers by Batra and his collaborators present optimization of the natural frequencies of a FGM plate through material grading [4] and through the graded fiber orientation [5]. The present paper is concerned with an optimum design of the system of stringers for a specified FGM panel. The task is to design the lightest system of stringers enabling the panel to achieve prescribed buckling loads or fundamental frequency.

  5. Ten Years of Change in Sierran Stringer Meadows: An Evaluation of Range Condition Models

    Treesearch

    Barbara H. Allen

    1989-01-01

    Grazed Sierra Nevada stringer meadow systems were sampled on Blodgett Forest Research Station in northern California between 1977 and 1987 to determine cattle use, and to examine changes in production and species composition over time. Utilization of meadow species averaged 61 percent over the 10 years, but use increased to more than 80 percent utilization after 1985....

  6. Leading Civilian Personnel.

    DTIC Science & Technology

    1988-04-08

    relationship between leadership style and organizational climate which, in turn, has a direct effect on performance. In their experiments, Litwin and Stringer...was derived from findings concerning the relationship between group norms and organizational climate. Litwin and Stringer report that, "Behavioral...the inner world of ideas. S: Sensing would rather work with known facts than look for possibilities and relationships . T: Thinkng. base judgements on

  7. 76 FR 4224 - Airworthiness Directives; The Boeing Company Model 767-300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-25

    ... backup structure at the lower VHF antenna cutout at station 1197 + 99 between stringers 39 left and 39... periphery of the VHF antenna baseplate at station 1197 + 99. We are issuing this AD to detect and correct... lower VHF antenna cutout at station 1197 + 99 between stringers 39L and 39R, and corrective actions if...

  8. CORSSTOL: Cylinder Optimization of Rings, Skin, and Stringers with Tolerance sensitivity

    NASA Technical Reports Server (NTRS)

    Finckenor, J.; Bevill, M.

    1995-01-01

    Cylinder Optimization of Rings, Skin, and Stringers with Tolerance (CORSSTOL) sensitivity is a design optimization program incorporating a method to examine the effects of user-provided manufacturing tolerances on weight and failure. CORSSTOL gives designers a tool to determine tolerances based on need. This is a decisive way to choose the best design among several manufacturing methods with differing capabilities and costs. CORSSTOL initially optimizes a stringer-stiffened cylinder for weight without tolerances. The skin and stringer geometry are varied, subject to stress and buckling constraints. Then the same analysis and optimization routines are used to minimize the maximum material condition weight subject to the least favorable combination of tolerances. The adjusted optimum dimensions are provided with the weight and constraint sensitivities of each design variable. The designer can immediately identify critical tolerances. The safety of parts made out of tolerance can also be determined. During design and development of weight-critical systems, design/analysis tools that provide product-oriented results are of vital significance. The development of this program and methodology provides designers with an effective cost- and weight-saving design tool. The tolerance sensitivity method can be applied to any system defined by a set of deterministic equations.

  9. KSC-2011-1005

    NASA Image and Video Library

    2011-01-05

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank begins in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians will modify 32 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges where they attach to the thrust panel area. The thrust panel is where the tank meets the two solid rocket boosters and sees the most stress during the flight into orbit. After the modifications and additional scans of the stringers are complete, foam insulation will be re-applied. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller

  10. KSC-2011-1003

    NASA Image and Video Library

    2011-01-05

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank begins in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians will modify 32 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges where they attach to the thrust panel area. The thrust panel is where the tank meets the two solid rocket boosters and sees the most stress during the flight into orbit. After the modifications and additional scans of the stringers are complete, foam insulation will be re-applied. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller

  11. KSC-2011-1002

    NASA Image and Video Library

    2011-01-05

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank begins in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians will modify 32 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges where they attach to the thrust panel area. The thrust panel is where the tank meets the two solid rocket boosters and sees the most stress during the flight into orbit. After the modifications and additional scans of the stringers are complete, foam insulation will be re-applied. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller

  12. KSC-2011-1000

    NASA Image and Video Library

    2011-01-05

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank begins in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians will modify 32 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges where they attach to the thrust panel area. The thrust panel is where the tank meets the two solid rocket boosters and sees the most stress during the flight into orbit. After the modifications and additional scans of the stringers are complete, foam insulation will be re-applied. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller

  13. KSC-2011-1004

    NASA Image and Video Library

    2011-01-05

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank begins in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians will modify 32 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges where they attach to the thrust panel area. The thrust panel is where the tank meets the two solid rocket boosters and sees the most stress during the flight into orbit. After the modifications and additional scans of the stringers are complete, foam insulation will be re-applied. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller

  14. KSC-2011-1006

    NASA Image and Video Library

    2011-01-05

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank begins in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians will modify 32 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges where they attach to the thrust panel area. The thrust panel is where the tank meets the two solid rocket boosters and sees the most stress during the flight into orbit. After the modifications and additional scans of the stringers are complete, foam insulation will be re-applied. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller

  15. KSC-2011-1001

    NASA Image and Video Library

    2011-01-05

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank begins in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians will modify 32 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges where they attach to the thrust panel area. The thrust panel is where the tank meets the two solid rocket boosters and sees the most stress during the flight into orbit. After the modifications and additional scans of the stringers are complete, foam insulation will be re-applied. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller

  16. KSC-2010-5762

    NASA Image and Video Library

    2010-12-02

    CAPE CANAVERAL, Fla. -- A backscatter device is being used to examine space shuttle Discovery's external fuel tank on Launch Pad 39A at NASA's Kennedy Space Center in Florida. The device bounces radiation off the tank, allowing technicians to see under the tank's foam insulation. The foam cracked during initial loading operations for Discovery’s STS-133 launch attempt on Nov. 5, and technicians later identified two cracked stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Those two stringers have been replaced and reinforced with doublers, which are shaped metal pieces twice as thick as the original stringers. Launch is no earlier than Dec. 17 at 8:51 p.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  17. KSC-2010-5760

    NASA Image and Video Library

    2010-12-02

    CAPE CANAVERAL, Fla. -- An engineer uses a backscatter device to examine space shuttle Discovery's external fuel tank on Launch Pad 39A at NASA's Kennedy Space Center in Florida. The device bounces radiation off the tank, allowing technicians to see under the tank's foam insulation. The foam cracked during initial loading operations for Discovery’s STS-133 launch attempt on Nov. 5, and technicians later identified two cracked stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Those two stringers have been replaced and reinforced with doublers, which are shaped metal pieces twice as thick as the original stringers. Launch is no earlier than Dec. 17 at 8:51 p.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  18. KSC-2010-5761

    NASA Image and Video Library

    2010-12-02

    CAPE CANAVERAL, Fla. -- A backscatter device is being used to examine space shuttle Discovery's external fuel tank on Launch Pad 39A at NASA's Kennedy Space Center in Florida. The device bounces radiation off the tank, allowing technicians to see under the tank's foam insulation. The foam cracked during initial loading operations for Discovery’s STS-133 launch attempt on Nov. 5, and technicians later identified two cracked stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Those two stringers have been replaced and reinforced with doublers, which are shaped metal pieces twice as thick as the original stringers. Launch is no earlier than Dec. 17 at 8:51 p.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  19. KSC-2010-5764

    NASA Image and Video Library

    2010-12-02

    CAPE CANAVERAL, Fla. -- A backscatter device is being used to examine space shuttle Discovery's external fuel tank on Launch Pad 39A at NASA's Kennedy Space Center in Florida. The device bounces radiation off the tank, allowing technicians to see under the tank's foam insulation. The foam cracked during initial loading operations for Discovery’s STS-133 launch attempt on Nov. 5, and technicians later identified two cracked stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Those two stringers have been replaced and reinforced with doublers, which are shaped metal pieces twice as thick as the original stringers. Launch is no earlier than Dec. 17 at 8:51 p.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  20. KSC-2010-5765

    NASA Image and Video Library

    2010-12-02

    CAPE CANAVERAL, Fla. -- Engineers will use a backscatter device to examine space shuttle Discovery's external fuel tank on Launch Pad 39A at NASA's Kennedy Space Center in Florida. The device bounces radiation off the tank, allowing technicians to see under the tank's foam insulation. The foam cracked during initial loading operations for Discovery’s STS-133 launch attempt on Nov. 5, and technicians later identified two cracked stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Those two stringers have been replaced and reinforced with doublers, which are shaped metal pieces twice as thick as the original stringers. Launch is no earlier than Dec. 17 at 8:51 p.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  1. KSC-2010-5758

    NASA Image and Video Library

    2010-12-02

    CAPE CANAVERAL, Fla. -- An engineer uses a backscatter device to examine space shuttle Discovery's external fuel tank on Launch Pad 39A at NASA's Kennedy Space Center in Florida. The device bounces radiation off the tank, allowing technicians to see under the tank's foam insulation. The foam cracked during initial loading operations for Discovery’s STS-133 launch attempt on Nov. 5, and technicians later identified two cracked stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Those two stringers have been replaced and reinforced with doublers, which are shaped metal pieces twice as thick as the original stringers. Launch is no earlier than Dec. 17 at 8:51 p.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  2. KSC-2010-5754

    NASA Image and Video Library

    2010-12-02

    CAPE CANAVERAL, Fla. -- An engineer uses a backscatter device to examine space shuttle Discovery's external fuel tank on Launch Pad 39A at NASA's Kennedy Space Center in Florida. The device bounces radiation off the tank, allowing technicians to see under the tank's foam insulation. The foam cracked during initial loading operations for Discovery’s STS-133 launch attempt on Nov. 5, and technicians later identified two cracked stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Those two stringers have been replaced and reinforced with doublers, which are shaped metal pieces twice as thick as the original stringers. Launch is no earlier than Dec. 17 at 8:51 p.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  3. KSC-2010-5756

    NASA Image and Video Library

    2010-12-02

    CAPE CANAVERAL, Fla. -- An engineer uses a backscatter device to examine space shuttle Discovery's external fuel tank on Launch Pad 39A at NASA's Kennedy Space Center in Florida. The device bounces radiation off the tank, allowing technicians to see under the tank's foam insulation. The foam cracked during initial loading operations for Discovery’s STS-133 launch attempt on Nov. 5, and technicians later identified two cracked stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Those two stringers have been replaced and reinforced with doublers, which are shaped metal pieces twice as thick as the original stringers. Launch is no earlier than Dec. 17 at 8:51 p.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  4. KSC-2010-5755

    NASA Image and Video Library

    2010-12-02

    CAPE CANAVERAL, Fla. -- An engineer uses a backscatter device to examine space shuttle Discovery's external fuel tank on Launch Pad 39A at NASA's Kennedy Space Center in Florida. The device bounces radiation off the tank, allowing technicians to see under the tank's foam insulation. The foam cracked during initial loading operations for Discovery’s STS-133 launch attempt on Nov. 5, and technicians later identified two cracked stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Those two stringers have been replaced and reinforced with doublers, which are shaped metal pieces twice as thick as the original stringers. Launch is no earlier than Dec. 17 at 8:51 p.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  5. Preliminary report on the Comet area, Jefferson County, Montana

    USGS Publications Warehouse

    Becraft, George Earle

    1952-01-01

    Several radioactivity anomalies and a few specimens of sooty pitchblende and other uranium minerals have been found on the mine dumps of formerly productive base-and precious-metal mines along the Comet-Gray Eagle shear zone in the Comet area in southwestern Montana. The shear zone is from 50 to 200 feet wide and has been traced for at least 5 1/2 miles. It trends N. 80° W. across the northern part of the area and cuts the quartz monzonitic rocks of the Boulder batholith and younger silicic intrusive rocks, as well as the pre-batholitic volcanic rocks, and is in turn cut by dacite and andesite dikes. The youngest period of mineralization is represented by chalcedonic vein zones comprising one or more discontinuous stringers and veins of cryptocrystalline silica in silicified quartz monzonite and in alaskite that has not been appreciably silicified. In some places these zones contain no distinct chalcedonic veins, but are represented only by silicified quartz monzonite. These zones locally contain uranium in association with very small amounts of the following minerals: pyrite, galena, ruby silver, argentite, native silver, molybdenite, chalcopyrite, arsenopyrite, and barite. At the Free Enterprise mine, uranium has been produced from a narrow chalcedonic vein that contains disseminated secondary uranium minerals and local small pods of pitchblende and from disseminated secondary uranium minerals in the adjacent quartz monzonite. Undiscovered commercial deposits of uranium ore may occur spatially associated with the base-and precious-metal deposits along the Comet-Gray Eagle shear zone, and chalcedonic vein zones similar to the Free Enterprise.

  6. 78 FR 38608 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-06-27

    .... This proposed AD was prompted by a report of cracks in stringer splices at body station STA 360 and STA 908, between stringer (S) S-10L and S-10R; cracks in butt straps between S-5L and S- 3L, and S-3R and S-5R; vertical chem-mill fuselage skin cracks at certain butt joints; and an instance of cracking...

  7. Strength of log bridge stringers after several year’s use in southeast Alaska

    Treesearch

    Russell C. Moody; R.L. Tuomi; W.E. Eslyn; F.W. Muchmore

    1979-01-01

    Bending tests of 28 untreated log stringers from 12-year-old native timber bridges in southeast Alaska showed significant reductions in strength due to decay. Compared to results on fresh logs, strength reduction was about 25 percent, and could be predicted based on the loss in section modulus due to decay. Log stiffness was not significantly affected. Results will be...

  8. The role of prescribed burning in regenerating Quercus macrocarpa and associated woody plants in stringer woodlands in the Black Hills, South Dakota

    Treesearch

    Carolyn Hull Sieg; Henry A. Wright

    1996-01-01

    Throughout the range of Quercus macrocarpa, fire historically played an important role in maintaining Quercus stands. However, little is known about the role of fire in maintaining stringer Quercus stands on the western edge of its distribution. This research suggests that prescribed burning could be used to rejuvenate woody plants...

  9. Exciting News From Va. Tech - Repaired Pallets May Be Stronger Than the Original

    Treesearch

    John W. Clarke; Marshall S. White; T.E. McLain; Philip A. Araman

    1995-01-01

    Virginia Tech, in cooperation with the NWPCA and the Southern Research Station of the USDA Forest Service, conducted a research program on the use of metal plates for repair of stringer pallets. This study looked at common stringer failure locations: splits between the notches, splits above the notches, and splits in the end feet. One of the research objectives was to...

  10. Load transfer in the stiffener-to-skin joints of a pressurized fuselage

    NASA Technical Reports Server (NTRS)

    Johnson, Eric R.; Rastogi, Naveen

    1995-01-01

    Structural analyses are developed to determine the linear elastic and the geometrically nonlinear elastic response of an internally pressurized, orthogonally stiffened, composite material cylindrical shell. The configuration is a long circular cylindrical shell stiffened on the inside by a regular arrangement of identical stringers and identical rings. Periodicity permits the analysis of a unit cell model consisting of a portion of the shell wall centered over one stringer-ring joint. The stringer-ring-shell joint is modeled in an idealized manner; the stiffeners are mathematically permitted to pass through one another without contact, but do interact indirectly through their mutual contact with the shell at the joint. Discrete beams models of the stiffeners include a stringer with a symmetrical cross section and a ring with either a symmetrical or an asymmetrical open section. Mathematical formulations presented for the linear response include the effect of transverse shear deformations and the effect of warping of the ring's cross section due to torsion. These effects are important when the ring has an asymmetrical cross section because the loss of symmetry in the problem results in torsion and out-of-plane bending of the ring, and a concomitant rotation of the joint at the stiffener intersection about the circumferential axis. Data from a composite material crown panel typical of a large transport fuselage structure are used for two numerical examples. Although the inclusion of geometric nonlinearity reduces the 'pillowing' of the shell, it is found that bending is localized to a narrow region near the stiffener. Including warping deformation of the ring into the analysis changes the sense of the joint rotation. Transverse shear deformation models result in increased joint flexibility.

  11. KSC-2010-5757

    NASA Image and Video Library

    2010-12-02

    CAPE CANAVERAL, Fla. -- An engineer examines images of space shuttle Discovery's external fuel tank taken from a backscatter device on Launch Pad 39A at NASA's Kennedy Space Center in Florida. The device bounces radiation off the tank, allowing technicians to see under the tank's foam insulation. The foam cracked during initial loading operations for Discovery’s STS-133 launch attempt on Nov. 5, and technicians later identified two cracked stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Those two stringers have been replaced and reinforced with doublers, which are shaped metal pieces twice as thick as the original stringers. Launch is no earlier than Dec. 17 at 8:51 p.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  12. KSC-2010-5763

    NASA Image and Video Library

    2010-12-02

    CAPE CANAVERAL, Fla. -- An engineer examines images of space shuttle Discovery's external fuel tank taken from a backscatter device on Launch Pad 39A at NASA's Kennedy Space Center in Florida. The device bounces radiation off the tank, allowing technicians to see under the tank's foam insulation. The foam cracked during initial loading operations for Discovery’s STS-133 launch attempt on Nov. 5, and technicians later identified two cracked stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Those two stringers have been replaced and reinforced with doublers, which are shaped metal pieces twice as thick as the original stringers. Launch is no earlier than Dec. 17 at 8:51 p.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  13. KSC-2010-5759

    NASA Image and Video Library

    2010-12-02

    CAPE CANAVERAL, Fla. -- An engineer examines images of space shuttle Discovery's external fuel tank taken from a backscatter device on Launch Pad 39A at NASA's Kennedy Space Center in Florida. The device bounces radiation off the tank, allowing technicians to see under the tank's foam insulation. The foam cracked during initial loading operations for Discovery’s STS-133 launch attempt on Nov. 5, and technicians later identified two cracked stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Those two stringers have been replaced and reinforced with doublers, which are shaped metal pieces twice as thick as the original stringers. Launch is no earlier than Dec. 17 at 8:51 p.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  14. Experimental Evaluation of Fatigue Damage Progression in Postbuckled Single Stringer Composite Specimens

    NASA Technical Reports Server (NTRS)

    Bisagni, Chiara; Davila, Carlos G.; Rose, Cheryl A.; Zalameda, Joseph N.

    2014-01-01

    The durability and damage tolerance of postbuckled composite structures are not yet completely understood, and remain difficult to predict due to the nonlinearity of the geometric response and its interaction with local damage modes. A research effort was conducted to investigate experimentally the quasi-static and fatigue damage progression in a single-stringer compression (SSC) specimen. Three specimens were manufactured with a hat-stiffener, and an initial defect was introduced with a Teflon film embedded between one flange of the stringer and the skin. One of the specimens was tested under quasi-static compressive loading, while the remaining two specimens were tested by cycling in postbuckling. The tests were performed at the NASA Langley Research Center under controlled conditions and with instrumentation that allows a precise evaluation of the postbuckling response and of the damage modes. Three-dimensional digital image correlation VIC-3D systems were used to provide full field displacements and strains on the skin and the stringer. Passive thermal monitoring was conducted during the fatigue tests using an infrared camera that showed the location of the delamination front while the specimen was being cycled. The live information from the thermography was used to stop the fatigue tests at critical stages of the damage evolution to allow detailed ultrasonic scans.

  15. Preemptive carprofen for peri-operative analgesia in dogs undergoing Tibial Plateau Leveling Osteotomy (TPLO): a prospective, randomized, blinded, placebo controlled clinical trial.

    PubMed

    Bufalari, A; Maggio, C; Cerasoli, I; Morath, U; Adami, C

    2012-03-01

    Eighteen client-owned dogs undergoing Tibial Plateau Leveling Osteotomy (TPLO) were included in this blinded clinical study and randomly assigned to one of two treatment groups. Group C (carprofen) received intravenous (IV) carprofen, 4 mg/kg, prior to anesthesia, whereas group P (placebo) received IV saline. General anesthesia was maintained with isoflurane in oxygen and a constant rate infusion (CRI) of sufentanyl IV. Intra-operatively, assessment of nociception was based on changes in physiological parameters and on the analgesics requirement, whereas in the post-operative period evaluation of pain was performed by using a Hellyer and Gaynor pain score and by comparing the doses of rescue buprenorphine required by the two treatment groups. Although no statistically significant differences in intra-operative sufentanyl doses were found between treatment groups, group C had superior cardiovascular stability, and lower post-operative pain scores and rescue buprenorphine doses than group P. Our results indicate that administration of carprofen prior to surgery was effective in improving peri-operative analgesia in dogs undergoing TPLO.

  16. Behavior Of Aircraft Components Under Crash-Type Loads

    NASA Technical Reports Server (NTRS)

    Carden, Huey D.; Boitnott, Richard L.; Fasanella, Edwin L.

    1993-01-01

    Report presents overview of research involving use of concepts of aircraft elements and substructures not necessarily designed or optimized with respect to energy-absorption or crash-loading considerations. Experimental and analytical data presented in report indicate some general trends in failure behaviors of class of composite-material structures including individual fuselage frames, skeleton subfloors with stringers and floor beams but without skin covering, and subfloors with skin added to frame/stringer arrangement.

  17. Feasibility Investigation into Strengthening of Timber Bridge Stringers

    DTIC Science & Technology

    2007-05-01

    life . They exhibit several types of damage, which occurs in their structural elements such as timber stringers. The most commonly encountered damage...United States are nearing, or at the end of their service life , which means they exhibit several types of damage. This occurs mostly on structural... life of a timber bridge is approximately 30–40 years, the majority of timber bridges in the United States are nearing the end of their service life

  18. On sound transmission into a stiffened cylindrical shell with rings and stringers treated as discrete elements

    NASA Technical Reports Server (NTRS)

    Koval, L. R.

    1980-01-01

    In the context of the transmission of airborne noise into an aircraft fuselage, a mathematical model is presented for the transmission of an oblique plane sound wave into a finite cylindrical shell stiffened by stringers and ring frames. The rings and stringers are modeled as discrete structural elements. The numerical case studied was typical of a narrow-bodied jet transport fuselage. The numerical results show that the ring-frequency dip in the transmission loss curve that is present for a monocoque shell is still present in the case of a stiffened shell. The ring frequency effect is a result of the cylindrical geometry of the shell. Below the ring frequency, stiffening does not appear to have any significant effect on transmission loss, but above the ring frequency, stiffeners can enhance the transmission loss of a cylindrical shell.

  19. Design, process development, manufacture, test and evaluation of boron-aluminum for space shuttle components

    NASA Technical Reports Server (NTRS)

    Garrett, R. A.; Niemann, J. T.; Otto, O. R.; Brown, N. M.; Heinrich, R. E.

    1973-01-01

    A multi phase boron-aluminum design and evaluation program for space shuttle components was conducted, culminating in the fabrication of a 1.22 m (48 inch) x 1.83 m (72 inch) boron-aluminum compression panel capable of distributing a point load of 1555 kN (350,000 lbs) into a uniform running load at a temperature of 589 K (600 F). This panel was of the skin-stringer construction with two intermediate frame supports; seven unidirectional stringers varied in thickness from 5 plies to 52 plies and the skin was contoured to thicknesses ranging from 10 plies to 62 plies. Both the stringers and the skin incorporated Ti-6Al-4V titanium interleaves to increase bearing and in-plane shear strength. The discrete program phases were materials evaluation, design studies, process technology development, fabrication and assembly, and test and evaluation.

  20. Study to investigate design, fabrication and test of low cost concepts for large hybrid composite helicopter fuselage, phase 2

    NASA Technical Reports Server (NTRS)

    Adams, K. M.; Lucas, J. J.

    1977-01-01

    The development of a frame/stringer/skin fabrication technique for composite airframe construction was studied as a low cost approach to the manufacturer of larger helicopter airframe components. A center cabin aluminum airframe section of the Sikorsky CH-53D, was selected for evaluation as a composite structure. The design, as developed, is composed of a woven KEVLAR R-49/epoxy skin and graphite/epoxy frames and stringers. The single cure concept is made possible by the utilization of pre-molded foam cores, over which the graphite/epoxy pre-impregnated frame and stringer reinforcements are positioned. Bolted composite channel sections were selected as the optimum joint construction. The applicability of the single cure concept to larger realistic curved airframe sections, and the durability of the composite structure in a realistic spectrum fatigue environment, was described.

  1. KSC-2011-1008

    NASA Image and Video Library

    2011-01-05

    CAPE CANAVERAL, Fla. – As part of the repair work to space shuttle Discovery's external fuel tank, a technician measures a fitted piece of metal, called a radius block, which will be attached to an intertank support beam, called a stringer. Technicians in the Vehicle Assembly Building at NASA’s Kennedy Space Center in Florida are modifying 32 stringers with the radius blocks near the intertank’s thrust panel area. The thrust panel is where the tank meets the two solid rocket boosters and sees the most stress during the flight into orbit. After the modifications and additional scans of the stringers are complete, foam insulation will be re-applied. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller

  2. Analysis of Composite Panel-Stiffener Debonding Using a Shell/3D Modeling Technique

    NASA Technical Reports Server (NTRS)

    Krueger, Ronald; Minguet, Pierre J.

    2006-01-01

    Interlaminar fracture mechanics has proven useful for characterizing the onset of delaminations in composites and has been used with limited success primarily to investigate onset in fracture toughness specimens and laboratory size coupon type specimens. Future acceptance of the methodology by industry and certification authorities however, requires the successful demonstration of the methodology on structural level. For this purpose a panel was selected that was reinforced with stringers. Shear loading cases the panel to buckle and the resulting out-of-plane deformations initiate skin/stringer separation at the location of an embedded defect. For finite element analysis, the panel and surrounding load fixture were modeled with shell element. A small section of the stringer foot and the panel in the vicinity of the embedded defect were modeled with a local 3D solid model. A failure index was calculated by correlating computed mixed-mode failure criterion of the graphite/epoxy material.

  3. Fracture of an isotropic medium strengthened with a regular system of stringers

    NASA Astrophysics Data System (ADS)

    Mir-Salim-zadeh, M. V.

    2007-01-01

    An isotropic medium containing a system of foreign transverse rectilinear inclusions is considered. Such a medium can be interpreted as an infinite plate strengthened with a regular system of ribs (stringers) whose cross section is a very narrow rectangle. The medium is weakened by a periodic system of rectilinear cracks. The action of the stringers is re placed by unknown equivalent concentrated forces at the points of their connection with the medium. The boundary-value problem on equilibrium of the periodic system of cracks under the action of external tensile forces is reduced to a singular integral equation, from the solution of which the stress in tensity factors are found. The condition of limiting state of equilibrium of the cracks is formulated based on a criterion of brittle fracture. The stress state in the case where crack faces come into a partial contact is also considered.

  4. Space Tethers Programmatic Infusion Opportunities

    NASA Technical Reports Server (NTRS)

    Bonometti, J. A.; Frame, K. L.

    2005-01-01

    Programmatic opportunities abound for space Cables, Stringers and Tethers, justified by the tremendous performance advantages that these technologies offer and the rather wide gaps that must be filled by the NASA Exploration program, if the "sustainability goal" is to be met. A definition and characterization of the three categories are presented along with examples. A logical review of exploration requirements shows how each class can be infused throughout the program, from small experimental efforts to large system deployments. The economics of tethers in transportation is considered along with the impact of stringers for structural members. There is an array of synergistic methodologies that interlace their fabrication, implementation and operations. Cables, stringers and tethers can enhance a wide range of other space systems and technologies, including power storage, formation flying, instrumentation, docking mechanisms and long-life space components. The existing tether (i.e., MXER) program's accomplishments are considered consistent with NASA's new vision and can readily conform to requirements-driven technology development.

  5. Test and Analyses of a Composite Multi-Bay Fuselage Panel Under Uni-Axial Compression

    NASA Technical Reports Server (NTRS)

    Li, Jian; Baker, Donald J.

    2004-01-01

    A composite panel containing three stringers and two frames cut from a vacuum-assisted resin transfer molded (VaRTM) stitched fuselage article was tested under uni-axial compression loading. The stringers and frames divided the panel into six bays with two columns of three bays each along the compressive loading direction. The two frames were supported at the ends with pins to restrict the out-of-plane translation. The free edges of the panel were constrained by knife-edges. The panel was modeled with shell finite elements and analyzed with ABAQUS nonlinear solver. The nonlinear predictions were compared with the test results in out-of-plane displacements, back-to-back surface strains on stringer flanges and back-to-back surface strains at the centers of the skin-bays. The analysis predictions were in good agreement with the test data up to post-buckling.

  6. 12. FLOOR BEAMS, BRACKETS, STRINGERS. (Also includes a schedule of ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    12. FLOOR BEAMS, BRACKETS, STRINGERS. (Also includes a schedule of parts.) American Bridge Company, Ambridge Plant No. 5, sheet no. 2, dated April 2, 1928 (revised 4-24-28), order no. F5073. For U.S. Steel Products Company, Pacific Coast Depot, order no. SF578. For Southern Pacific Company, order no. 8873-P-28746. Scale 1/4 inch to one foot. - Napa River Railroad Bridge, Spanning Napa River, east of Soscol Avenue, Napa, Napa County, CA

  7. Debonding in Composite Skin/Stringer Configurations Under Multi-Axial Loading

    NASA Technical Reports Server (NTRS)

    Cvitkovich, Michael K.; Krueger, Ronald; OBrien, T.; Minguet, Pierre J.

    2004-01-01

    The objective of this work was to investigate the damage mechanisms in composite bonded skin/stringer constructions under uniaxial and biaxial (in-plane/out-of-plane) loading conditions as typically experienced by aircraft crown fuselage panels. The specimens for all tests were identical and consisted of a tapered composite flange, representing a stringer or frame, bonded onto a composite skin. Tests were performed under monotonic loading conditions in tension, three-point bending, and combined tension/bending to evaluate the debonding mechanisms between the skin and the bonded stringer. For combined tension/bending testing, a unique servohydraulic load frame was used that was capable of applying both loads simultaneously. Microscopic investigations of the specimen edges were used to document the damage occurrence and to identify typical damage patterns. The observations showed that, for all three load cases, failure initiated in the flange near the flange tip causing the flange to almost fully debond from the skin. A two-dimensional plain-strain finite element model was developed to analyze the different test cases using a geometrically nonlinear solution. For all three loading conditions, principal stresses exceeded the transverse strength of the material in the flange area. Additionally, delaminations of various lengths were simulated in the locations where delaminations were experimentally observed. The analyses showed that unstable delamination propagation is likely to occur at the loads corresponding to matrix ply crack initiation for all three loadings.

  8. Stability Analysis of Intertank Formed Skin/Stringer Compression Panel with Simulated Damage

    NASA Technical Reports Server (NTRS)

    Harper, David W.; Wingate, Robert J.

    2012-01-01

    The External Tank (ET) is a component of the Space Shuttle launch vehicle that contains fuel and oxidizer. During launch, the ET supplies the space shuttle main engines with liquid hydrogen and liquid oxygen. In addition to supplying fuel and oxidizer, it is the backbone structural component of the Space Shuttle. It is comprised of a liquid hydrogen (LH2) tank and a liquid oxygen (LOX) tank, which are separated by an Intertank. The Intertank is a stringer-stiffened cylindrical structure with hat-section stringers that are roll formed from aluminum-lithium alloy Al-2090. Cracks in the Intertank stringers of the STS-133 ET were noticed after a November 5, 2010 launch attempt. The cracks were approximately nine inches long and occurred on the forward end of the Intertank (near the LOX tank), along the fastener line, and were believed to have occurred while loading the ET with the cryogenic propellants. These cracks generated questions about the structural integrity of the Intertank. In order to determine the structural capability of the Intertank with varying degrees of damage, a finite element model (FEM) simulating a 1995 compression panel test was analyzed and correlated to test data. Varying degrees of damage were simulated in the FEM, and non-linear stability analyses were performed. The high degree of similarity between the compression panel and the Intertank provided confidence that the ET Intertank would have similar capabilities.

  9. Composite Structure Modeling and Analysis of Advanced Aircraft Fuselage Concepts

    NASA Technical Reports Server (NTRS)

    Mukhopadhyay, Vivek; Sorokach, Michael R.

    2015-01-01

    NASA Environmentally Responsible Aviation (ERA) project and the Boeing Company are collabrating to advance the unitized damage arresting composite airframe technology with application to the Hybrid-Wing-Body (HWB) aircraft. The testing of a HWB fuselage section with Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) construction is presently being conducted at NASA Langley. Based on lessons learned from previous HWB structural design studies, improved finite-element models (FEM) of the HWB multi-bay and bulkhead assembly are developed to evaluate the performance of the PRSEUS construction. In order to assess the comparative weight reduction benefits of the PRSEUS technology, conventional cylindrical skin-stringer-frame models of a cylindrical and a double-bubble section fuselage concepts are developed. Stress analysis with design cabin-pressure load and scenario based case studies are conducted for design improvement in each case. Alternate analysis with stitched composite hat-stringers and C-frames are also presented, in addition to the foam-core sandwich frame and pultruded rod-stringer construction. The FEM structural stress, strain and weights are computed and compared for relative weight/strength benefit assessment. The structural analysis and specific weight comparison of these stitched composite advanced aircraft fuselage concepts demonstrated that the pressurized HWB fuselage section assembly can be structurally as efficient as the conventional cylindrical fuselage section with composite stringer-frame and PRSEUS construction, and significantly better than the conventional aluminum construction and the double-bubble section concept.

  10. STS-133/ET-137 Tanking Test Photogrammetry Assessment

    NASA Technical Reports Server (NTRS)

    Oliver, Stanley T.

    2012-01-01

    Following the launch scrub of Space Shuttle mission STS-133 on November 5, 2010, an anomalous condition of cracked and raised thermal protection system (TPS) foam was observed on the External Tank (ET). Subsequent dissection of the affected TPS region revealed cracks in the feet of two Intertank (IT) metallic stringers. An extensive investigation into the cause(s) and corrective action(s) for the cracked stringers was initiated, involving a wide array of material and structural tests and nondestructive evaluations, with the intent to culminate into the development of flight rational. One such structural test was the instrumented tanking test performed on December 17, 2010. The tanking test incorporated two three-dimensional optical displacement measurement systems to measure full-field outer surface displacements of the TPS surrounding the affected region that contained the stringer cracks. The results showed that the radial displacement and rotation of the liquid oxygen (LO2) tank flange changed significantly as the fluid level of the LO2 approached and passed the LO2 tank flange.

  11. Supplementary Microstructural Features Induced During Laser Surface Melting of Thermally Sprayed Inconel 625 Coatings

    NASA Astrophysics Data System (ADS)

    Ahmed, Nauman; Voisey, K. T.; McCartney, D. G.

    2014-02-01

    Laser surface melting of thermally sprayed coatings has the potential to enhance their corrosion properties by incorporating favorable microstructural changes. Besides homogenizing the as-sprayed structure, laser melting may induce certain microstructural modifications (i.e., supplementary features) in addition to those that directly improve the corrosion performance. Such features, being a direct result of the laser treatment process, are described in this paper which is part of a broader study in which high velocity oxy-fuel sprayed Inconel 625 coatings on mild-steel substrates were treated with a diode laser and the modified microstructure characterized using optical and scanning electron microscopy and x-ray diffraction. The laser treated coating features several different zones, including a region with a microstructure in which there is a continuous columnar dendritic structure through a network of retained oxide stringers.

  12. Pressure Testing of a Minimum Gauge PRSEUS Panel

    NASA Technical Reports Server (NTRS)

    Lovejoy, Andrew J.; Rouse, Marshall; Linton, Kim A.; Li, Victor P.

    2011-01-01

    Advanced aircraft configurations that have been developed to increase fuel efficiency require advanced, novel structural concepts capable of handling the unique load conditions that arise. One such concept is the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) developed by the Boeing Company. The PRSEUS concept is being investigated by NASA s Environmentally Responsible Aviation (ERA) Program for use in a hybrid-wing body (HWB) aircraft. This paper summarizes the analysis and test of a PRSEUS panel subjected to internal pressure, the first such pressure test for this structural concept. The pressure panel used minimum gauge skin, with stringer and frame configurations consistent with previous PRSEUS tests. Analysis indicated that for the minimum gauge skin panel, the stringer locations exhibit fairly linear response, but the skin bays between the stringers exhibit nonlinear response. Excellent agreement was seen between nonlinear analysis and test results in the critical portion at the center of the panel. The pristine panel was capable of withstanding the required 18.4 psi pressure load condition without exhibiting any damage. The impacted panel was capable of withstanding a pressure load in excess of 28 psi before initial failure occurred at the center stringer, and the panel was capable of sustaining increased pressure load after the initial failure. This successful PRSEUS panel pressure panel test was a critical step in the building block approach for enabling the use of this advanced structural concept on future aircraft, such as the HWB.

  13. Stress distributions caused by three types of loading on a circular semimonocoque cylinder with flexible rings

    NASA Technical Reports Server (NTRS)

    Mccomb, Harvey G , Jr

    1954-01-01

    Equations are derived for the stress distributions caused by three types of loading on infinitely long circular, semimonocoque cylinders with flexible rings. The results are given as formula for the stringer loads and shear flows in the shell due to each type of loading. For each loading case these formulas can be used to construct tables of influence coefficients giving stringer loads and shear flows in the neighborhood of the load due to a unit magnitude of the load. (author)

  14. Aircraft interior noise models - Sidewall trim, stiffened structures, and cabin acoustics with floor partition

    NASA Technical Reports Server (NTRS)

    Pope, L. D.; Wilby, E. G.; Willis, C. M.; Mayes, W. H.

    1983-01-01

    As part of the continuing development of an aircraft interior noise prediction model, in which a discrete modal representation and power flow analysis are used, theoretical results are considered for inclusion of sidewall trim, stiffened structures, and cabin acoustics with floor partition. For validation purposes, predictions of the noise reductions for three test articles (a bare ring-stringer stiffened cylinder, an unstiffened cylinder with floor and insulation, and a ring-stringer stiffened cylinder with floor and sidewall trim) are compared with measurements.

  15. Progressive Damage Analyses of Skin/Stringer Debonding

    NASA Technical Reports Server (NTRS)

    Daville, Carlos G.; Camanho, Pedro P.; deMoura, Marcelo F.

    2004-01-01

    The debonding of skin/stringer constructions is analyzed using a step-by-step simulation of material degradation based on strain softening decohesion elements and a ply degradation procedure. Decohesion elements with mixed-mode capability are placed at the interface between the skin and the flange to simulate the initiation and propagation of the delamination. In addition, the initiation and accumulation of fiber failure and matrix damage is modeled using Hashin-type failure criteria and their corresponding material degradation schedules. The debonding predictions using simplified three-dimensional models correlate well with test results.

  16. Application of boron/epoxy reinforced aluminum stringers and boron/epoxy skid gear for the CH54B helicopter tail cone. Phase 2: Fabrication, inspection and flight test

    NASA Technical Reports Server (NTRS)

    Welge, R. T.

    1972-01-01

    A CH-54B Skycrane helicopter was fabricated with boron/epoxy reinforced stringers in the tail cone and boron/epoxy tubes in the tail skid. The fabrication of the tail cone was made with conventional tooling, production shop personnel, and no major problems. The flight test program includes a stress and vibration survey using strain gages and vibration transducers located in critical areas. The program to inspect and monitor the reliability of the components is discussed.

  17. Compression strength of composite primary structural components

    NASA Technical Reports Server (NTRS)

    Johnson, Eric R.

    1994-01-01

    The linear elastic response is determined for an internally pressurized, long circular cylindrical shell stiffened on the inside by a regular arrangement of identical stringers and identical rings. Periodicity of this configuration permits the analysis of a portion of the shell wall centered over a generic stringer-ring joint; i.e., a unit cell model. The stiffeners are modeled as discrete beams, and the stringer is assumed to have a symmetrical cross section and the ring an asymmetrical section. Asymmetery causes out-of-plane bending and torsion of the ring. Displacements are assumed as truncated double Fourier series plus simple terms in the axial coordinate to account for the closed and pressure vessel effect (a non-periodic effect). The interacting line loads between the stiffeners and the inside shell wall are Lagrange multipliers in the formulation, and they are also assumed as truncated Fourier series. Displacement continuity constraints between the stiffeners and shell along the contact lines are satisfied point-wise. Equilibrium is imposed by the principle of virtual work. A composite material crown panel from the fuselage of a large transport aircraft is the numerical example. The distributions of the interacting line loads, and the out-of-plane bending moment and torque in the ring, are strongly dependent on modeling the deformations due to transverse shear and cross-sectional warping of the ring in torsion. This paper contains the results from the semiannual report on research on 'Pressure Pillowing of an Orthogonally Stiffened Cylindrical Shell'. The results of the new work are illustrated in the included appendix.

  18. Uranium deposits of the northern part of the Boulder Batholith, Montana

    USGS Publications Warehouse

    Becraft, George E.

    1955-01-01

    Uranium minerals and radioactivity anomalies occur in many silver-lead veins and chalcedony veins and vein zones in the Boulder batholith of southwestern Montanao Pitchblende has been identified in a few silver-lead veins. These veins occupy shear zones along which there is no evidence of large-scale lateral displacement. The wall rock adjacent to the veins is intensely silicified and sencitized quartz monzonite and granodiortte. The veins have yielded substantial quantities of lead, silver, zinc, and gold. The silver-lead veins consist principal1y of galena, spha1erite, tetrahedrite, cha1copyrite and pyrite in a gangue of light to dark gray quartz, altered rock, gouge, and subordinate chalcedony and carbonate minerals. No anomalous radioactivity nor uranium minerals have been found in similar veins in pre-batholithic rocks of the area. Chalcedony veins and vein zones, some of which are ttraniferous, are distinctly different from the silver-lead veins and, with a single except1on, are known only in the batholith. The chalcedony vein zones consist of one or more discontinuous stringers or veins of cha1cedony and microcrystalline quartz in silicified and sericitized quartz monzonite and granodiorite, and in less strongly altered alaskite. On1y small amounts of silver ore have been produced from these chalcedony veins and vein zones. All of the veins are ear1y Tertiary in age, but the silver-lead veins probably are older than the chalcedony veins. Uranium is closely associated with chalcedory and microcrystalline quartz in both types of veins. This association suggests that all of the uranium in the area is of the same age. If so, some of the silver-lead veins must have been reopened during the period of chalcedony vein formation.

  19. An Investigation into the Postbuckling Response of a Single Blade-Stiffened Composite Panel

    NASA Astrophysics Data System (ADS)

    Spediacci, Alexander Daniel

    The large strength reserves of stiffened composite structures in the postbuckling range appeal to the aerospace industry because of the high strength-to weight-ratio. Design and analysis of these large-scale, complex structures is technical, and requires major computational effort. Using the building-block approach, a smaller, single-stringer panel can be a useful and efficient tool for initial design, and can reveal critical behavior of a larger, multi-stringer panel. A characterization, through finite element modeling, of buckling and postbuckling response of a single blade-stiffened composite panel is proposed. Several factors affecting buckling and postbuckling behavior are investigated, including specimen length, initial imperfections, mode switching, and skin stringer separation. Two specimens are repeatedly tested under quasi- static compression loading well into the postbuckling range, showing no sign of damage. The test data from the specimens are used to compare and validate the nonlinear finite element models, show good correlation with the models. Ultimately, this work will serve to demonstrate the safety of stiffened structures operating in the postbuckling range and allow for thinner, lighter structures, which can increase the overall efficiency of aircraft.

  20. Study to investigate design, fabrication and test of low cost concepts for large hybrid composite helicopter fuselage, phase 1

    NASA Technical Reports Server (NTRS)

    Adams, K. M.; Lucas, J. J.

    1975-01-01

    The development of a frame/stringer/skin fabrication technique for composite airframe construction was studied as a low cost approach to the manufacture of large helicopter airframe components. A center cabin aluminum airframe section of the Sikorsky CH-53D helicopter was selected for evaluation as a composite structure. The design, as developed, is composed of a woven KEVLAR-49/epoxy skin and graphite/epoxy frames and stringers. To support the selection of this specific design concept a materials study was conducted to develop and select a cure compatible graphite and KEVLAR-49/epoxy resin system, and a foam system capable of maintaining shape and integrity under the processing conditions established. The materials selected were, Narmco 5209/Thornel T-300 graphite, Narmco 5209/KEVLAR-49 woven fabric, and Stathane 8747 polyurethane foam. Eight specimens were fabricated, representative of the frame, stringer, and splice joint attachments. Evaluation of the results of analysis and test indicate that design predictions are good to excellent except for some conservatism of the complex frame splice.

  1. Software For Design And Analysis Of Tanks And Cylindrical Shells

    NASA Technical Reports Server (NTRS)

    Luz, Paul L.; Graham, Jerry B.

    1995-01-01

    Skin-stringer Tank Analysis Spreadsheet System (STASS) computer program developed for use as preliminary design software tool that enables quick-turnaround design and analysis of structural domes and cylindrical barrel sections in propellant tanks or other cylindrical shells. Determines minimum required skin thicknesses for domes and cylindrical shells to withstand material failure due to applied pressures (ullage and/or hydrostatic) and runs buckling analyses on cylindrical shells and skin-stringers. Implemented as workbook program, using Microsoft Excel v4.0 on Macintosh II. Also implemented using Microsoft Excel v4.0 for Microsoft Windows v3.1 IBM PC.

  2. Fatigue Life of Postbuckled Structures with Indentation Damage

    NASA Technical Reports Server (NTRS)

    Davila, Carlos G.; Bisagni, Chiara

    2016-01-01

    The fatigue life of composite stiffened panels with indentation damage was investigated experimentally using single stringer compression specimens. Indentation damage was induced on one of the two flanges of the stringer. The experiments were conducted using advanced instrumentation, including digital image correlation, passive thermography, and in-situ ultrasonic scanning. Specimens with initial indentation damage lengths of 37 millimeters to 56 millimeters were tested in fatigue and the effects of cyclic load amplitude and damage size were studied. A means of comparison of the damage propagation rates and collapse loads based on a stress intensity measure and the Paris law is proposed.

  3. Global Failure Modes in Composite Structures

    NASA Technical Reports Server (NTRS)

    Knauss, W. G.; Gonzalez, Luis

    2001-01-01

    Composite materials provide well-known advantages for space and aeronautical applications in terms of strength and rigidity to weight ratios and other mechanical properties. As a consequence, their use has experienced a constant increase in the past decades and it is anticipated that this trend will be maintained in the near future. At the same time, being these materials relatively new compared to metals, and having failure characteristics completely different from them, their damage growth and their failure mechanisms are not as well understood in a predictive sense. For example, while in metals fracture produces "clean" cracks with their well defined analytically stress fields at the crack tip, composite fracture is a more complex phenomenon. Instead of a crack, we confront a "damage zone" that may include fiber breakage, fiber microbuckling, fiber pullout, matrix cracking, delamination, debonding or any combination of all these different mechanisms. These phenomena are prevalent in any failure process through an aircraft structure, whether one addresses a global failure such as the ripping of a fuselage or wing section, or whether one is concerned with the failure initiation near a thickness change at stringers or other reinforcement. Thus the topic that has been under consideration has wide application in any real structure and is considered an essential contribution to the predictive failure analysis capability for aircraft containing composite components. The heterogeneity and the anisotropy of composites are not only advantageous but essential characteristics, yet these same features provide complex stress fields, especially in the presence of geometrical discontinuities such as notches, holes or cutouts or structural elements such as stiffeners, stringers, etc. To properly address the interaction between a damage/crack front and a hole with a stringer it is imperative that the stress and deformation fields of the former be (sufficiently well) characterized. The question of "scaling" is an essential concern in any structural materials investigation. For example, experiments in the past have shown that the "strength" of a composite depends on hole size. As a consequence the validity of traditional fracture mechanics concepts applied to composite materials failure must be questioned. The size of the fibers, the dimensions of the laminae, etc. together with the fact that, because of the layered anisotropy, the stress field is no longer two-dimensional, prevent the otherwise obviously confident use of "similarity concepts". Therefore, the question needs to be raised of whether in composites "size matters or not", i.e., whether the results obtained in a laboratory using small coupons are truly representative of the situation involving a full scale component.

  4. Fatigue Life of Postbuckled Structures with Indentation Damages

    NASA Technical Reports Server (NTRS)

    Davila, Carlos G.; Bisagni, Chiara

    2016-01-01

    The fatigue life of composite stiffened panels with indentation damage was investigated experimentally using single stringer compression specimens. Indentation damage was induced on one of the two flanges of each stringer. The experiments were conducted using advanced instrumentation, including digital image correlation, passive thermography, and in-situ ultrasonic scanning. Specimens with initial indentation damage lengths of 32 millimeters to 56 millimeters were tested quasi-statically and in fatigue, and the effects of cyclic load amplitude and damage size were studied. A means of comparison of the damage propagation rates and collapse loads based on a stress intensity measure and the Paris law is proposed.

  5. Transmission electron microscopy characterization of microstructural features of Al-Li-Cu alloys

    NASA Technical Reports Server (NTRS)

    Avalos-Borja, M.; Pizzo, P. P.; Larson, L. A.

    1983-01-01

    A transmission electron microscopy (TEM) examination of aluminum-lithium-copper alloys was conducted. The principal purpose is to characterize the nature, size, and distribution of stringer particles which result from the powder metallurgy (P/M) processing of these alloys. Microstructural features associated with the stringer particles are reported that help explain the stress corrosion susceptibility of the powder metallurgy-processed Al-Li-Cu alloys. In addition, matrix precipitation events are documented for a variety of heat treatments and process variations. Hot rolling is observed to significant alter the nature of matrix precipitation, and the observations are correlated with concomitant mechanical property variations.

  6. Design of cryogenic tanks for space vehicles shell structures analytical modeling

    NASA Technical Reports Server (NTRS)

    Copper, Charles; Mccarthy, K.; Pilkey, W. D.; Haviland, J. K.

    1991-01-01

    The initial objective was to study the use of superplastically formed corrugated hat section stringers and frames in place of integrally machined stringers over separate frames for the tanks of large launch vehicles subjected to high buckling loads. The ALS was used as an example. The objective of the follow-on project was to study methods of designing shell structures subjected to severe combinations of structural loads and thermal gradients, with emphasis on new combinations of structural arrangements and materials. Typical applications would be to fuselage sections of high speed civil transports and to cryogenic tanks on the National Aerospace Plane.

  7. Transmission electron microscopy characterization of microstructural features in aluminum-lithium-copper alloys

    NASA Technical Reports Server (NTRS)

    Avalos-Borja, M.; Larson, L. A.; Pizzo, P. P.

    1984-01-01

    A transmission electron microscopy (TEM) examination of aluminum-lithium-copper alloys was conducted. The principal purpose is to characterize the nature, size, and distribution of stringer particles which result from the powder metallurgy (P/M) processing of these alloys. Microstructural features associated with the stringer particles are reported that help explain the stress corrosion susceptibility of the powder metallurgy-processed Al-Li-Cu alloys. In addition, matrix precipitaton events are documented for a variety of heat treatments and process variations. Hot rolling is observed to significantly alter the nature of matrix precipitation, and the observations are correlated with concomitant mechanical property variations.

  8. Vibration and stress analysis of soft-bonded shuttle insulation tiles. Modal analysis with compact widely space stringers

    NASA Technical Reports Server (NTRS)

    Ojalvo, I. U.; Austin, F.; Levy, A.

    1974-01-01

    An efficient iterative procedure is described for the vibration and modal stress analysis of reusable surface insulation (RSI) of multi-tiled space shuttle panels. The method, which is quite general, is rapidly convergent and highly useful for this application. A user-oriented computer program based upon this procedure and titled RESIST (REusable Surface Insulation Stresses) has been prepared for the analysis of compact, widely spaced, stringer-stiffened panels. RESIST, which uses finite element methods, obtains three dimensional tile stresses in the isolator, arrestor (if any) and RSI materials. Two dimensional stresses are obtained in the tile coating and the stringer-stiffened primary structure plate. A special feature of the program is that all the usual detailed finite element grid data is generated internally from a minimum of input data. The program can accommodate tile idealizations with up to 850 nodes (2550 degrees-of-freedom) and primary structure idealizations with a maximum of 10,000 degrees-of-freedom. The primary structure vibration capability is achieved through the development of a new rapid eigenvalue program named ALARM (Automatic LArge Reduction of Matrices to tridiagonal form).

  9. CORSS: Cylinder Optimization of Rings, Skin, and Stringers

    NASA Technical Reports Server (NTRS)

    Finckenor, J.; Rogers, P.; Otte, N.

    1994-01-01

    Launch vehicle designs typically make extensive use of cylindrical skin stringer construction. Structural analysis methods are well developed for preliminary design of this type of construction. This report describes an automated, iterative method to obtain a minimum weight preliminary design. Structural optimization has been researched extensively, and various programs have been written for this purpose. Their complexity and ease of use depends on their generality, the failure modes considered, the methodology used, and the rigor of the analysis performed. This computer program employs closed-form solutions from a variety of well-known structural analysis references and joins them with a commercially available numerical optimizer called the 'Design Optimization Tool' (DOT). Any ring and stringer stiffened shell structure of isotropic materials that has beam type loading can be analyzed. Plasticity effects are not included. It performs a more limited analysis than programs such as PANDA, but it provides an easy and useful preliminary design tool for a large class of structures. This report briefly describes the optimization theory, outlines the development and use of the program, and describes the analysis techniques that are used. Examples of program input and output, as well as the listing of the analysis routines, are included.

  10. Earth Observations taken by Expedition 38 crewmember

    NASA Image and Video Library

    2014-02-22

    ISS038-E-057977 (22 Feb. 2014) --- Snow-covered fields appear as geometric patterns on Washington Island, on Lake Michigan, in this photograph taken by the Expedition 38 crew of the International Space Station. The island is nine kilometers long (5.6 miles) and lies on the western shore of Lake Michigan, as a continuation of Door Peninsula (Wisconsin). Note that north is to the lower left in the image. White coastal ice hugs the shoreline and connects Washington Island with Detroit Island and Rock Island. Ice typically accumulates first near land, where cooling is more rapid than in deeper lake water. Two other snow-covered islands (image top left) are small enough and far enough from land to evade the collars of ice. On the day this image was taken, southwesterly winds were blowing ice into the lake in the form of long, coherent stringers. The thickness of a stringer is related to the length of coastline that feeds it. The smallest northern stringer (image left) is fed by the shortest section of upwind coastline, and the longest (image right) is supplied by the large amount of shore ice around Detroit Island.

  11. Complex deformation associated with anhydrite layers in the Tromsø Basin, SW Barents Sea.

    NASA Astrophysics Data System (ADS)

    Marfo, George; Olakunle Omosanya, Kamaldeen; Johansen, Ståle Emil; Zervas, Ioannis

    2017-04-01

    Internal and external deformation associated with salt structures is of prime interest due to their economic importance as hydrocarbon seals, reservoirs, repositories for chemical waste and their implication on drilling. Salt structures are often associated with anhydrites, which may 'cap' or are enclosed within the allochthonous salt structures. Despite their economic importance, the internal and external structures of evaporites remain poorly studied from field and seismic data due to the sparse outcrops of evaporites and poor seismic imaging. The zero-phased, normal polarity, high resolution multiple 2D seismic data, in combination with detailed interpretation of wireline logs provide an excellent study into the salt structures, and offers a good opportunity to investigate the dynamics, geometries and mechanisms driving deformation of internal and external salt layers associated with the Late Carboniferous to Early Permian Salt structures in the Tromsø Basin. The methods include seismic interpretation and the application of multiple seismic attributes to map stratigraphic units and discontinuities. Our results show that the anhydrite layers are marked by high amplitude reflections at the crests and flanks or fully enclosed within the salt diapirs. Crestal and lateral anhydrite caprocks represent external salt structures whilst the entrained anhydrites or stringers are intrasalt structures. Anhydrite caprocks generally show structural styles such as faults and large-scale folds which are harmonic to the top salt structure. In contrast, anhydrite stringers show folds of varying scale, which are harmonic to disharmonic to the top salt structure. Boudins and steeply dipping stringer fragments are also interpreted within the stringers. Caprock deformation is attributed to salt upwelling. Folding and boudinaging of originally horizontal and continuous stringer layers formed from a multiphase superimposed sequence of ductile and brittle deformation in response to complex multi-dimensional salt flow. Internal salt flow involves radial and tangential compression, which leads to dominant fold structures near the margins. Boudins on the lower flanks of the diapir formed due radial extension. Our study further demonstrates that differential geometries exhibited by the different anhydrite groups imply that the mechanisms deforming internal and external salt structures are different. The results from this study are comparable to observations from salt mines, field exposures, scaled physical and numerical models.

  12. KSC-2010-5744

    NASA Image and Video Library

    2010-11-30

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the cracks on space shuttle Discovery's external fuel tank have been repaired. The foam cracked during initial loading operations for Discovery’s STS-133 mission to the International Space Station on Nov. 5. The cracks were on two of the 108 stringers, which are the composite aluminum ribs located vertically on the intertank area. Discovery's next launch attempt is no earlier than Dec. 17 at 8:51 p.m. EST. Until then, engineers will continue to analyze data from the GUCP and stringer crack repairs. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  13. KSC-2010-5743

    NASA Image and Video Library

    2010-11-30

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the cracks on space shuttle Discovery's external fuel tank have been repaired. The foam cracked during initial loading operations for Discovery’s STS-133 mission to the International Space Station on Nov. 5. The cracks were on two of the 108 stringers, which are the composite aluminum ribs located vertically on the intertank area. Discovery's next launch attempt is no earlier than Dec. 17 at 8:51 p.m. EST. Until then, engineers will continue to analyze data from the GUCP and stringer crack repairs. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  14. Minimum stiffness criteria for ring frame stiffeners of space launch vehicles

    NASA Astrophysics Data System (ADS)

    Friedrich, Linus; Schröder, Kai-Uwe

    2016-12-01

    Frame stringer-stiffened shell structures show high load carrying capacity in conjunction with low structural mass and are for this reason frequently used as primary structures of aerospace applications. Due to the great number of design variables, deriving suitable stiffening configurations is a demanding task and needs to be realized using efficient analysis methods. The structural design of ring frame stringer-stiffened shells can be subdivided into two steps. One, the design of a shell section between two ring frames. Two, the structural design of the ring frames such that a general instability mode is avoided. For sizing stringer-stiffened shell sections, several methods were recently developed, but existing ring frame sizing methods are mainly based on empirical relations or on smeared models. These methods do not mandatorily lead to reliable designs and in some cases the lightweight design potential of stiffened shell structures can thus not be exploited. In this paper, the explicit physical behaviour of ring frame stiffeners of space launch vehicles at the onset of panel instability is described using mechanical substitute models. Ring frame stiffeners of a stiffened shell structure are sized applying existing methods and the method suggested in this paper. To verify the suggested method and to demonstrate its potential, geometrically non-linear finite element analyses are performed using detailed finite element models.

  15. Multiscale Analysis of Nanocomposites and Their Use in Structural Level Applications

    NASA Astrophysics Data System (ADS)

    Hasan, Zeaid

    This research focuses on the benefits of using nanocomposites in aerospace structural components to prevent or delay the onset of unique composite failure modes, such as delamination. Analytical, numerical, and experimental analyses were conducted to provide a comprehensive understanding of how carbon nanotubes (CNTs) can provide additional structural integrity when they are used in specific hot spots within a structure. A multiscale approach was implemented to determine the mechanical and thermal properties of the nanocomposites, which were used in detailed finite element models (FEMs) to analyze interlaminar failures in T and Hat section stringers. The delamination that first occurs between the tow filler and the bondline between the stringer and skin was of particular interest. Both locations are considered to be hot spots in such structural components, and failures tend to initiate from these areas. In this research, nanocomposite use was investigated as an alternative to traditional methods of suppressing delamination. The stringer was analyzed under different loading conditions and assuming different structural defects. Initial damage, defined as the first drop in the load displacement curve was considered to be a useful variable to compare the different behaviors in this study and was detected via the virtual crack closure technique (VCCT) implemented in the FE analysis. Experiments were conducted to test T section skin/stringer specimens under pull-off loading, replicating those used in composite panels as stiffeners. Two types of designs were considered: one using pure epoxy to fill the tow region and another that used nanocomposite with 5 wt. % CNTs. The response variable in the tests was the initial damage. Detailed analyses were conducted using FEMs to correlate with the experimental data. The correlation between both the experiment and model was satisfactory. Finally, the effects of thermal cure and temperature variation on nanocomposite structure behavior were studied, and both variables were determined to influence the nanocomposite structure performance.

  16. Testing and Analysis of Composite Skin/Stringer Debonding Under Multi-Axial Loading

    NASA Technical Reports Server (NTRS)

    Krueger, Ronald; Cvitkovich, Michael K.; O'Brien, T. Kevin; Minguet, Pierre J.

    2000-01-01

    A consistent step-wise approach is presented to investigate the damage mechanism in composite bonded skin/stringer constructions under uniaxial and biaxial (in-plane/out-of-plane) loading conditions. The approach uses experiments to detect the failure mechanism, computational stress analysis to determine the location of first matrix cracking and computational fracture mechanics to investigate the potential for delamination growth. In a first step, tests were performed on specimens, which consisted of a tapered composite flange, representing a stringer or frame, bonded onto a composite skin. Tests were performed under monotonic loading conditions in tension, three-point bending, and combined tension/bending to evaluate the debonding mechanisms between the skin and the bonded stringer. For combined tension/bending testing, a unique servohydraulic load frame was used that was capable of applying both in-plane tension and out-of-plane bending loads simultaneously. Specimen edges were examined on the microscope to document the damage occurrence and to identify typical damage patterns. For all three load cases, observed failure initiated in the flange, near the flange tip, causing the flange to almost fully debond from skin. In a second step, a two dimensional plane-strain finite element model was developed to analyze the different test cases using a geometrically nonlinear solution. For all three loading conditions, computed principal stresses exceeded the transverse strength of the material in those areas of the flange where the matrix cracks had developed during the tests. In a third step, delaminations of various lengths were simulated in two locations where delaminations were observed during the tests. The analyses showed that at the loads corresponding to matrix ply crack initiation computed strain energy release rates exceeded the values obtained from a mixed mode failure criterion in one location, Hence. Unstable delamination propagation is likely to occur as observed in the experiments.

  17. Testing and Analysis of Composite Skin/Stringer Debonding under Multi-Axial Loading

    NASA Technical Reports Server (NTRS)

    Krueger, Ronald; Cvitkovich, Michael; OBrien, Kevin; Minguet, Pierre J.

    2000-01-01

    A consistent step-wise approach is presented to investigate the damage mechanism in composite bonded skin/stringer constructions under uniaxial and biaxial (in-plane/out-of-plane) loading conditions. The approach uses experiments to detect the failure mechanism, computational stress analysis to determine the location of first matrix cracking and computational fracture mechanics to investigate the potential for delamination growth. In a first step, tests were performed on specimens, which consisted of a tapered composite flange, representing a stringer or frame, bonded onto a composite skin. Tests were performed under monotonic loading conditions in tension, three-point bending, and combined tension/bending to evaluate the debonding mechanisms between the skin and the bonded stringer. For combined tension/bending testing, a unique servohydraulic load frame was used that was capable of applying both in-plane tension and out-of-plane bending loads simultaneously. Specimen edges were examined on the microscope to document the damage occurrence and to identify typical damage patterns. For all three load cases, observed failure initiated in the flange, near the flange tip, causing the flange to almost fully debond from the skin. In a second step, a two-dimensional plane-strain finite element model was developed to analyze the different test cases using a geometrically nonlinear solution. For all three loading conditions, computed principal stresses exceeded the transverse strength of the material in those areas of the flange where the matrix cracks had developed during the tests. In a third step, delaminations of various lengths were simulated in two locations where delaminations were observed during the tests. The analyses showed that at the loads corresponding to matrix ply crack initiation computed strain energy release rates exceeded the values obtained from a mixed mode failure criterion in one location. Hence, unstable delamination propagation is likely to occur as observed in the experiments.

  18. Photogrammetry Measurements During a Tanking Test on the Space Shuttle External Tank, ET-137

    NASA Technical Reports Server (NTRS)

    Littell, Justin D.; Schmidt, Tim; Tyson, John; Oliver, Stanley T.; Melis, Matthew E.; Ruggeri, Charles

    2012-01-01

    On November 5, 2010, a significant foam liberation threat was observed as the Space Shuttle STS-133 launch effort was scrubbed because of a hydrogen leak at the ground umbilical carrier plate. Further investigation revealed the presence of multiple cracks at the tops of stringers in the intertank region of the Space Shuttle External Tank. As part of an instrumented tanking test conducted on December 17, 2010, a three dimensional digital image correlation photogrammetry system was used to measure radial deflections and overall deformations of a section of the intertank region. This paper will describe the experimental challenges that were overcome in order to implement the photogrammetry measurements for the tanking test in support of STS-133. The technique consisted of configuring and installing two pairs of custom stereo camera bars containing calibrated cameras on the 215-ft level of the fixed service structure of Launch Pad 39-A. The cameras were remotely operated from the Launch Control Center 3.5 miles away during the 8 hour duration test, which began before sunrise and lasted through sunset. The complete deformation time history was successfully computed from the acquired images and would prove to play a crucial role in the computer modeling validation efforts supporting the successful completion of the root cause analysis of the cracked stringer problem by the Space Shuttle Program. The resulting data generated included full field fringe plots, data extraction time history analysis, section line spatial analyses and differential stringer peak ]valley motion. Some of the sample results are included with discussion. The resulting data showed that new stringer crack formation did not occur for the panel examined, and that large amounts of displacement in the external tank occurred because of the loads derived from its filling. The measurements acquired were also used to validate computer modeling efforts completed by NASA Marshall Space Flight Center (MSFC).

  19. Evaluating four-dimensional time-lapse electrical resistivity tomography for monitoring DNAPL source zone remediation.

    PubMed

    Power, Christopher; Gerhard, Jason I; Karaoulis, Marios; Tsourlos, Panagiotis; Giannopoulos, Antonios

    2014-07-01

    Practical, non-invasive tools do not currently exist for mapping the remediation of dense non-aqueous phase liquids (DNAPLs). Electrical resistivity tomography (ERT) exhibits significant potential but has not yet become a practitioner's tool due to challenges in interpreting the survey results at real sites. This study explores the effectiveness of recently developed four-dimensional (4D, i.e., 3D space plus time) time-lapse surface ERT to monitor DNAPL source zone remediation. A laboratory experiment demonstrated the approach for mapping a changing NAPL distribution over time. A recently developed DNAPL-ERT numerical model was then employed to independently simulate the experiment, providing confidence that the DNAPL-ERT model is a reliable tool for simulating real systems. The numerical model was then used to evaluate the potential for this approach at the field scale. Four DNAPL source zones, exhibiting a range of complexity, were initially simulated, followed by modeled time-lapse ERT monitoring of complete DNAPL remediation by enhanced dissolution. 4D ERT inversion provided estimates of the regions of the source zone experiencing mass reduction with time. Results show that 4D time-lapse ERT has significant potential to map both the outline and the center of mass of the evolving treated portion of the source zone to within a few meters in each direction. In addition, the technique can provide a reasonable, albeit conservative, estimate of the DNAPL volume remediated with time: 25% underestimation in the upper 2m and up to 50% underestimation at late time between 2 and 4m depth. The technique is less reliable for identifying cleanup of DNAPL stringers outside the main DNAPL body. Overall, this study demonstrates that 4D time-lapse ERT has potential for mapping where and how quickly DNAPL mass changes in real time during site remediation. Copyright © 2014 Elsevier B.V. All rights reserved.

  20. Fatigue damage assessment of high-usage in-service aircraft fuselage structure

    NASA Astrophysics Data System (ADS)

    Mosinyi, Bao Rasebolai

    As the commercial and military aircraft fleets continue to age, there is a growing concern that multiple-site damage (MSD) can compromise structural integrity. Multiple site damage is the simultaneous occurrence of many small cracks at independent structural locations, and is the natural result of fatigue, corrosion, fretting and other possible damage mechanisms. These MSD cracks may linkup and form a fatigue lead crack of critical length. The presence of MSD also reduces the structure's ability to withstand longer cracks. The objective of the current study is to assess, both experimentally and analytically, MSD formation and growth in the lap joint of curved panels removed from a retired aircraft. A Boeing 727-232 airplane owned and operated by Delta Air Lines, and retired at its design service goal, was selected for the study. Two panels removed from the left-hand side of the fuselage crown, near stringer 4L, were subjected to extended fatigue testing using the Full-Scale Aircraft Structural Test Evaluation and Research (FASTER) facility located at the Federal Aviation Administration (FAA) William J. Hughes Technical Center. The state of MSD was continuously assessed using several nondestructive inspection (NDI) methods. Damage to the load attachment points of the first panel resulted in termination of the fatigue test at 43,500 fatigue cycles, before cracks had developed in the lap joint. The fatigue test for the second panel was initially conducted under simulated in-service loading conditions for 120,000 cycles, and no cracks were detected in the skin of the panel test section. Artificial damage was then introduced into the panel at selected rivets in the critical (lower) rivet row, and the fatigue loads were increased. Visually detectable crack growth from the artificial notches was first seen after 133,000 cycles. The resulting lead crack grew along the lower rivet row, eventually forming an 11.8" long unstable crack after 141,771 cycles, at which point the test was terminated. Posttest fractograpic examinations of the crack surfaces were conducted, revealing the presence of subsurface MSD at the critical rivet row of the lap joint. Special attention was also given to the stringer clips that attach the fuselage frames to the stringers, since they also experienced cracking during the fatigue tests. The performance of the different conventional and emerging NDI methods was also assessed, and some of the emerging NDI methods were quite effective in detecting and measuring the length of subsurface cracks. Delta Air Lines conducted a separate destructive investigation on the state of damage along the right-hand side of the fuselage, near stringer 4R. A comparison of these two studies showed that the lap joint on the left hand-side of the aircraft, along stringer 4L, had better fatigue life than the one on the opposite side, along stringer 4R. The cause of the difference in fatigue life was investigated by close examination of the rivet installation qualities, and was found to be a result of better rivet installation along the lap joint at stringer 4L. Finite element models for both the skin and substructures of the panels were developed and geometrically nonlinear finite element analyses were conducted to verify the loading conditions and to determine near-field parameters governing MSD initiation and growth. Fatigue crack growth predictions based on the NASGRO equation were in good agreement with the experimental crack growth data for through-the-thickness cracks. For subsurface cracks, simulation of crack growth was found to correlate better with fractography data when an empirical crack growth model was used. The results of the study contribute to the understanding of the initiation and growth of MSD in the inner skin layer of a lap joint, and provide valuable data for the evaluation and validation of analytical methodologies to predict MSD initiation and growth and a better understanding on the effect of manufacturing quality on damage accumulation along the lap joint.

  1. Study on utilization of advanced composites in fuselage structures of large transports

    NASA Technical Reports Server (NTRS)

    Johnson, R. W.; Thomson, L. W.; Wilson, R. D.

    1985-01-01

    The potential for utilizing advanced composites in fuselage structures of large transports was assessed. Six fuselage design concepts were selected and evaluated in terms of structural performance, weight, and manufacturing development and costs. Two concepts were selected that merit further consideration for composite fuselage application. These concepts are: (1) a full depth honeycomb design with no stringers, and (2) an I section stringer stiffened laminate skin design. Weight reductions due to applying composites to the fuselages of commercial and military transports were calculated. The benefits of applying composites to a fleet of military transports were determined. Significant technology issues pertinent to composite fuselage structures were identified and evaluated. Program plans for resolving the technology issues were developed.

  2. NASTRAN DMAP Fuzzy Structures Analysis: Summary of Research

    NASA Technical Reports Server (NTRS)

    Sparrow, Victor W.

    2001-01-01

    The main proposed tasks of Cooperative Agreement NCC1-382 were: (1) developing MSC/NASTRAN DMAP language scripts to implement the Soize fuzzy structures approach for modeling the dynamics of complex structures; (2) benchmarking the results of the new code to those for a cantilevered beam in the literature; and (3) testing and validating the new code by comparing the fuzzy structures results to NASA Langley experimental and conventional finite element results for two model test structures representative of aircraft fuselage sidewall construction: (A) a small aluminum test panel (SLP, single longeron panel) with a single longitudinal stringer attached with bolts; and (B) a 47 by 72 inch flat aluminum fuselage panel (AFP, aluminum fuselage panel) including six longitudinal stringers and four frame stiffeners attached with rivets.

  3. An overview of the crash dynamics failure behavior of metal and composite aircraft structures

    NASA Technical Reports Server (NTRS)

    Carden, Huey D.; Boitnott, Richard L.; Fasanella, Edwin L.; Jones, Lisa E.

    1991-01-01

    An overview of failure behavior results is presented from some of the crash dynamics research conducted with concepts of aircraft elements and substructure not necessarily designed or optimized for energy absorption or crash loading considerations. Experimental and analytical data are presented that indicate some general trends in the failure behavior of a class of composite structures that includes fuselage panels, individual fuselage sections, fuselage frames, skeleton subfloors with stringers and floor beams without skin covering, and subfloors with skin added to the frame stringer structure. Although the behavior is complex, a strong similarity in the static/dynamic failure behavior among these structures is illustrated through photographs of the experimental results and through analytical data of generic composite structural models.

  4. Skin, Stringer, and Fastener Loads in Buckled Fuselage Panels

    NASA Technical Reports Server (NTRS)

    Young, Richard D.; Rose, Cheryl A.; Starnes, James H., Jr.

    2001-01-01

    The results of a numerical study to assess the effect of skin buckling on the internal load distribution in a stiffened fuselage panel, with and without longitudinal cracks, are presented. In addition, the impact of changes in the internal loads on the fatigue life and residual strength of a fuselage panel is assessed. A generic narrow-body fuselage panel is considered. The entire panel is modeled using shell elements and considerable detail is included to represent the geometric-nonlinear response of the buckled skin, cross section deformation of the stiffening components, and details of the skin-string attachment with discrete fasteners. Results are presented for a fixed internal pressure and various combinations of axial tension or compression loads. Results illustrating the effect of skin buckling on the stress distribution in the skin and stringer, and fastener loads are presented. Results are presented for the pristine structure, and for cases where damage is introduced in the form of a longitudinal crack adjacent to the stringer, or failed fastener elements. The results indicate that axial compression loads and skin buckling can have a significant effect on the circumferential stress in the skin, and fastener loads, which will influence damage initiation, and a comparable effect on stress intensity factors for cases with cracks. The effects on stress intensity factors will influence damage propagation rates and the residual strength of the panel.

  5. KSC-2011-1194

    NASA Image and Video Library

    2011-01-25

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank begins to wrap up in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians modified 94 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges. They also were re-applying foam to the modified areas of the tank. Attached to its fuel tank and two solid rocket boosters, Discovery is scheduled to roll out to Launch Pad 39A atop a giant crawler-transporter on Jan. 31. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is targeted for Feb. 24. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  6. KSC-2011-1192

    NASA Image and Video Library

    2011-01-25

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank begins to wrap up in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians modified 94 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges. They also were re-applying foam to the modified areas of the tank. Attached to its fuel tank and two solid rocket boosters, Discovery is scheduled to roll out to Launch Pad 39A atop a giant crawler-transporter on Jan. 31. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is targeted for Feb. 24. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  7. KSC-2011-1193

    NASA Image and Video Library

    2011-01-25

    CAPE CANAVERAL, Fla. -- Repair work to space shuttle Discovery's external fuel tank begins to wrap up in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Technicians modified 94 support beams, called stringers, on the tank's intertank region by fitting pieces of metal, called radius blocks, over the stringers' edges. They also were re-applying foam to the modified areas of the tank. Attached to its fuel tank and two solid rocket boosters, Discovery is scheduled to roll out to Launch Pad 39A atop a giant crawler-transporter on Jan. 31. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is targeted for Feb. 24. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  8. Failure behavior of generic metallic and composite aircraft structural components under crash loads

    NASA Technical Reports Server (NTRS)

    Carden, Huey D.; Robinson, Martha P.

    1990-01-01

    Failure behavior results are presented from crash dynamics research using concepts of aircraft elements and substructure not necessarily designed or optimized for energy absorption or crash loading considerations. To achieve desired new designs incorporating improved energy absorption capabilities often requires an understanding of how more conventional designs behave under crash loadings. Experimental and analytical data are presented which indicate some general trends in the failure behavior of a class of composite structures including individual fuselage frames, skeleton subfloors with stringers and floor beams without skin covering, and subfloors with skin added to the frame-stringer arrangement. Although the behavior is complex, a strong similarity in the static/dynamic failure behavior among these structures is illustrated through photographs of the experimental results and through analytical data of generic composite structural models.

  9. The effect of thermomechanical processing on second phase particle redistribution in U-10 wt%Mo

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Hu, Xiaohua; Wang, Xiaowo; Joshi, Vineet V.

    2018-03-01

    The multi-pass hot-rolling process of an annealed uranium-10 wt% molybdenum coupon was studied by plane-strain compression finite element modeling. Two point correlation function (2PCF) was used to analyze the carbide particle distribution after each rolling reduction. The hot rolling simulation results show that the alignment of UC particles along grain boundaries will rotate during rolling until it is parallel to the rolling direction, to form stringer-like distributions which are typically observed in rolled products that contain inclusions. 2PCF analysis of simulation shows that the interparticle spacing shrinks along the normal direction. The number of major peaks of 2PCF along NDmore » decreases after large reduction. The locations of major peaks indicate the inter-stringer distances.« less

  10. Design and fabrication of a stringer stiffened discrete-tube actively cooled panel for a hypersonic aircraft

    NASA Technical Reports Server (NTRS)

    Anthony, F. M.; Halenbrook, R. G.

    1981-01-01

    A 0.61 x 1.22 m (2 x 4 ft) test panel was fabricated and delivered to the Langley Research Center for assessment of the thermal and structural features of the optimized panel design. The panel concept incorporated an aluminum alloy surface panel actively cooled by a network of discrete, parallel, redundant, counterflow passage interconnected with appropriate manifolding, and assembled by adhesive bonding. The cooled skin was stiffened with a mechanically fastened conventional substructure of stringers and frames. A 40 water/60 glycol solution was the coolant. Low pressure leak testing, radiography, holography and infrared scanning were applied at various stages of fabrication to assess integrity and uniformity. By nondestructively inspecting selected specimens which were subsequently tested to destruction, it was possible to refine inspection standards as applied to this cooled panel design.

  11. 46 CFR 154.440 - Allowable stress.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ...: (1) For tank web frames, stringers, or girders of carbon manganese steel or aluminum alloys, meet σB... in appendix A of this part. (c) Tank plating must meet the American Bureau of Shipping's deep tank...

  12. 46 CFR 154.440 - Allowable stress.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ...: (1) For tank web frames, stringers, or girders of carbon manganese steel or aluminum alloys, meet σB... in appendix A of this part. (c) Tank plating must meet the American Bureau of Shipping's deep tank...

  13. 46 CFR 154.440 - Allowable stress.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ...: (1) For tank web frames, stringers, or girders of carbon manganese steel or aluminum alloys, meet σB... in appendix A of this part. (c) Tank plating must meet the American Bureau of Shipping's deep tank...

  14. 18. View of Clark Fork Vehicle Bridge facing north. Looking ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    18. View of Clark Fork Vehicle Bridge facing north. Looking at north concrete abutment and timber stringers. - Clark Fork Vehicle Bridge, Spanning Clark Fork River, serves Highway 200, Clark Fork, Bonner County, ID

  15. Glulam timber deck bridges : final report.

    DOT National Transportation Integrated Search

    1979-01-01

    This report discusses the construction and initial condition of the Virginia Department of Highways and Transportation's first three bridges built with glulam panels on steel stringers. The data show that superstructures with glulam deck panels are m...

  16. 6. VIEW OF UNDERSIDE OF BRIDGE DECK, SHOWING LOWER CHORDS, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    6. VIEW OF UNDERSIDE OF BRIDGE DECK, SHOWING LOWER CHORDS, FLOOR BEAMS, STRINGERS, BOTTOM LATERAL BRACINGS, AND NORTHERN STONE ABUTMENT. - Brown Street Bridge, Brown Street, spanning Oil Creek, Titusville, Crawford County, PA

  17. 6. VIEW EAST OF CEMENT PIER AND TRAFFIC DECK SUPPORT ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    6. VIEW EAST OF CEMENT PIER AND TRAFFIC DECK SUPPORT SYSTEM; NOTE FLOOR BEAMS AND STRINGERS VIEWED FROM UNDERNEATH THE BRIDGE - Water Street Bridge, County Route 119/26, over Guyandotte River, Logan, Logan County, WV

  18. 7. DETAIL VIEW OF PIN CONNECTION, NORTH WEB, SHOWING FLOOR ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    7. DETAIL VIEW OF PIN CONNECTION, NORTH WEB, SHOWING FLOOR BEANS, STRINGERS, LATTICE BRACING, EYEBARS AND DECKING, LOOKING SOUTH - Four Mile Bridge, Spanning Elk River on County Road 42, Steamboat Springs, Routt County, CO

  19. 9. South abutment, detail of collapsed east wing wall; also ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    9. South abutment, detail of collapsed east wing wall; also detail of bottom lateral bracing and stringers; looking southeast - Dodd Ford Bridge, County Road 147 Spanning Blue Earth River, Amboy, Blue Earth County, MN

  20. Beware Participation

    ERIC Educational Resources Information Center

    Jones, Arfon

    1978-01-01

    In 1972 Sidney Stringer Community School and College was established in the inner city of Coventry. Its aims directed attention to community participation and the enlargement of the decision making process. Discusses the problems with delegating educational responsibility to the community. (Author/RK)

  1. Non-Destructive Inspection of Impact Damage in Composite Aircraft Panels by Ultrasonic Guided Waves and Statistical Processing.

    PubMed

    Capriotti, Margherita; Kim, Hyungsuk E; Scalea, Francesco Lanza di; Kim, Hyonny

    2017-06-04

    This paper discusses a non-destructive evaluation (NDE) technique for the detection of damage in composite aircraft structures following high energy wide area blunt impact (HEWABI) from ground service equipment (GSE), such as heavy cargo loaders and other heavy equipment. The test structures typically include skin, co-cured stringers, and C-frames that are bolt-connected onto the skin with shear ties. The inspection exploits the waveguide geometry of these structures by utilizing ultrasonic guided waves and a line scan approach. Both a contact prototype and a non-contact prototype were developed and tested on realistic test panels subjected to impact in the laboratory. The results are presented in terms of receiver operating characteristic curves that show excellent probability of detection with low false alarm rates for defects located in the panel skin and stringers.

  2. Non-Destructive Inspection of Impact Damage in Composite Aircraft Panels by Ultrasonic Guided Waves and Statistical Processing

    PubMed Central

    Capriotti, Margherita; Kim, Hyungsuk E.; Lanza di Scalea, Francesco; Kim, Hyonny

    2017-01-01

    This paper discusses a non-destructive evaluation (NDE) technique for the detection of damage in composite aircraft structures following high energy wide area blunt impact (HEWABI) from ground service equipment (GSE), such as heavy cargo loaders and other heavy equipment. The test structures typically include skin, co-cured stringers, and C-frames that are bolt-connected onto the skin with shear ties. The inspection exploits the waveguide geometry of these structures by utilizing ultrasonic guided waves and a line scan approach. Both a contact prototype and a non-contact prototype were developed and tested on realistic test panels subjected to impact in the laboratory. The results are presented in terms of receiver operating characteristic curves that show excellent probability of detection with low false alarm rates for defects located in the panel skin and stringers. PMID:28772976

  3. Analytical prediction of the interior noise for cylindrical models of aircraft fuselages for prescribed exterior noise fields. Phase 2: Models for sidewall trim, stiffened structures and cabin acoustics with floor partition

    NASA Technical Reports Server (NTRS)

    Pope, L. D.; Wilby, E. G.

    1982-01-01

    An airplane interior noise prediction model is developed to determine the important parameters associated with sound transmission into the interiors of airplanes, and to identify apropriate noise control methods. Models for stiffened structures, and cabin acoustics with floor partition are developed. Validation studies are undertaken using three test articles: a ring stringer stiffened cylinder, an unstiffened cylinder with floor partition, and ring stringer stiffened cylinder with floor partition and sidewall trim. The noise reductions of the three test articles are computed using the heoretical models and compared to measured values. A statistical analysis of the comparison data indicates that there is no bias in the predictions although a substantial random error exists so that a discrepancy of more than five or six dB can be expected for about one out of three predictions.

  4. KSC-2010-5745

    NASA Image and Video Library

    2010-11-30

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the ground umbilical carrier plate (GUCP) and cracks on space shuttle Discovery's external fuel have been repaired. A hydrogen gas leak at the GUCP during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. Also during initial loading operations, the foam cracked on two of the tank's 108 stringers, which are the composite aluminum ribs located vertically on the intertank area. Discovery's next launch attempt is no earlier than Dec. 17 at 8:51 p.m. EST. Until then, engineers will continue to analyze data from the GUCP and stringer crack repairs. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  5. Actively cooled plate fin sandwich structural panels for hypersonic aircraft

    NASA Technical Reports Server (NTRS)

    Smith, L. M.; Beuyukian, C. S.

    1979-01-01

    An unshielded actively cooled structural panel was designed for application to a hypersonic aircraft. The design was an all aluminum stringer-stiffened platefin sandwich structure which used a 60/40 mixture of ethylene glycol/water as the coolant. Eight small test specimens of the basic platefin sandwich concept and three fatigue specimens from critical areas of the panel design was fabricated and tested (at room temperature). A test panel representative of all features of the panel design was fabricated and tested to determine the combined thermal/mechanical performance and structural integrity of the system. The overall findings are that; (1) the stringer-stiffened platefin sandwich actively cooling concept results in a low mass design that is an excellent contender for application to a hypersonic vehicle, and (2) the fabrication processes are state of the art but new or modified facilities are required to support full scale panel fabrication.

  6. Development and demonstration of manufacturing processes for fabricating graphite/Larc-160 polyimide structural elements, part 4, paragraph C

    NASA Technical Reports Server (NTRS)

    1981-01-01

    Progress in the development of processes for production of Celion/LARC-160 graphite-polyimide materials, quality control methods, and the fabrication of Space Shuttle composite structure components is reported. The formulation and processing limits for three batches of resin are presented. Process improvements for simplification of the imidizing and autoclave cure cycles are described. Imidized and autoclave cured test panels were prepared. Celion/LARC-160 cure process verification and the fabrication of honeycomb sandwich panel elements and skin/stringer panels are described. C-scans of laminates imidized at 163 C to 218 C for periods from 30 to 180 minutes, and of process verification laminates made from different batches of prepreg are presented. Failure modes and load/strain characteristics of sandwich elements and C-scans of stringer to skin bond joints are also given.

  7. 18. DETAIL, WEST ABUTMENT, FROM NORTHEAST, SHOWING SQUARED STONE MASONRY ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    18. DETAIL, WEST ABUTMENT, FROM NORTHEAST, SHOWING SQUARED STONE MASONRY ABUTMENT, WITH STRINGERS AND LATERAL BRACING - Virginia Department of Transportation Bridge No. 6051, Spanning Catoctin Creek at State Route 673 (Featherbottom Road), Waterford, Loudoun County, VA

  8. Investigation of cause of cracked stringer on the Blanchette Bridge.

    DOT National Transportation Integrated Search

    2006-10-05

    The Blanchette Bridge carries Interstate 70 across the Missouri River, connecting St. Louis and St. Charles : counties in eastern Missouri. The westbound bridge was constructed in 1958. In 1979, the original : reinforced concrete roadway deck on the ...

  9. Evaluation of a Compression-Loaded-Stitched-Multi-Bay Fuselage Panel With Barely Visible Impact Damage

    NASA Technical Reports Server (NTRS)

    Baker, Donald J.; Li, Ji-An

    2005-01-01

    The experimental results from a stitched VaRTM carbon-epoxy composite panel tested under uni-axial compression loading are presented along with nonlinear finite element analysis prediction of the response. The curved panel is divided by frames and stringers into six bays with a column of three bays along the compressive loading direction. The frames are supported at the frame ends to resist out-of-plane translation. Back-to-back strain gages are used to record the strain and displacement transducers were used to record the out-of-plane displacements. In addition a full-field-displacement measurement technique that utilizes a camera-based-stereo-vision system was used to record the displacements. The panel was loaded to 1.5 times the predicted initial buckling load (1st bay buckling load, P(sub er) from the nonlinear finite element analysis and then was removed from the test machine for impact testing. After impacting with 20 ft-lbs of energy using a spherical impactor to produce barely visible damage the panel was loaded in compression until failure. The buckling load of the first bay to buckle was 97% of the buckling load before impact. The stitching constrained the impact damage from growing during the loading to failure. Impact damage had very little overall effect on panel stiffness. Panel stiffness measured by the full-field-displacement technique indicated a 13% loss in stiffness after impact. The panel failed at 1.64 times the first panel buckling load. The barely visible impact damage did not grow noticeably as the panel failed by global instability due to stringer-web terminations at the frame locations. The predictions from the nonlinear analysis of the finite element modeling of the entire specimen were very effective in the capture of the initial buckling and global behavior of the panel. In addition, the prediction highlighted the weakness of the panel under compression due to stringer web terminations. Both the test results and the nonlinear predictions serve to reinforce the severe penalty in structural integrity caused by the low cost manufacturing technique to terminate the stringer webs, and demonstrates the importance of this type of sub-component testing and high fidelity failure analysis in the design of a composite fuselage.

  10. Membrane protection for steel stringer tops : Yaquina Bay Bridge , Newport, Oregon : final report.

    DOT National Transportation Integrated Search

    1983-09-01

    Direct coastal exposure imposes serious problems to structural and reinforcing steel in bridges. Corrosion causes expansion of the steel resulting in a variety of problems including spalling of reinforced concrete. This problem can become especially ...

  11. 9. VIEW OF SOUTHERN ROCKFACED DRESSED AND MORTARED STONE ABUTMENT, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    9. VIEW OF SOUTHERN ROCKFACED DRESSED AND MORTARED STONE ABUTMENT, SHOWING STEEL CROSSBEAMS, TORSIONAL DIAGONAL STRUTS, AND WOODEN STRINGERS. FACING SOUTHWEST. - Coverts Crossing Bridge, Spanning Mahoning River along Township Route 372 (Covert Road), New Castle, Lawrence County, PA

  12. Effect of initial moisture content on performance of hardwood pallets.

    Treesearch

    Daniel E. Dunmire

    1966-01-01

    Four years of service testing 90 red oak pallets showed that those made with predrilled air-dry deckboards and green stringers gave better service and cost less to maintain than pallets made entirely from either green or air-dry lumber.

  13. 76 FR 29021 - Written Re-Evaluation and Record of Decision for the Final Environmental Impact Statement for the...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-19

    ..., Orlando Airports District Office, 5950 Hazeltine National Drive, Suite 400, Orlando, FL 32822-5024. 407-812-6331 Ext. 129. Issued in Orlando, Florida, on May 12, 2011. W. Dean Stringer, Manager, FAA Orlando...

  14. Facies heterogeneity, pay continuity, and infill potential in barrier-island, fluvial, and submarine fan reservoirs: examples from the Texas Gulf Coast and Midland basins

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Ambrose, W.A.; Tyler, N.

    1989-03-01

    Three reservoirs representing different depositional environments - barrier island (West Ranch field, south-central Texas), fluvial (La Gloria field, south Texas), and submarine fan (Spraberry trend, Midland basin) - illustrate variations in reservoir continuity. Pay continuity methods based on facies geometry and variations in permeability and thickness between wells can quantify reservoir heterogeneity in each of these examples. Although barrier-island reservoirs are relatively homogeneous, West Ranch field contains wide (1000-5000 ft or 300-1500 m) dip-parallel belts of lenticular inlet-fill facies that disrupt reservoir continuity in the main barrier-core facies. Other reservoir compartments in West Ranch field are in flood-tidal delta depositsmore » partly encased in lagoonal mudstones updip of the barrier core. Fluvial reservoirs have a higher degree of internal complexity than barrier-island reservoirs. In La Gloria field, reservoirs exhibit significant heterogeneity in the form of numerous sandstone stringers bounded vertically and laterally by thin mudstone layers. Successful infill wells in La Gloria field contact partly drained reservoir compartments in splay deposits that pinch out laterally into flood-plain mudstones. Recompletions in vertically isolated sandstone stringers in La Gloria field contact other reservoir compartments. Submarine fan deposits are extremely heterogeneous and may have the greatest potential for infill drilling to tap isolated compartments in clastic reservoirs. The Spraberry trend contains thin discontinuous reservoir sandstones deposited in complex mid-fan channels. Although facies relationships in Spraberry reservoirs are similar to those in fluvial reservoirs in La Gloria field, individual pay stringers are thinner and more completely encased in low-permeability mudstone facies.« less

  15. Unibody Composite Pressurized Structure

    NASA Technical Reports Server (NTRS)

    Rufer, Markus; Conger, Robert; Bauer, Thomas; Newman, John

    2013-01-01

    An integrated, generic unibody composite pressurized structure (UCPS) combined with a positive expulsion device (PED), consisting of an elastomeric bladder for monopropellant hydrazine, has been quasi-standardized for spacecraft use. The combination functions as an all-composite, non-metallic, propellant tank with bladder. The integrated UCPS combines several previous innovations - specifically, the linerless, all-composite cryogenic tank technology; all-composite boss; resin formulation; and integrated stringer system. The innovation combines the UCPS with an integrated propellant management device (PMD), the PED or bladder, to create an entirely unique system for in-space use. The UCPS is a pressure vessel that incorporates skirts, stringers, and other structures so that it is both an in-space hydrazine tank, and also a structural support system for a spacecraft in a single, all-composite unit. This innovation builds on the progress in the development of a previous SBIR (Small Business Innovation Research) Phase I with Glenn Research Center and an SBIR III with Johnson Space Center that included the fabrication of two 42-in. (˜107-cm) diameter all-composite cryogenic (LOX and liquid methane) UCPS test tanks for a lunar lander. This Phase II provides hydra zine compatibility testing of the elastomeric bladder, a see-through PED to validate the expulsion process and model, and a complete UCPS-based PED with stringers and skirts that will be used to conduct initial qualification and expulsion tests. This extends the UCPS technology to include hydrazine-based, in-space pro - pulsion applications and can also be used for electric propulsion. This innovation creates a system that, in comparison to the traditional approach, is lower in weight, cost, volume, and production time; is stronger; and is capable of much higher pressures. It also has fewer failure modes, and is applicable to both chemical and electric propulsion systems.

  16. The effect of thermomechanical processing on second phase particle redistribution in U-10 wt%Mo

    NASA Astrophysics Data System (ADS)

    Hu, Xiaohua; Wang, Xiaowo; Joshi, Vineet V.; Lavender, Curt A.

    2018-03-01

    The multi-pass hot-rolling process of an annealed uranium-10 wt% molybdenum (U10Mo) coupon was studied by plane-strain compression finite element modeling. As-cast U10Mo typically contains second phase particles such as uranium carbides (UC) and silicides along the grain boundaries. The volume fraction of UC is typically large, while the other phases can be redissolved in the matrix by certain heat treatments. The UC particle distribution is important due to its influence on the recrystallization processes (particle stimulated nucleation) that occur during annealing between rolling passes. Unfavorable particle distribution and fracture after rolling can affect the grain size and also influence the fuel performance in the reactor. A statistical method, i.e., the two-point correlation function (2PCF), was used to analyze the carbide particle distribution after each rolling reduction. The hot rolling simulation results show that the alignment of UC particles along grain boundaries will rotate during rolling until it is parallel to the rolling direction, to form stringer-like distributions which are typically observed in rolled products that contain inclusions. 2PCF analysis shows that the interparticle spacing shrinks along the normal direction (ND) and increases along the rolling direction (RD). The simulated particle distribution is very similar to that measured experimentally for similar rolling reductions. The magnitudes of major peaks of 2PCF along the ND decrease after large reduction. The locations of major peaks indicate the inter-stringer distances. Many more small peaks appear for the 2PCF along the RD, and this is related to the neighboring particles within stringers, which are along the RD.

  17. Age-forming aluminum panels

    NASA Technical Reports Server (NTRS)

    Baxter, G. I.

    1976-01-01

    Contoured-stiffened 63 by 337 inch 2124 aluminum alloy panels are machined in-the-flat to make integral, tapered T-capped stringers, parallel with longitudinal centerline. Aging fixture, which includes net contour formers made from lofted contour templates, has eggcrate-like structure for use in forming and checking panels.

  18. 46 CFR 190.07-10 - Construction.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ..., including stringers and treads, shall be of steel. (6) Except for washrooms and toilet spaces, deck... laboratories spaces within a general laboratory area may be of B or C class construction. (2) Temporary divisional bulkheads between laboratory spaces within a general laboratory area may be constructed of...

  19. 46 CFR 190.07-10 - Construction.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ..., including stringers and treads, shall be of steel. (6) Except for washrooms and toilet spaces, deck... laboratories spaces within a general laboratory area may be of B or C class construction. (2) Temporary divisional bulkheads between laboratory spaces within a general laboratory area may be constructed of...

  20. 46 CFR 190.07-10 - Construction.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ..., including stringers and treads, shall be of steel. (6) Except for washrooms and toilet spaces, deck... laboratories spaces within a general laboratory area may be of B or C class construction. (2) Temporary divisional bulkheads between laboratory spaces within a general laboratory area may be constructed of...

  1. 46 CFR 190.07-10 - Construction.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ..., including stringers and treads, shall be of steel. (6) Except for washrooms and toilet spaces, deck... laboratories spaces within a general laboratory area may be of B or C class construction. (2) Temporary divisional bulkheads between laboratory spaces within a general laboratory area may be constructed of...

  2. 10. GIRDER APPROACH ON YORKTOWN SIDE, SHOWING PIERS 8S5S (LEFT ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    10. GIRDER APPROACH ON YORKTOWN SIDE, SHOWING PIERS 8S-5S (LEFT TO RIGHT), AND FLOORBEAM/STRINGER SYSTEM. VIEW LOOKING NORTH. - George P. Coleman Memorial Bridge, Spanning York River at U.S. Route 17, Yorktown, York County, VA

  3. Design and fabrication of a boron reinforced intertank skirt

    NASA Technical Reports Server (NTRS)

    Henshaw, J.; Roy, P. A.; Pylypetz, P.

    1974-01-01

    Analytical and experimental studies were performed to evaluate the structural efficiency of a boron reinforced shell, where the medium of reinforcement consists of hollow aluminum extrusions infiltrated with boron epoxy. Studies were completed for the design of a one-half scale minimum weight shell using boron reinforced stringers and boron reinforced rings. Parametric and iterative studies were completed for the design of minimum weight stringers, rings, shells without rings and shells with rings. Computer studies were completed for the final evaluation of a minimum weight shell using highly buckled minimum gage skin. The detail design is described of a practical minimum weight test shell which demonstrates a weight savings of 30% as compared to an all aluminum longitudinal stiffened shell. Sub-element tests were conducted on representative segments of the compression surface at maximum stress and also on segments of the load transfer joint. A 10 foot long, 77 inch diameter shell was fabricated from the design and delivered for further testing.

  4. Low frequency cabin noise reduction based on the intrinsic structural tuning concept: The theory and the experimental results, phase 2. [jet aircraft noise

    NASA Technical Reports Server (NTRS)

    Sengupta, G.

    1978-01-01

    Low frequency cabin noise and sonically induced stresses in an aircraft fuselage may be reduced by intrinsic tuning of the various structural members such as the skin, stringers, and frames and then applying damping treatments on these members. The concept is also useful in identifying the key structural resonance mechanisms controlling the fuselage response to broadband random excitation and in developing suitable damping treatments for reducing the structural response in various frequency ranges. The mathematical proof of the concept and the results of some laboratory and field tests on a group of skin-stringer panels are described. In the so-called stiffness-controlled region, the noise transmission may actually be controlled by stiffener resonances, depending upon the relationship between the natural frequencies of the skin bay and the stiffeners. Therefore, cabin noise in the stiffness-controlled region may be effectively reduced by applying damping treatments on the stiffeners.

  5. Critical joints in large composite primary aircraft structures. Volume 2: Technology demonstration test report

    NASA Technical Reports Server (NTRS)

    Bunin, Bruce L.

    1985-01-01

    A program was conducted to develop the technology for critical structural joints in composite wing structure that meets all the design requirements of a 1990 commercial transport aircraft. The results of four large composite multirow bolted joint tests are presented. The tests were conducted to demonstrate the technology for critical joints in highly loaded composite structure and to verify the analytical methods that were developed throughout the program. The test consisted of a wing skin-stringer transition specimen representing a stringer runout and skin splice on the wing lower surface at the side of the fuselage attachment. All tests were static tension tests. The composite material was Toray T-300 fiber with Ciba-Geigy 914 resin in 10 mil tape form. The splice members were metallic, using combinations of aluminum and titanium. Discussions are given of the test article, instrumentation, test setup, test procedures, and test results for each of the four specimens. Some of the analytical predictions are also included.

  6. Simplified Models for the Study of Postbuckled Hat-Stiffened Composite Panels

    NASA Technical Reports Server (NTRS)

    Vescovini, Riccardo; Davila, Carlos G.; Bisagni, Chiara

    2012-01-01

    The postbuckling response and failure of multistringer stiffened panels is analyzed using models with three levels of approximation. The first model uses a relatively coarse mesh to capture the global postbuckling response of a five-stringer panel. The second model can predict the nonlinear response as well as the debonding and crippling failure mechanisms in a single stringer compression specimen (SSCS). The third model consists of a simplified version of the SSCS that is designed to minimize the computational effort. The simplified model is well-suited to perform sensitivity analyses for studying the phenomena that lead to structural collapse. In particular, the simplified model is used to obtain a deeper understanding of the role played by geometric and material modeling parameters such as mesh size, inter-laminar strength, fracture toughness, and fracture mode mixity. Finally, a global/local damage analysis method is proposed in which a detailed local model is used to scan the global model to identify the locations that are most critical for damage tolerance.

  7. A NASTRAN investigation of simulated projectile damage effects on a UH-1B tail boom model

    NASA Technical Reports Server (NTRS)

    Futterer, A. T.

    1980-01-01

    A NASTRAN model of a UH-1B tail boom that had been designed for another project was used to investigate the effect on structural integrity of simulated projectile damage. Elements representing skin, and sections of stringers, longerons and bulkheads were systematically deleted to represent projectile damage. The structure was loaded in a manner to represent the flight loads that would be imposed on the tail boom at a 130 knot cruise. The deflection of four points on the rear of the tail boom relative to the position of these points for the unloaded, undamaged condition of the tail boom was used as a measure of the loss of structural rigidity. The same procedure was then used with the material properties of the aluminum alloys replaced with the material properties of T300/5208 high strength graphite/epoxy fibrous composite material, (0, + or - 45, 90)s for the skin and (0, + or - 45)s for the longerons, stringers, and bulk heads.

  8. Geochemical, microtextural and petrological studies of the Samba prospect in the Zambian Copperbelt basement: a metamorphosed Palaeoproterozoic porphyry Cu deposit.

    NASA Astrophysics Data System (ADS)

    Master, Sharad; Mirrander Ndhlovu, N.

    2015-04-01

    Ever since Wakefield (1978, IMM Trans., B87, 43-52) described a porphyry-type meta-morphosed Cu prospect, the ca 50 Mt, 0.5% Cu Samba deposit (12.717°S, 27.833°E), hosted by porphyry-associated quartz-sericite-biotite schists in northern Zambia, there has been controversy about its origin and significance. This is because it is situated in the basement to the world's largest stratabound sediment-hosted copper province, the Central African Copperbelt, which is hosted by rocks of the Neoproterozoic Katanga Supergroup. Mineralization in the pre-Katangan basement has long played a prominent role in ore genetic models, with some authors suggesting that basement Cu mineralization may have been recycled into the Katangan basin through erosion and redeposition, while others have suggested that the circulation of fluids through Cu-rich basement may have leached out the metals which are found concentrated in the Katangan orebodies. On the basis of ca 490-460 Ma Ar-Ar ages, Hitzman et al. (2012, Sillitoe Vol., SEG Spec. Publ., 16, 487-514) suggested that Samba represents late-stage impregnation of copper mineralization into the basement, and that it was one of the youngest copper deposits known in the Central African Copperbelt. If the Samba deposit really is that young, then it would have post-dated regional deformation and metamorphism (560-510 Ma), and it ought to be undeformed and unmetamorphosed. The Samba mineralization consists of chalcopyrite and bornite, occurring as disseminations, stringers and veinlets, found in a zone >1 km along strike, in steeply-dipping lenses up to 10m thick and >150m deep. Our new major and trace element XRF geochemical data (14 samples) show that the host rocks are mainly calc-alkaline metadacites. Cu is correlated with Ag (Cu/Ag ~10,000:1) with no Au or Mo. Our study focused on the microtextures and petrology of the Samba ores. We confirm that there is alteration of similar style to that accompanying classical porphyry Cu mineralization, including potassic (biotite+sericite+ quartz), propylitic (clinozoisite+chlorite+saussuritized plagioclase), phyllic (sericite+quartz+ pyrite+hydromuscovite/illite) and argillic (kaolinite+chlorite+dolomite) alteration. The clays were identified with XRD. All the rocks show penetrative deformational textures and fabrics. Our textural studies show that phyllic zone pyrite crystals have quartz-rich pressure shadows, and they predate all phases of deformation. Similarly, in the potassic zone, fracture-controlled biotite stringers in particular orientations are deformed, and partly replaced by chlorite, again showing their pre-deformational, pre-metamorphic origin. Copper sulfide-bearing quartz veinlets are deformed. Many of the alteration assemblages containing biotite or sericite have been deformed into crenulated schists, showing that they were formed early in the deformation history. Coupled with the dating of a Samba metavolcanic rock at 1964±12 Ma (Rainaud et al., 2005, JAES, 42, 1-31), we regard the Samba deposit as a metamorphosed Palaeoproterozoic porphyry-type Cu deposit, which has undergone deformation, and retrograde metamorphism of its alteration assemblages, during the Neoproterozoic Lufilian Orogeny, followed by post-tectonic cooling, which occurred throughout the Copperbelt at about 480±20 Ma. Samba, together with the Mkushi deposits, is part of a long-lived (>100 Ma) Palaeoproterozoic porphyry-Cu province in the Zambian Copperbelt basement, and ore genetic theories for the Copperbelt mineralization must now seriously take this into account.

  9. Deployment of Lightweight Shock Mitigating Boat Manufacturing Innovation

    DTIC Science & Technology

    2012-12-21

    70 LC1- AMI- Z Displacement- Deck ~ HHH ~EEE~~~~~~~ ~~~~!!!!!!~5...between bulkheads Applied to two panels and included stringer 69 LC1- AMI-10 psi Pressure Load 70 LC1- AMI- Z Displacement- Deck ~ HHH ~EEE

  10. Strength and fatigue of three glass fiber reinforced composite bridge decks with mechanical deck to stringer connections.

    DOT National Transportation Integrated Search

    2012-02-01

    Replacement of the steel grating deck on the lift span of the Morrison Bridge in Portland, OR, will utilize glass : fiber reinforced polymer (FRP) panels to address ongoing maintenance issues of the deteriorated existing deck, improve driver : safety...

  11. View of pony truss approach span, showing metal caissons and ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    View of pony truss approach span, showing metal caissons and deck system, including metal floor beams and timber stringers. The same decking system was used on movable span. Looking north from civilian land. - Naval Supply Annex Stockton, Rough & Ready Island, Stockton, San Joaquin County, CA

  12. 78 FR 57053 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-09-17

    ... Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA... Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor... frame from stringers 23 through 31 per Figure 5 or Figure 6 of the service bulletins specified in...

  13. 46 CFR 72.05-20 - Stairways, ladders, and elevators.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... factor of safety of 4 based on the ultimate strength. (j) The stringers, treads, and all platforms and... means of an intermediate landing of rectangular or nearly rectangular shape based on the actual...) Except as further noted the provisions of this section apply to all vessels. (2) For small vessels...

  14. 46 CFR 72.05-20 - Stairways, ladders, and elevators.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... factor of safety of 4 based on the ultimate strength. (j) The stringers, treads, and all platforms and... means of an intermediate landing of rectangular or nearly rectangular shape based on the actual...) Except as further noted the provisions of this section apply to all vessels. (2) For small vessels...

  15. Repair Plate Research Results Released

    Treesearch

    Tom McLain

    1993-01-01

    The Pallet and Container Research Laboratory, Virginia Polytechnic Institute and State University, in cooperation with NWPCA and the Southern Research Station (USDA Forest Service), embarked on a research project two years ago to evaluate the use of metal connector plates (MCP) for the repair and reinforcement of stringer-class pallets. This article discusses the...

  16. 77 FR 63270 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-16

    ... missing fastener between certain stringers of the fuselage frame which connects the frame to a tee. This proposed AD would require a rototest inspection and modification or repair of the fuselage frame at the... Portal: Go to http://www.regulations.gov . Follow the instructions for submitting comments. Fax: (202...

  17. Evaluation of the performance of a press-lam timber bridge : interim report no. 1, bridge installation and load test.

    DOT National Transportation Integrated Search

    1977-01-01

    The report describes the installation and load test of the world's first press-lam timber bridge superstructure. A five-man crew replaced the substandard steel stringer-timber deck superstructure on Rte. 610 over Little Stoney Creek in Shenandoah Cou...

  18. 77 FR 16914 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-03-23

    ... Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: We are adopting a new airworthiness... repetitive inspections for cracking at the fastener hole area just above stringer 28, of both left- and right... Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE...

  19. 78 FR 59801 - Airworthiness Directives; the Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-09-30

    .... ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing... chords between stringers S-22 and S-23, left and right sides; and corrective actions and preventive...-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Alan Pohl...

  20. Fuselage structure using advanced technology fiber reinforced composites

    NASA Technical Reports Server (NTRS)

    Robinson, R. K.; Tomlinson, H. M. (Inventor)

    1982-01-01

    A fuselage structure is described in which the skin is comprised of layers of a matrix fiber reinforced composite, with the stringers reinforced with the same composite material. The high strength to weight ratio of the composite, particularly at elevated temperatures, and its high modulus of elasticity, makes it desirable for use in airplane structures.

  1. Flexural Properties of Eastern Hardwood Pallet Parts

    Treesearch

    John A. McLeod; Marshall S. White; Paul A. Ifju; Philip A. Araman

    1991-01-01

    Accurate estimates of the flexural properties of pallet parts are critical to the safe, yet efficient, design of wood pallets. To develop more accurate data for hardwood pallet parts, 840 stringers and 2,520 deckboards, representing 14 hardwood species, were sampled from 35 mills distributed throughout the Eastern United States. The parts were sorted by species,...

  2. 78 FR 14469 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-03-06

    ... inspections to find cracking of the web, strap, inner chords, inner chord angle of the forward edge frame of the number 5 main entry door cutouts, the frame segment between stringers 16 and 31, and repair if... Portal: Go to http://www.regulations.gov . Follow the instructions for submitting comments. Fax: 202-493...

  3. 76 FR 9225 - Drawbridge Operation Regulation; Curtis Creek, Baltimore, MD

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-17

    ...; Department of Homeland Security Delegation No. 0170.1. 0 2. From February 17, 2011 to November 30, 2011... of the Pennington Avenue Bridge, across Curtis Creek, mile 0.9, at Baltimore, MD. This temporary... replacement of the grid deck, floor beams and stringers. DATES: This temporary final rule is effective from 6...

  4. An Action Research Approach to Supporting Elite Student-Athletes in Higher Education

    ERIC Educational Resources Information Center

    McKenna, Jim; Dunstan-Lewis, Nicky

    2004-01-01

    Support for elite student-athletes was explored within a single English university using Stringer's (1996) Look, Think, Act model of action research. Entry to the ongoing support programme is competitive and participation is voluntary, with sessions delivered every second week after lectures. Based on supporting documentation, interviews, focus…

  5. View of pony truss approach span, showing metal caissons and ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    View of pony truss approach span, showing metal caissons and deck system, including metal floor beams and timber stringers. The same decking system was used on movable span. Looking north from civilian land. - Naval Supply Annex Stockton, Daggett Road Bridge, Daggett Road traversing Burns Cut Off, Stockton, San Joaquin County, CA

  6. 77 FR 43547 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-25

    ...). SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737... stringers S-22 and S-23, left and right sides; and corrective actions and preventive modification if... Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590...

  7. Cryotank Skin/Stringer Bondline Analysis

    NASA Technical Reports Server (NTRS)

    Nguyen, Bao

    1999-01-01

    The need for light weight structure for advanced launch systems have presented great challenges and led to the usage of composites materials in a variety of structural assemblies where joining of two or more components is imperative. Although joints can be mechanically bolted, adhesive bonding has always been a very desirable method for joining the composite components, particularly for the cryotank systems, to achieve maximum structural efficiency. This paper presents the analytical approach resulted from the conceptual development of the DC-Y composite cryotank, conducted under the NASA/Boeing NRA 8-12 Partnership, to support the continued progress of SSTO (Single-Stage-To-Orbit) concepts. One of the critical areas of design was identified as the bonded interface between the skin (tank wall) and stringer. The approach to analyze this critical area will be illustrated through the steps which were used to evaluate the structural integrity of the bondline. Detailed finite element models were developed and numerous coupon test data were also gathered as part of the approach. Future plan is to incorporate this approach as a building block in analyzing bondline for the cryotank systems of RLVs (Reusable Launch Vehicles).

  8. Cost studies for commercial fuselage crown designs

    NASA Technical Reports Server (NTRS)

    Walker, T. H.; Smith, P. J.; Truslove, G.; Willden, K. S.; Metschan, S. L.; Pfahl, C. L.

    1991-01-01

    Studies were conducted to evaluate the cost and weight potential of advanced composite design concepts in the crown region of a commercial transport. Two designs from each of three design families were developed using an integrated design-build team. A range of design concepts and manufacturing processes were included to allow isolation and comparison of cost centers. Detailed manufacturing/assembly plans were developed as the basis for cost estimates. Each of the six designs was found to have advantages over the 1995 aluminum benchmark in cost and weight trade studies. Large quadrant panels and cobonded frames were found to save significant assembly labor costs. Comparisons of high- and intermediate-performance fiber systems were made for skin and stringer applications. Advanced tow placement was found to be an efficient process for skin lay up. Further analysis revealed attractive processes for stringers and frames. Optimized designs were informally developed for each design family, combining the most attractive concepts and processes within that family. A single optimized design was selected as the most promising, and the potential for further optimization was estimated. Technical issues and barriers were identified.

  9. Test results from large wing and fuselage panels

    NASA Technical Reports Server (NTRS)

    Madan, Ram C.; Voldman, Mike

    1993-01-01

    This paper presents the first results in an assessment of the strength, stiffness, and damage tolerance of stiffened wing and fuselage subcomponents. Under this NASA funded program, 10 large wing and fuselage panels, variously fabricated by automated tow placement and dry-stitched preform/resin transfer molding, are to be tested. The first test of an automated tow placement six-longeron fuselage panel under shear load was completed successfully. Using NASTRAN finite-element analysis the stiffness of the panel in the linear range prior to buckling was predicted within 3.5 percent. A nonlinear analysis predicted the buckling load within 10 percent and final failure load within 6 percent. The first test of a resin transfer molding six-stringer wing panel under compression was also completed. The panel failed unexpectedly in buckling because of inadequate supporting structure. The average strain was 0.43 percent with a line load of 20.3 kips per inch of width. This strain still exceeds the design allowable strains. Also, the stringers did not debond before failure, which is in contrast to the general behavior of unstitched panels.

  10. Behavior of composite/metal aircraft structural elements and components under crash type loads: What are they telling us

    NASA Technical Reports Server (NTRS)

    Carden, Huey D.; Boitnott, Richard L.; Fasanella, Edwin L.

    1990-01-01

    Failure behavior results are presented from crash dynamics research using concepts of aircraft elements and substructure not necessarily designed or optimized for energy absorption or crash loading considerations. To achieve desired new designs which incorporate improved energy absorption capabilities often requires an understanding of how more conventional designs behave under crash loadings. Experimental and analytical data are presented which indicate some general trends in the failure behavior of a class of composite structures which include individual fuselage frames, skeleton subfloors with stringers and floor beams but without skin covering, and subfloors with skin added to the frame-stringer arrangement. Although the behavior is complex, a strong similarity in the static and dynamic failure behavior among these structures is illustrated through photographs of the experimental results and through analytical data of generic composite structural models. It is believed that the similarity in behavior is giving the designer and dynamists much information about what to expect in the crash behavior of these structures and can guide designs for improving the energy absorption and crash behavior of such structures.

  11. Behavior of composite/metal aircraft structural elements and components under crash type loads - What are they telling us?

    NASA Technical Reports Server (NTRS)

    Carden, Huey D.; Boitnott, Richard L.; Fasanella, Edwin L.

    1990-01-01

    Failure behavior results are presented from crash dynamics research using concepts of aircraft elements and substructure not necessarily designed or optimized for energy absorption or crash loading considerations. To achieve desired new designs which incorporate improved energy absorption capabilities often requires an understanding of how more conventional designs behave under crash loadings. Experimental and analytical data are presented which indicate some general trends in the failure behavior of a class of composite structures which include individual fuselage frames, skeleton subfloors with stringers and floor beams but without skin covering, and subfloors with skin added to the frame-stringer arrangement. Although the behavior is complex, a strong similarity in the static and dynamic failure behavior among these structures is illustrated through photographs of the experimental results and through analytical data of generic composite structural models. It is believed that the similarity in behavior is giving the designer and dynamists much information about what to expect in the crash behavior of these structures and can guide designs for improving the energy absorption and crash behavior of such structures.

  12. Unique failure behavior of metal/composite aircraft structural components under crash type loads

    NASA Technical Reports Server (NTRS)

    Carden, Huey D.

    1990-01-01

    Failure behavior results are presented on some of the crash dynamics research conducted with concepts of aircraft elements and substructure which have not necessarily been designed or optimized for energy absorption or crash loading considerations. To achieve desired new designs which incorporate improved energy absorption capabilities often requires an understanding of how more conventional designs behave under crash type loadings. Experimental and analytical data are presented which indicate some general trends in the failure behavior of a class of composite structures which include individual fuselage frames, skeleton subfloors with stringers and floor beams but without skin covering, and subfloors with skin added to the frame-stringer arrangement. Although the behavior is complex, a strong similarity in the static/dynamic failure behavior among these structures is illustrated through photographs of the experimental results and through analytical data of generic composite structural models. It is believed that the thread of similarity in behavior is telling the designer and dynamists a great deal about what to expect in the crash behavior of these structures and can guide designs for improving the energy absorption and crash behavior of such structures.

  13. Design Optimization and Residual Strength Assessment of a Cylindrical Composite Shell Structure

    NASA Technical Reports Server (NTRS)

    Rais-Rohani, Masoud

    2000-01-01

    A summary of research conducted during the specified period is presented. The research objectives included the investigation of an efficient technique for the design optimization and residual strength assessment of a semi-monocoque cylindrical shell structure made of composite materials. The response surface methodology is used in modeling the buckling response of individual skin panels under the combined axial compression and shear loading. These models are inserted into the MSC/NASTRAN code for design optimization of the cylindrical structure under a combined bending-torsion loading condition. The comparison between the monolithic and sandwich skin design cases indicated a 35% weight saving in using sandwich skin panels. In addition, the residual strength of the optimum design was obtained by identifying the most critical region of the structure and introducing a damage in the form of skin-stringer and skin-stringer-frame detachment. The comparison between the two skin design concepts indicated that the sandwich skin design is capable of retaining a higher residual strength than its monolithic counterpart. The results of this investigation are presented and discussed in this report.

  14. Demonstration and Methodology of Structural Monitoring of Stringer Runs out Composite Areas by Embedded Optical Fiber Sensors and Connectors Integrated during Production in a Composite Plant.

    PubMed

    Miguel Giraldo, Carlos; Zúñiga Sagredo, Juan; Sánchez Gómez, José; Corredera, Pedro

    2017-07-21

    Embedding optical fibers sensors into composite structures for Structural Health Monitoring purposes is not just one of the most attractive solutions contributing to smart structures, but also the optimum integration approach that insures maximum protection and integrity of the fibers. Nevertheless this intended integration level still remains an industrial challenge since today there is no mature integration process in composite plants matching all necessary requirements. This article describes the process developed to integrate optical fiber sensors in the Production cycle of a test specimen. The sensors, Bragg gratings, were integrated into the laminate during automatic tape lay-up and also by a secondary bonding process, both in the Airbus Composite Plant. The test specimen, completely representative of the root joint of the lower wing cover of a real aircraft, is comprised of a structural skin panel with the associated stringer run out. The ingress-egress was achieved through the precise design and integration of miniaturized optical connectors compatible with the manufacturing conditions and operational test requirements. After production, the specimen was trimmed, assembled and bolted to metallic plates to represent the real triform and buttstrap, and eventually installed into the structural test rig. The interrogation of the sensors proves the effectiveness of the integration process; the analysis of the strain results demonstrate the good correlation between fiber sensors and electrical gauges in those locations where they are installed nearby, and the curvature and load transfer analysis in the bolted stringer run out area enable demonstration of the consistency of the fiber sensors measurements. In conclusion, this work presents strong evidence of the performance of embedded optical sensors for structural health monitoring purposes, where in addition and most importantly, the fibers were integrated in a real production environment and the ingress-egress issue was solved by the design and integration of miniaturized connectors compatible with the manufacturing and structural test phases.

  15. Demonstration and Methodology of Structural Monitoring of Stringer Runs out Composite Areas by Embedded Optical Fiber Sensors and Connectors Integrated during Production in a Composite Plant

    PubMed Central

    Miguel Giraldo, Carlos; Zúñiga Sagredo, Juan; Sánchez Gómez, José; Corredera, Pedro

    2017-01-01

    Embedding optical fibers sensors into composite structures for Structural Health Monitoring purposes is not just one of the most attractive solutions contributing to smart structures, but also the optimum integration approach that insures maximum protection and integrity of the fibers. Nevertheless this intended integration level still remains an industrial challenge since today there is no mature integration process in composite plants matching all necessary requirements. This article describes the process developed to integrate optical fiber sensors in the Production cycle of a test specimen. The sensors, Bragg gratings, were integrated into the laminate during automatic tape lay-up and also by a secondary bonding process, both in the Airbus Composite Plant. The test specimen, completely representative of the root joint of the lower wing cover of a real aircraft, is comprised of a structural skin panel with the associated stringer run out. The ingress-egress was achieved through the precise design and integration of miniaturized optical connectors compatible with the manufacturing conditions and operational test requirements. After production, the specimen was trimmed, assembled and bolted to metallic plates to represent the real triform and buttstrap, and eventually installed into the structural test rig. The interrogation of the sensors proves the effectiveness of the integration process; the analysis of the strain results demonstrate the good correlation between fiber sensors and electrical gauges in those locations where they are installed nearby, and the curvature and load transfer analysis in the bolted stringer run out area enable demonstration of the consistency of the fiber sensors measurements. In conclusion, this work presents strong evidence of the performance of embedded optical sensors for structural health monitoring purposes, where in addition and most importantly, the fibers were integrated in a real production environment and the ingress-egress issue was solved by the design and integration of miniaturized connectors compatible with the manufacturing and structural test phases. PMID:28754009

  16. Structural Integrity Testing Method for PRSEUS Rod-Wrap Stringer Design

    NASA Technical Reports Server (NTRS)

    Wang, John T.; Grenoble, Ray W.; Pickell, Robert D.

    2012-01-01

    NASA Langley Research Center and The Boeing Company are developing an innovative composite structural concept, called PRSEUS, for the flat center section of a future environmentally friendly hybrid wing body (HWB) aircraft. The PRSEUS (Pultruded Rod Stitched Efficient Unitized Structure) concept uses dry textile preforms for the skins, frames, and stiffener webs. The highly loaded stiffeners are made from precured unidirectional carbon/epoxy rods and dry fiber preforms. The rods are wrapped with the dry fiber preforms and a resin infusion process is used to form the rod-wrap stiffeners. The structural integrity of the rod-wrap interface is critical for maintaining the panel s high strength and bending rigidity. No standard testing method exists for testing the strength of the rod-wrap bondline. Recently, Boeing proposed a rod push-out testing method and conducted some preliminary tests using this method. This paper details an analytical study of the rod-wrap bondline. The rod-wrap interface is modeled as a cohesive zone for studying the initiation and growth of interfacial debonding during push-out testing. Based on the correlations of analysis results and Boeing s test data, the adequacy of the rod-wrap testing method is evaluated, and potential approaches for improvement of the test method are proposed.

  17. Redesigning of a Canard Control Surface of an Advanced Fighter Aircraft: Effect on Buckling and Aerodynamic Behavior

    NASA Astrophysics Data System (ADS)

    Shrivastava, Sachin; Mohite, P. M.

    2015-01-01

    A redesign of canard control-surface of an advanced all-metallic fighter aircraft was carried out by using carbon fibre composite (CFC) for ribs and panels. In this study ply-orientations of CFC structure are optimized using a Genetic-Algorithm (GA) with an objective function to have minimum failure index (FI) according to Tsai-Wu failure criterion. The redesigned CFC structure was sufficiently strong to withstand aerodynamic loads from stress and deflection points of view. Now, in the present work CFC canard structure has been studied for its buckling strength in comparison to existing metallic design. In this study, the existing metallic design was found to be weak in buckling. Upon a detailed investigation, it was revealed that there are reported failures in the vicinity of zones where initial buckling modes are excited as predicted by the finite element based buckling analysis. In view of buckling failures, the redesigned CFC structure is sufficiently reinforced with stringers at specific locations. After providing reinforcements against buckling, the twist and the camber variations of the airfoil are checked and compared with existing structure data. Finally, the modal analysis has been carried out to compare the variation in excitation frequency due to material change. The CFC structure thus redesigned is safe from buckling and aerodynamic aspects as well.

  18. 75 FR 53843 - Airworthiness Directives; The Boeing Company Model 737-100 and -200 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-02

    ... damaged fasteners of certain fuselage frames and stub beams, and corrective actions if necessary. For... hole of the frame at body station 639, stringer S-16, and corrective actions if necessary. For certain... terminates the repetitive inspections for the repaired or modified frame only. For airplanes on which the...

  19. Ultrasonic Inspection of Wooden Pallet Parts Using Time of Flight

    Treesearch

    Daniel L. Schmoldt; Robert M. Nelson; Robert J. Ross; Kent A. McDonald

    1997-01-01

    Wooden pallets are the largest single use of sawn hardwood logs in the USA. Unfortunately, millions of wooden pallets are discarded annually due to damage or because their low cost makes them readily disposable. In general, pallets are constructed from stringers and deckboards of random quality. Higher quality wooden pallets, however, can be built from higher quality...

  20. 75 FR 52907 - Airworthiness Directives; The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-30

    ... stringer or frame bay stress were used along the entire joint, the work instructions would become too large...-body fairings locations, and external repair and cutout reinforcement areas; and related investigative...-body fairing locations, and external repair and cutout reinforcement areas; and related investigative...

  1. Strength and stiffness of reinforced yellow-poplar glued-laminated beams

    Treesearch

    R. Hernandez; R. C. Moody

    In bridge applications, it is often necessary to minimize the depth of the bridge structure to provide for the required hydraulic opening or reduce the volume of approach fill. For bridges that utilize structural glued-laminated (glulam) timber beams as stringers, reinforcement using thin strips of pultruded E-glass-fiber-reinforced plastic (GFRP) composites may permit...

  2. Street Fight: Welcome to the World of Urban Lit

    ERIC Educational Resources Information Center

    Pattee, Amy

    2008-01-01

    Street lit is controversial stuff. Even though street lit is a huge hit with today's teens, one will not find the semiautobiographical novels of Vickie Stringer and Nikki Turner, the grandes dames of urban fiction, on many (if any) high school reading lists or, for that matter, on some public libraries' shelves. That's because street lit (aka…

  3. View, underside of deck, from northwest and below, showing structural ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    View, underside of deck, from northwest and below, showing structural configuration, including pin connections of vertical truss members to lower chord, transverse floor beams, stringers, lateral bracing, concrete deck, and squared cut stone masonry center pier, including upstream concrete encased nose - Castle Garden Bridge, Township Route 343 over Bennetts Branch of Sinnemahoning Creek, Driftwood, Cameron County, PA

  4. 78 FR 60804 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-02

    ... detailed and eddy current inspections to detect cracking of the frame web around the cutout for the doorstop intercostal strap at the aft side of the station (STA) 291.5 frame at stringer 16R, and corrective... various locations of the STA 277 to STA 291.5 frames and intercostals, including webs, chords, clips, and...

  5. 75 FR 27969 - Airworthiness Directives; The Boeing Company Model 737-100 and -200 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-19

    ... cracking and damaged fasteners of certain fuselage frames and stub beams, and corrective actions if... the inboard chord fastener hole of the frame at body station 639, stringer S-16, and corrective... inspections for the repaired or modified frame only. For airplanes on which the modification or repair is done...

  6. A Field Assessment of Timber Highway Bridge Durability in the United States

    Treesearch

    J.P. Wacker; B.K. Brashaw; F. Jalinoos

    2015-01-01

    This paper summarizes a cooperative project to assess the current condition and life expectancy of 132 timber highway bridge superstructures at locations throughout the United States. Several superstructure types were included in this comprehensive effort, of which two-thirds were sawn timber stringer systems. In-depth inspections were conducted by the project team...

  7. Public Understanding to Political Voice: Action Research and Generative Curricular Practices in Issues and Reform

    ERIC Educational Resources Information Center

    Agnello, Mary Frances

    2007-01-01

    The author and preservice teachers in a postbaccalaureate Issues and Reform in Secondary Education course engaged Ernest Stringer's (2004) model of action research to develop generative curricula. They adhered to Walter C. Parker's (1991, 2006) vision of public formation and essential social studies teaching and used student-centered teaching…

  8. A Different Pitch to Slope

    ERIC Educational Resources Information Center

    Wolbert, William

    2017-01-01

    The query "When are we ever going to use this?" is easily answered when discussing the slope of a line. The pitch of a roof, the grade of a road, and stair stringers are three applications of slope that are used extensively. The concept of slope, which is introduced fairly early in the mathematics curriculum has hands-on applications…

  9. Research Out On What Buyers of Used Pallets Think

    Treesearch

    Robert J. Bush; Ronen Roudik; Philip A. Araman

    1995-01-01

    Preliminary findings from a new study on repaired pallets indicate that pallet users donât like half companion stringers, split deckboards and protruding fasteners. There has been an awareness for some time that buyers of repaired/recycled pallets prefer to receive pallets that are "like new". However, the reality of the business is that repaired/recycled...

  10. Nondestructive evaluation of defects in wood pallet parts by ultrasonic scanning

    Treesearch

    M. Firoz Kabir; Philip A. Araman

    2003-01-01

    Ultrasonic scanning experiments were conducted for detecting defects in wood pallet parts using rolling transducers. The characterization of defects is important for sorting and grading pallet parts, as well as for manufacturing quality and durable pallets. This paper reports the scanning results for stringers and deckboards – the two main components of pallet for red...

  11. 19. MAIN MEETING ROOM LOOKING SOUTH FROM GALLERY. Note coved ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    19. MAIN MEETING ROOM LOOKING SOUTH FROM GALLERY. Note coved extension of gallery, erected when offices were built on gallery for the use of the Friends Service Committee in 1936. Note also the short stair balusters resulting from the wide modesty stair stringer provided for the women's side. - Twelfth Street Meeting House, 20 South Twelfth Street, Philadelphia, Philadelphia County, PA

  12. Combat Oak Shortage Problems Using Fortified Stringers

    Treesearch

    Philip A. Araman

    1993-01-01

    Oak pallet material supplies from sawmills have been and may continue to be difficult to secure in quantities by the pallet industry. Other oak using markets such as the furniture, cabinet, tie and flooring markets need more oak and are paying much higher prices than pallet manufacturers and recyclers wish to or can pay. These other markets are also willing to take...

  13. Factor Stability of Primary Scales of the General Organization Questionnaire

    DTIC Science & Technology

    1980-10-01

    leadership , climate , and processes function optimally. The Leadership and Organizational Effectiveness Work Unit re- searches personal, small-group...the Litwin and Stringer (1968) Organizational Climate Questionnaire found a factor structure that was dif- ferent from the a priori structure...number) General Organization Questionnaire (GOQ) Organizational climate Organizational effectiveness 20. ATRACT (Cnm N eriwem7 d Iderntify by block numbst

  14. Skin-stringer panel normal mode response experimental data and finite element computer program documentation

    NASA Technical Reports Server (NTRS)

    Rudder, F. F., Jr.

    1971-01-01

    Detailed information is presented for the analytical and the experimental programs described in the report on Effects of Design Details on Structural Response to Acoustic Excitation, NASA CR-1959. This is a supplement to the basic report and detailed experimental data from all the specimens described in that report are discussed and presented in tabular form.

  15. Calibration of streamflow gauging stations at the Tenderfoot Creek Experimental Forest

    Treesearch

    Scott W. Woods

    2007-01-01

    We used tracer based methods to calibrate eleven streamflow gauging stations at the Tenderfoot Creek Experimental Forest in western Montana. At six of the stations the measured flows were consistent with the existing rating curves. At Lower and Upper Stringer Creek, Upper Sun Creek and Upper Tenderfoot Creek the published flows, based on the existing rating curves,...

  16. Investigation of early timber–concrete composite bridges in the United States

    Treesearch

    James P. Wacker; Alfredo Dias; Travis K. Hosteng

    2017-01-01

    The use of timber–concrete composite (TCC) bridges in the United States dates back to circa 1925. Two different TCC systems were constructed during this early period. The first system included a longitudinal nail-laminated deck composite with a concrete deck top layer. The second system included sawn timber stringers supporting a concrete deck top layer. Records...

  17. Finite Elements Analysis of a Composite Semi-Span Test Article With and Without Discrete Damage

    NASA Technical Reports Server (NTRS)

    Lovejoy, Andrew E.; Jegley, Dawn C. (Technical Monitor)

    2000-01-01

    AS&M Inc. performed finite element analysis, with and without discrete damage, of a composite semi-span test article that represents the Boeing 220-passenger transport aircraft composite semi-span test article. A NASTRAN bulk data file and drawings of the test mount fixtures and semi-span components were utilized to generate the baseline finite element model. In this model, the stringer blades are represented by shell elements, and the stringer flanges are combined with the skin. Numerous modeling modifications and discrete source damage scenarios were applied to the test article model throughout the course of the study. This report details the analysis method and results obtained from the composite semi-span study. Analyses were carried out for three load cases: Braked Roll, LOG Down-Bending and 2.5G Up-Bending. These analyses included linear and nonlinear static response, as well as linear and nonlinear buckling response. Results are presented in the form of stress and strain plots. factors of safety for failed elements, buckling loads and modes, deflection prediction tables and plots, and strainage prediction tables and plots. The collected results are presented within this report for comparison to test results.

  18. Global and Local Stress Analyses of McDonnell Douglas Stitched/RFI Composite Wing Stub Box

    NASA Technical Reports Server (NTRS)

    Wang, John T.

    1996-01-01

    This report contains results of structural analyses performed in support of the NASA structural testing of an all-composite stitched/RFI (resin film infusion) wing stub box. McDonnell Douglas Aerospace Company designed and fabricated the wing stub box. The analyses used a global/local approach. The global model contains the entire test article. It includes the all-composite stub box, a metallic load-transition box and a metallic wing-tip extension box. The two metallic boxes are connected to the inboard and outboard ends of the composite wing stub box, respectively. The load-transition box was attached to a steel and concrete vertical reaction structure and a load was applied at the tip of the extension box to bend the wing stub box upward. The local model contains an upper cover region surrounding three stringer runouts. In that region, a large nonlinear deformation was identified by the global analyses. A more detailed mesh was used for the local model to obtain more accurate analysis results near stringer runouts. Numerous analysis results such as deformed shapes, displacements at selected locations, and strains at critical locations are included in this report.

  19. Current Thoughts on Reactive Element Effects in Alumina-Forming Systems: In Memory of John Stringer

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Naumenko, D.; Pint, B. A.; Quadakkers, W. J.

    In memory of John Stringer (1934–2014), one of the leaders in studying the reactive element (RE) effects, this paper reviews the current status of understanding of the effect of RE dopants on high-temperature oxidation behavior, with an emphasis on recent research related to deploying alumina-forming alloys and coatings with optimal performance in commercial systems. Additionally, to the well-known interaction between indigenous sulfur and RE additions, effects have been observed with C, N, and O found in commercial alloys and coatings. While there are many similarities between alumina-forming alloys and coatings, the latter bring additional complicating factors such as the effectsmore » of O incorporation during thermal spraying MCrAlY coatings, coating roughness, and heat treatments that must be considered in optimizing the beneficial dopant addition. We can see analogies between RE effects in alloys and in the substrates beneath diffusion M–Al coatings. Recently, there has been more interest in the influence of mixed oxidant environments, since these may modify the manifestation of the RE effect. Some thoughts are provided on optimizing the RE benefit and modeling oxidation of RE-doped alloys.« less

  20. Current Thoughts on Reactive Element Effects in Alumina-Forming Systems: In Memory of John Stringer

    DOE PAGES

    Naumenko, D.; Pint, B. A.; Quadakkers, W. J.

    2016-05-06

    In memory of John Stringer (1934–2014), one of the leaders in studying the reactive element (RE) effects, this paper reviews the current status of understanding of the effect of RE dopants on high-temperature oxidation behavior, with an emphasis on recent research related to deploying alumina-forming alloys and coatings with optimal performance in commercial systems. Additionally, to the well-known interaction between indigenous sulfur and RE additions, effects have been observed with C, N, and O found in commercial alloys and coatings. While there are many similarities between alumina-forming alloys and coatings, the latter bring additional complicating factors such as the effectsmore » of O incorporation during thermal spraying MCrAlY coatings, coating roughness, and heat treatments that must be considered in optimizing the beneficial dopant addition. We can see analogies between RE effects in alloys and in the substrates beneath diffusion M–Al coatings. Recently, there has been more interest in the influence of mixed oxidant environments, since these may modify the manifestation of the RE effect. Some thoughts are provided on optimizing the RE benefit and modeling oxidation of RE-doped alloys.« less

  1. Structural analysis of Aircraft fuselage splice joint

    NASA Astrophysics Data System (ADS)

    Udaya Prakash, R.; Kumar, G. Raj; Vijayanandh, R.; Senthil Kumar, M.; Ramganesh, T.

    2016-09-01

    In Aviation sector, composite materials and its application to each component are one of the prime factors of consideration due to the high strength to weight ratio, design flexibility and non-corrosive so that the composite materials are widely used in the low weight constructions and also it can be treated as a suitable alternative to metals. The objective of this paper is to estimate and compare the suitability of a composite skin joint in an aircraft fuselage with different joints by simulating the displacement, normal stress, vonmises stress and shear stress with the help of numerical solution methods. The reference Z-stringer component of this paper is modeled by CATIA and numerical simulation is carried out by ANSYS has been used for splice joint presents in the aircraft fuselage with three combinations of joints such as riveted joint, bonded joint and hybrid joint. Nowadays the stringers are using to avoid buckling of fuselage skin, it has joined together by rivets and they are connected end to end by splice joint. Design and static analysis of three-dimensional models of joints such as bonded, riveted and hybrid are carried out and results are compared.

  2. Ultrasonic defect detection in wooden pallet parts for quality sorting

    Treesearch

    Daniel L. Schmoldt; Robert J. Ross; Robert M. Nelson

    1996-01-01

    Millions of wooden pallets are discarded annually due to damage or because their low cost makes them readily disposable. Higher quality wooden pallets, however, can be built from high quality deckboards and stringers, and have a much longer life cycle and a lower cost per trip. The long-term goal of this project is to develop an automated pallet part inspection system...

  3. Ultrasonic Defect Detection in Wooden Pallet Parts for Quality Sorting

    Treesearch

    Daniel L. Schmoldt; Robert M. Nelson; Robert J. Ross

    1996-01-01

    Millions of wooden pallets are discarded annually due to damage or because their low cost makes them readily disposable. Higher quality wooden pallets, however, can be built from high quality deckboards and stringers, and have a much longer life cycle and a lower cost per trip. The long-term goal of this project is to develop an automated pallet part inspection system...

  4. 20. Underside of swingspan showing bottom truss chords, floor beams ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    20. Underside of swing-span showing bottom truss chords, floor beams and stringers. The draw rests on the end-lift pedestals (end ram supports) at each side of the masonry rest pier. The end-lift drive shaft is supported from the center of the draw. (Nov. 25, 1988) - University Heights Bridge, Spanning Harlem River at 207th Street & West Harlem Road, New York County, NY

  5. Global Response of the Space Shuttle External Tank with the Presence of Intertank Stringer Cracks and Radius Blocks

    NASA Technical Reports Server (NTRS)

    Lovejoy, Andrew E.; Rankin, Charles C.

    2013-01-01

    After propellant was loaded into the external tank (ET), the November 5, 2010 launch of Space Shuttle mission STS-133 was scrubbed due to a gaseous hydrogen leak located in a vent line near the ground umbilical and ET connection. Subsequent visual inspections identified cracks in the sprayed-on foam insulation in the forward end of the ET intertank segment, adjacent to the liquid oxygen (LOX) tank, as shown in Figure 1. These cracks necessitated repair of the foam due to debris concerns that violated launch constraints. As part of the repair process, the affected foam was removed to reveal cracks in the underlying external hat stiffeners on the intertank, as shown in Figure 2. Ultimately, five stiffeners were discovered to be cracked adjacent to the LOX tank. As the managing center for the ET Project, NASA Marshall Space Flight Center (MSFC) coordinated failure investigation and repair activities among multiple organizations, which included the ET prime contractor (Lockheed Martin Space Systems Michoud Operations), the Space Shuttle Program Office at the NASA Johnson Space Center (JSC), the NASA Kennedy Space Center (KSC), and the NASA Engineering and Safety Center (NESC). STS-133 utilized the external tank designated as ET-137. Many aspects of the investigation have been reported previously in Refs. 1-7, which focus on the root cause of the failures, the flight readiness rationale and the local analyses of the stringer failures and repair. This paper summarizes the global analyses that were conducted on ET-137 as part of the NESC effort during the investigation, which was conducted primarily to determine if the repairs that were introduced to the stringers would alter the global response of the ET. In the process of the investigation, a new STAGS tabular input capability was developed to more easily introduce the aerodynamic pressure loads using a method that could easily be extended to incorporate finite element property data such as skin and stiffener thicknesses and beam cross-sectional properties.

  6. Brazing of beryllium for structural applications

    NASA Technical Reports Server (NTRS)

    Vogan, J. W.

    1972-01-01

    Progress made in fabricating a beryllium compression tube structure and a stiffened beryllium panel. The compression tube was 7.6cm in diameter and 30.5cm long with titanium end fittings. The panel was 203cm long and stiffened with longitudinal stringers. Both units were assembled by brazing with BAg-18 braze alloy. The detail parts were fabricated by hot forming 0.305cm beryllium sheet and the brazing parameters established.

  7. Synopsis: the role of prescribed burning in regenerating Quercus macrocarpa and associated woody plants in stringer woodlands in the Black Hills, South Dakota

    Treesearch

    Carolyn Hull Sieg; Henry A. Wright

    1998-01-01

    Poor tree reproduction, sparse shrub cover, and increasing amounts of exotic species such as Kentucky bluegrass (Poa pratensis) are common problems in woody draws in the Northern Great Plains. Although the historic role of fire in maintaining woody draws is unclear, it is likely that these woodlands burned periodically, especially in dry years on hot...

  8. Development of a Resource Manager Framework for Adaptive Beamformer Selection

    DTIC Science & Technology

    2013-12-27

    DEVELOPMENT OF A RESOURCE MANAGER FRAMEWORK FOR ADAPTIVE BEAMFORMER SELECTION DISSERTATION Jeremy P. Stringer, Major, USAF AFIT-ENG-DS-13-D-01...Force, the United States Department of Defense or the United States Government. AFIT-ENG-DS-13-D-01 DEVELOPMENT OF A RESOURCE MANAGER FRAMEWORK FOR...ADAPTIVE BEAMFORMER SELECTION DISSERTATION Presented to the Faculty Graduate School of Engineering and Management Air Force Institute of Technology Air

  9. Metal matrix composite structural panel construction

    NASA Technical Reports Server (NTRS)

    Mcwithey, R. R.; Royster, D. M. (Inventor); Bales, T. T.

    1983-01-01

    Lightweight capped honeycomb stiffeners for use in fabricating metal or metal/matrix exterior structural panels on aerospace type vehicles and the process for fabricating same are disclosed. The stiffener stringers are formed in sheets, cut to the desired width and length and brazed in spaced relationship to a skin with the honeycomb material serving directly as the required lightweight stiffeners and not requiring separate metal encasement for the exposed honeycomb cells.

  10. Advanced tow placement of composite fuselage structure

    NASA Technical Reports Server (NTRS)

    Anderson, Robert L.; Grant, Carroll G.

    1992-01-01

    The Hercules NASA ACT program was established to demonstrate and validate the low cost potential of the automated tow placement process for fabrication of aircraft primary structures. The program is currently being conducted as a cooperative program in collaboration with the Boeing ATCAS Program. The Hercules advanced tow placement process has been in development since 1982 and was developed specifically for composite aircraft structures. The second generation machine, now in operation at Hercules, is a production-ready machine that uses a low cost prepreg tow material form to produce structures with laminate properties equivalent to prepreg tape layup. Current program activities are focused on demonstration of the automated tow placement process for fabrication of subsonic transport aircraft fuselage crown quadrants. We are working with Boeing Commercial Aircraft and Douglas Aircraft during this phase of the program. The Douglas demonstration panels has co-cured skin/stringers, and the Boeing demonstration panel is an intricately bonded part with co-cured skin/stringers and co-bonded frames. Other aircraft structures that were evaluated for the automated tow placement process include engine nacelle components, fuselage pressure bulkheads, and fuselage tail cones. Because of the cylindrical shape of these structures, multiple parts can be fabricated on one two placement tool, thus reducing the cost per pound of the finished part.

  11. Testing and Analysis of Composite Skin/Stringer Debonding Under Multi-Axial Loading

    NASA Technical Reports Server (NTRS)

    Krueger, Ronald; Cvitkovich, Michael K.; OBrien, T. Kevin; Minguet, Pierre J.

    1999-01-01

    Damage mechanisms in composite bonded skin/stringer constructions under uniaxial and biaxial (in-plane/out- of-plane) loading conditions were examined. Specimens consisted of a tapered composite flange bonded onto a composite skin. Tests were performed under monotonic loading conditions in tension, three-point bending, and combined tension/bending . For combined tension/bending testing, a unique servohydraulic load frame was used that was capable of applying both in-plane tension and out-of-plane bending loads simultaneously. Specimen edges were examined on the microscope to document the damage occurrence and to identify typical damage patterns. The observations showed that, for all three load cases, failure initiated in the flange, near the flange tip, causing the flange to almost fully debond from the skin. A two-dimensional plane-strain finite element model was developed to analyze the different test cases using a geometrically nonlinear solution. For all three loading conditions, principal stresses exceeded the transverse strength of the material in the flange area. Additionally, delaminations of various lengths were simulated in two locations where delaminations were observed. The analyses showed that unstable delamination propagation is likely to occur in one location at the loads corresponding to matrix ply crack initiation for all three load cases.

  12. Analysis of Composite Skin-Stiffener Debond Specimens Using a Shell/3D Modeling Technique and Submodeling

    NASA Technical Reports Server (NTRS)

    OBrien, T. Kevin (Technical Monitor); Krueger, Ronald; Minguet, Pierre J.

    2004-01-01

    The application of a shell/3D modeling technique for the simulation of skin/stringer debond in a specimen subjected to tension and three-point bending was studied. The global structure was modeled with shell elements. A local three-dimensional model, extending to about three specimen thicknesses on either side of the delamination front was used to model the details of the damaged section. Computed total strain energy release rates and mixed-mode ratios obtained from shell/3D simulations were in good agreement with results obtained from full solid models. The good correlation of the results demonstrated the effectiveness of the shell/3D modeling technique for the investigation of skin/stiffener separation due to delamination in the adherents. In addition, the application of the submodeling technique for the simulation of skin/stringer debond was also studied. Global models made of shell elements and solid elements were studied. Solid elements were used for local submodels, which extended between three and six specimen thicknesses on either side of the delamination front to model the details of the damaged section. Computed total strain energy release rates and mixed-mode ratios obtained from the simulations using the submodeling technique were not in agreement with results obtained from full solid models.

  13. Preliminary Design and Analysis of an In-plane PRSEUS Joint

    NASA Technical Reports Server (NTRS)

    Lovejoy, Andrew E.; Poplawski, Steven

    2013-01-01

    As part of the National Aeronautics and Space Administration's (NASA's) Environmentally Responsible Aviation (ERA) program, the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) has been designed, developed and tested. However, PRSEUS development efforts to date have only addressed joints required to transfer bending moments between PRSEUS panels. Development of in-plane joints for the PRSEUS concept is necessary to facilitate in-plane transfer of load from PRSEUS panels to an adjacent structure, such as from a wing panel into a fuselage. This paper presents preliminary design and analysis of an in-plane PRSEUS joint for connecting PRSEUS panels at the termination of the rod-stiffened stringers. Design requirements are provided, the PRSEUS blade joint concept is presented, and preliminary design changes and analyses are carried out to examine the feasibility of the proposed in-plane PRSEUS blade joint. The study conducted herein focuses mainly on the PRSEUS structure on one side of the joint. In particular, the design requirements for the rod shear stress and bolt bearing stress are examined. A PRSEUS blade joint design was developed that demonstrates the feasibility of this in-plane PRSEUS joint concept to terminate the rod-stiffened stringers. The presented design only demonstrates feasibility, therefore, some areas of refinement are presented that would lead to a more optimum and realistic design.

  14. Application of the superfine fraction analysis method in ore gold geochemical prospecting in the Shamanikha-Stolbovsky Area (Magadan Region)

    NASA Astrophysics Data System (ADS)

    Makarova, Yuliya; Sokolov, Sergey; Glukhov, Anton

    2014-05-01

    The Shamanikha-Stolbovsky gold cluster is located in the North-East of Russia, in the basin of the Kolyma River. In 1933, gold placers were discovered there, but the search for significant gold targets for more than 50 years did not give positive results. In 2009-2011, geochemical and geophysical studies, mining and drilling were conducted within this cluster. Geochemical exploration was carried out in a modification based on superimposed secondary sorption-salt haloes (sampling density of 250x250 m, 250x50 m, 250x20 m) using the superfine fraction analysis method (SFAM) because of complicated landscape conditions (thick Quaternary sediments, widespread permafrost). The method consists in the extraction of superfine fraction (<10 microns) from unconsolidated sediment samples followed by transfer to a solution of sorption-salt forms of elements and analysis using quantitative methods. The method worked well in areal geochemical studies of various scales in the Karelian-Kola region and in the Far East. Main results of the work in the Shamanikha-Stolbovsky area: 1. Geochemical exploration using the hyperfine fractions analysis method with sampling density of 250x250 m allowed the identification of zonal anomalous geochemical fields (AGCF) classified as an ore deposit promising for the discovery of gold mineralization (Nadezhda, Timsha, and Temny prospects). These AGCF are characterized by following three-zonal structure (from the center to the periphery): nucleus zone - area of centripetal elements concentration (Au, Ag, Sb, As, Cu, Hg, Bi, Pb, Mo); exchange zone - area of centrifugal elements concentration (Mn, Zn, V, Ti, Co, Cr, Ni); flank concentration zone - area of elevated contents of centripetal elements with subbackground centrifugal elements. 2. Detailed AGCF studies with sampling density of 250x50 m (250x20 m) in the Nadezhda, Timsha, and Temny prospects made it possible to refine the composition and structure of anomalous geochemical fields, identify potential gold zones, and determine their formation affinity. Nadezhda Site. Contrast Au, Ag, Pb, Bi, Sb, As dispersion halos that form a linear anomalous geochemical field of ore body rank are identified. Predicted mineralization was related to the gold-sulfosalt mineral association according to the secondary dispersion halos chemical composition. Timsha Site. Contrast secondary Au, Ag, Sb, As, Hg, Pb, Bi dispersion halos are identified. These halos have rhythmically-banded structure, which can be caused by stringer morphological type of mineralization. Bands with anomalously high contents of elements have been interpreted by the authors as probable auriferous bodies. Four such bodies of 700 to 1500 m long were identified. Mineralization of the gold-sulfide formation similar to the "Carlin" type is predicted according to the secondary dispersion halos chemical composition as well as geological features. Temny Site. Contrast secondary Au, Ag, W, Sb dispersion halos are identified. A series of geochemical associations was identified based on factor analysis results. Au-Bi-W-Hg, and Pb-Sb-Ag-Zn associations, apparently related to the mineralization are of the greatest interest. Geochemical fields of these associations are closely spaced and overlapped in plan that may be caused by axial zoning of the subvertically dipping auriferous body. Three linear geochemical zones corresponding to potentially auriferous zones with pyrite type mineralization of the gold-quartz formation are identified within the anomalous geochemical field core zone. 3. In all these prospects, mining and drilling penetrated gold ore bodies within the identified potentially gold zones. The Nadezhda target now has the status of gold deposit.

  15. 58. MISSISSIPPI, NOXUBEE CO. MACON MAHORNER'S BRIDGE, 1884, Ms. 14, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    58. MISSISSIPPI, NOXUBEE CO. MACON MAHORNER'S BRIDGE, 1884, Ms. 14, E 6.5 mi. to McLeod, 4.5 miles S on McLeod-Shuqualak road. Mahorner's bridge (1884). Lower panel point, west span. View is at right-angles to the bridge and from below deck level. show pin connection, floor beams, and stringers. Sarcone Photography, Columbus, Ms. Sep 1978. - Bridges of the Upper Tombigbee River Valley, Columbus, Lowndes County, MS

  16. An analysis of stream channel cross section technique as a means to determine anthropogenic change in second order streams at the Tenderfoot Creek Experimental Forest, Meagher County, Montana

    Treesearch

    Jeff Boice

    1999-01-01

    Five second order tributaries to Tenderfoot Creek were investigated: Upper Tenderfoot Creek, Sun Creek, Spring Park Creek, Bubbling Creek, and Stringer Creek. Second order reaches were initially located on 7.5 minute topographic maps using techniques first applied by Strahler (1952). Reach breaks were determined in the field through visual inspection. Vegetation type (...

  17. SPECT Imaging to Evaluate Post Traumatic Stress Disorder

    DTIC Science & Technology

    2011-02-01

    Verbeem, and D.M. Kuhn, Gene expression profile of activated microglia under conditions associated with dopamine neuronal damage. FASEB J., 2005: p. 05...specific. Pharmacology Biochemistry and Behavior, 1995. 50(4): p. 551. 39. Drugan, R.C., P.V. Holmes, and A.P. Stringer, Sexual dimorphism of stress...childhood sexual abuse and posttraumatic stress disorder. Am J Psychiatry, 2003. 160(5): p. 924-32. 22 48. Sapolsky, R.M., Atrophy of the hippocampus

  18. Dimensional stability of curved panels with cocured stiffeners and cobonded frames

    NASA Technical Reports Server (NTRS)

    Mabson, G. E.; Flynn, B. W.; Swanson, G. D.; Lundquist, R. C.; Rupp, P. L.

    1993-01-01

    Closed form and finite element analyses are presented for axial direction and transverse direction dimensional stability of skin/stringer panels. Several sensitivity studies are presented to illustrate the influence of various design parameters on the dimensional stability of these panels. Panel geometry, material properties (stiffness and coefficient of thermal expansion), restraint conditions and local details, such as resin fillets, all combine to influence dimensional stability, residual and assembly forces.

  19. The United States Air Force Academy: A Bibliography 1954 - 1964

    DTIC Science & Technology

    1966-01-01

    August 1958. 498 Stringer, Roger. " Pro Nobis Astra" (Class of 󈨁 selects its ring), Talon 5;5, May 1960. 499 Trotogott, Pete. Cadet...relate to establishing an air academy. These are not included since they have no specific bearing on the Academy as it now exists. The Library staff...Newsletter AF Times - Air Force Times Air Cond Heat & Ven - Air Conditioning, Heating, and Venti- lating Air Force Airman Air Power Historian

  20. Spot-weld bonding on the Blackhawk helicopter

    NASA Technical Reports Server (NTRS)

    Salking, M. J.

    1972-01-01

    The Sikorsky S-67 Blackhawk attack helicopter utilizes spot-weld bonding for stringer to skin attachment on more than 5 per cent of its surface area. It is the first American aircraft to utilize spot weld bonding, although the process has been used for some years in the U.S.S.R. The process consists of applying adhesive on the surfaces to be joined, spot welding through the adhesive, then curing the adhesive.

  1. 15. Detail, lower chord connection point on downstream side, showing ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    15. Detail, lower chord connection point on downstream side, showing pinned connection of lower chord eye bars, laced vertical compression member, diagonal eye bar tension members, turnbuckled diagonal counters, and floor beam. Note also timber floor stringers supported by floor beam, and exposed ends of timber deck members visible at left above lower chord eye bar. View to northwest. - Dry Creek Bridge, Spanning Dry Creek at Cook Road, Ione, Amador County, CA

  2. One Time Passwords in Everything (OPIE): Experiences with Building and Using Stringer Authentication

    DTIC Science & Technology

    1995-01-01

    opiepasswd(1). The name change brings it more in line with its UNIX counterpart passwd (1), which should make both programs easier to remember for users. This...char * passwd ) int opiehash(char *x, unsigned algorithm) The one-time password schemes implemented in OPIE, as rst described in [Hal94], compute a...seed, passwd ); while (sequence-- != 0) opiehash(result, algorithm); opiebtoe(result,words); Send words. : : : 6 Deployment Every machine that has

  3. Decade of War, Volume 1. Enduring Lessons from the Past Decade of Operations

    DTIC Science & Technology

    2012-06-15

    the incident took on political dimensions or was highlighted in the international news media .14 Conventional war features a hierarchical top-down...half of the decade. The proliferation of the internet, social media , and personal electronic devices caused the paradigm of communication to shift...unconstrained by the truth: for example, they could feed false information to the media through the use of news stringers on fast-dial from an

  4. Investigating the Transport and Fate of Polychlorinated Biphenyls with Stable Chlorine Isotopes

    DTIC Science & Technology

    2001-09-30

    recently accepted in the journal Organic Geochemistry. We published another manuscript in Environmental Science and Pollution Research on the...Chlorine in the Environment a book written by Ruth Stringer and Paul Johnson. This review will soon appear in the journal Environmental Science and...Heraty, L.J., Holt, B.D., Sturchio, N.C., Eglinton, T.I., Drenzek, N.J., Xu, L., Lake, J.L., Maruya, K.A., 2000. Environmental Science and

  5. Anatomy of a Plate Boundary at Shallow Crustal Levels: a Composite Section from the Alpine Fault, New Zealand

    NASA Astrophysics Data System (ADS)

    Barth, N. C.; Toy, V. G.; Boulton, C. J.; Carpenter, B. M.

    2010-12-01

    New Zealand's Alpine Fault is mostly a moderately SE-dipping dextral reverse plate boundary structure, but at its southern end, strike-slip-normal motion is indicated by offset of recent surfaces, juxtaposition of sediments, and both brittle and ductile shear sense indicators. At the location of uplift polarity reversal fault rocks exhumed from both the hangingwall Pacific and footwall Australian Plates are juxtaposed, offering a remarkably complete cross section of the plate boundary at shallow crustal levels. We describe Alpine Fault damage zone and fault core structures overprinted on Pacific and Australian plate mylonites of a variety of compositions, in a fault-strike perpendicular composite section spanning the reversal in dip-slip polarity. The damage zone is asymmetric; on the Australian Plate 160m of quartzose paragneiss-derived mylonites are overprinted by brittle faults and fractures that increase in density towards the principal slip surface (PSS). This damage zone fabric consists of 1-10m-spaced, moderately to steeply-dipping, 1-20cm-thick gouge-filled faults, overprinted on and sub-parallel to a mylonitic foliation sub-parallel to the PSS. On the Pacific Plate, only 40m of the 330m section of volcaniclastic-derived mylonites have brittle damage in the form of unhealed fractures and faults, as well as a pervasive greenschist facies hydrothermal alteration absent in the footwall. These damage-related structures comprise a network of small-offset faults and fractures with increasing density and intensity towards the PSS. The active Pacific Plate fault core is composed of ~1m of cataclasite grading into folded protocataclasite that is less folded and fractured with increasing distance from the PSS. The active Australian Plate fault core is <1.5m wide and consists of 3 distinct foliated clay gouges, as well as a 4cm thick brittle ultracataclasite immediately adjacent to the active PSS. The Australian Plate foliated clay gouge contains stringers of quartz that become less continuous and more sigmoidal toward the PSS, indicating a strain gradient across the gouge zone. Gouge textures are consistent with deformation by pressure solution. Intact wafers from one of the gouges, experimentally -sheared in a biaxial configuration under true-triaxial loading at σn’= 31MPa and Pf = 10MPa, yielded a friction coefficient, μss = 0.32 and displayed velocity strengthening behavior. No significant re-strengthening was observed during hold periods of slide-hold tests. Well-cemented glacial till (~8000 years old), which caps many outcrops, is a marker that shows that the damage zone is not active in the near-surface, but most of the fault core is. The active near-surface damage zone here is <40m wide and the active fault core is <2.5m wide. Both overprint a much wider, inactive damage zone. The combination of rheologically-weak Australian Plate fault rocks with surface rupture traces indicates distinctly different coseismic and interseismic behaviors along the southern strike-slip-normal segment of the Alpine Fault.

  6. Improving animal health for poverty alleviation and sustainable livelihoods.

    PubMed

    Stringer, Andy

    2014-11-29

    Animals are vital to ensuring food security for individuals, families and communities in countries around the world. In this, the latest article in Veterinary Record's series promoting One Health, Andy Stringer, director of veterinary programmes at the Society for the Protection of Animals Abroad, discusses how improving animal health, particularly of poultry and working equids, has the potential to reduce poverty and promote food security and sustainable livelihoods in low-income countries. British Veterinary Association.

  7. Internal Structural Design of the Common Research Model Wing Box for Aeroelastic Tailoring

    NASA Technical Reports Server (NTRS)

    Jutte, Christine V.; Stanford, Bret K.; Wieseman, Carol D.

    2015-01-01

    This work explores the use of alternative internal structural designs within a full-scale wing box structure for aeroelastic tailoring, with a focus on curvilinear spars, ribs, and stringers. The baseline wing model is a fully-populated, cantilevered wing box structure of the Common Research Model (CRM). Metrics of interest include the wing weight, the onset of dynamic flutter, and the static aeroelastic stresses. Twelve parametric studies alter the number of internal structural members along with their location, orientation, and curvature. Additional evaluation metrics are considered to identify design trends that lead to lighter-weight, aeroelastically stable wing designs. The best designs of the individual studies are compared and discussed, with a focus on weight reduction and flutter resistance. The largest weight reductions were obtained by removing the inner spar, and performance was maintained by shifting stringers forward and/or using curvilinear ribs: 5.6% weight reduction, a 13.9% improvement in flutter speed, but a 3.0% increase in stress levels. Flutter resistance was also maintained using straight-rotated ribs although the design had a 4.2% lower flutter speed than the curved ribs of similar weight and stress levels were higher. For some configurations, the differences between curved and straight ribs were smaller, which provides motivation for future optimization-based studies to fully exploit the trade-offs.

  8. Variscan ore formation and metamorphism at the Felbertal scheelite deposit (Austria): constraining tungsten mineralisation from Re-Os dating of molybdenite

    NASA Astrophysics Data System (ADS)

    Raith, Johann G.; Stein, Holly J.

    2006-10-01

    The Felbertal scheelite deposit in the Eastern Alps has been regarded as the type locality for stratabound scheelite deposits. It is hosted by a Cambro-Ordovician metavolcanic arc sequence with minor Variscan granitoids (˜ 340 Ma) in the central Tauern Window. Re-Os model ages for molybdenite from the Felbertal tungsten deposit range between ˜ 358 and ˜ 336 Ma and record several pulses of magmatic-hydrothermal-metamorphic molybdenite formation. Molybdenite ages from the K2 orebody, a scheelite-rich quartz mylonite in the Western ore field, indicate that both mineralisation and mylonite are Variscan in age and suggest that the shear zone was active for ˜ 20 million years. Early stage tungsten mineralisation ( Scheelite 1) in quartzitic ores in the Eastern ore field, which is free of molybdenite, yielded very low to near blank levels of Re and Os and thus could not be dated. However, molybdenite from scheelite-quartz stringers, previously interpreted as a feeder stockwork to quartzitic scheelite ore of presumed Cambrian age, yielded Variscan Re-Os ages of ˜ 342 and ˜ 337 Ma. Dating of molybdenite contained in scheelite ores thus far provides no indication of a Cambrian component to the tungsten mineralisation. Our data are consistent with a model of either granite intrusion-related ore formation and coeval metamorphic overprint during the Early Carboniferous or, alternatively, molybdenite formation may be exclusively attributed to Variscan metamorphism (see Stein 2006).

  9. Investigation of the Structural Behavior and Maximum Bending Strength of Six Multiweb Beams with Three Types of Webs

    NASA Technical Reports Server (NTRS)

    Peterson, James P.; Bruce, Walter E., Jr.

    1959-01-01

    The results of bending tests on six multiweb beams of optimum weight-strength design are presented. The internal structure of the beams consisted of various combinations of two types of full-depth solid webs and a post-stringer web. The observed structural behavior, buckling load, and failing load of the beams are compared with results obtained by the use of existing methods of analysis and found to be quite predictable.

  10. Superplasticity - A Fundamental Investigation on Deformation Mechanism and Cavitation Phenomena.

    DTIC Science & Technology

    1988-02-15

    NI-MODIFIED SUPERPLASTIC Ti- 6Al - 4V ALLOY, B. Hidalgo-Prada and A.K. Mukherjee, Proc. of Intnl. Conf. of Strength of Metals and AlloyS-7, Montreal...features, e.g., initial porosity (15 to 500 pm diam.), stringers (of Fe-rich particles, 5-30 pm diam.), and small (0.3-3 pm) copper- rich particles...500% or greater, porosity between grains was observed. Some grains as well as grain clusters are visible in Fig. 6. The grain clusters are believed to

  11. Proceedings of the Tri-Service Conference on Corrosion Held in Atlantic City, New Jersey on 17-19 October 1989

    DTIC Science & Technology

    1989-10-19

    installation. 4. Corrosion inhibiting compounds need to be applied in the final assealbly of models to all corrosion prone areas of the structure, e.g...Figure 12 shows an example of poor surface treatment of a previously repaired stringer area. Application of a corrosion inhibiting compound may have... compounds and a good corrosion control maintenance program. REFERENCE U. G. Goranson and M. Miller, "Aging Fleet - Aging Fleet Evaluation Program

  12. Preliminary analysis techniques for ring and stringer stiffened cylindrical shells

    NASA Technical Reports Server (NTRS)

    Graham, J.

    1993-01-01

    This report outlines methods of analysis for the buckling of thin-walled circumferentially and longitudinally stiffened cylindrical shells. Methods of analysis for the various failure modes are presented in one cohesive package. Where applicable, more than one method of analysis for a failure mode is presented along with standard practices. The results of this report are primarily intended for use in launch vehicle design in the elastic range. A Microsoft Excel worksheet with accompanying macros has been developed to automate the analysis procedures.

  13. Experimental Stress Analysis of Stiffened Cylinders with Cutouts : Pure Bending

    NASA Technical Reports Server (NTRS)

    Schlechte, Floyd R; Rosecrans, Richard

    1954-01-01

    Bending tests were made on a cylindrical semimonocoque shell of circular cross section. The cylinder was tested without a cutout and then with a rectangular cutout which was successively enlarged through six sizes varying from 30 degrees to 130 degrees in circumference and from 1 to 2 bays in length. Strain measurements were made with resistance-type wire strain gages near the cutout on the stringers, the skin, and the rings for each size of cutout, and the stresses obtained are presented in tables. (author)

  14. Shock transmission in coupled beams and rib stiffened structures

    NASA Technical Reports Server (NTRS)

    Pope, L. D.; Manning, J. E.; Scharton, T. D.

    1971-01-01

    Shock transmission in a simple coupled beam structure and in a ring-stringer stiffened cylinder is investigated experimentally and analytically using wave transmission and statistical energy analysis concepts. The use of the response spectrum to characterize the excitation provided to a simple beam by a force pulse is studied. Analysis of the transmission of a dilatation wave in a periodically stiffened plate indicates that the stiffeners are fairly transparent to the wave, but some of the dilatational energy is scattered into bending at each support.

  15. Finite Element Modeling of the NASA Langley Aluminum Testbed Cylinder

    NASA Technical Reports Server (NTRS)

    Grosveld, Ferdinand W.; Pritchard, Joselyn I.; Buehrle, Ralph D.; Pappa, Richard S.

    2002-01-01

    The NASA Langley Aluminum Testbed Cylinder (ATC) was designed to serve as a universal structure for evaluating structural acoustic codes, modeling techniques and optimization methods used in the prediction of aircraft interior noise. Finite element models were developed for the components of the ATC based on the geometric, structural and material properties of the physical test structure. Numerically predicted modal frequencies for the longitudinal stringer, ring frame and dome component models, and six assembled ATC configurations were compared with experimental modal survey data. The finite element models were updated and refined, using physical parameters, to increase correlation with the measured modal data. Excellent agreement, within an average 1.5% to 2.9%, was obtained between the predicted and measured modal frequencies of the stringer, frame and dome components. The predictions for the modal frequencies of the assembled component Configurations I through V were within an average 2.9% and 9.1%. Finite element modal analyses were performed for comparison with 3 psi and 6 psi internal pressurization conditions in Configuration VI. The modal frequencies were predicted by applying differential stiffness to the elements with pressure loading and creating reduced matrices for beam elements with offsets inside external superelements. The average disagreement between the measured and predicted differences for the 0 psi and 6 psi internal pressure conditions was less than 0.5%. Comparably good agreement was obtained for the differences between the 0 psi and 3 psi measured and predicted internal pressure conditions.

  16. Stress analysis of circular semimonocoque cylinders with cutouts

    NASA Technical Reports Server (NTRS)

    Mccomb, Harvey G , Jr

    1955-01-01

    A method is presented for analyzing the stresses about cutouts in circular semimonocoque cylinders with flexible rings. The method involves the use of so-called perturbation stress distributions which are superposed on the stress distribution that would exist in the structure with no cutout in such a way as to give the effects of a cutout. The method can be used for any loading case for which the structure without the cutout can be analyzed and is sufficiently versatile to account for stringer and shear reinforcement about the cutout.

  17. Stress Analysis of Beams with Shear Deformation of the Flanges

    NASA Technical Reports Server (NTRS)

    Kuhn, Paul

    1937-01-01

    This report discusses the fundamental action of shear deformation of the flanges on the basis of simplifying assumptions. The theory is developed to the point of giving analytical solutions for simple cases of beams and of skin-stringer panels under axial load. Strain-gage tests on a tension panel and on a beam corresponding to these simple cases are described and the results are compared with analytical results. For wing beams, an approximate method of applying the theory is given. As an alternative, the construction of a mechanical analyzer is advocated.

  18. Analysis of Discrete-Source Damage Progression in a Tensile Stiffened Composite Panel

    NASA Technical Reports Server (NTRS)

    Wang, John T.; Lotts, Christine G.; Sleight, David W.

    1999-01-01

    This paper demonstrates the progressive failure analysis capability in NASA Langley s COMET-AR finite element analysis code on a large-scale built-up composite structure. A large-scale five stringer composite panel with a 7-in. long discrete source damage was analyzed from initial loading to final failure including the geometric and material nonlinearities. Predictions using different mesh sizes, different saw cut modeling approaches, and different failure criteria were performed and assessed. All failure predictions have a reasonably good correlation with the test result.

  19. Helicopter Pitch-Control Mechanism Reduces Vibration

    NASA Technical Reports Server (NTRS)

    Lemont, H.

    1986-01-01

    Large forces accommodated without increasing weight of helicopter structure. New mechanism yields stiffer control and improves accuracy of pitch changes under load. As result, heavy casting not for gearbox, nor extra reinforcing members needed for fuselage bulkheads, stringers, skin, and other parts. In new mechanism, reaction forces developed in rotor hub. Long load paths to gearbox and fuselage elminated. Reaction member rigidly attached to hub and rotates with it. At lower end of reaction member, bearing forms bridge to fuselage through stationary beam and antirotation link. Beam connected to reaction plate through rods.

  20. Astronat Dale Gardner using MMU to travel to Westar VI satellite

    NASA Image and Video Library

    1984-11-14

    51A-104-008 (14 Nov 1984) --- Astronaut Dale A. Gardner appears to be under the remote manipulator system (RMS) end effector as he makes a turn in space and prepared to traverse, using the manned maneuvering unit (MMU) backpack, to the nearby Westar VI to "Sting" it with the device he carries. The stringer will enter the communications satellite through the nozzle of the spent motor. Gardner achieved a hard dock at 6:32 A.M. and this picture was photographed about five minutes earlier, on Nov. 14, 1984.

  1. Fabrication of graphite/polyimide composite structures.

    NASA Technical Reports Server (NTRS)

    Varlas, M.

    1972-01-01

    Selection of graphite/polyimide composite as a prime candidate for high-temperature structural applications involving long-duration temperature environments of 400 to 600 F. A variety of complex graphite/polyimide components has been fabricated, using a match-metal die approach developed for making fiber-reinforced resin composites. Parts produced include sections of a missile adapter skin flange, skin frame section, and I-beam and hat-section stringers, as well as unidirectional (0 deg) and plus or minus 45 deg oriented graphite/polyimide tubes in one-, two-, and six-inch diameters.

  2. Thermostructural analysis of three structural concepts for reusable space vehicles

    NASA Technical Reports Server (NTRS)

    Taylor, A. H.; Jackson, L. R.

    1979-01-01

    Three structural concepts are studied: (1) a state-of-the-art insulated aluminum skin-stringer structure; (2) a near-art insulated evacuated aluminum-alloy honeycomb structure; and (3) an advanced evacuated Rene 41 honeycomb hot structure. Each is evaluated for its thermostructural performance for each of the flight profiles (ascent, entry, and a recall or abort). Results indicate that (1) the state-of-the-art structure encounters negligible thermal stress; (2) the near-art structure has acceptable thermal stresses; and (3) the advanced structure will have thermal stress levels above the material allowables.

  3. Weld bonding of titanium with polyimide adhesives

    NASA Technical Reports Server (NTRS)

    Vaughan, R. W.; Sheppard, C. H.; Orell, M. K.

    1975-01-01

    A conductive adhesive primer and a capillary flow adhesive were developed for weld bonding titanium alloy joints. Both formulations contained ingredients considered to be non-carcinogenic. Lap-shear joint test specimens and stringer-stiffened panels were weld bonded using a capillary flow process to apply the adhesive. Static property information was generated for weld bonded joints over the temperature range of 219K (-65 F) to 561K (550 F). The capillary flow process was demonstrated to produce weld bonded joints of equal strength to the weld through weld bonding process developed previously.

  4. METHOD FOR ANNEALING AND ROLLING ZIRCONIUM-BASE ALLOYS

    DOEpatents

    Picklesimer, M.L.

    1959-07-14

    A fabrication procedure is presented for alpha-stabilized zirconium-base alloys, and in particular Zircaloy-2. The alloy is initially worked at a temperature outside the alpha-plus-beta range (810 to 970 deg ), held at a temperature above 970 deg C for 30 minutes and cooled rapidly. The alloy is then cold-worked to reduce the size at least 20% and annealed at a temperature from 700 to 810 deg C. This procedure serves both to prevent the formation of stringers and to provide a randomly oriented crystal structure.

  5. Variable control of neutron albedo in toroidal fusion devices

    DOEpatents

    Jassby, Daniel L.; Micklich, Bradley J.

    1986-01-01

    An arrangement is provided for controlling neutron albedo in toroidal fusion devices having inboard and outboard vacuum vessel walls for containment of the neutrons of a fusion plasma. Neutron albedo material is disposed immediately adjacent the inboard wall, and is movable, preferably in vertical directions, so as to be brought into and out of neutron modifying communication with the fusion neutrons. Neutron albedo material preferably comprises a liquid form, but may also take pebble, stringer and curtain-like forms. A neutron flux valve, rotatable about a vertical axis is also disclosed.

  6. Friction stir welding of T joints of dissimilar aluminum alloy: A review

    NASA Astrophysics Data System (ADS)

    Thakare, Shrikant B.; Kalyankar, Vivek D.

    2018-04-01

    Aluminum alloys are preferred in the mechanical design due to their advantages like high strength, good corrosion resistance, low density and good weldability. In various industrial applications T joints configuration of aluminum alloys are used. In different fields, T joints having skin (horizontal sheet) strengthen by stringers (vertical sheets) were used to increase the strength of structure without increasing the weight. T joints are usually carried out by fusion welding which has limitations in joining of aluminum alloy due to significant distortion and metallurgical defects. Some aluminum alloys are even non weldable by fusion welding. The friction stir welding (FSW) has an excellent replacement of conventional fusion welding for T joints. In this article, FSW of T joints is reviewed by considering aluminum alloy and various joint geometries for defect analysis. The previous experiments carried out on T joints shows the factors such as tool geometry, fixturing device and joint configurations plays significant role in defect free joints. It is essential to investigate the material flow during FSW to know joining mechanism and the formation of joint. In this study the defect occurred in the FSW are studied for various joint configurations and parameters. Also the effect of the parameters and defects occurs on the tensile strength are studied. It is concluded that the T-joints of different joint configurations can be pretended successfully. Comparing to base metal some loss in tensile strength was observed in the weldments as well as overall reduction of the hardness in the thermos mechanically affected zone also observed.

  7. Textures and trace element composition of pyrite from the Bukit Botol volcanic-hosted massive sulphide deposit, Peninsular Malaysia

    NASA Astrophysics Data System (ADS)

    Basori, Mohd Basril Iswadi; Gilbert, Sarah; Large, Ross Raymond; Zaw, Khin

    2018-06-01

    The Bukit Botol volcanic-hosted massive sulphide (VHMS) deposit is located in the Central Belt of Peninsular Malaysia. The deposit occurs in a package of Permian-aged coherent felsic volcanic and volcaniclastic rocks which have a geochemical signature indicative of a volcanic arc tectonic setting. Mineralisation shows distinct ore zonation, forming a stringer to massive sulphide zone at the footwall followed by barite lenses and exhalite layers (Fe-Mn ore) at the top. Mineralogy is characterised by pyrite as the major sulphide mineral, with minor chalcopyrite, sphalerite, and rare galena; traces of gold, silver- and tin-bearing minerals also occur in the massive sulphide and barite ores. Laser ablation inductively coupled plasma mass spectrometry (LA-ICP-MS) analysis combined with the textural characteristics of pyrite provides evidence for significant variations of trace elements in different pyrite types at Bukit Botol, having three types of pyrite in the paragenetic sequence. The concentrations of As, Se, Te, Cu, Zn and Pb decrease from the early pyrite 1 to the late stage pyrite 3, and the Co/Ni ratios vary for the three pyrite types. The combined textural and compositional data of pyrite suggest that the hydrothermal fluid responsible for mineralisation evolved from an early, high temperature, reduced, low pH and desulphurized fluid to more S-rich, oxidized, high pH and cooler fluid. Available sulphur isotope data from the Bukit Botol deposit point to reduced seawater, along with a possible magmatic contribution, as the most probable sources for the ore-forming fluids.

  8. Stresses in and General Instability of Monocoque Cylinders with Cutouts I : Experimental Investigation of Cylinders with a Symmetric Cutout Subjected to Pure Bending

    NASA Technical Reports Server (NTRS)

    Hoff, N J; Boley, Bruno A

    1946-01-01

    Ten 24S-T alclad cylinders of 20-inch diameter, 45- or 58-inch length, and 0.012-inch wall thickness, reinforced with 24S-T aluminum alloy stringers and rings were tested in pure bending. In the middle of the compression side of the cylinders there was a cutout extending over 19 inches in the longitudinal direction, and over an angle of 45 degrees, 90 degrees, or 135 degrees in the circumferential direction. The strain in the stringers and in the sheet covering was measured with metal electric strain gages. The stress distribution in the cylinders deviate considerably from the linear law valid for cylinders without a cutout. The maximum strain measured was about four-thirds of the value calculated from the Mc/I formula when I was taken as the moment of inertia of the cross section of the portion of the cylinder where the cutout was situated. A diagram is presented containing the strain factors defined as the ratios of measured strain to strain calculated with the Mc/I formula. All the 10 cylinders tested failed in general instability. Two symmetric and one antisymmetric pattern of buckling were observed and the buckling load appeared to be independent of the method of manufacture and the length of the cylinder. The buckling load of the cylinders having cutouts extending over 45 degrees, 90 degrees, and 135 degrees was 66, 47, and 31 percent, respectively, of the buckling load of the cylinder without a cutout.

  9. Ultrasonic Nondestructive Evaluation of Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) During Large-Scale Load Testing and Rod Push-Out Testing

    NASA Technical Reports Server (NTRS)

    Johnston, Patrick H.; Juarez, Peter D.

    2016-01-01

    The Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) is a structural concept developed by the Boeing Company to address the complex structural design aspects associated with a pressurized hybrid wing body (HWB) aircraft configuration. The HWB has long been a focus of NASA's environmentally responsible aviation (ERA) project, following a building block approach to structures development, culminating with the testing of a nearly full-scale multi-bay box (MBB), representing a segment of the pressurized, non-circular fuselage portion of the HWB. PRSEUS is an integral structural concept wherein skins, frames, stringers and tear straps made of variable number of layers of dry warp-knit carbon-fiber stacks are stitched together, then resin-infused and cured in an out-of-autoclave process. The PRSEUS concept has the potential for reducing the weight and cost and increasing the structural efficiency of transport aircraft structures. A key feature of PRSEUS is the damage-arresting nature of the stitches, which enables the use of fail-safe design principles. During the load testing of the MBB, ultrasonic nondestructive evaluation (NDE) was used to monitor several sites of intentional barely-visible impact damage (BVID) as well as to survey the areas surrounding the failure cracks after final loading to catastrophic failure. The damage-arresting ability of PRSEUS was confirmed by the results of NDE. In parallel with the large-scale structural testing of the MBB, mechanical tests were conducted of the PRSEUS rod-to-overwrap bonds, as measured by pushing the rod axially from a short length of stringer.

  10. Use of nondestructive inspection and fiber optic sensing for damage characterization in carbon fiber fuselage structure

    NASA Astrophysics Data System (ADS)

    Neidigk, Stephen; Le, Jacqui; Roach, Dennis; Duvall, Randy; Rice, Tom

    2014-04-01

    To investigate a variety of nondestructive inspection technologies and assess impact damage characteristics in carbon fiber aircraft structure, the FAA Airworthiness Assurance Center, operated by Sandia National Labs, fabricated and impact tested two full-scale composite fuselage sections. The panels are representative of structure seen on advanced composite transport category aircraft and measured approximately 56"x76". The structural components consisted of a 16 ply skin, co-cured hat-section stringers, fastened shear ties and frames. The material used to fabricate the panels was T800 unidirectional pre-preg (BMS 8-276) and was processed in an autoclave. Simulated hail impact testing was conducted on the panels using a high velocity gas gun with 2.4" diameter ice balls in collaboration with the University of California San Diego (UCSD). Damage was mapped onto the surface of the panels using conventional, hand deployed ultrasonic inspection techniques, as well as more advanced ultrasonic and resonance scanning techniques. In addition to the simulated hail impact testing performed on the panels, 2" diameter steel tip impacts were used to produce representative impact damage which can occur during ground maintenance operations. The extent of impact damage ranges from less than 1 in2 to 55 in2 of interply delamination in the 16 ply skin. Substructure damage on the panels includes shear tie cracking and stringer flange disbonding. It was demonstrated that the fiber optic distributed strain sensing system is capable of detecting impact damage when bonded to the backside of the fuselage.

  11. Development of pressure containment and damage tolerance technology for composite fuselage structures in large transport aircraft

    NASA Technical Reports Server (NTRS)

    Smith, P. J.; Thomson, L. W.; Wilson, R. D.

    1986-01-01

    NASA sponsored composites research and development programs were set in place to develop the critical engineering technologies in large transport aircraft structures. This NASA-Boeing program focused on the critical issues of damage tolerance and pressure containment generic to the fuselage structure of large pressurized aircraft. Skin-stringer and honeycomb sandwich composite fuselage shell designs were evaluated to resolve these issues. Analyses were developed to model the structural response of the fuselage shell designs, and a development test program evaluated the selected design configurations to appropriate load conditions.

  12. A mixed optimization method for automated design of fuselage structures.

    NASA Technical Reports Server (NTRS)

    Sobieszczanski, J.; Loendorf, D.

    1972-01-01

    A procedure for automating the design of transport aircraft fuselage structures has been developed and implemented in the form of an operational program. The structure is designed in two stages. First, an overall distribution of structural material is obtained by means of optimality criteria to meet strength and displacement constraints. Subsequently, the detailed design of selected rings and panels consisting of skin and stringers is performed by mathematical optimization accounting for a set of realistic design constraints. The practicality and computer efficiency of the procedure is demonstrated on cylindrical and area-ruled large transport fuselages.

  13. Pulse-Echo Phased Array Ultrasonic Inspection of Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS)

    NASA Technical Reports Server (NTRS)

    Johnston, Pat H.

    2010-01-01

    A PRSEUS test article was subjected to controlled impact on the skin face followed by static and cyclic axial compressions. Phased array ultrasonic inspection was conducted before impact, and after each of the test conditions. A linear phased array probe with a manual X-Y scanner was used for interrogation. Ultrasound showed a delamination between the skin and stringer flange adjacent to the impact. As designed, the stitching in the flange arrested the lateral flaw formation. Subsequent ultrasonic data showed no delamination growth due to continued loading. Keywords: Phased Array, Ultrasonics, Composites, Out-of-Autoclave

  14. Finite Element Models and Properties of a Stiffened Floor-Equipped Composite Cylinder

    NASA Technical Reports Server (NTRS)

    Grosveld, Ferdinand W.; Schiller, Noah H.; Cabell, Randolph H.

    2010-01-01

    Finite element models were developed of a floor-equipped, frame and stringer stiffened composite cylinder including a coarse finite element model of the structural components, a coarse finite element model of the acoustic cavities above and below the beam-supported plywood floor, and two dense models consisting of only the structural components. The report summarizes the geometry, the element properties, the material and mechanical properties, the beam cross-section characteristics, the beam element representations and the boundary conditions of the composite cylinder models. The expressions used to calculate the group speeds for the cylinder components are presented.

  15. Body weight of hypersonic aircraft, part 1

    NASA Technical Reports Server (NTRS)

    Ardema, Mark D.

    1988-01-01

    The load bearing body weight of wing-body and all-body hypersonic aircraft is estimated for a wide variety of structural materials and geometries. Variations of weight with key design and configuration parameters are presented and discussed. Both hot and cool structure approaches are considered in isotropic, organic composite, and metal matrix composite materials; structural shells are sandwich or skin-stringer. Conformal and pillow-tank designs are investigated for the all-body shape. The results identify the most promising hypersonic aircraft body structure design approaches and their weight trends. Geometric definition of vehicle shapes and structural analysis methods are presented in appendices.

  16. Development and demonstration of manufacturing processes for fabricating graphite/LARC 160 polyimide structural elements

    NASA Technical Reports Server (NTRS)

    Frost, R. K.; Jones, J. S.; Dynes, P. J.; Wykes, D. H.

    1981-01-01

    The development and demonstration of manufacturing technologies for the structural application of Celion graphite/LARC-160 polyimide composite material is discussed. Process development and fabrication of demonstration components are discussed. Process development included establishing quality assurance of the basic composite material and processing, nondestructive inspection of fabricated components, developing processes for specific structural forms, and qualification of processes through mechanical testing. Demonstration components were fabricated. The demonstration components consisted of flat laminates, skin/stringer panels, honeycomb panels, chopped fiber compression moldings, and a technology demonstrator segment (TDS) representative of the space shuttle aft body flap.

  17. Noise-reduction measurements of stiffened and unstiffened cylindrical models of an airplane fuselage

    NASA Technical Reports Server (NTRS)

    Willis, C. M.; Mayes, W. H.

    1984-01-01

    Noise-reduction measurements are presented for a stiffened and an unstiffened model of an airplane fuselage. The cylindrical models were tested in a reverberant-field noise environment over a frequency range from 20 Hz to 6 kHz. An unstiffened metal fuselage provided more noise reduction than a fuselage having the same sidewall weight divided between skin and stiffening stringers and ring frames. The addition of acoustic insulation to the models tended to smooth out the interior-noise spectrum by reducing or masking the noise associated with the structural response at some of the resonant frequencies.

  18. AfricaArray International Geophysics Field School: Applications of Near Surface Geophysics to challenges encountered in mine planning

    NASA Astrophysics Data System (ADS)

    Webb, S. J.; Jones, M. Q.; Durrheim, R. J.; Nyblade, A.; Snyman, Q.

    2012-12-01

    Hard rock exploration and mining presents many opportunities for the effective use of near surface geophysics. For over 10 years the AfricaArray international geophysics field school has been hosted at a variety of mines in South Africa. While the main objective of the field school is practical training for the next generation of geophysicists, being hosted at a mine has allowed us to investigate applications of near surface geophysics in the early stages of mine planning and development as geophysics is often cheaper and faster than drilling. Several applications include: detailed delineation of dykes and stringer dykes, physical property measurements on drill core for modeling and marker horizons, determination of overburden thickness, locations of water and faults. Dolerite dykes are usually magnetic and are associated with loss of ground (i.e. where the dyke replaces the ore and thus reduces the amount of ore available) and safety/stability concerns. Thus the accurate mapping of dykes and narrow stringers that are associated with them are crucial to the safe planning of a mine. We have acquired several case studies where ground magnetic surveys have greatly improved on the resolution and detail of airborne magnetic surveys in regions of complicated dyke swarms. In many cases, thin stringer dykes of less than 5 cm have been detected. Physical property measurements of these dykes can be used to distinguish between different ages of dykes. It is important to accurately determine overburden thickness when planning an open pit mine as this directly affects the cost of development. Depending on the nature of the overburden, both refraction seismic and or DC resistivity can provide continuous profiling in the area of interest that fills in gaps between boreholes. DC resistivity is also effective for determining water associated with dykes and structures that may affect mine planning. The field school mainly addresses the training of a variety of students. The core students are the geophysics Honours students (~4th year undergraduates). In addition, up to 8 students from all over Africa are included in the program to help address practical training in Africa. The final cohort are minority students from the USA. Participants spend a week planning and costing out surveys, a week in the field collecting data using different methods including: gravity, DGPS, magnetics, resistivity, refraction seismic, EM methods, core logging and physical property measurements. The final week is spent interpreting and integrating their results. Graduate students are given the opportunity to instruct on the field school and manage the logistics for a particular method. The field school is unique in Africa and satisfies a need for practical training with limited resources, with a rare blend of cultural interactions!

  19. Analysis of Composite Skin-Stiffener Debond Specimens Using Volume Elements and a Shell/3D Modeling Technique

    NASA Technical Reports Server (NTRS)

    Krueger, Ronald; Minguet, Pierre J.; Bushnell, Dennis M. (Technical Monitor)

    2002-01-01

    The debonding of a skin/stringer specimen subjected to tension was studied using three-dimensional volume element modeling and computational fracture mechanics. Mixed mode strain energy release rates were calculated from finite element results using the virtual crack closure technique. The simulations revealed an increase in total energy release rate in the immediate vicinity of the free edges of the specimen. Correlation of the computed mixed-mode strain energy release rates along the delamination front contour with a two-dimensional mixed-mode interlaminar fracture criterion suggested that in spite of peak total energy release rates at the free edge the delamination would not advance at the edges first. The qualitative prediction of the shape of the delamination front was confirmed by X-ray photographs of a specimen taken during testing. The good correlation between prediction based on analysis and experiment demonstrated the efficiency of a mixed-mode failure analysis for the investigation of skin/stiffener separation due to delamination in the adherents. The application of a shell/3D modeling technique for the simulation of skin/stringer debond in a specimen subjected to three-point bending is also demonstrated. The global structure was modeled with shell elements. A local three-dimensional model, extending to about three specimen thicknesses on either side of the delamination front was used to capture the details of the damaged section. Computed total strain energy release rates and mixed-mode ratios obtained from shell/3D simulations were in good agreement with results obtained from full solid models. The good correlations of the results demonstrated the effectiveness of the shell/3D modeling technique for the investigation of skin/stiffener separation due to delamination in the adherents.

  20. Aeroelastic Tailoring of the NASA Common Research Model via Novel Material and Structural Configurations

    NASA Technical Reports Server (NTRS)

    Jutte, Christine V.; Stanford, Bret K.; Wieseman, Carol D.; Moore, James B.

    2014-01-01

    This work explores the use of tow steered composite laminates, functionally graded metals (FGM), thickness distributions, and curvilinear rib/spar/stringer topologies for aeroelastic tailoring. Parameterized models of the Common Research Model (CRM) wing box have been developed for passive aeroelastic tailoring trade studies. Metrics of interest include the wing weight, the onset of dynamic flutter, and the static aeroelastic stresses. Compared to a baseline structure, the lowest aggregate static wing stresses could be obtained with tow steered skins (47% improvement), and many of these designs could reduce weight as well (up to 14%). For these structures, the trade-off between flutter speed and weight is generally strong, although one case showed both a 100% flutter improvement and a 3.5% weight reduction. Material grading showed no benefit in the skins, but moderate flutter speed improvements (with no weight or stress increase) could be obtained by grading the spars (4.8%) or ribs (3.2%), where the best flutter results were obtained by grading both thickness and material. For the topology work, large weight reductions were obtained by removing an inner spar, and performance was maintained by shifting stringers forward and/or using curvilinear ribs: 5.6% weight reduction, a 13.9% improvement in flutter speed, but a 3.0% increase in stress levels. Flutter resistance was also maintained using straightrotated ribs although the design had a 4.2% lower flutter speed than the curved ribs of similar weight and stress levels were higher. These results will guide the development of a future design optimization scheme established to exploit and combine the individual attributes of these technologies.

  1. Ground-water quality and vulnerability to contamination in selected agricultural areas of southeastern Michigan, northwestern Ohio, and northeastern Indiana

    USGS Publications Warehouse

    Thomas, Mary Ann

    2000-01-01

    Ground-water quality was assessed in the northeastern part of the Corn Belt, where tile-drained row crops are underlain by fractured glacial till. Data were collected from 30 shallow monitor wells and 18 co-located domestic wells as part of the U.S. Geological Survey?s National Water-Quality Assessment in the Lake Erie-Lake St. Clair Basin. Pesticides or pesticide degradates were detected in 41 percent of the monitor wells and 6 percent of the domestic wells. The pesticides detected closely correspond to those most heavily applied?herbicides used on corn and soybeans. Pesticide degradates were detected three times more frequently, and at higher concentrations, than were parent compounds. No pesticide concentration exceeded a USEPA Maximum Contaminant Level (MCL), but MCL?s have not been established for 9 of the 11 compounds detected. Thirty-seven percent of monitor-well samples had nitrate concentrations indicative of human influences such as fertilizer, manure or septic systems. Nitrate was the only chemical constituent detected at a concentration greater than an MCL. The MCL was exceeded in 7 percent of samples from monitor wells which were too shallow to be used as a source of drinking water. Pesticide and nitrate concentrations in the study area are low relative to other agricultural areas of the Nation. Several authors have suggested that ground water in parts of the Upper Mid-west is minimally contaminated because it is protected by the surficial glacial till or tile drains. These ideas are examined in light of the relations between concentration, well depth, and ground-water age in the study area. Most of the shallow ground water is hydraulically connected to the land surface, based on the observations that 83 percent of waters from monitor wells were recharged after 1953, and 57 percent contained a pesticide or an elevated nitrate concentration. Fractures or sand-and-gravel stringers within the till are the probable pathways. In some areas, deeper parts of the ground-water-flow system are also hydraulically connected to the land surface. Almost half the waters from wells 50 to 100 feet deep were recharged after 1953. Anthropogenic constituents were detected in samples from three domestic wells 60 to 121 feet deep, in areas where the till is relatively coarse-grained. The hydrogeologic system has several geochemical characteristics conducive to transformations or sorption of nitrate or pesticides: (1) the till is clay-rich, has a high organic-carbon content, and contains an abundance of pyrite-rich shale fragments, (2) the ground water has low dissolved-oxygen concentrations, and (3) iron and manganese oxides and oxyhyroxides line the faces of fractures in the unsaturated zone. Although the aquifer system appears be protected from contamination in some areas, the fact that the surficial till is heterogeneous and of variable thickness suggests that the protection is not uniform. The protection can be breached by fractures or sand-and-gravel stringers, which are apparent in core samples but not noted on domestic-well logs.

  2. Litho- and chemostratigraphy of the Flatreef PGE deposit, northern Bushveld Complex

    NASA Astrophysics Data System (ADS)

    Grobler, D. F.; Brits, J. A. N.; Maier, W. D.; Crossingham, A.

    2018-05-01

    The Flatreef is a world-class platinum-group element (PGE) deposit recently discovered down-dip from existing mining and exploration operations on the northern limb of the Bushveld Complex. Current indicated resources stand at 42 Moz PGE (346 Mt with 3.8 g/t Pt+Pd+Rh+Au, 0.32% Ni and 0.16% Cu) which, in the case of Pt, is equivalent to 10 years global annual production, making it one of the largest PGE deposits on earth. The grade and thickness of the Flatreef mineralised interval is highly unusual, with some drill core intersections containing up to 4.5 g/t Pt+Pd+Rh+Au over 90 m in drill core. Here, we document the down-dip and along-strike litho- and chemostratigraphy of the Flatreef and its footwall and hanging wall rocks, based on a diamond drill core database totalling > 720 km. At the base of the sequence intersected in the drill cores are up to 700-m-thick sills of ultramafic rocks (dunite, harzburgite, pyroxenite) emplaced into pelitic, dolomitic, and locally quartzitic and evaporitic rocks belonging to the Duitschland Formation of the Transvaal Supergroup. Next is an approximately 100-200-m sequence of low-grade-sulphide-mineralised, layered mafic-ultramafic rocks containing abundant sedimentary xenoliths and, in places, several chromite seams or stringers. This is overlain by a 100-m-thick sequence of well-mineralised mafic-ultramafic rocks (the Flatreef sensu strictu), overlain by a laterally persistent mottled compositional analogies at the base of > 1 km of homogenous Main Zone gabbronorite. Based on stratigraphic, lithological and compositional alanalogies to the layered rocks in the eastern and western Bushveld Complex, we correlate the Flatreef and its chromite bearing footwall rocks with the Upper Critical Zone, notably the interval between the UG2 chromitite and the Bastard Reef as found elsewhere in the Bushveld Complex. This includes recognition of a Merensky Reef correlative. The ultramafic rocks below the main chromitite seam (UG2 correlative) in the Flatreef footwall are correlated with the Lower Critical and Lower zones. However, compared to the western and eastern Bushveld limbs, the studied sequence is strongly enriched in sulphide and PGE, many of the rocks show elevated CaO, K2O, Rb and Zr contents, and lateral continuity of layers between drill cores is less pronounced than elsewhere in the Bushveld, whereas ultramafic units are locally considerably thickened. These compositional and lithological traits are interpreted to result from a range of processes which include contamination with calcsilicate and hornfels, intrusion of granitic magmas, and the influence of multiple structural events such as pre- to syn-emplacement regional-scale open folding and growth faults. Evidence for the existence of potholes also exists. In the shallow, up-dip portions of the project area, the entire magmatic sequence below the Main Zone becomes increasingly contaminated to the extent that individual units are somewhat more difficult to correlate between drill cores. This package represents the Platreef as exposed in outcrop and shallow bore holes across much of the northern limb of the Bushveld Complex. The new data presented here thus indicate that the Platreef is a relatively more contaminated up-dip extension of parts of the Critical and Lower zones.

  3. KSC-2010-5618

    NASA Image and Video Library

    2010-11-10

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, a worker examines the foam insulation on space shuttle Discovery's external fuel tank. Two cracks on a section of the tank’s metal exterior were found on one of the stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Engineers will review images of the cracks to determine the best possible repair method. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder

  4. DOE Office of Scientific and Technical Information (OSTI.GOV)

    Degenhardt, R.; PFH, Private University of Applied Sciences Goettingen, Composite Engineering Campus Stade; Araujo, F. C. de

    European aircraft industry demands for reduced development and operating costs. Structural weight reduction by exploitation of structural reserves in composite aerospace structures contributes to this aim, however, it requires accurate and experimentally validated stability analysis of real structures under realistic loading conditions. This paper presents different advances from the area of computational stability analysis of composite aerospace structures which contribute to that field. For stringer stiffened panels main results of the finished EU project COCOMAT are given. It investigated the exploitation of reserves in primary fibre composite fuselage structures through an accurate and reliable simulation of postbuckling and collapse. Formore » unstiffened cylindrical composite shells a proposal for a new design method is presented.« less

  5. Axial crack propagation and arrest in pressurized fuselage

    NASA Technical Reports Server (NTRS)

    Kosai, M.; Shimamoto, A.; Yu, C.-T.; Walker, S. I.; Kobayashi, A. S.; Tan, P.

    1994-01-01

    The crack arrest capability of a tear strap in a pressurized precracked fuselage was studied through instrumented axial rupture tests of small scale models of an idealized fuselage. Upon pressurization, rapid crack propagation initiated at an axial through crack along the stringer and immediately kinked due to the mixed modes 1 and 2 state caused by the one-sided opening of the crack flap. The diagonally running crack further turned at the tear straps. Dynamic finite element analysis of the rupturing cylinder showed that the crack kinked and also ran straight in the presence of a mixed mode state according to a modified two-parameter crack kinking criterion.

  6. Methodology of shell structure reinforcement layout optimization

    NASA Astrophysics Data System (ADS)

    Szafrański, Tomasz; Małachowski, Jerzy; Damaziak, Krzysztof

    2018-01-01

    This paper presents an optimization process of a reinforced shell diffuser intended for a small wind turbine (rated power of 3 kW). The diffuser structure consists of multiple reinforcement and metal skin. This kind of structure is suitable for optimization in terms of selection of reinforcement density, stringers cross sections, sheet thickness, etc. The optimisation approach assumes the reduction of the amount of work to be done between the optimization process and the final product design. The proposed optimization methodology is based on application of a genetic algorithm to generate the optimal reinforcement layout. The obtained results are the basis for modifying the existing Small Wind Turbine (SWT) design.

  7. Lightweight Structures

    NASA Technical Reports Server (NTRS)

    Whittenberger, J. Daniel

    2001-01-01

    Present structural concepts for hot static structures are conventional "sheet & stringer" or truss core construction. More weight-efficient concepts such as honeycomb and lattice block are being investigated, in combination with both conventional superalloys and TiAl. Development efforts for components made from TiAl sheet are centered on lower cost methods for sheet and foil production, plus alloy development for higher temperature capability. A low-cost casting technology recently developed for aluminum and steel lattice blocks has demonstrated the required higher strength and stiffness, with weight efficiency approach- ing honeycombs. The current effort is based on extending the temperature capability by developing lattice block materials made from IN-718 and Mar-M247.

  8. Comparison between theoretical and experimental stresses in circular semimonocoque cylinders with rectangular cutouts

    NASA Technical Reports Server (NTRS)

    Mccomb, Harvey G , Jr; Low, Emmet F , Jr

    1955-01-01

    Comparisons are made between a theory for calculating stresses about rectangular cutouts in circular cylinders of semimonocoque construction published in NACA-TN-3200 and previously published NACA experimental data. The comparisons include stresses in the stringers and shear stresses in the center of the shear panels in the neighborhood of the cutout. The theory takes into account the bending flexibility of the rings in the structure, and this factor is found to be important in the calculation of stresses about cutouts. In general, when the ring flexibility is considered, good agreement is exhibited between the calculated and experimental results. (author)

  9. Mechanical Controls on Halokinesis in Layered Evaporite Sequences: Insights from 2D Geomechanical Forward Models

    NASA Astrophysics Data System (ADS)

    Goteti, Rajesh; Agar, Susan M.; Brown, John P.; Ball, Philip; Zuhlke, Rainer

    2017-04-01

    Mechanical stratification in LES (Layered Evaporate Sequences) can have a distinct impact on structural and depositional styles in rifted margin salt tectonics. The bulk mechanical response of an LES under geological loading is dependent, among other factors, on the relative proportions of salt and sediment, salt mobility and sedimentation rate. To assess the interactions among the aforementioned factors in a physically consistent manner, we present 2D, large-strain finite element models of an LES salt minibasin and diapirs. Loading from the deposition of alternating salt and sediment layers (i.e., LES), gravity and a prescribed geothermal gradient provide the driving force for halokinesis in the models. To accurately capture the mechanical impact of stratification within the modeled LES, salt is assigned a temperature-dependent visco-plastic rheology, whereas the sediments are assigned a non-associative cap-plasticity model that supports both compaction and shear localization. Perturbations in the initial salt-sediment interface are used to initiate the salt diapirs. Model results suggest that active diapirism in the basal halite layer initiates when the pressure at the base of the incipient salt diapir exceeds that beneath the minibasin. Vertical growth of the diapir is also accompanied by its lateral expansion at higher structural levels where it preferentially intrudes the adjacent pre- and syn-kinematic salt layers. This pressure pumping of deeper salt into shallow salt layers, can result in rapid thickness changes between successive sediment layers within the LES. Caution needs to be exercised as such thickness changes observed in seismic images may not be entirely due to the shifting of depocenters but also due to the lateral pumping of salt within the LES. The presence of salt layers at multiple structural levels decouples the deformation between successive clastic layers resulting in disharmomic folding with contrasting strain histories in the sedimentary stringers. A significant proportion of the bulk deviatoric strain is preferentially partitioned into the salt layers. Effective plastic shear strains within the sediment stringers generally remain low in the minibasin but can be significantly higher with attendant intense folding near the diapirs. In non-LES systems, the shape of a salt diapir is often used as indicator of relative rates of salt supply and sedimentation over geological time. However our models suggest that this rule-of-thumb may not apply in LES where the shape of the salt diapir is a function of the mechanical properties of the salt layers at various structural levels in addition to the relative rates of salt supply and sedimentation. Imaging challenges in LES may preclude placing strong constraints on structural timing based on interpretation of interfaces between the stringers and the salt diapir. In such situations, geomechanical forward modeling can be a useful tool in placing physics-based quantitative constraints on the timing of LES structures.

  10. New PDC bit optimizes drilling performance

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Besson, A.; Gudulec, P. le; Delwiche, R.

    1996-05-01

    The lithology in northwest Argentina contains a major section where polycrystalline diamond compact (PDC) bits have not succeeded in the past. The section consists of dense shales and cemented sandstone stringers with limestone laminations. Conventional PDC bits experienced premature failures in the section. A new generation PDC bit tripled rate of penetration (ROP) and increased by five times the potential footage per bit. Recent improvements in PDC bit technology that enabled the improved performance include: the ability to control the PDC cutter quality; use of an advanced cutter lay out defined by 3D software; using cutter face design code formore » optimized cleaning and cooling; and, mastering vibration reduction features, including spiraled blades.« less

  11. KSC-2010-5961

    NASA Image and Video Library

    2010-12-29

    CAPE CANAVERAL, Fla. -- Inside the intertank of space shuttle Discovery's external fuel tank, a technician holds the film used to project computed radiography scans. The shuttle stack, consisting of the shuttle, external tank and solid rocket boosters, was moved from Launch Pad 39A to the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida so technicians could examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank and re-apply foam insulation. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frankie Martin

  12. Data-Driven Mechanistic Modeling of Influence of Microstructure on High-Cycle Fatigue Life of Nickel Titanium

    NASA Astrophysics Data System (ADS)

    Kafka, Orion L.; Yu, Cheng; Shakoor, Modesar; Liu, Zeliang; Wagner, Gregory J.; Liu, Wing Kam

    2018-04-01

    A data-driven mechanistic modeling technique is applied to a system representative of a broken-up inclusion ("stringer") within drawn nickel-titanium wire or tube, e.g., as used for arterial stents. The approach uses a decomposition of the problem into a training stage and a prediction stage. It is applied to compute the fatigue crack incubation life of a microstructure of interest under high-cycle fatigue. A parametric study of a matrix-inclusion-void microstructure is conducted. The results indicate that, within the range studied, a larger void between halves of the inclusion increases fatigue life, while larger inclusion diameter reduces fatigue life.

  13. Fabrication and evaluation of advanced titanium structural panels for supersonic cruise aircraft

    NASA Technical Reports Server (NTRS)

    Payne, L.

    1977-01-01

    Flightworthy primary structural panels were designed, fabricated, and tested to investigate two advanced fabrication methods for titanium alloys. Skin-stringer panels fabricated using the weldbraze process, and honeycomb-core sandwich panels fabricated using a diffusion bonding process, were designed to replace an existing integrally stiffened shear panel on the upper wing surface of the NASA YF-12 research aircraft. The investigation included ground testing and Mach 3 flight testing of full-scale panels, and laboratory testing of representative structural element specimens. Test results obtained on full-scale panels and structural element specimens indicate that both of the fabrication methods investigated are suitable for primary structural applications on future civil and military supersonic cruise aircraft.

  14. Design and Analysis of a Stiffened Composite Fuselage Panel

    NASA Technical Reports Server (NTRS)

    Dickson, J. N.; Biggers, S. B.

    1980-01-01

    A stiffened composite panel has been designed that is representative of the fuselage structure of existing wide bodied aircraft. The panel is a minimum weight design, based on the current level of technology and realistic loads and criteria. Several different stiffener configurations were investigated in the optimization process. The final configuration is an all graphite epoxy J-stiffened design in which the skin between adjacent stiffeners is permitted to buckle under design loads. Fail-safe concepts typically employed in metallic fuselage structure have been incorporated in the design. A conservative approach has been used with regard to structural details such as skin frame and stringer frame attachments and other areas where sufficient design data was not available.

  15. Propeller aircraft interior noise model

    NASA Technical Reports Server (NTRS)

    Pope, L. D.; Wilby, E. G.; Wilby, J. F.

    1984-01-01

    An analytical model was developed to predict the interior noise of propeller-driven aircraft. The fuselage model is that of a cylinder with a structurally-integral floor. The cabin sidewall is stiffened by stringers and ring frames, and the floor by longitudinal beams. The cabin interior is covered with a sidewall treatments consisting of layers of porous material and an impervious trim septum. Representation of the propeller pressure field is utilized as input data in the form of the propeller noise signature at a series of locations on a grid over the fuselage structure. Results obtained from the analytical model are compared with test data measured by NASA in a scale model cylindrical fuselage excited by a model propeller.

  16. Real Time Fatigue Damage Growth Assessment of a Composite Three-Stringer Panel Using Passive Thermography

    NASA Technical Reports Server (NTRS)

    Zalameda, Joseph N.; Burke, Eric R.; Horne, Michael R.; Bly, James B.

    2015-01-01

    Fatigue testing of advanced composite structures is critical to validate both structural designs and damage prediction models. In-situ inspection methods are necessary to track damage onset and growth as a function of load cycles. Passive thermography is a large area, noncontact inspection technique that is used to detect composite damage onset and growth in real time as a function of fatigue cycles. The thermal images are acquired in synchronicity to the applied compressive load using a dual infrared camera acquisition system for full (front and back) coverage. Image processing algorithms are investigated to increase defect contrast areas. The thermal results are compared to non-immersion ultrasound inspections and acoustic emission data.

  17. Level II scour analysis for Bridge 28 (BRNATH00660028) on Town Highway 66, crossing Locust Creek, Barnard, Vermont

    USGS Publications Warehouse

    Severence, Timothy

    1997-01-01

    The Town Highway 66 crossing of the Locust Creek is a 41-ft-long, one-lane bridge consisting of a 39 ft steel stringer type bridge with a concrete deck (Vermont Agency of Transportation, written communication, August 24, 1994). The clear span is 36.8 ft. The bridge is supported by vertical, concrete abutments with wingwalls. The upstream right wingwall is protected by stone fill. The channel is skewed approximately 10 degrees to the opening while the opening-skew-to-roadway is 0 degrees. Additional details describing conditions at the site are included in the Level II Summary and Appendices D and E.

  18. Influence of an asymmetric ring on the modeling of an orthogonally stiffened cylindrical shell

    NASA Technical Reports Server (NTRS)

    Rastogi, Naveen; Johnson, Eric R.

    1994-01-01

    Structural models are examined for the influence of a ring with an asymmetrical cross section on the linear elastic response of an orthogonally stiffened cylindrical shell subjected to internal pressure. The first structural model employs classical theory for the shell and stiffeners. The second model employs transverse shear deformation theories for the shell and stringer and classical theory for the ring. Closed-end pressure vessel effects are included. Interacting line load intensities are computed in the stiffener-to-skin joints for an example problem having the dimensions of the fuselage of a large transport aircraft. Classical structural theory is found to exaggerate the asymmetric response compared to the transverse shear deformation theory.

  19. A Method for Calculating Strain Energy Release Rates in Preliminary Design of Composite Skin/Stringer Debonding Under Multi-Axial Loading

    NASA Technical Reports Server (NTRS)

    Krueger, Ronald; Minguet, Pierre J.; OBrien, T. Kevin

    1999-01-01

    Three simple procedures were developed to determine strain energy release rates, G, in composite skin/stringer specimens for various combinations of unaxial and biaxial (in-plane/out-of-plane) loading conditions. These procedures may be used for parametric design studies in such a way that only a few finite element computations will be necessary for a study of many load combinations. The results were compared with mixed mode strain energy release rates calculated directly from nonlinear two-dimensional plane-strain finite element analyses using the virtual crack closure technique. The first procedure involved solving three unknown parameters needed to determine the energy release rates. Good agreement was obtained when the external loads were used in the expression derived. This superposition technique was only applicable if the structure exhibits a linear load/deflection behavior. Consequently, a second technique was derived which was applicable in the case of nonlinear load/deformation behavior. The technique involved calculating six unknown parameters from a set of six simultaneous linear equations with data from six nonlinear analyses to determine the energy release rates. This procedure was not time efficient, and hence, less appealing. A third procedure was developed to calculate mixed mode energy release rates as a function of delamination lengths. This procedure required only one nonlinear finite element analysis of the specimen with a single delamination length to obtain a reference solution for the energy release rates and the scale factors. The delamination was extended in three separate linear models of the local area in the vicinity of the delamination subjected to unit loads to obtain the distribution of G with delamination lengths. This set of sub-problems was Although additional modeling effort is required to create the sub- models, this local technique is efficient for parametric studies.

  20. KSC-2010-5940

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Technicians in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida will begin to remove thermal sensors that will give engineers data about the changes space shuttle Discovery's external fuel tank went through during the loading and draining of super-cold propellants during a tanking test on Dec. 17. Engineers also will examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank region. Also on the agenda, is to re-apply foam to the outside of the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis

  1. KSC-2010-5938

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Preparations are under way in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida to examine space shuttle Discovery's external fuel tank. Technicians will begin to remove thermal sensors that will give engineers data about the changes the tank went through during the loading and draining of super-cold propellants. Engineers also will examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank region. Also on the agenda, is to re-apply foam to the outside of the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis

  2. Properties of splat-quenched 7075 aluminum type alloys

    NASA Technical Reports Server (NTRS)

    Durand, J. P. H. A.; Pelloux, R. M.; Grant, N. J.

    1976-01-01

    The 7075 alloy belonging to the Al-Zn-Mg-Cu system, prepared by powder metallurgy techniques, was used in a study of alloys prepared from splat-quenched foils consolidated into bar material by hot extrusion. Ni and Fe were included in one alloy specimen, producing a fine dispersion of FeAl3 type particles which added to the strength of the aged alloy but did not coarsen upon heat treatment. Fine oxide films showing up on air-splatted foils induce finely dispersed oxide stringers (if the foils are not hot-worked subsequently) which in turn promote axial cracking (but longitudinal tensile strength is not seriously impaired). Splatting in a protective atmosphere, or thermomechanical processing, is recommended to compensate for this.

  3. KSC-2010-5741

    NASA Image and Video Library

    2010-11-30

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the ground umbilical carrier plate (GUCP) of space shuttle Discovery's external fuel tank has been repaired. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. Discovery's next launch attempt is no earlier than Dec. 17 at 8:51 p.m. EST. Until then, engineers will continue to analyze data from the GUCP and stringer crack repairs. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  4. KSC-2010-5742

    NASA Image and Video Library

    2010-11-30

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the ground umbilical carrier plate (GUCP) of space shuttle Discovery's external fuel tank has been repaired. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. Discovery's next launch attempt is no earlier than Dec. 17 at 8:51 p.m. EST. Until then, engineers will continue to analyze data from the GUCP and stringer crack repairs. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  5. Design and analysis of a stiffened composite fuselage panel

    NASA Technical Reports Server (NTRS)

    Dickson, J. N.; Biggers, S. B.

    1980-01-01

    The design and analysis of stiffened composite panel that is representative of the fuselage structure of existing wide bodied aircraft is discussed. The panel is a minimum weight design, based on the current level of technology and realistic loads and criteria. Several different stiffener configurations were investigated in the optimization process. The final configuration is an all graphite/epoxy J-stiffened design in which the skin between adjacent stiffeners is permitted to buckle under design loads. Fail safe concepts typically employed in metallic fuselage structure have been incorporated in the design. A conservative approach has been used with regard to structural details such as skin/frame and stringer/frame attachments and other areas where sufficient design data was not available.

  6. PROTECTIVELY COVERED ARTICLE AND METHOD OF MANUFACTURE

    DOEpatents

    Plott, R.F.

    1958-10-28

    A method of casting a protective jacket about a ura nium fuel element that will bond completely to the uranium without the use of stringers or supports that would ordinarily produce gaps in the cast metal coating and bond is presented. Preformed endcaps of alumlnum alloyed with 13% silicon are placed on the ends of the uranium fuel element. These caps will support the fuel element when placed in a mold. The mold is kept at a ing alloy but below that of uranium so the cast metal jacket will fuse with the endcaps forming a complete covering and bond to the fuel element, which would otherwise oxidize at the gaps or discontinuities lefi in the coating by previous casting methods.

  7. A potentiodynamic study of aluminum-lithium alloys in an aqueous sodium chloride environment

    NASA Technical Reports Server (NTRS)

    Tsao, C.-H. T.; Pizzo, P. P.

    1985-01-01

    The characteristics of the potentiodynamic curves for Al-Li alloys in 3.5 percent NaCl aqueous solution are explained and the electrochemical parameters of the potentiodynamic technique are correlated to observed pitting and intergranular cracking behavior. It is shown that the oxygen content of the sodium chloride electrolyte plays an important role in the electrochemical behavior of Al-Li alloys. The potentiodynamic behavior of the alloys is found to be insensitive to variation in compositional content and heat treatment, both of which affect the stress-corrosion behavior. Stringer oxide particle attack and random pitting are observed. It is shown that alternate-immersion exposure prior to potentiodynamic polarization may offer a means of assessing susceptibility to stress-corrosion cracking.

  8. Fatigue design curve of a TiNi/Al shape memory alloy composite for aircraft stringer design

    NASA Astrophysics Data System (ADS)

    Park, Young-Chul; Jo, Young-Jik; Baek, Seok-Heum; Furuya, Yasubumi

    2009-05-01

    In this study, a TiNi/Al6061 shape memory alloy (SMA) composite was fabricated by the hot press method, and pressed by a roller for its strength improvement using the shape memory fiber shrinkage phenomenon. These two kinds of specimens were fabricated with 0% and 5% volume ratio and 0%, 10 % and 20% reduction ratio of TiNi alloy fiber, respectively. A fatigue test has been performed to evaluate the fatigue life for the fabricated TiNi/Al SMA composite as an S-N curve. The results from the Goodman diagram is able to illustrate the failure criterion and fatigue limit between tensile and bending fatigue strength in the fatigue characterization of TiNi/Al SMA composites.

  9. Application of the Shell/3D Modeling Technique for the Analysis of Skin-Stiffener Debond Specimens

    NASA Technical Reports Server (NTRS)

    Krueger, Ronald; O'Brien, T. Kevin; Minguet, Pierre J.

    2002-01-01

    The application of a shell/3D modeling technique for the simulation of skin/stringer debond in a specimen subjected to three-point bending is demonstrated. The global structure was modeled with shell elements. A local three-dimensional model, extending to about three specimen thicknesses on either side of the delamination front was used to capture the details of the damaged section. Computed total strain energy release rates and mixed-mode ratios obtained from shell/13D simulations were in good agreement with results obtained from full solid models. The good correlations of the results demonstrated the effectiveness of the shell/3D modeling technique for the investigation of skin/stiffener separation due to delamination in the adherents.

  10. Paleontological interpretations of crater processes and infilling of synimpact sediments from the Chesapeake Bay impact structure

    USGS Publications Warehouse

    Self-Trail, Jean M.; Edwards, Lucy E.; Litwin, Ronald J.

    2009-01-01

    Biostratigraphic analysis of sedimentary breccias and diamictons in the Chesapeake Bay impact structure provides information regarding the timing and processes of late-stage gravitational crater collapse and ocean resurge. Studies of calcareous nannofossil and palynomorph assemblages in the International Continental Scientific Drilling Program (ICDP)–U.S. Geological Survey (USGS) Eyreville A and B cores show the mixed-age, mixed-preservation microfossil assemblages that are typical of deposits from the upper part of the Chesapeake Bay impact structure. Sparse, poorly preserved, possibly thermally altered pollen is present within a gravelly sand interval below the granite slab at 1392 m in Eyreville core B, an interval that is otherwise barren of calcareous nannofossils and dinocysts. Gravitational collapse of water- saturated sediments from the transient crater wall resulted in the deposition of sediment clasts primarily derived from the nonmarine Cretaceous Potomac Formation. Collapse occurred before the arrival of resurge. Low pollen Thermal Alteration Index (TAI) values suggest that these sediments were not thermally altered by contact with the melt sheet. The arrival of resurge sedimentation is identified based on the presence of diamicton zones and stringers rich in glauconite and marine microfossils at 866.7 m. This horizon can be traced across the crater and can be used to identify gravitational collapse versus ocean-resurge sedimentation. Glauconitic quartz sand diamicton dominates the sediments above 618.2 m. Calcareous nannofossil and dino-flagellate data from this interval suggest that the earliest arriving resurge from the west contained little or no Cretaceous marine input, but later resurge pulses mined Cretaceous sediments east of the Watkins core in the annular trough. Additionally, the increased distance traveled by resurge to the central crater in turbulent flow conditions resulted in the disaggregation of Paleogene unconsolidated sediments. As a result, intact Paleogene clasts in Eyreville cores are rare, but clasts of semilithified Potomac Formation silts and clays are common.

  11. Paleontological interpretations of crater processes and infilling of synimpact sediments from the Chesapeake Bay impact structure

    USGS Publications Warehouse

    ,; Edwards, L.E.; Litwin, R.J.

    2009-01-01

    Biostratigraphic analysis of sedimentary breccias and diamictons in the Chesapeake Bay impact structure provides information regarding the timing and processes of late-stage gravitational crater collapse and ocean resurge. Studies of calcareous nannofossil and palynomorph assemblages in the International Continental Scientific Drilling Program (ICDP)-U.S. Geological Survey (USGS) Eyreville A and B cores show the mixed-age, mixed-preservation microfossil assemblages that are typical of deposits from the upper part of the Chesapeake Bay impact structure. Sparse, poorly preserved, possibly thermally altered pollen is present within a gravelly sand interval below the granite slab at 1392 m in Eyreville core B, an interval that is otherwise barren of calcareous nannofossils and dinocysts. Gravitational collapse of watersaturated sediments from the transient crater wall resulted in the deposition of sediment clasts primarily derived from the nonmarine Cretaceous Potomac Formation. Collapse occurred before the arrival of resurge. Low pollen Thermal Alteration Index (TAI) values suggest that these sediments were not thermally altered by contact with the melt sheet. The arrival of resurge sedimentation is identified based on the presence of diamicton zones and stringers rich in glauconite and marine microfossils at 866.7 m. This horizon can be traced across the crater and can be used to identify gravitational collapse versus ocean-resurge sedimentation. Glauconitic quartz sand diamicton dominates the sediments above 618.2 m. Calcareous nannofossil and dinoflagellate data from this interval suggest that the earliest arriving resurge from the west contained little or no Cretaceous marine input, but later resurge pulses mined Cretaceous sediments east of the Watkins core in the annular trough. Additionally, the increased distance traveled by resurge to the central crater in turbulent flow conditions resulted in the disaggregation of Paleogene unconsolidated sediments. As a result, intact Paleogene clasts in Eyreville cores are rare, but clasts of semilithified Potomac Formation silts and clays are common. ?? 2009 The Geological Society of America.

  12. Mineralogical, IR-spectral and geochemical monitoring of hydrothermal alteration in a deformed and metamorphosed Jurassic VMS deposit at Arroyo Rojo, Tierra del Fuego, Argentina

    NASA Astrophysics Data System (ADS)

    Biel, C.; Subías, I.; Acevedo, R. D.; Yusta, I.; Velasco, F.

    2012-04-01

    The Arroyo Rojo Zn-Pb-Cu volcanogenic massive sulfide deposit is the main deposit of the Fin del Mundo District in the Fuegian Andes, Argentina. This deposit is hosted by a Middle Jurassic volcanic and volcanoclastic sequence forming the Lemaire Formation. The latter consists, from the base up, of the following: rhyolitic and dacitic porphyritic rocks, ignimbrite, tuff, and flow. It is underlain by a pre-Jurassic basement and overlain by the hyaloclastic andesites of the Yahgán Formation. The Arroyo Rojo consists of stacked lenticular lenses that are associated with disseminated mineralization in both the footwall and the hanging wall. The internal structure of the ore lenses is marked by the occurrence of massive, semi-massive and banded facies, along with stringer and brecciated zones and minor ore disseminations. The mineral assemblage comprises mainly pyrite and sphalerite, with minor amounts of galena and chalcopyrite and rare pyrrhotite, arsenopyrite, tetrahedrite and bournonite. The ores and the volcanic host rocks have metamorphosed to greenschist facies and were overprinted by a penetrative tectonic foliation, which led to the development of mylonitic, and cataclastic textures, recrystallization and remobilization. Primary depositional characteristics and regional and hydrothermal alteration patterns were preserved despite deformation and metamorphism. Therefore, primary banding was preserved between facies boundaries. In addition, some remnants of magmatic origin are recognizable in preserved phenocrysts and volcaniclastic phenoclasts. Most of the volcanic and volcaniclastic rocks of the host sequence show a rhyolitic to rhyo-dacitic composition. Regional seafloor alteration, characterized by the presence of clinozoisite, Fe-chlorite and titanite, along with quartz and albite, is partially obliterated by hydrothermal alteration. The hydrothermal alteration is stratabound with the following assemblages, which developed from the base to top: (1) Quartz-Chlorite ± Sericite, (2) Quartz-Chlorite, (3) Chlorite ± Quartz-Sericite-Calcite, (4) Quartz-Chlorite ± Calcite and (5) Sericite + Quartz ± Chlorite ± Calcite. Magnesium-chlorite and phengitic white mica typically occur in the vicinity of the Arroyo Rojo ore lenses. To provide field criteria for exploration vectoring, the chemical composition of chlorite and the phengitic and paragonitic content of the white mica were determined and correlated with PIMA Fe-OH and Al-OH absorption wavelengths, respectively, relative to their proximity to the mineralized lenses. The results of this study can be used to help identify (1) felsic proximal facies associations, (2) ore horizons and (3) favorable hydrothermal alteration zones in other parts of the Fin del Mundo district.

  13. KSC-2010-5946

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Preparations are under way in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida to examine space shuttle Discovery's external fuel tank. Technicians will begin to remove thermal sensors that will give engineers data about the changes the tank went through during the loading and draining of super-cold propellants during a tanking test on Dec. 17. Engineers also will examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank region. Also on the agenda, is to re-apply foam to the outside of the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis

  14. KSC-2010-5941

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Preparations are under way in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida to examine space shuttle Discovery's external fuel tank. Technicians will begin to remove thermal sensors that will give engineers data about the changes the tank went through during the loading and draining of super-cold propellants during a tanking test on Dec. 17. Engineers also will examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank region. Also on the agenda, is to re-apply foam to the outside of the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis

  15. KSC-2010-5942

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Preparations are under way in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida to examine space shuttle Discovery's external fuel tank. Technicians will begin to remove thermal sensors that will give engineers data about the changes the tank went through during the loading and draining of super-cold propellants during a tanking test on Dec. 17. Engineers also will examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank region. Also on the agenda, is to re-apply foam to the outside of the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis

  16. KSC-2010-5944

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Preparations are under way in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida to examine space shuttle Discovery's external fuel tank. Technicians will begin to remove thermal sensors that will give engineers data about the changes the tank went through during the loading and draining of super-cold propellants during a tanking test on Dec. 17. Engineers also will examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank region. Also on the agenda, is to re-apply foam to the outside of the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis

  17. KSC-2010-5852

    NASA Image and Video Library

    2010-12-14

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery's external fuel tank is outfitted with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

  18. KSC-2010-5848

    NASA Image and Video Library

    2010-12-14

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery's external fuel tank is outfitted with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

  19. KSC-2010-5851

    NASA Image and Video Library

    2010-12-14

    CAPE CANAVERAL, Fla. -- Technicians outfit space shuttle Discovery's external fuel tank with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

  20. KSC-2010-5849

    NASA Image and Video Library

    2010-12-14

    CAPE CANAVERAL, Fla. -- Technicians outfit space shuttle Discovery's external fuel tank with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

  1. KSC-2010-5855

    NASA Image and Video Library

    2010-12-14

    CAPE CANAVERAL, Fla. -- Technicians outfit space shuttle Discovery's external fuel tank with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

  2. KSC-2010-5854

    NASA Image and Video Library

    2010-12-14

    CAPE CANAVERAL, Fla. -- Technicians outfit space shuttle Discovery's external fuel tank with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

  3. KSC-2010-5853

    NASA Image and Video Library

    2010-12-14

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery's external fuel tank is outfitted with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

  4. KSC-2010-5850

    NASA Image and Video Library

    2010-12-14

    CAPE CANAVERAL, Fla. -- Technicians outfit space shuttle Discovery's external fuel tank with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

  5. Thermal math model analysis of FRSI test article subjected to cold soak and entry environments. [Flexible Reuseable Surface Insulation in Space Shuttle Orbiter

    NASA Technical Reports Server (NTRS)

    Gallegos, J. J.

    1978-01-01

    A multi-objective test program was conducted at the NASA/JSC Radiant Heat Test Facility in which an aluminum skin/stringer test panel insulated with FRSI (Flexible Reusable Surface Insulation) was subjected to 24 simulated Space Shuttle Orbiter ascent/entry heating cycles with a cold soak in between in the 10th and 20th cycles. A two-dimensional thermal math model was developed and utilized to predict the thermal performance of the FRSI. Results are presented which indicate that the modeling techniques and property values have been proven adequate in predicting peak structure temperatures and entry thermal responses from both an ambient and cold soak condition of an FRSI covered aluminum structure.

  6. KSC-2010-5621

    NASA Image and Video Library

    2010-11-10

    CAPE CANAVERAL, Fla. -- During the removal of external fuel tank foam insulation on Launch Pad 39A at NASA's Kennedy Space Center in Florida, technicians identified two cracks, each about 9 inches long, on a section of the tank’s metal exterior. The foam cracked during initial loading operations for space shuttle Discovery’s launch attempt on Nov. 5. The cracks are on one of the stringers, which are the composite aluminum ribs located vertically on the tank’s intertank area. Engineers will review images of the cracks to determine the best possible repair method, which would be done at the pad. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA

  7. Quiet Honeycomb Panels

    NASA Technical Reports Server (NTRS)

    Palumbo, Daniel L.; Klos, Jacob

    2010-01-01

    Sandwich honeycomb composite panels are lightweight and strong, and, therefore, provide a reasonable alternative to the aluminum ring frame/stringer architecture currently used for most aircraft airframes. The drawback to honeycomb panels is that they radiate noise into the aircraft cabin veil- efficiently provoking the need for additional sound treatment which adds weight and reduces the material's cost advantage. A series of honeycomb panels was made -hick incorporated different design strategies aimed at reducing the honeycomb panels' radiation efficiency while at the same time maintaining their strength. The majority of the designs were centered around the concept of creating areas of reduced stiffness in the panel by adding voids and recesses to the core. The effort culminated with a reinforced/recessed panel which had 6 dB higher transmission loss than the baseline solid core panel while maintaining comparable strength.

  8. Fracture Mechanics for Composites: State of the Art and Challenges

    NASA Technical Reports Server (NTRS)

    Krueger, Ronald; Krueger, Ronald

    2006-01-01

    Interlaminar fracture mechanics has proven useful for characterizing the onset of delaminations in composites and has been used with limited success primarily to investigate onset in fracture toughness specimens and laboratory size coupon type specimens. Future acceptance of the methodology by industry and certification authorities however, requires the successful demonstration of the methodology on the structural level. In this paper, the state-of-the-art in fracture toughness characterization, and interlaminar fracture mechanics analysis tools are described. To demonstrate the application on the structural level, a panel was selected which is reinforced with stringers. Full implementation of interlaminar fracture mechanics in design however remains a challenge and requires a continuing development effort of codes to calculate energy release rates and advancements in delamination onset and growth criteria under mixed mode conditions.

  9. Thermo-mechanical process for treatment of welds

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Malik, R K

    1980-03-01

    Benefits from thermo-mechanical processing (TMP) of austenitic stainless steel weldments, analogous to hot isostatic pressing (HIP) of castings, most likely result from compressive plastic deformation, enhanced diffusion, and/or increased dislocation density. TMP improves ultrasonic inspectability of austenitic stainless steel welds owing to: conversion of cast dendrites into equiaxed austenitic grains, reduction in size and number of stringers and inclusions, and reduction of delta ferrite content. TMP induces structural homogenization and healing of void-type defects and thus contributes to an increase in elongation, impact strength, and fracture toughness as well as a significant reduction in data scatter for these properties. Anmore » optimum temperature for TMP or HIP of welds is one which causes negligible grain growth and an acceptable reduction in yield strength, and permits healing of porosity.« less

  10. Polymerisation processes in expoy resins under influence of free space environment

    NASA Astrophysics Data System (ADS)

    Kondyurin, A.; Lauke, B.; Kondyurina, I.

    A creation of large size constructions in space or on celestial bodies is possible by the way of chemical reactions of liquid viscous components under space environment conditions [1-2]. In particular, a new technology for large-size space module for electronic components, energy and materials production is developed on the basis of polymerisation technique. The factors of free space environment have a significant influence on the polymerisation processes. The polymerisation processes in active liquid components are sensitive to microgravitation, temperature variations (-150{ldots}+1500C), high vacuum (10-3{ldots}10-7 Pa), atomic oxygen flux (on LEO), UV and VUV irradiations, X-ray and γ -irradiations, high energy electron and ion fluxes. Experiments of polymerisation processes under simulated free space conditions were conducted. The influences of high vacuum, high energy ion beam and rf- and mw-plasma on polymerisation of epoxy resins were observed. The effects of low molecular components evaporations, free radical formations, additional chemical reactions and mixing processes during polymerisation were observed. Our results showed, that the space factors can initiate the polymerisation reaction in epoxy matrix of glass and carbon fibre composites. The result can be used for a technology for large size constructions on Earth orbit, in far space and on space bodies as for deployed antennas, solar sail stringers, solar shield stringers, frame for large-size space station, frame for Moon, Mars, asteroids bases, frame for space plant on Earth orbit and on other celestial bodies. The study was partially supported by Alexander von Humboldt Foundation (A. Kondyurin) and European Space Agency, ESTEC (contract 17083/03/NL/Sfe "Space Environmental Effects on the Polymerisation of Composite Structures"). 1. A.Kondyurin, B.Lauke, Polymerisation processes in simulated free space conditions, Proceedings of the 9th International Symposium on Materials in a Space Environment, Noordwijk, The Netherlands, 16-20 June, 2003, ESA SP-540, September 2003, pp.75-80. 2. V.A.Briskman, T.M.Yudina, K.G.Kostarev, A.V.Kondyurin, V.B.Leontyev, M.G.Levkovich, A.L.Mashinsky, G.S.Nechitailo, Polymerization in microgravity as a new process in space technology, Acta Astronautica, vol.48, N2-3, 2001, pp.169-180.

  11. Job Hunting, Introduction

    NASA Astrophysics Data System (ADS)

    Goldin, Ed; Stringer, Susan

    1998-05-01

    The AAS is again sponsoring a career workshop for Astronomers seeking employment. The workshop will cover a wide range of tools needed by a job seeker with a background in astronomy. There are increasingly fewer job opportunities in the academic areas. Today, astronomers need placement skills and career information to compete strongly in a more diversified jobs arena. The workshop will offer practical training on preparing to enter the job market. Topics covered include resume and letter writing as well as how to prepare for an interview. Advice is given on resources for jobs in astronomy, statistics of employment and education, and networking strategies. Workshop training also deals with a diverse range of career paths for astronomers. The workshop will consist of an two approximately three-hour sessions. The first (1-4pm) will be on the placement tools and job-search skills described above. The second session will be for those who would like to stay and receive personalized information on individual resumes, job search problems, and interview questions and practice. The individual appointments with Ed Goldin and Susan Stringer that will take place during the second session (6-9pm) will be arranged on-site during the first session. A career development and job preparation manual "Preparing Physicists for Work" will be on sale at the workshop for \\9.00. TOPICS FOR DISCUSSION: How to prepare an effective resume How to research prospective employers Interviewing skills Networking to uncover employment Job prospects present and future Traditional and non-traditional positions for astronomers This workshop will be presented by Ed Goldin and Susan Stringer of the American Institute of Physics. The cost of the workshop is \\15.00 which includes a packet of resource materials supporting the workshop presentation. Please send your request for attendance by 8 May 1998 to the Executive Office along with a check, payable to the AAS, for the fee. Credit cards will not be accepted. Preference will be given to AAS members in the event of a large number of registrants. For further information, contact the AAS Executive Office, 202-328-2010, dawn@aas.org

  12. Geology of the Jabal Riah area, Kingdom of Saudi Arabia

    USGS Publications Warehouse

    Wells, J.D.

    1982-01-01

    The Jabal Riah area is in the southern part of the Jibal al Hamdah quadrangle (lat 19?00'00'' to 19?07'S0'' N., long 45?37'30'' to 43?45'00' E.) in the southeastern Precambrian Shield, Asir Province, Kingdom of Saudi Arabia. The Jabal Mahanid group of ancient gold mines, which is part of the Jabal Ishmas-Wadi Tathlith gold belt, is in the west-central part of the area. Rocks in the Jabal Riah area consist of Precambrian layered metasedimentary and metavolcanic rocks intruded by Precambrian igneous rocks. The metamorphic rocks are, from oldest to youngest, interlayered hornblende and biotite schist, quartz-biotite schist, hornblende schist, serpentinite, and chlorite schist. The igneous rocks are, from oldest to youngest, diorite-gabbro including dikes, granodiorite, monzogranite-granodiorite, leucocratic quartz porphyry, rhyolite, and aplite and pegmatite dikes. A large area of jasper replaces serpentinite. On the valley floors, recent alluvium and pediment deposits overlie the bedrock. The structure of the area is dominated by a dome centered over the eastern border of the area; leucocratic quartz porphyry forms the core of the dome. Minor folds and faults are present. The Jabal Mahanid group of ancient gold mines is on a northwest-trending vein system, and major ancient mine areas are found where the system splits or changes direction. The veins consist of zones of brecciated and crushed rock, which are generally less than 0.5 m wide but may be as wide as 1 m. These zones contain quartz and calcite stringers and commonly are along hornblende schist-serpentinite contacts; however, they also cut both units. Most aplite, pegmatite, and quartz dikes in the area are thin and discontinuous and are intruded along the vein trend. Similar veins, at the same stratigraphic interval, have been found beyond the northeastern part of the map area. The veins contain detectable gold and silver (median gold, approximately 0.14 ppm; median silver, approximately 1 ppm). Gold and silver are most abundant in calcium-rich rocks and veins; silver was not detected in igneous rocks. Altered wall-rock zones are mineralized as much as 10 m away from the veins. Away from the Jabal Mahanid vein-system, silver was detected in the jasper. Gold and silver were detected in minor brecciated and sheared structures and in metasedimentary rocks. Gold was detected in sericitized margins of the leucocratic quartz porphyry, in unaltered rhyolite, and in aplite dikes. The presence of unusual amounts of gold and silver over a wide area is indicated by the ancient gold mines along veins at or near the hornblende schist-serpentinite contact in the map area and to the south in the Hajrah-Hamdah area and by the widespread evidence of precious metals in igneous rocks and other vein structures. A domed-shaped area, approximately 30 km in diameter, is outlined by the hornblende schist-serpentinite contact and has leucocratic quartz prophyry in the middle. Additional study of this area might reveal economic concentrations of gold and silver.

  13. KSC-2010-5943

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Preparations are under way in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida to examine space shuttle Discovery's external fuel tank. Shown here, is the inside of the tank's intertank region. Technicians will begin to remove thermal sensors that will give engineers data about the changes the tank went through during the loading and draining of super-cold propellants during a tanking test on Dec. 17. Engineers also will examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank region. Also on the agenda, is to re-apply foam to the outside of the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis

  14. Impact evaluation of composite floor sections

    NASA Technical Reports Server (NTRS)

    Boitnott, Richard L.; Fasanella, Edwin L.

    1989-01-01

    Graphite-epoxy floor sections representative of aircraft fuselage construction were statically and dynamically tested to evaluate their response to crash loadings. These floor sections were fabricated using a frame-stringer design typical of present aluminum aircraft without features to enhance crashworthiness. The floor sections were tested as part of a systematic research program developed to study the impact response of composite components of increasing complexity. The ultimate goal of the research program is to develop crashworthy design features for future composite aircraft. Initially, individual frames of six-foot diameter were tested both statically and dynamically. The frames were then used to construct built-up floor sections for dynamic tests at impact velocities of approximately 20 feet/sec to simulate survivable crash velocities. In addition, static tests were conducted to gain a better understanding of the failure mechanisms seen in the dynamic tests.

  15. KSC-2010-5844

    NASA Image and Video Library

    2010-12-10

    CAPE CANAVERAL, Fla. -- Technicians prepare space shuttle Discovery's external fuel tank for a tanking test no earlier than Dec. 15 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the intertank, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Teams already have installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  16. KSC-2010-5845

    NASA Image and Video Library

    2010-12-10

    CAPE CANAVERAL, Fla. -- Technicians prepare space shuttle Discovery's external fuel tank for a tanking test no earlier than Dec. 15 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the intertank, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Teams already have installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  17. KSC-2010-5834

    NASA Image and Video Library

    2010-12-09

    CAPE CANAVERAL, Fla. -- Technicians prepare space shuttle Discovery's external fuel tank for a tanking test no earlier than Dec. 15 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the intertank, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Teams already have installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Ben Smegelsky

  18. KSC-2010-5847

    NASA Image and Video Library

    2010-12-10

    CAPE CANAVERAL, Fla. -- Technicians prepare space shuttle Discovery's external fuel tank for a tanking test no earlier than Dec. 15 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the intertank, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Teams already have installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  19. KSC-2010-5833

    NASA Image and Video Library

    2010-12-09

    CAPE CANAVERAL, Fla. -- Technicians prepare space shuttle Discovery's external fuel tank for a tanking test no earlier than Dec. 15 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the intertank, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Teams already have installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Ben Smegelsky

  20. KSC-2010-5846

    NASA Image and Video Library

    2010-12-10

    CAPE CANAVERAL, Fla. -- Technicians prepare space shuttle Discovery's external fuel tank for a tanking test no earlier than Dec. 15 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the intertank, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Teams already have installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  1. Excitation, response, and fatigue life estimation methods for the structural design of externally blown flaps

    NASA Technical Reports Server (NTRS)

    Ungar, E. E.; Chandiramani, K. L.; Barger, J. E.

    1972-01-01

    Means for predicting the fluctuating pressures acting on externally blown flap surfaces are developed on the basis of generalizations derived from non-dimensionalized empirical data. Approaches for estimation of the fatigue lives of skin-stringer and honeycomb-core sandwich flap structures are derived from vibration response analyses and panel fatigue data. Approximate expressions for fluctuating pressures, structural response, and fatigue life are combined to reveal the important parametric dependences. The two-dimensional equations of motion of multi-element flap systems are derived in general form, so that they can be specialized readily for any particular system. An introduction is presented of an approach to characterizing the excitation pressures and structural responses which makes use of space-time spectral concepts and promises to provide useful insights, as well as experimental and analytical savings.

  2. Iron aluminide useful as electrical resistance heating elements

    DOEpatents

    Sikka, V.K.; Deevi, S.C.; Fleischhauer, G.S.; Hajaligol, M.R.; Lilly, A.C. Jr.

    1997-04-15

    The invention relates generally to aluminum containing iron-base alloys useful as electrical resistance heating elements. The aluminum containing iron-base alloys have improved room temperature ductility, electrical resistivity, cyclic fatigue resistance, high temperature oxidation resistance, low and high temperature strength, and/or resistance to high temperature sagging. The alloy has an entirely ferritic microstructure which is free of austenite and includes, in weight %, over 4% Al, {<=}1% Cr and either {>=}0.05% Zr or ZrO{sub 2} stringers extending perpendicular to an exposed surface of the heating element or {>=}0.1% oxide dispersoid particles. The alloy can contain 14-32% Al, {<=}2% Ti, {<=}2% Mo, {<=}1% Zr, {<=}1% C, {<=}0.1% B, {<=}30% oxide dispersoid and/or electrically insulating or electrically conductive covalent ceramic particles, {<=}1% rare earth metal, {<=}1% oxygen, {<=}3% Cu, balance Fe. 64 figs.

  3. NASA/FAA general aviation crash dynamics program - An update

    NASA Technical Reports Server (NTRS)

    Hayduk, R. J.; Thomson, R. G.; Carden, H. D.

    1979-01-01

    Work in progress in the NASA/FAA General Aviation Crash Dynamics Program for the development of technology for increased crash-worthiness and occupant survivability of general aviation aircraft is presented. Full-scale crash testing facilities and procedures are outlined, and a chronological summary of full-scale tests conducted and planned is presented. The Plastic and Large Deflection Analysis of Nonlinear Structures and Modified Seat Occupant Model for Light Aircraft computer programs which form part of the effort to predict nonlinear geometric and material behavior of sheet-stringer aircraft structures subjected to large deformations are described, and excellent agreement between simulations and experiments is noted. The development of structural concepts to attenuate the load transmitted to the passenger through the seats and subfloor structure is discussed, and an apparatus built to test emergency locator transmitters in a realistic environment is presented.

  4. Slow plastic strain rate compressive flow in binary CoAl intermetallics

    NASA Technical Reports Server (NTRS)

    Whittenberger, J. D.

    1985-01-01

    Constant-velocity elevated temperature compression tests have been conducted on a series of binary CoAl intermetallics produced by hot extrusion of blended prealloyed powders. The as-extruded materials were polycrystalline, and they retained their nominal 10-micron grain size after being tested between 1100 and 1400 K at strain rates ranging from 2 x 10 to the -4th to 2 x 10 to the -7th per sec. Significant plastic flow was obtained in all cases; while cracking was observed, much of this could be due to failure at matrix-oxide interfaces along extrusion stringers rather than to solely intergranular fracture. A maximum in flow strength occurs at an aluminum-to-cobalt ratio of 0.975, and the stress exponent appears to be constant for aluminum-to-cobalt ratios of 0.85 or more. It is likely that very aluminum-deficient materials deform by a different mechanism than do other compositions.

  5. Iron aluminide useful as electrical resistance heating elements

    DOEpatents

    Sikka, Vinod K.; Deevi, Seetharama C.; Fleischhauer, Grier S.; Hajaligol, Mohammad R.; Lilly, Jr., A. Clifton

    1997-01-01

    The invention relates generally to aluminum containing iron-base alloys useful as electrical resistance heating elements. The aluminum containing iron-base alloys have improved room temperature ductility, electrical resistivity, cyclic fatigue resistance, high temperature oxidation resistance, low and high temperature strength, and/or resistance to high temperature sagging. The alloy has an entirely ferritic microstructure which is free of austenite and includes, in weight %, over 4% Al, .ltoreq.1% Cr and either .gtoreq.0.05% Zr or ZrO.sub.2 stringers extending perpendicular to an exposed surface of the heating element or .gtoreq.0.1% oxide dispersoid particles. The alloy can contain 14-32% Al, .ltoreq.2% Ti, .ltoreq.2% Mo, .ltoreq.1% Zr, .ltoreq.1% C, .ltoreq.0.1% B, .ltoreq.30% oxide dispersoid and/or electrically insulating or electrically conductive covalent ceramic particles, .ltoreq.1% rare earth metal, .ltoreq.1% oxygen, .ltoreq.3% Cu, balance Fe.

  6. Oxidation, carburization and/or sulfidation resistant iron aluminide alloy

    DOEpatents

    Sikka, Vinod K.; Deevi, Seetharama C.; Fleischhauer, Grier S.; Hajaligol, Mohammad R.; Lilly, Jr., A. Clifton

    2003-08-19

    The invention relates generally to aluminum containing iron-base alloys useful as electrical resistance heating elements. The aluminum containing iron-base alloys have improved room temperature ductility, electrical resistivity, cyclic fatigue resistance, high temperature oxidation resistance, low and high temperature strength, and/or resistance to high temperature sagging. The alloy has an entirely ferritic microstructure which is free of austenite and includes, in weight %, over 4% Al, .ltoreq.1% Cr and either .gtoreq.0.05% Zr or Zro.sub.2 stringers extending perpendicular to an exposed surface of the heating element or .gtoreq.0.1% oxide dispersoid particles. The alloy can contain 14-32% Al, .ltoreq.2% Ti, .ltoreq.2% Mo, .ltoreq.1% Zr, .ltoreq.1% C, .ltoreq.0.1% B. .ltoreq.30% oxide dispersoid and/or electrically insulating or electrically conductive covalent ceramic particles, .ltoreq.1% rare earth metal, .ltoreq.1% oxygen, .ltoreq.3% Cu, balance Fe.

  7. Iron aluminide useful as electrical resistance heating elements

    DOEpatents

    Sikka, Vinod K.; Deevi, Seetharama C.; Fleischhauer, Grier S.; Hajaligol, Mohammad R.; Lilly, Jr., A. Clifton

    1999-01-01

    The invention relates generally to aluminum containing iron-base alloys useful as electrical resistance heating elements. The aluminum containing iron-base alloys have improved room temperature ductility, electrical resistivity, cyclic fatigue resistance, high temperature oxidation resistance, low and high temperature strength, and/or resistance to high temperature sagging. The alloy has an entirely ferritic microstructure which is free of austenite and includes, in weight %, over 4% Al, .ltoreq.1% Cr and either .gtoreq.0.05% Zr or ZrO.sub.2 stringers extending perpendicular to an exposed surface of the heating element or .gtoreq.0.1% oxide dispersoid particles. The alloy can contain 14-32% Al, .ltoreq.2% Ti, .ltoreq.2% Mo, .ltoreq.1% Zr, .ltoreq.1% C, .ltoreq.0.1% B, .ltoreq.30% oxide dispersoid and/or electrically insulating or electrically conductive covalent ceramic particles, .ltoreq.1% rare earth metal, .ltoreq.1% oxygen, .ltoreq.3% Cu, balance Fe.

  8. Iron aluminide useful as electrical resistance heating elements

    DOEpatents

    Sikka, Vinod K.; Deevi, Seetharama C.; Fleischhauer, Grier S.; Hajaligol, Mohammad R.; Lilly, Jr., A. Clifton

    2001-01-01

    The invention relates generally to aluminum containing iron-base alloys useful as electrical resistance heating elements. The aluminum containing iron-base alloys have improved room temperature ductility, electrical resistivity, cyclic fatigue resistance, high temperature oxidation resistance, low and high temperature strength, and/or resistance to high temperature sagging. The alloy has an entirely ferritic microstructure which is free of austenite and includes, in weight %, over 4% Al, .ltoreq.1% Cr and either .gtoreq.0.05% Zr or ZrO.sub.2 stringers extending perpendicular to an exposed surface of the heating element or .gtoreq.0.1% oxide dispersoid particles. The alloy can contain 14-32% Al, .ltoreq.2% Ti, .ltoreq.2% Mo, .ltoreq.1% Zr, .ltoreq.1% C, .ltoreq.0.1% B, .ltoreq.30% oxide dispersoid and/or electrically insulating or electrically conductive covalent ceramic particles, .ltoreq.1% rare earth metal, .ltoreq.1% oxygen, .ltoreq.3% Cu, balance Fe.

  9. KSC-2010-5939

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Preparations are under way in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida to examine space shuttle Discovery's external fuel tank. Shown here, is one of two solid rocket boosters, which are still attached to the external tank and shuttle. Technicians will begin to remove thermal sensors that will give engineers data about the changes the tank went through during the loading and draining of super-cold propellants during a tanking test on Dec. 17. Engineers also will examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank region. Also on the agenda, is to re-apply foam to the outside of the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis

  10. KSC-2010-5945

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Preparations are under way in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida to examine space shuttle Discovery's external fuel tank. Shown here is the nose of the shuttle, which still is attached to the external tank and solid rocket boosters. Technicians will begin to remove thermal sensors that will give engineers data about the changes the tank went through during the loading and draining of super-cold propellants during a tanking test on Dec. 17. Engineers also will examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank region. Also on the agenda, is to re-apply foam to the outside of the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis

  11. KSC-2010-5843

    NASA Image and Video Library

    2010-12-09

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, technicians removed a few items from space shuttle Discovery's middeck payload, including food, prior to a tanking test planned for no earlier than Dec. 15. During the test, engineers will monitor what happens to the external fuel tank's newly replaced ground umbilical carrier plate (GUCP) and the intertank's stringers, which are 21-foot long, U-shaped aluminum brackets located on the intertank, during loading of cryogenic propellants. Technicians already installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Ben Smegelsky

  12. KSC-2010-5842

    NASA Image and Video Library

    2010-12-09

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, technicians remove a few items from space shuttle Discovery's middeck payload, including food, prior to a tanking test planned for no earlier than Dec. 15. During the test, engineers will monitor what happens to the external fuel tank's newly replaced ground umbilical carrier plate (GUCP) and the intertank's stringers, which are 21-foot long, U-shaped aluminum brackets located on the intertank, during loading of cryogenic propellants. Technicians already installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Ben Smegelsky

  13. KSC-2010-5841

    NASA Image and Video Library

    2010-12-09

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, technicians remove a few items from space shuttle Discovery's middeck payload, including food, prior to a tanking test planned for no earlier than Dec. 15. During the test, engineers will monitor what happens to the external fuel tank's newly replaced ground umbilical carrier plate (GUCP) and the intertank's stringers, which are 21-foot long, U-shaped aluminum brackets located on the intertank, during loading of cryogenic propellants. Technicians already installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Ben Smegelsky

  14. KSC-2010-5840

    NASA Image and Video Library

    2010-12-09

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, technicians remove a few items from space shuttle Discovery's middeck payload, including food, prior to a tanking test planned for no earlier than Dec. 15. During the test, engineers will monitor what happens to the external fuel tank's newly replaced ground umbilical carrier plate (GUCP) and the intertank's stringers, which are 21-foot long, U-shaped aluminum brackets located on the intertank, during loading of cryogenic propellants. Technicians already installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Ben Smegelsky

  15. Automatic Fastening Large Structures: a New Approach

    NASA Technical Reports Server (NTRS)

    Lumley, D. F.

    1985-01-01

    The external tank (ET) intertank structure for the space shuttle, a 27.5 ft diameter 22.5 ft long externally stiffened mechanically fastened skin-stringer-frame structure, was a labor intensitive manual structure built on a modified Saturn tooling position. A new approach was developed based on half-section subassemblies. The heart of this manufacturing approach will be 33 ft high vertical automatic riveting system with a 28 ft rotary positioner coming on-line in mid 1985. The Automatic Riveting System incorporates many of the latest automatic riveting technologies. Key features include: vertical columns with two sets of independently operating CNC drill-riveting heads; capability of drill, insert and upset any one piece fastener up to 3/8 inch diameter including slugs without displacing the workpiece offset bucking ram with programmable rotation and deep retraction; vision system for automatic parts program re-synchronization and part edge margin control; and an automatic rivet selection/handling system.

  16. Repair techniques for celion/LARC-160 graphite/polyimide composite structures

    NASA Technical Reports Server (NTRS)

    Jones, J. S.; Graves, S. R.

    1984-01-01

    The large stiffness-to-weight and strength-to-weight ratios of graphite composite in combination with the 600 F structural capability of the polyimide matrix can reduce the total structure/TPS weight of reusable space vehicles by 20-30 percent. It is inevitable that with planned usage of GR/PI structural components, damage will occur either in the form of intrinsic flaw growth or mechanical damage. Research and development programs were initiated to develop repair processes and techniques specific to Celion/LARC-160 GR/PI structure with emphasis on highly loaded and lightly loaded compression critical structures for factory type repair. Repair processes include cocure and secondary bonding techniques applied under vacuum plus positive autoclave pressure. Viable repair designs and processes are discussed for flat laminates, honeycomb sandwich panels, and hat-stiffened skin-stringer panels. The repair methodology was verified through structural element compression tests at room temperature and 315 C (600 F).

  17. Partial melting of amphibolite to trondhjemite at Nunatak Fiord, St. Elias Mountains, Alaska

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Barker, F.; McLellan, E.L.; Plafker, G.

    1985-01-01

    At Nunatak Fiord, 55km NE of Yakutat, Alaska, a uniform layer of Cretaceous basalt ca. 3km thick was metamorphosed ca. 67 million years ago to amphibolite and locally partially melted to pegmatitic trondhjemite. Segregations of plagioclase-quartz+/-biotite rock, leucosomes in amphibolite matrix, range from stringers 5-10mm thick to blunt pods as thick as 6m. They tend to be parallel to foliation of the amphibolite, but crosscutting is common. The assemblage aluminous hornblende-plagioclase-epidote-sphene-quartz gave a hydrous melt that crystallized to plagioclase-quartz+/-biotite pegmatitic trondhjemite. 5-10% of the rock melted. Eu at 2x chondrites is positively anomalous. REE partitioning in melt/residum was controlled largelymore » by hornblende and sphene. Though the mineralogical variability precludes quantitative modeling, partial melting of garnet-free amphibolite to heavy-REE-depleted trondhjemitic melt is a viable process.« less

  18. Chemical-mechanical polishing of recessed microelectromechanical devices

    DOEpatents

    Barron, Carole C.; Hetherington, Dale L.; Montague, Stephen

    1999-01-01

    A method is disclosed for micromachining recessed layers (e.g. sacrificial layers) of a microelectromechanical system (MEMS) device formed in a cavity etched into a semiconductor substrate. The method uses chemical-mechanical polishing (CMP) with a resilient polishing pad to locally planarize one or more of the recessed layers within the substrate cavity. Such local planarization using the method of the present invention is advantageous for improving the patterning of subsequently deposited layers, for eliminating mechanical interferences between functional elements (e.g. linkages) of the MEMS device, and for eliminating the formation of stringers. After the local planarization of one or more of the recessed layers, another CMP step can be provided for globally planarizing the semiconductor substrate to form a recessed MEMS device which can be integrated with electronic circuitry (e.g. CMOS, BiCMOS or bipolar circuitry) formed on the surface of the substrate.

  19. Nurse practitioners: leadership behaviors and organizational climate.

    PubMed

    Jones, L C; Guberski, T D; Soeken, K L

    1990-01-01

    The purpose of this article is to examine the relationships of individual nurse practitioners' perceptions of the leadership climate in their organizations and self-reported formal and informal leadership behaviors. The nine climate dimensions (Structure, Responsibility, Reward, Perceived Support of Risk Taking, Warmth, Support, Standard Setting, Conflict, and Identity) identified by Litwin and Stringer in 1968 were used to predict five leadership dimensions (Meeting Organizational Needs, Managing Resources, Leadership Competence, Task Accomplishment, and Communications). Demographic variables of age, educational level, and percent of time spent performing administrative functions were forced as a first step in each multiple regression analysis and used to explain a significant amount of variance in all but one analysis. All leadership dimensions were predicted by at least one organizational climate dimension: (1) Meeting Organizational Needs by Risk and Reward; (2) Managing Resources by Risk and Structure; (3) Leadership Competence by Risk and Standards; (4) Task Accomplishment by Structure, Risk, and Standards; and (5) Communication by Rewards.

  20. Development of design data for graphite reinforced epoxy and polyimide composites

    NASA Technical Reports Server (NTRS)

    Scheck, W. G.

    1974-01-01

    Processing techniques and design data were characterized for a graphite/epoxy composite system that is useful from 75 K to 450 K, and a graphite/polyimide composite system that is useful from 75 K to 589 K. The Monsanto 710 polyimide resin was selected as the resin to be characterized and used with the graphite fiber reinforcement. Material was purchased using the prepreg specification for the design data generation for both the HT-S/710 and HM-S/710 graphite/polyimide composite system. Lamina and laminate properties were determined at 75 K, 297 K, and 589 K. The test results obtained on the skin-stringer components proved that graphite/polyimide composites can be reliably designed and analyzed much like graphite/epoxy composites. The design data generated in the program includes the standard static mechanical properties, biaxial strain data, creep, fatigue, aging, and thick laminate data.

  1. Compressive Behavior of Frame-Stiffened Composite Panels

    NASA Technical Reports Server (NTRS)

    Yovanof, Nicolette P.; Jegley, Dawn C.

    2011-01-01

    New technologies are being developed under NASA's Environmentally Responsible Aviation (ERA) Program aimed at reducing fuel burn and emissions in large commercial aircraft. A Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept is being developed which offers advantages over traditional metallic structure. In this concept a stitched carbon-epoxy material system is employed with the potential for reducing the weight and cost of transport aircraft structure by eliminating fasteners and producing a more damage tolerant design. In addition, by adding unidirectional carbon rods to the top of stiffeners and minimizing the interference between the sandwich frames and the rod-stiffened stringers, the panel becomes more structurally efficient. This document describes the results of experimentation on a PRSEUS panel in which the frames are loaded in unidirectional compression beyond the local buckling of the skin of a Hybrid Wing Body (HWB) aircraft. A comparison with analytical predictions and the relationship between these test results and the global aircraft design is presented.

  2. Chemical-mechanical polishing of recessed microelectromechanical devices

    DOEpatents

    Barron, C.C.; Hetherington, D.L.; Montague, S.

    1999-07-06

    A method is disclosed for micromachining recessed layers (e.g. sacrificial layers) of a microelectromechanical system (MEMS) device formed in a cavity etched into a semiconductor substrate. The method uses chemical-mechanical polishing (CMP) with a resilient polishing pad to locally planarize one or more of the recessed layers within the substrate cavity. Such local planarization using the method of the present invention is advantageous for improving the patterning of subsequently deposited layers, for eliminating mechanical interferences between functional elements (e.g. linkages) of the MEMS device, and for eliminating the formation of stringers. After the local planarization of one or more of the recessed layers, another CMP step can be provided for globally planarizing the semiconductor substrate to form a recessed MEMS device which can be integrated with electronic circuitry (e.g., CMOS, BiCMOS or bipolar circuitry) formed on the surface of the substrate. 23 figs.

  3. Design, fabrication, and test of lightweight shell structure, phase 2

    NASA Technical Reports Server (NTRS)

    1974-01-01

    A cylindrical shell skirt structure 4.57 m (180 in.) in diameter and 3.66 m (144 in.) high was subjected to a design and analysis study using a wide variety of structural materials and concepts. The design loading of 1225.8 N/cm (700 lb/in.) axial compression and 245.2 N/cm (140 lb/in.) torsion is representative of that expected on a typical space tug skirt section. Structural concepts evaluated included honeycomb sandwich, truss, isogrid, and skin/stringer/frame. The materials considered included a wide variety of structural metals as well as glass, graphite, and boron-reinforced composites. The most unique characteristic of the candidate designs is that they involve the use of very thin-gage material. Fabrication and structural test of small panels and components representative of many of the candidate designs served to demonstrate proposed fabrication techniques and to verify design and analysis methods.

  4. A theoretical investigation of noise reduction through the cylindrical fuselage of a twin-engine, propeller-driven aircraft

    NASA Technical Reports Server (NTRS)

    Bhat, R. B.; Mixson, J. S.

    1978-01-01

    Interior noise in the fuselage of a twin-engine, propeller-driven aircraft with two propellers rotating in opposite directions is studied analytically. The fuselage was modeled as a stiffened cylindrical shell with simply supported ends, and the effects of stringers and frames were averaged over the shell surface. An approximate mathematical model of the propeller noise excitation was formulated which includes some of the propeller noise characteristics such as sweeping pressure waves around the sidewalls due to propeller rotation and the localized nature of the excitation with the highest levels near the propeller plane. Results are presented in the form of noise reduction, which is the difference between the levels of external and interior noise. The influence of propeller noise characteristics on the noise reduction was studied. The results indicate that the sweep velocity of the excitation around the fuselage sidewalls is critical to noise reduction.

  5. Program for establishing long-time flight service performance of composite materials in the center wing structure of C-130 aircraft. Phase 4: Ground/flight acceptance tests

    NASA Technical Reports Server (NTRS)

    Harvill, W. E.; Kizer, J. A.

    1976-01-01

    The advantageous structural uses of advanced filamentary composites are demonstrated by design, fabrication, and test of three boron-epoxy reinforced C-130 center wing boxes. The advanced development work necessary to support detailed design of a composite reinforced C-130 center wing box was conducted. Activities included the development of a basis for structural design, selection and verification of materials and processes, manufacturing and tooling development, and fabrication and test of full-scale portions of the center wing box. Detailed design drawings, and necessary analytical structural substantiation including static strength, fatigue endurance, flutter, and weight analyses are considered. Some additional component testing was conducted to verify the design for panel buckling, and to evaluate specific local design areas. Development of the cool tool restraint concept was completed, and bonding capabilities were evaluated using full-length skin panel and stringer specimens.

  6. On the interaction of jet noise with a nearby flexible structure

    NASA Technical Reports Server (NTRS)

    Mcgreevy, J. L.; Bayliss, A.; Maestrello, L.

    1994-01-01

    The model of the interaction of the noise from a spreading subsonic jet with a panel-stringer assembly is studied numerically in two dimensions. The radiation resulting from this flow/acoustic/structure coupling is computed and analyzed in both the time and frequency domains. The jet is initially excited by a pulse-like source inserted into the flow field. The pulse triggers instabilities associated with the inviscid instability of the jet mean flow shear layer. These instabilities in turn generate sound which provides the primary loading for the panels. The resulting structural vibration and radiation depends strongly on their placement relative to the jet/nozzle configuration. Results are obtained for the panel responses as well as the transmitted and incident pressure. The effect of the panels is to act as a narrow filter, converting the relatively broad band forcing, heavily influenced by jet instabilities, into radiation concentrated in narrow spectral bands.

  7. Comparison of Modal Analysis Methods Applied to a Vibro-Acoustic Test Article

    NASA Technical Reports Server (NTRS)

    Pritchard, Jocelyn; Pappa, Richard; Buehrle, Ralph; Grosveld, Ferdinand

    2001-01-01

    Modal testing of a vibro-acoustic test article referred to as the Aluminum Testbed Cylinder (ATC) has provided frequency response data for the development of validated numerical models of complex structures for interior noise prediction and control. The ATC is an all aluminum, ring and stringer stiffened cylinder, 12 feet in length and 4 feet in diameter. The cylinder was designed to represent typical aircraft construction. Modal tests were conducted for several different configurations of the cylinder assembly under ambient and pressurized conditions. The purpose of this paper is to present results from dynamic testing of different ATC configurations using two modal analysis software methods: Eigensystem Realization Algorithm (ERA) and MTS IDEAS Polyreference method. The paper compares results from the two analysis methods as well as the results from various test configurations. The effects of pressurization on the modal characteristics are discussed.

  8. KSC-2010-5838

    NASA Image and Video Library

    2010-12-09

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, technicians remove a few items from space shuttle Discovery's middeck payload, including food, prior to a tanking test planned for no earlier than Dec. 15. During the test, engineers will monitor what happens to the external fuel tank's newly replaced ground umbilical carrier plate (GUCP) and the intertank's stringers, which are 21-foot long, U-shaped aluminum brackets located on the intertank, during loading of cryogenic propellants. Technicians already installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Ben Smegelsky

  9. KSC-2010-5839

    NASA Image and Video Library

    2010-12-09

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, technicians remove a few items from space shuttle Discovery's middeck payload, including food, prior to a tanking test planned for no earlier than Dec. 15. During the test, engineers will monitor what happens to the external fuel tank's newly replaced ground umbilical carrier plate (GUCP) and the intertank's stringers, which are 21-foot long, U-shaped aluminum brackets located on the intertank, during loading of cryogenic propellants. Technicians already installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Ben Smegelsky

  10. KSC-2010-5836

    NASA Image and Video Library

    2010-12-09

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, technicians remove a few items from space shuttle Discovery's middeck payload, including food, prior to a tanking test planned for no earlier than Dec. 15. During the test, engineers will monitor what happens to the external fuel tank's newly replaced ground umbilical carrier plate (GUCP) and the intertank's stringers, which are 21-foot long, U-shaped aluminum brackets located on the intertank, during loading of cryogenic propellants. Technicians already installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Ben Smegelsky

  11. KSC-2010-5837

    NASA Image and Video Library

    2010-12-09

    CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, technicians remove a few items from space shuttle Discovery's middeck payload, including food, prior to a tanking test planned for no earlier than Dec. 15. During the test, engineers will monitor what happens to the external fuel tank's newly replaced ground umbilical carrier plate (GUCP) and the intertank's stringers, which are 21-foot long, U-shaped aluminum brackets located on the intertank, during loading of cryogenic propellants. Technicians already installed environmental enclosures on the tank, removed foam and prepared the tank's skin for approximately 89 strain gauges and thermocouples. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Ben Smegelsky

  12. Residual strength and crack propagation tests on C-130 airplane center wings with service-imposed fatigue damage

    NASA Technical Reports Server (NTRS)

    Snider, H. L.; Reeder, F. L.; Dirkin, W. J.

    1972-01-01

    Fourteen C-130 airplane center wings, each containing service-imposed fatigue damage resulting from 4000 to 13,000 accumulated flight hours, were tested to determine their fatigue crack propagation and static residual strength characteristics. Eight wings were subjected to a two-step constant amplitude fatigue test prior to static testing. Cracks up to 30 inches long were generated in these tests. Residual static strengths of these wings ranged from 56 to 87 percent of limit load. The remaining six wings containing cracks up to 4 inches long were statically tested as received from field service. Residual static strengths of these wings ranged from 98 to 117 percent of limit load. Damage-tolerant structural design features such as fastener holes, stringers, doublers around door cutouts, and spanwise panel splices proved to be effective in retarding crack propagation.

  13. Application of Ultrasonic Phased Array Technology to the Detection of Defect in Composite Stiffened-structures

    NASA Astrophysics Data System (ADS)

    Zhou, Yuan-Qi; Zhan, Li-Hua

    2016-05-01

    Composite stiffened-structure consists of the skin and stringer has been widely used in aircraft fuselage and wings. The main purpose of the article is to detect the composite material reinforced structure accurately and explore the relationship between defect formation and structural elements or curing process. Based on ultrasonic phased array inspection technology, the regularity of defects in the manufacture of composite materials are obtained, the correlation model between actual defects and nondestructive testing are established. The article find that the forming quality of deltoid area in T-stiffened structure is obviously improved by pre-curing, the defects of hat-stiffened structure are affected by the mandrel. The results show that the ultrasonic phased array inspection technology can be an effectively way for the detection of composite stiffened-structures, which become an important means to control the defects of composite and improve the quality of the product.

  14. KSC-2010-5883

    NASA Image and Video Library

    2010-12-17

    CAPE CANAVERAL, Fla. -- Team members stationed at consoles in the Launch Control Center at NASA's Kennedy Space Center in Florida monitor space shuttle Discovery's external fuel tank as it is loaded with more than 535,000 gallons of cryogenic propellants. During today's tanking test, the team is paying particular attention to the external tank's ribbed intertank region. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  15. Emergency in-flight egress opening for general aviation aircraft

    NASA Technical Reports Server (NTRS)

    Bement, L. J.

    1980-01-01

    In support of a stall/spin research program, an emergency in-flight egress system is being installed in a light general aviation airplane. To avoid a major structural redesign for a mechanical door, an add-on 11.2 kg pyrotechnic-actuated system was developed to create an opening in the existing structure. The airplane skin will be explosively severed around the side window, across a central stringer, and down to the floor, creating an opening of approximately 76 by 76 cm. The severed panel will be jettisoned at an initial velocity of approximately 13.7 m/sec. System development included a total of 68 explosive severance tests on aluminum material using small samples, small and full scale flat panel aircraft structural mock-ups, and an actual aircraft fuselage. These tests proved explosive sizing/severance margins, explosive initiation, explosive product containment, and system dynamics.

  16. Paleoproterozoic Keulik-Kenirim Ore-Bearing Gabbro-Peridotite Complex, Kola Region: A New Occurrence of Ferropicritic Magmatism

    NASA Astrophysics Data System (ADS)

    Smolkin, V. F.; Lokhov, K. I.; Skublov, S. G.; Sergeeva, L. Yu.; Lokhov, D. K.; Sergeev, S. A.

    2018-03-01

    Comprehensive research of ore-bearing differentiated intrusions of the Keulik-Kenirim structural unit, which represents a fragment of the Paleoproterozoic Pechenga-Varzuga Belt, has been carried out for the first time. The intrusions are subvolcanic by type and lenticular in shape, nearly conformable and steeply dipping. They are made up of peridotite, olivine and plagioclase pyroxenites, and gabbro metamorphosed under amphibolite facies conditions along with host basic volcanics. All intrusive rocks are enriched in TiO2 and FeO. Sulfide Cu-Ni mineralization is represented by disseminated, pocket, and stringer-disseminated types, which are clustered in the peridotitic zone as hanging units and bottom lodes. The Ni content in disseminated ore is estimated at 0.45-0.55 wt % and 1.15-3.32 wt % in ore pockets; the Cu grades are 0.17-0.20 and 0.46-5.65 wt %, respectively. To determine the age of intrusions and metamorphism of intrusive and volcanic rocks, various isotopic systems have been used: Sm-Nd (TIMS) in rock and U-Pb (SIMS SHRIMP) and Lu-Hf (LA-ICP-MS) in zircon. Conclusions on the origin of zircons are based on concentrations of trace elements including REE therein and Hf-Nd correlation in zircons and rocks. The U-Pb system of zircons reflects episodes of igneous rock formation (1982 ± 12 Ma) and their postmagmatic transformation (1938 ± 20 Ma). The last disturbance of the U-Pb isotopic system occurred 700 and 425 Ma. Xenogenic zircons dated from 3.17 to 2.65 Ga have been revealed in the studied samples. These zircons were captured by magma from the Archean basement during its ascent. The intrusions were emplaced synchronously with economic ore formation in the Pechenga ore field (1985 ± 10 Ma). The peak metamorphism of intrusive rocks under amphibolite facies conditions is recorded at 40 Ma later. The differentiated intrusions of the Keulik-Kenirim structural unit are close in their internal structure, mineralogy, and geochemistry, as well as in age and features of related Cu-Ni mineralization to ore-bearing intrusions of the Pechenga ore field, which are derivatives of ferropicritic (ferriferous) magmatism.

  17. Composite Design and Manufacturing Development for Human Spacecrafts

    NASA Technical Reports Server (NTRS)

    Litteken, Douglas; Lowry, David

    2013-01-01

    The Structural Engineering Division at the NASA Johnson Space Center (JSC) has begun work on lightweight, multi-functional pressurized composite structures. The first candidate vehicle for technology development is the Multi-Mission Space Exploration Vehicle (MMSEV) cabin, known as the Gen 2B cabin, which has been built at JSC by the Robotics Division. Of the habitable MMSEV vehicle prototypes designed to date, this is the first one specifically analyzed and tested to hold internal pressure and the only one made out of composite materials. This design uses a laminate base with zoned reinforcement and external stringers, intended to demonstrate certain capabilities, and to prepare for the next cabin design, which will be a composite sandwich panel construction with multi-functional capabilities. As part of this advanced development process, a number of new technologies were used to assist in the design and manufacturing process. One of the methods, new to JSC, was to build the Gen 2B cabin with Out of Autoclave technology to permit the creation of larger parts with fewer joints. An 8-ply pre-preg layup was constructed to form the cabin body. Prior to lay-up, a design optimization software called FiberSIM was used to create each ply pattern. This software is integrated with Pro/Engineer to allow for customized draping of each fabric ply over the complex tool surface. Slits and darts are made in the software model to create an optimal design that maintains proper fiber placement and orientation. The flat pattern of each ply is then exported and sent to an automated cutting table where the patterns are cut out of graphite material. Additionally, to assist in lay-up, a laser projection system (LPT) is used to project outlines of each ply directly onto the tool face for accurate fiber placement and ply build-up. Finally, as part of the OoA process, a large oven was procured to post-cure each part. After manufacturing complete, the cabin underwent modal and pressure testing (currently in progress at date of writing) and will go on to be outfitted and used for further ops usage.

  18. Tiny Molybdenites Tell Diffusion Tales

    NASA Astrophysics Data System (ADS)

    Stein, H. J.; Hannah, J. L.

    2014-12-01

    Diffusion invokes micron-scale exchange during crystal growth and dissolution in magma chambers on short time-scales. Fundamental to interpreting such data are assumptions on magma-fluid dynamics at all scales. Nevertheless, elemental diffusion profiles are used to estimate time scales for magma storage, eruption, and recharge. An underutilized timepiece to evaluate diffusion and 3D mobility of magmatic fluids is high-precision Re-Os dating of molybdenite. With spatially unique molybdenite samples from a young ore system (e.g., 1 Ma) and a double Os spike, analytical errors of 1-3 ka unambiguously separate events in time. Re-Os ages show that hydrous shallow magma chambers locally recharge and expel Cu-Mo-Au-silica as superimposed stockwork vein networks at time scales less than a few thousand years [1]. Re-Os ages provide diffusion rates controlled by a dynamic crystal mush, accumulation and expulsion of metalliferous fluid, and magma reorganization after explosive crystallization events. Importantly, this approach has broad application far from ore deposits. Here, we use Re-Os dating of molybdenite to assess time scales for generating and diffusing metals through the deep crust. To maximize opportunity for chemical diffusion, we use a continental-scale Sveconorwegian mylonite zone for the study area. A geologically constrained suite of molybdenite samples was acquired from quarry exposures. Molybdenite, previously unreported, is extremely scarce. Tiny but telling molybdenites include samples from like occurrences to assure geologic accuracy in Re-Os ages. Ages range from mid-Mesoproterozoic to mid-Neoproterozoic, and correspond to early metamorphic dehydration of a regionally widespread biotite-rich gneiss, localized melting of gneiss to form cm-m-scale K-feldspar ± quartz pods, development of vapor-rich, vuggy mm stringers that serve as volatile collection surfaces in felsic leucosomes, and low-angle (relative to foliation) cross-cutting cm-scale quartz veins. Re-Os ages and detailed geologic observation document a 200 m.y. history of metal liberation and diffusion through oxidation. [1] Stein, H.J. (2014) Dating and Tracing the History of Ore Formation, in Holland, H.D. & Turekian, K.K. (eds) Treatise on Geochemistry, 2nd Ed. 13: 87-118, Oxford: Elsevier.

  19. Geology, Ground-Water Occurrence, and Estimated Well Yields from the Mariana Limestone, Kagman Area, Saipan, Commonwealth of the Northern Mariana Islands

    USGS Publications Warehouse

    Hoffmann, John P.; Carruth, Rob; Meyer, William

    1998-01-01

    A study of the geology, ground-water occurrence, and estimated well yields from the Mariana Limestone was done to investigate ground-water availability in the Kagman area, Saipan. The Mariana and Tagpochau Limestone formations form the major aquifer in the Kagman drainage basin. The Mariana Limestone, which is the major water-bearing unit in the Kagman area, ranges in thickness from 300 to 500 feet and contains intermittent, thin clay stringers. The calcareous rocks of the Tagpochau Limestone range in thickness from 500 to 1,000 feet and are more sandy than those of the Mariana Limestone. Ground water is unconfined in the Mariana Limestone and ranges from unconfined to confined in the Tagpochau Limestone. The fresh ground-water lens (that part of the lens with less than 2-percent of the chloride-ion concentration in seawater) in the Mariana Limestone is relatively thin, ranging from about 15 to 21 feet. Altitude of the water table ranges from about 1.5 to 2.5 feet above mean sea level. Freshwater in the Mariana Limestone is underlain by seawater and is separated by a transition zone about 8 to 25 feet thick. Hydraulic conductivity and transmissivity of the Mariana Limestone were calculated from data collected at six test wells. Using the Newman method, estimated hydraulic conductivity and transmissivity range from 290 to 2,500 feet per day and 7,600 to 62,000 feet squared per day, respectively. The higher values probably are indicative of average conditions in the Mariana Limestone. The estimated storage coefficient of the Mariana Limestone is about 0.1. The availability of water from the Mariana Limestone is restricted by the thinness of the freshwater lens. Results of the study indicate that fresh ground water can be obtained from the Mariana Limestone when wells are designed for minimum drawdown, effectively skimming freshwater from the top of the lens. Wells that are shallow, widely spaced, and pumped at low uniform rates can prevent saltwater intrusion. Calculated long-term yields of wells are about 30 gallons per minute or less for potable water.

  20. Construction of the bridge in the cavern in the Vrata tunnel (Croatia)

    NASA Astrophysics Data System (ADS)

    Garasic, Mladen; Sasa Kovacevic, Meho; Juric-Kacunic, Danijela

    2010-05-01

    In the Dinaric karst system in Croatia some 11500 speleological objects have been explored so far, more than 1000 of which were discovered during construction works. Such speleological objects without natural entrance on the terrain surface (which are called "caverns") have been discovered on the construction sites of the highways. Over the past twenty years they have been systematically investigated and treated. A special kind of remediation was conducted in the cavern's large hall of the "Vrata" tunnel on the Zagreb - Rijeka highway. Due to size, shape, cavern's position and hydrogeological parameters (fissured and karstified aquifers) within the karst system it was necessary to design and construct a 58 m bridge over the cavern. In addition, the cavern's vault had to be reinforced and stabilized, as the overburden was very thin. The beam-and -stringer grid with special anchors was used. The cavern's rehabilitation in the "Vrata" tunnel was a unique undertaking, and the bridge (without piers) is the cavern's longest bridge in the world. A speleological object of large dimensions was discovered in the "Vrata"tunnel's right tube on the Rijeka-Zagreb highway. Speleological, geotechnical, engineering geological and hydrogeological investigation works were carried out for the purpose of preservation the speleological object (cavern). On the basis of classification results of rock masses and conducted numerical analyses the support system for the cavern's vault stabilization was selected. The support system's elements include the beam-and-stringer grid constructed on the terrain's surface above the cavern, tendons and geotechnical anchors. To ensure stability of the speleological object, and to conduct the backward numerical analyses the measurement of vertical deformations from the terrain's surface along the rock's mass by means of sliding micrometers was undertaken. Backward numerical analyses combined with geotechnical measurements enable safer and more rational approach to design and construction of underground structures. They contribute to the knowledge on rock mass performance and to determination of its physical and mechanical parameters connecting them with rock classification results. The analyses are a great help in verification or modification of elements' features of primary support system. Tunnel and bridge in tunnel "Vrata" were opened for traffic in November 2008. Keywords: speleology, cave, Dinaric karst, Croatia, tunnel, karst phenomena, geotechnical engineering.

  1. KSC-2010-5934

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Work platforms inside the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida begin to surround space shuttle Discovery, its solid rocket boosters and external fuel tank at dawn. The shuttle rolled back from Launch Pad 39A so technicians can examine the external tank and re-apply foam where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  2. Integrated Thermal Insulation System for Spacecraft

    NASA Technical Reports Server (NTRS)

    Kolodziej, Paul (Inventor); Bull, Jeff (Inventor); Kowalski, Thomas (Inventor); Switzer, Matthew (Inventor)

    1998-01-01

    An integrated thermal protection system (TPS) for a spacecraft includes a grid that is bonded to skin of the spacecraft, e.g., to support the structural loads of the spacecraft. A plurality of thermally insulative, relatively large panels are positioned on the grid to cover the skin of the spacecraft to which the grid has been bonded. Each panel includes a rounded front edge and a front flange depending downwardly from the front edge. Also, each panel includes a rear edge formed with a rounded socket for receiving the rounded front edge of another panel therein, and a respective rear flange depends downwardly from each rear edge. Pins are formed on the front flanges, and pin receptacles are formed on the rear flanges, such that the pins of a panel mechanically interlock with the receptacles of the immediately forward panel. To reduce the transfer to the skin of heat which happens to leak through the panels to the grid, the grid includes stringers that are chair-shaped in cross-section.

  3. Unraveling the Effect of Thermomechanical Treatment on the Dissolution of Delta Ferrite in Austenitic Stainless Steels

    NASA Astrophysics Data System (ADS)

    Rezayat, Mohammad; Mirzadeh, Hamed; Namdar, Masih; Parsa, Mohammad Habibi

    2016-02-01

    Considering the detrimental effects of delta ferrite stringers in austenitic stainless steels and the industrial considerations regarding energy consumption, investigating, and optimizing the kinetics of delta ferrite removal is of vital importance. In the current study, a model alloy prone to the formation of austenite/delta ferrite dual phase microstructure was subjected to thermomechanical treatment using the wedge rolling test aiming to dissolve delta ferrite. The effect of introducing lattice defects and occurrence of dynamic recrystallization (DRX) were investigated. It was revealed that pipe diffusion is responsible for delta ferrite removal during thermomechanical process, whereas when the DRX is dominant, the kinetics of delta ferrite dissolution tends toward that of the static homogenization treatment for delta ferrite removal that is based on the lattice diffusion of Cr and Ni in austenite. It was concluded that the optimum condition for dissolution of delta ferrite can be defined by the highest rolling temperature and strain in which DRX is not pronounced.

  4. New technique of skin embedded wire double-sided laser beam welding

    NASA Astrophysics Data System (ADS)

    Han, Bing; Tao, Wang; Chen, Yanbin

    2017-06-01

    In the aircraft industry, double-sided laser beam welding is an approved method for producing skin-stringer T-joints on aircraft fuselage panels. As for the welding of new generation aluminum-lithium alloys, however, this technique is limited because of high hot cracking susceptibility and strengthening elements' uneven distributions within weld. In the present study, a new technique of skin embedded wire double-sided laser beam welding (LBW) has been developed to fabricate T-joints consisting of 2.0 mm thick 2060-T8/2099-T83 aluminum-lithium alloys using eutectic alloy AA4047 filler wire. Necessary dimension parameters of the novel groove were reasonably designed for achieving crack-free welds. Comparisons were made between the new technique welded T-joint and conventional T-joint mainly on microstructure, hot crack, elements distribution features and mechanical properties within weld. Excellent crack-free microstructure, uniform distribution of silicon and superior tensile properties within weld were found in the new skin embedded wire double-sided LBW T-joints.

  5. Stress-corrosion behavior of aluminum-lithium alloys in aqueous salt environments

    NASA Technical Reports Server (NTRS)

    Pizzo, P. P.; Galvin, R. P.; Nelson, H. G.

    1984-01-01

    The stress corrosion susceptibility of two powder metallurgy (P/M) alloys, Al-Li-Cu and Al-Li-Cu-Mg; two mechanically attrited (M/A) alloys, Al-Li-Cu and Al-Li-Mg; and two wrought, ingot alloys, X-2020 and AA7475, are compared. Time-dependent fracture in an aqueous sodium chloride environment under alternate immersion condition was found to vary significantly between alloys. The stress corrosion behavior of the two powder metallurgy processed alloys was studied in detail under conditions of crack initiation, static crack growth, and fatigue crack growth. A variety of stress corrosion tests were performed including smooth surface, time-to-failure tests; potentiostatic tests on smooth surfaces exposed to constant applied strain rates; and fracture mechanics-type tests under static and cyclic loads. Both alloys show surface pitting and subsequent intergranular corrosion. Pitting is more severe in the magnesium-bearing alloy and is associated with stringer particles strung along the extrusion direction as a result of P/M processing.

  6. The Repair and Return to Flight of Solid Rocket Booster Forward Skirt Serial Number 20022

    NASA Technical Reports Server (NTRS)

    Malone, T. W.; Jones, C. S.; Honeycutt, J. H., Sr.

    2008-01-01

    On April 5, 1991, a solid rocket booster (SRB) forward skirt serial number (S/N) 20022 sustained buckling damage during water impact after the launch of Space Transportation System Flight 37 (STS-37). As of that date, five forward skirts had been lost during water impact. Repair attempts began with the least damaged skirt available (S/N 20022). Sp ecial hydraulic tooling was used to remove buckled areas of the skirt. Afterwards, its aft clevis pinholes were found to be out of alignment with the redesigned solid rocket motor (RSRM) check gauge, but weld passes were used to correct this condition. Meanwhile, USA Analytics generated mechanical property data for buckled and subsequently debuckled material. Their analysis suggested that structural integrity might be improved by adding stringer reinforcements, stiffeners, to the aft bay section of the skirt. This improvement was recommended as a fleet modification to be implemented on a case-by-case basis.

  7. KSC-2010-5887

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  8. KSC-2010-5933

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery enters the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The 3.4-mile trek, called rollback, from Launch Pad 39A began at 10:48 p.m. yesterday and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  9. KSC-2010-5923

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery, secured to a crawler-transporter, begins its 3.4-mile trek, known as rollback, from Launch Pad 39A to the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Rollback began at 10:48 p.m. and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  10. KSC-2010-5932

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- The bright lights inside the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida invite space shuttle Discovery inside. The 3.4-mile trek, called rollback, from Launch Pad 39A began at 10:48 p.m. yesterday and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  11. KSC-2010-5927

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery, secured to a crawler-transporter, slowly moves away from Launch Pad 39A at NASA's Kennedy Space Center in Florida. The 3.4-mile trek, called rollback, to the Vehicle Assembly Building began at 10:48 p.m. and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  12. KSC-2010-5925

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery, secured to a crawler-transporter, slowly moves away from Launch Pad 39A at NASA's Kennedy Space Center in Florida. The 3.4-mile trek, called rollback, to the Vehicle Assembly Building began at 10:48 p.m. and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  13. KSC-2010-5924

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery, secured to a crawler-transporter, begins its 3.4-mile trek, known as rollback, from Launch Pad 39A to the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Rollback began at 10:48 p.m. and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  14. KSC-2010-5888

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  15. KSC-2010-5928

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery slowly moves down the crawlerway at NASA's Kennedy Space Center in Florida. The 3.4-mile trek, called rollback, from Launch Pad 39A to the Vehicle Assembly Building began at 10:48 p.m. yesterday and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  16. KSC-2010-5926

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery, secured to a crawler-transporter, slowly moves away from Launch Pad 39A at NASA's Kennedy Space Center in Florida. The 3.4-mile trek, called rollback, to the Vehicle Assembly Building began at 10:48 p.m. and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  17. KSC-2010-5929

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery slowly moves down the crawlerway at NASA's Kennedy Space Center in Florida. The 3.4-mile trek, called rollback, from Launch Pad 39A to the Vehicle Assembly Building began at 10:48 p.m. yesterday and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  18. KSC-2011-1516

    NASA Image and Video Library

    2011-02-20

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery's STS-133 crew arrived on the Shuttle Landing Facility runway at NASA's Kennedy Space Center in Florida aboard four T-38 jets. In the days leading up to their launch to the International Space Station, the crew members will check the fit of their launch-and-entry suits, review launch-day procedures, receive weather briefings and remain medically quarantined to prevent sickness. This will be the second launch attempt for Discovery's crew, following a scrub in November 2010 due to a hydrogen gas leak at the ground umbilical carrier plate (GUCP) as well as modifications to the external fuel tank's intertank support beams, called stringers. Scheduled to lift off Feb. 24 at 4:50 p.m. EST, Discovery and its crew will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, the dexterous humanoid astronaut helper, to the orbiting outpost. For more information on the STS-133 mission, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASAFrank Michaux

  19. Failure at Frame-Stringer Intersections in PRSEUS Panels

    NASA Technical Reports Server (NTRS)

    Jegley, Dawn C.

    2012-01-01

    NASA, the Air Force Research Laboratory and The Boeing Company have worked to develop new low-cost, light-weight composite structures for aircraft. A Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept has been developed which offers advantages over traditional metallic structures. In this concept a stitched carbon-epoxy material system has been developed with the potential for reducing the weight and cost of transport aircraft structure by eliminating fasteners, thereby reducing part count and labor. By adding unidirectional carbon rods to the top of stiffeners, the panel becomes more structurally efficient. This combination produces a more damage tolerant design. This study focuses on the intersection between the rod-stiffener and the foam-filled frame in a PRSEUS specimen. Compression loading is considered, which induces stress concentrations at the intersection point that can lead to failures. An experiment with accompanying analysis for a single-frame specimen is described, followed by a parametric study of simple reinforcements to reduce strains in the intersection region.

  20. KSC-2010-5930

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery approached the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The 3.4-mile trek, called rollback, from Launch Pad 39A began at 10:48 p.m. yesterday and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  1. KSC-2010-5922

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery, secured to a crawler-transporter, slowly moves away from Launch Pad 39A at NASA's Kennedy Space Center in Florida. The 3.4-mile trek, called rollback, to the Vehicle Assembly Building began at 10:48 p.m. and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  2. KSC-2010-5931

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery begins to enter the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The 3.4-mile trek, called rollback, from Launch Pad 39A began at 10:48 p.m. yesterday and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  3. KSC-2010-5935

    NASA Image and Video Library

    2010-12-22

    CAPE CANAVERAL, Fla. -- Work platforms inside the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida begin to surround space shuttle Discovery, its solid rocket boosters and external fuel tank. The shuttle rolled back from Launch Pad 39A so technicians can examine the external tank and re-apply foam where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  4. KSC-2010-5886

    NASA Image and Video Library

    2010-12-17

    CAPE CANAVERAL, Fla. -- Shuttle Launch Director Mike Leinbach monitors space shuttle Discovery's external fuel tank as it is loaded with more than 535,000 gallons of cryogenic propellants from his console in the Launch Control Center at NASA's Kennedy Space Center in Florida. During today's tanking test, the team is paying particular attention to the external tank's ribbed intertank region. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  5. KSC-2010-5921

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery, secured to a crawler-transporter, slowly moves away from Launch Pad 39A at NASA's Kennedy Space Center in Florida. The 3.4-mile trek, called rollback, to the Vehicle Assembly Building began at 10:48 p.m. and took about eight hours. Next, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  6. Large Area Nondestructive Evaluation of a Fatigue Loaded Composite Structure

    NASA Technical Reports Server (NTRS)

    Zalameda, Joseph N.; Burke, Eric R.; Horne, Michael R.; Madaras, Eric I.

    2016-01-01

    Large area nondestructive evaluation (NDE) inspections are required for fatigue testing of composite structures to track damage initiation and growth. Of particular interest is the progression of damage leading to ultimate failure to validate damage progression models. In this work, passive thermography and acoustic emission NDE were used to track damage growth up to failure of a composite three-stringer panel. Fourteen acoustic emission sensors were placed on the composite panel. The signals from the array were acquired simultaneously and allowed for acoustic emission location. In addition, real time thermal data of the composite structure were acquired during loading. Details are presented on the mapping of the acoustic emission locations directly onto the thermal imagery to confirm areas of damage growth leading to ultimate failure. This required synchronizing the acoustic emission and thermal data with the applied loading. In addition, processing of the thermal imagery which included contrast enhancement, removal of optical barrel distortion and correction of angular rotation before mapping the acoustic event locations are discussed.

  7. Emergency in-flight egress opening for general aviation aircraft. [pilot bailout

    NASA Technical Reports Server (NTRS)

    Bement, L. J.

    1980-01-01

    An emergency in-flight egress system was installed in a light general aviation airplane. The airplane had no provision for egress on the left side. To avoid a major structural redesign for a mechanical door, an add on 11.2 kg (24.6 lb) pyrotechnic-actuated system was developed to create an opening in the existing structure. The skin of the airplane was explosively severed around the side window, across a central stringer, and down to the floor, creating an opening of approximately 76 by 76 cm. The severed panel was jettisoned at an initial velocity of approximately 13.7 m/sec. System development included a total of 68 explosive severance tests on aluminum material using small samples, small and full scale flat panel aircraft structural mockups, and an actual aircraft fuselage. These tests proved explosive sizing/severance margins, explosive initiation, explosive product containment, and system dynamics. This technology is applicable to any aircraft of similar construction.

  8. KSC-2010-5867

    NASA Image and Video Library

    2010-12-17

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery's external fuel tank is being filled with more than 535,000 gallons of super-cold liquid hydrogen and liquid oxygen during a tanking test on Launch Pad 39A at NASA's Kennedy Space Center in Florida. Engineers are closely monitoring what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the tank's intertank region, as well as the newly replaced ground umbilical carrier plate (GUCP). Data from 89 sensors will be evaluated after the tank returns to ambient temperature. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  9. KSC-2010-5866

    NASA Image and Video Library

    2010-12-17

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery's external fuel tank is being filled with more than 535,000 gallons of super-cold liquid hydrogen and liquid oxygen during a tanking test on Launch Pad 39A at NASA's Kennedy Space Center in Florida. Engineers are closely monitoring what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the tank's intertank region, as well as the newly replaced ground umbilical carrier plate (GUCP). Data from 89 sensors will be evaluated after the tank returns to ambient temperature. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  10. KSC-2010-5865

    NASA Image and Video Library

    2010-12-17

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery's external fuel tank is being filled with more than 535,000 gallons of super-cold liquid hydrogen and liquid oxygen during a tanking test on Launch Pad 39A at NASA's Kennedy Space Center in Florida. Engineers are closely monitoring what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the tank's intertank region, as well as the newly replaced ground umbilical carrier plate (GUCP). Data from 89 sensors will be evaluated after the tank returns to ambient temperature. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  11. KSC-2011-1517

    NASA Image and Video Library

    2011-02-18

    CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, NASA Public Affairs Officer Michael Curie, left, Associate Administrator for Space Operations Bill Gerstenmaier, Space Shuttle Program Launch Integration Manager Mike Moses and Shuttle Launch Director Mike Leinbach talk to media following a Flight Readiness Review that gave a unanimous "go" to launch space shuttle Discovery on the STS-133 mission to the International Space Station. This will be the second launch attempt for Discovery, following a scrub in November 2010 due to a hydrogen gas leak at the ground umbilical carrier plate (GUCP) as well as modifications to the external fuel tank's intertank support beams, called stringers. Scheduled to lift off Feb. 24 at 4:50 p.m. EST, Discovery and its six-member crew will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, the dexterous humanoid astronaut helper, to the orbiting outpost. For more information on the STS-133 mission, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  12. Stress-corrosion behavior of aluminum-lithium alloys in aqueous environments

    NASA Technical Reports Server (NTRS)

    Pizzo, P. P.; Galvin, R. P.; Nelson, H. G.

    1983-01-01

    The stress corrosion susceptibility of two powder metallurgy (P/M) alloys, Al-Li-Cu and Al-Li-Cu-Mg two mechanically attrited (M/A) alloys, Al-Li-Cu and Al-Li-Mg; and two wrought, ingot alloys, X-2020 and AA7475, are compared. Time-dependent fracture in an aqueous sodium chloride environment under alternate immersion condition was found to vary significantly between alloys. The stress corrosion behavior of the two powder metallurgy processed alloys was studied in detail under conditions of crack initiation, static crack growth, and fatigue crack growth. A variety of stress corrosion tests were performed including smooth surface, time-to-failure tests; potentiostatic tests on smooth surfaces exposed to constant applied strain rates; and fracture mechanics-type tests under static and cyclic loads. Both alloys show surface pitting and subsequent intergranular corrosion. Pitting is more severe in the magnesium-bearing alloy and is associated with stringer particles strung along the extrusion direction as a result of P/M processing.

  13. Prediction of gas production using well logs, Cretaceous of north-central Montana

    USGS Publications Warehouse

    Hester, T.C.

    1999-01-01

    Cretaceous gas sands underlie much of east-central Alberta and southern Saskatchewan, eastern Montana, western North Dakota, and parts of South Dakota and Wyoming. Estimates of recoverable biogenic methane from these rocks in the United States are as high as 91 TCF. In northern Montana, current production is localized around a few major structural features, while vast areas in between these structures are not being exploited. Although the potential for production exists, the lack of commercial development is due to three major factors: 1) the lack of pipeline infrastructure; 2) the lack of predictable and reliable rates of production; and 3) the difficulty in recognizing and selecting potentially productive gas-charged intervals. Unconventional (tight), continuous-type reservoirs, such as those in the Cretaceous of the northern Great Plains, are not well suited for conventional methods of formation evaluation. Pay zones frequently consist only of thinly laminated intervals of sandstone, silt, shale stringers, and disseminated clay. Potential producing intervals are commonly unrecognizable on well logs, and thus are overlooked. To aid in the identification and selection of potential producing intervals, a calibration system is developed here that empirically links the 'gas effect' to gas production. The calibration system combines the effects of porosity, water saturation, and clay content into a single 'gas-production index' (GPI) that relates the in-situ rock with production potential. The fundamental method for isolating the gas effect for calibration is a crossplot of neutron porosity minus density porosity vs gamma-ray intensity. Well-log and gas-production data used for this study consist of 242 perforated intervals from 53 gas-producing wells. Interval depths range from about 250 to 2400 ft. Gas volumes in the peak calendar year of production range from about 4 to 136 MMCF. Nine producing formations are represented. Producing-interval data show that porosity and gas production are closely linked to clay volume. Highest porosities and maximum gas production occur together at an intermediate clay content of about 12% (60 API). As clay volume exceeds 35% (130 API), minimum porosity required for production increases rapidly, and the number of potential producing intervals declines. Gas production from intervals where clay volume exceeds 50% is rare. Effective porosities of less than about 8% are probably inadequate for commercial gas production in these rocks regardless of clay content.

  14. Propeller aircraft interior noise model: User's manual for computer program

    NASA Technical Reports Server (NTRS)

    Wilby, E. G.; Pope, L. D.

    1985-01-01

    A computer program entitled PAIN (Propeller Aircraft Interior Noise) has been developed to permit calculation of the sound levels in the cabin of a propeller-driven airplane. The fuselage is modeled as a cylinder with a structurally integral floor, the cabin sidewall and floor being stiffened by ring frames, stringers and floor beams of arbitrary configurations. The cabin interior is covered with acoustic treatment and trim. The propeller noise consists of a series of tones at harmonics of the blade passage frequency. Input data required by the program include the mechanical and acoustical properties of the fuselage structure and sidewall trim. Also, the precise propeller noise signature must be defined on a grid that lies in the fuselage skin. The propeller data are generated with a propeller noise prediction program such as the NASA Langley ANOPP program. The program PAIN permits the calculation of the space-average interior sound levels for the first ten harmonics of a propeller rotating alongside the fuselage. User instructions for PAIN are given in the report. Development of the analytical model is presented in NASA CR 3813.

  15. Crashworthiness of light aircraft fuselage structures: A numerical and experimental investigation

    NASA Technical Reports Server (NTRS)

    Nanyaro, A. P.; Tennyson, R. C.; Hansen, J. S.

    1984-01-01

    The dynamic behavior of aircraft fuselage structures subject to various impact conditions was investigated. An analytical model was developed based on a self-consistent finite element (CFE) formulation utilizing shell, curved beam, and stringer type elements. Equations of motion were formulated and linearized (i.e., for small displacements), although material nonlinearity was retained to treat local plastic deformation. The equations were solved using the implicit Newmark-Beta method with a frontal solver routine. Stiffened aluminum fuselage models were also tested in free flight using the UTIAS pendulum crash test facility. Data were obtained on dynamic strains, g-loads, and transient deformations (using high speed photography in the latter case) during the impact process. Correlations between tests and predicted results are presented, together with computer graphics, based on the CFE model. These results include level and oblique angle impacts as well as the free-flight crash test. Comparisons with a hybrid, lumped mass finite element computer model demonstrate that the CFE formulation provides the test overall agreement with impact test data for comparable computing costs.

  16. The Effect of Tool Profiles on Mechanical Properties of Friction Stir Welded Al5052 T-Joints.

    PubMed

    Kim, Byeong-Jin; Bang, Hee-Seon; Bang, Han-Sur

    2018-03-01

    Al5052 T butt joints with two skins (5 mm) and one stringer (3 mm) has been successfully welded by friction stir welding (FSW). Notably, this paper has been investigated the effect of tool shape on welded formation mechanism and mechanical properties. The used shapes of tool pin are two types which are cylinder (type 1) and frustum (type 2). Dimension on two types of tool pin shape is respectively pin length of 4.7 mm and pin diameter of frustum type of top (5 mm) and bottom (3 mm). The results of experiment show that inner defects in FSWed T-joints increase significantly in accordance with traverse speed. The maximum tensile strength of welded joint fabricated using type 1 is equivalent to 85% that of the base metal, which is approximately 10% higher than that of type 2. Because welded joint of type 1 has more smoothly plastic flow in comparison with type 2. Consequently, the results show that type 1 is better appropriate for friction stir welded Al5052 T butt joints than type 2.

  17. Sub-Alfvénic reduced magnetohydrodynamic equations for tokamaks

    NASA Astrophysics Data System (ADS)

    Sengupta, W.; Hassam, A. B.; Antonsen, T. M.

    2017-06-01

    A reduced set of magnetohydrodynamic (MHD) equations is derived, applicable to large aspect ratio tokamaks and relevant for dynamics that is sub-Alfvénic with respect to ideal ballooning modes. This ordering optimally allows sound waves, Mercier modes, drift modes, geodesic-acoustic modes (GAM), zonal flows and shear Alfvén waves. Wavelengths long compared to the gyroradius but comparable to the minor radius of a typical tokamak are considered. With the inclusion of resistivity, tearing modes, resistive ballooning modes, Pfirsch-Schluter cells and the Stringer spin-up are also included. A major advantage is that the resulting system is two-dimensional in space, and the system incorporates self-consistent and dynamic Shafranov shifts. A limitation is that the system is valid only in radial domains where the tokamak safety factor, , is close to rational. In the tokamak core, the system is well suited to study the sawtooth discharge in the presence of Mercier modes. The systematic ordering scheme and methodology developed are versatile enough to reduce the more general collisional two-fluid equations or possibly the Vlasov-Maxwell system in the MHD ordering.

  18. KSC-2010-5891

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- The moon shines brightly over space shuttle Discovery following a total lunar eclipse as the spacecraft waits to roll back from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. The move was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  19. KSC-2010-5917

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter, which is in front of the shuttle. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  20. KSC-2010-5913

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter, which is in front of the shuttle. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  1. KSC-2010-5905

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  2. KSC-2010-5890

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- The beginning of a total lunar eclipse hovers over the top of space shuttle Discovery as the spacecraft waits to roll back from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. The move was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  3. KSC-2010-5910

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter, which is in front of the shuttle. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  4. KSC-2010-5892

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- The moon shines brightly over space shuttle Discovery following a total lunar eclipse as the spacecraft waits to roll back from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. The move was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  5. KSC-2010-5894

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery shares the stage with the moon following a total lunar eclipse as the spacecraft waits to roll back from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. The move was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  6. KSC-2011-1501

    NASA Image and Video Library

    2011-02-20

    CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, space shuttle Discovery's STS-133 Commander Steve Lindsey arrives on the Shuttle Landing Facility runway aboard a T-38 jet. In the days leading up to their launch to the International Space Station, Lindsey and his crew members will check the fit of their launch-and-entry suits, review launch-day procedures, receive weather briefings and remain medically quarantined to prevent sickness. This will be the second launch attempt for Discovery's crew, following a scrub in November 2010 due to a hydrogen gas leak at the ground umbilical carrier plate (GUCP) as well as modifications to the external fuel tank's intertank support beams, called stringers. Scheduled to lift off Feb. 24 at 4:50 p.m. EST, Discovery and its crew will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, the dexterous humanoid astronaut helper, to the orbiting outpost. For more information on the STS-133 mission, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  7. KSC-2011-1506

    NASA Image and Video Library

    2011-02-20

    CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, space shuttle Discovery's STS-133 Pilot Eric Boe arrives on the Shuttle Landing Facility runway aboard a T-38 jet. In the days leading up to their launch to the International Space Station, Boe and his crew members will check the fit of their launch-and-entry suits, review launch-day procedures, receive weather briefings and remain medically quarantined to prevent sickness. This will be the second launch attempt for Discovery's crew, following a scrub in November 2010 due to a hydrogen gas leak at the ground umbilical carrier plate (GUCP) as well as modifications to the external fuel tank's intertank support beams, called stringers. Scheduled to lift off Feb. 24 at 4:50 p.m. EST, Discovery and its crew will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, the dexterous humanoid astronaut helper, to the orbiting outpost. For more information on the STS-133 mission, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  8. KSC-2011-1507

    NASA Image and Video Library

    2011-02-20

    CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, space shuttle Discovery's STS-133 Mission Specialist Michael Barratt arrives on the Shuttle Landing Facility runway aboard a T-38 jet. In the days leading up to their launch to the International Space Station, Barratt and his crew members will check the fit of their launch-and-entry suits, review launch-day procedures, receive weather briefings and remain medically quarantined to prevent sickness. This will be the second launch attempt for Discovery's crew, following a scrub in November 2010 due to a hydrogen gas leak at the ground umbilical carrier plate (GUCP) as well as modifications to the external fuel tank's intertank support beams, called stringers. Scheduled to lift off Feb. 24 at 4:50 p.m. EST, Discovery and its crew will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, the dexterous humanoid astronaut helper, to the orbiting outpost. For more information on the STS-133 mission, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  9. KSC-2011-1512

    NASA Image and Video Library

    2011-02-20

    CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, space shuttle Discovery's STS-133 Mission Specialist Nicole Stott arrives on the Shuttle Landing Facility runway aboard a T-38 jet. In the days leading up to their launch to the International Space Station, Stott and her crew members will check the fit of their launch-and-entry suits, review launch-day procedures, receive weather briefings and remain medically quarantined to prevent sickness. This will be the second launch attempt for Discovery's crew, following a scrub in November 2010 due to a hydrogen gas leak at the ground umbilical carrier plate (GUCP) as well as modifications to the external fuel tank's intertank support beams, called stringers. Scheduled to lift off Feb. 24 at 4:50 p.m. EST, Discovery and its crew will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, the dexterous humanoid astronaut helper, to the orbiting outpost. For more information on the STS-133 mission, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  10. KSC-2011-1510

    NASA Image and Video Library

    2011-02-20

    CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, space shuttle Discovery's STS-133 Mission Specialist Michael Barratt greets NASA Administrator Charlie Bolden, left, and Kennedy Center Director Bob Cabana on the Shuttle Landing Facility runway after arriving aboard a T-38 jet. In the days leading up to their launch to the International Space Station, Barratt and his crew members will check the fit of their launch-and-entry suits, review launch-day procedures, receive weather briefings and remain medically quarantined to prevent sickness. This will be the second launch attempt for Discovery's crew, following a scrub in November 2010 due to a hydrogen gas leak at the ground umbilical carrier plate (GUCP) as well as modifications to the external fuel tank's intertank support beams, called stringers. Scheduled to lift off Feb. 24 at 4:50 p.m. EST, Discovery and its crew will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, the dexterous humanoid astronaut helper, to the orbiting outpost. For more information on the STS-133 mission, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  11. KSC-2011-1505

    NASA Image and Video Library

    2011-02-20

    CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, space shuttle Discovery's STS-133 Commander Steve Lindsey talks with NASA Administrator Charlie Bolden and Kennedy Center Director Bob Cabana on the Shuttle Landing Facility runway after arriving aboard a T-38 jet. In the days leading up to their launch to the International Space Station, Lindsey and his crew members will check the fit of their launch-and-entry suits, review launch-day procedures, receive weather briefings and remain medically quarantined to prevent sickness. This will be the second launch attempt for Discovery's crew, following a scrub in November 2010 due to a hydrogen gas leak at the ground umbilical carrier plate (GUCP) as well as modifications to the external fuel tank's intertank support beams, called stringers. Scheduled to lift off Feb. 24 at 4:50 p.m. EST, Discovery and its crew will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, the dexterous humanoid astronaut helper, to the orbiting outpost. For more information on the STS-133 mission, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  12. KSC-2011-1509

    NASA Image and Video Library

    2011-02-20

    CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, space shuttle Discovery's STS-133 Pilot Eric Boe chats with NASA Administrator Charlie Bolden on the Shuttle Landing Facility runway after arriving aboard a T-38 jet. In the days leading up to their launch to the International Space Station, Boe and his crew members will check the fit of their launch-and-entry suits, review launch-day procedures, receive weather briefings and remain medically quarantined to prevent sickness. This will be the second launch attempt for Discovery's crew, following a scrub in November 2010 due to a hydrogen gas leak at the ground umbilical carrier plate (GUCP) as well as modifications to the external fuel tank's intertank support beams, called stringers. Scheduled to lift off Feb. 24 at 4:50 p.m. EST, Discovery and its crew will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, the dexterous humanoid astronaut helper, to the orbiting outpost. For more information on the STS-133 mission, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  13. KSC-2011-1508

    NASA Image and Video Library

    2011-02-20

    CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, space shuttle Discovery's STS-133 Pilot Eric Boe talks with Kennedy Center Director Bob Cabana on the Shuttle Landing Facility runway after arriving aboard a T-38 jet. In the days leading up to their launch to the International Space Station, Boe and his crew members will check the fit of their launch-and-entry suits, review launch-day procedures, receive weather briefings and remain medically quarantined to prevent sickness. This will be the second launch attempt for Discovery's crew, following a scrub in November 2010 due to a hydrogen gas leak at the ground umbilical carrier plate (GUCP) as well as modifications to the external fuel tank's intertank support beams, called stringers. Scheduled to lift off Feb. 24 at 4:50 p.m. EST, Discovery and its crew will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, the dexterous humanoid astronaut helper, to the orbiting outpost. For more information on the STS-133 mission, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  14. KSC-2011-1504

    NASA Image and Video Library

    2011-02-20

    CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, space shuttle Discovery's STS-133 Mission Specialist Alvin Drew greets Kennedy Center Director Bob Cabana on the Shuttle Landing Facility runway after arriving aboard a T-38 jet. In the days leading up to their launch to the International Space Station, Drew and his crew members will check the fit of their launch-and-entry suits, review launch-day procedures, receive weather briefings and remain medically quarantined to prevent sickness. This will be the second launch attempt for Discovery's crew, following a scrub in November 2010 due to a hydrogen gas leak at the ground umbilical carrier plate (GUCP) as well as modifications to the external fuel tank's intertank support beams, called stringers. Scheduled to lift off Feb. 24 at 4:50 p.m. EST, Discovery and its crew will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, the dexterous humanoid astronaut helper, to the orbiting outpost. For more information on the STS-133 mission, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  15. KSC-2011-1500

    NASA Image and Video Library

    2011-02-20

    CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, space shuttle Discovery's STS-133 Mission Specialist Alvin Drew arrives on the Shuttle Landing Facility runway aboard a T-38 jet. In the days leading up to their launch to the International Space Station, Drew and his crew members will check the fit of their launch-and-entry suits, review launch-day procedures, receive weather briefings and remain medically quarantined to prevent sickness. This will be the second launch attempt for Discovery's crew, following a scrub in November 2010 due to a hydrogen gas leak at the ground umbilical carrier plate (GUCP) as well as modifications to the external fuel tank's intertank support beams, called stringers. Scheduled to lift off Feb. 24 at 4:50 p.m. EST, Discovery and its crew will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, the dexterous humanoid astronaut helper, to the orbiting outpost. For more information on the STS-133 mission, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  16. Applications of laser ultrasound NDT methods on composite structures in aerospace industry

    NASA Astrophysics Data System (ADS)

    Kalms, Michael; Focke, Oliver; v. Kopylow, Christoph

    2008-09-01

    Composite materials are used more and more in aircraft production. Main composite types are Carbon Fiber Reinforced Plastics (CFRP), Glass Fiber Reinforced Plastics (GFRP) and metal-aluminium laminates (e. g. Glass Fiber Aluminium Reinforced GLARE©). Typical parts made of CFRP material are flaps, vertical and horizontal tail planes, center wing boxes, rear pressure bulkheads, ribs and stringers. These composite parts require adequate nondestructive testing (NDT) methods. Flaws to be detected are delaminations and debondings, porosity and foreign body inclusion. Manual ultrasonic testing with single element transducers is still the most applied method for composite parts with small and medium size. The extension of the conventional ultrasound technique for nondestructive testing with the laser ultrasound method brings new possibilities into the production processes for example the inspection of complex CFRP-components and the possibilities of online observation under remote control. In this paper we describe the principle of laser ultrasound with respect to the demands of nondestructive testing especially of small complex CFRP and C/PPS parts. We report applications of laser-based ultrasound options with generated types of guided and bulk waves on modern aircraft materials.

  17. Structural Efficiency and Behavior of Pristine and Notched Stitched Structure

    NASA Technical Reports Server (NTRS)

    Jegley, Dawn C.

    2011-01-01

    Two driving factors in aircraft panel design are structural efficiency and response to in-service damage. Stitching through the thickness can improve both of these considerations. Combining stitching with a post-buckling design approach can provide additional improvements. The buckling behavior of stitched structure is considered since lighter structures can be achieved if local skin buckling is allowed to occur at less than design ultimate load. Through-the-thickness stitching can suppress delamination between skin and flange, thereby allowing the structure to reliably carry load into the postbuckling range. Hat-stiffened and rod-stiffened panels in which the skin and flanges were stitched together through-the-thickness prior to curing are considered through experiment and analysis. In both types of panels no mechanical fasteners were used for the assembly. Specimens were loaded to failure in axial compression. In this study all specimens buckled in the skin between the stiffeners and continued to carry load. In addition, the behavior of panels with a severed stringer or notch are considered. Failure loads and strain distributions in the notched panel are compared to those in the unnotched panel.

  18. Flight demonstration of aircraft fuselage and bulkhead monitoring using optical fiber distributed sensing system

    NASA Astrophysics Data System (ADS)

    Wada, Daichi; Igawa, Hirotaka; Tamayama, Masato; Kasai, Tokio; Arizono, Hitoshi; Murayama, Hideaki; Shiotsubo, Katsuya

    2018-02-01

    We have developed an optical fiber distributed sensing system based on optical frequency domain reflectometry (OFDR) that uses long-length fiber Bragg gratings (FBGs). This technique obtains strain data not as a point data from an FBG but as a distributed profile within the FBG. This system can measure the strain distribution profile with an adjustable high spatial resolution of the mm or sub-mm order in real-time. In this study, we applied this OFDR-FBG technique to a flying test bed that is a mid-sized jet passenger aircraft. We conducted flight tests and monitored the structural responses of a fuselage stringer and the bulkhead of the flying test bed during flights. The strain distribution variations were successfully monitored for various events including taxiing, takeoff, landing and several other maneuvers. The monitoring was effective not only for measuring the strain amplitude applied to the individual structural parts but also for understanding the characteristics of the structural responses in accordance with the flight maneuvers. We studied the correlations between various maneuvers and strains to explore the relationship between the operation and condition of aircraft.

  19. KSC-2010-5882

    NASA Image and Video Library

    2010-12-17

    CAPE CANAVERAL, Fla. -- Team members stationed at consoles in the Launch Control Center at NASA's Kennedy Space Center in Florida monitor space shuttle Discovery's external fuel tank as it is loaded with more than 535,000 gallons of cryogenic propellants. From left, are NASA Commentator Allard Beutel, Discovery's NASA Vehicle Manager Jennifer Nufer and Lead NASA Test Director Charlie Blackwell-Thompson. During today's tanking test, the team is paying particular attention to the external tank's ribbed intertank region. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  20. KSC-2010-5885

    NASA Image and Video Library

    2010-12-17

    CAPE CANAVERAL, Fla. -- Team members stationed at consoles in the Launch Control Center at NASA's Kennedy Space Center in Florida monitor space shuttle Discovery's external fuel tank as it is loaded with more than 535,000 gallons of cryogenic propellants. From back, are STS-133 Assistant NASA Test Director Jeff Spaulding, STS-133 NASA Test Director Steve Payne and Launch Orbiter Test Conductor John Kracsun. During today's tanking test, the team is paying particular attention to the external tank's ribbed intertank region. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  1. KSC-2010-5878

    NASA Image and Video Library

    2010-12-17

    CAPE CANAVERAL, Fla. -- The Final Inspection Team, also known as the Ice Team, gathers before heading out to Launch Pad 39A at NASA's Kennedy Space Center in Florida to inspect space shuttle Discovery's external fuel tank during the loading of more than 535,000 gallons of cryogenic propellants. During today's tanking test, the team members will pay particular attention to the external tank's ribbed intertank region and report their findings to engineers located in the Launch Control Center. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  2. Composite hot drape forming

    NASA Technical Reports Server (NTRS)

    Ott, Thomas

    1994-01-01

    This program was initiated to replace labor-intensive ply-by-ply layup of composite I-beam posts and angle stiffeners used in the Space Station Freedom (SSF) rack structure. Hot drape forming (HDF) has been successfully implemented by BCAG for 777 composite I-stringers and by Bell Helicopter/Textron for the V-22 I-stingers. The two companies utilize two vastly different approaches to the I-beam fabrication process. A drape down process is used by Bell Helicopter where the compacted ply charge is placed on top of a forming mandrel and heated. When the heated ply charge reached a set temperature, vacuum pressure is applied and the plies are formed over the mandrel. The BCAG 777 process utilizes an inverted forming process where the ply stack is placed on a forming table and the mandrel is inverted and placed upon the ply stack. A heating and vacuum bladder underneath the ply stack form the play stack up onto the mandrels after reaching the temperature setpoint. Both methods have their advantages, but the drape down process was selected for SSF because it was more versatile and could be fabricated from readily available components.

  3. KSC-2010-5904

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  4. KSC-2010-5884

    NASA Image and Video Library

    2010-12-17

    CAPE CANAVERAL, Fla. -- Team members stationed at consoles in the Launch Control Center at NASA's Kennedy Space Center in Florida monitor space shuttle Discovery's external fuel tank as it is loaded with more than 535,000 gallons of cryogenic propellants. From back, are STS-133 Assistant NASA Test Director Jeff Spaulding, STS-133 NASA Test Director Steve Payne, Launch Orbiter Test Conductor John Kracsun and Assistant Launch Orbiter Test Conductor Mark Taffet. During today's tanking test, the team is paying particular attention to the external tank's ribbed intertank region. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  5. KSC-2010-5879

    NASA Image and Video Library

    2010-12-17

    CAPE CANAVERAL, Fla. -- The Final Inspection Team, also known as the Ice Team, gathers before heading out to Launch Pad 39A at NASA's Kennedy Space Center in Florida to inspect space shuttle Discovery's external fuel tank during the loading of more than 535,000 gallons of cryogenic propellants. During today's tanking test, the team members will pay particular attention to the external tank's ribbed intertank region and report their findings to engineers located in the Launch Control Center. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  6. KSC-2010-5907

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  7. KSC-2010-5916

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter, which is in front of the shuttle. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  8. KSC-2010-5914

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  9. KSC-2010-5912

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter, which is in front of the shuttle. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  10. KSC-2010-5903

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  11. KSC-2010-5889

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- The beginning of a total lunar eclipse illuminates the top of space shuttle Discovery as the spacecraft waits to roll back from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. The move was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  12. KSC-2010-5881

    NASA Image and Video Library

    2010-12-17

    CAPE CANAVERAL, Fla. -- Team members stationed at consoles in the Launch Control Center at NASA's Kennedy Space Center in Florida monitor space shuttle Discovery's external fuel tank as it is loaded with more than 535,000 gallons of cryogenic propellants. From left, are STS-133 Assistant NASA Test Director Jeff Spaulding, NASA Test Director Jeremy Graeber and STS-133 NASA Test Director Steve Payne. During today's tanking test, the team is paying particular attention to the external tank's ribbed intertank region. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

  13. KSC-2010-5911

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter, which is in front of the shuttle. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  14. KSC-2010-5893

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- The moon shines brightly over space shuttle Discovery following a total lunar eclipse as the spacecraft waits to roll back from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. The move was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett

  15. KSC-2010-5915

    NASA Image and Video Library

    2010-12-21

    CAPE CANAVERAL, Fla. -- Space shuttle Discovery awaits its move, called rollback, from Launch Pad 39A to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Rollback was scheduled for 12:30 a.m., but was postponed until 10 p.m. so technicians could resolve an issue with a leveling system on the crawler-transporter, which is in front of the shuttle. Once inside the VAB, Discovery's external fuel tank will be examined and foam reapplied where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

  16. Experimental Results From Stitched Composite Multi-Bay Fuselage Panels Tested Under Uni-Axial Compression

    NASA Technical Reports Server (NTRS)

    Baker, Donald J.

    2004-01-01

    The experimental results from two stitched VARTM composite panels tested under uni-axial compression loading are presented. The curved panels are divided by frames and stringers into five or six bays with a column of three bays along the compressive loading direction. The frames are supported at the ends to resist out-of-plane translation. Back-to-back strain gages are used to record the strain and displacement transducers were used to record the out-of-plane displacements. In addition a full-field measurement technique that utilizes a camera-based-stero-vision system was used to record displacements. The panels were loaded in increments to determine the first bay to buckle. Loading was discontinued at limit load and the panels were removed from the test machine for impact testing. After impacting at 20 ft-lbs to 25 ft-lbs of energy with a spherical indenter, the panels were loaded in compression until failure. Impact testing reduced the axial stiffness 4 percent and less than 1 percent. Postbuckled axial panel stiffness was 52 percent and 70 percent of the pre-buckled stiffness.

  17. Wavenumber Imaging For Damage Detection and Measurement

    NASA Technical Reports Server (NTRS)

    Rogge, Matthew D.; Johnson, Pat H.

    2011-01-01

    This paper presents a method for analyzing ultrasonic wavefield data using the Continuous Wavelet Transform (CWT) applied in the spatial domain. Unlike data obtained by sparse arrays of transducers, full wavefield data contains information local to the structure and can be used to obtain more detailed measurements of damage type, location, size, etc. By calculating the CWT of the wavefield in the spatial domain, the wavenumber spectrum is determined for the inspected locations. Because wavenumber is affected by the local geometry and material properties of the structure through which Lamb waves propagate, the wavenumber spectrum can be analyzed to assess the location, severity, and size of damage. The technique is first applied to experimental wavefield data obtained using a laser Doppler vibrometer and automated positioning stage. The out-of-plane velocity along the length of a composite stringer was measured to detect the presence of delaminations within the composite overwrap. Next, simulated corrosion is detected and measured within an aluminum plate using the two dimensional CWT. The experimental results show the usefulness of the technique for vehicle structure inspection applications.

  18. Thin tailored composite wing for civil tiltrotor

    NASA Technical Reports Server (NTRS)

    Rais-Rohani, Masoud

    1994-01-01

    The tiltrotor aircraft is a flight vehicle which combines the efficient low speed (i.e., take-off, landing, and hover) characteristics of a helicopter with the efficient cruise speed of a turboprop airplane. A well-known example of such vehicle is the Bell-Boeing V-22 Osprey. The high cruise speed and range constraints placed on the civil tiltrotor require a relatively thin wing to increase the drag-divergence Mach number which translates into lower compressibility drag. It is required to reduce the wing maximum thickness-to-chord ratio t/c from 23% (i.e., V-22 wing) to 18%. While a reduction in wing thickness results in improved aerodynamic efficiency, it has an adverse effect on the wing structure and it tends to reduce structural stiffness. If ignored, the reduction in wing stiffness leads to susceptibility to aeroelastic and dynamic instabilities which may consequently cause a catastrophic failure. By taking advantage of the directional stiffness characteristics of composite materials the wing structure may be tailored to have the necessary stiffness, at a lower thickness, while keeping the weight low. The goal of this study is to design a wing structure for minimum weight subject to structural, dynamic and aeroelastic constraints. The structural constraints are in terms of strength and buckling allowables. The dynamic constraints are in terms of wing natural frequencies in vertical and horizontal bending and torsion. The aeroelastic constraints are in terms of frequency placement of the wing structure relative to those of the rotor system. The wing-rotor-pylon aeroelastic and dynamic interactions are limited in this design study by holding the cruise speed, rotor-pylon system, and wing geometric attributes fixed. To assure that the wing-rotor stability margins are maintained a more rigorous analysis based on a detailed model of the rotor system will need to ensue following the design study. The skin-stringer-rib type architecture is used for the wing-box structure. The design variables include upper and lower skin ply thicknesses and orientation angles, spar and rib web thicknesses and cap areas, and stringer cross-sectional areas. These design variables will allow the maximum tailoring of the structure to meet the design requirements most efficiently. Initial dynamic analysis has been conducted using MSC/NASTRAN to determine the baseline wing's frequencies and mode shapes. For the design study we intend to use the finite-element based code called WIDOWAC (Wing Design Optimization With Aeroeastic Constraints) that was developed at NASA Langley in early 1970's for airplane wing structural analysis and preliminary design. Currently, the focus is on modification and validation of this code which will be used for the civil tiltrotor design efforts.

  19. Unraveling the hydrocarbon charge potential of the Nordkapp Basin, Barents Sea: An integrated approach to reduce exploration risk in complex salt basins

    NASA Astrophysics Data System (ADS)

    Schenk, Oliver; Shtukert, Olga; Bishop, Andrew; Kornpihl, Kristijan; Milne, Graham

    2014-05-01

    The Nordkapp Basin, Barents Sea, is an intra-continental syn-rift basin containing many complex salt structures. The salt is late-Carboniferous to Early Permian in age, with regional extension in the Triassic initiating the salt movement resulting in formation of sub- and mini-basins with significant subsidence (especially in the northeastern part of the basin). Subsequent tectonic phases allowed growth and distortion of salt diapirs that were later affected by uplift and erosion during Tertiary resulting in the formation of salt-related traps in Triassic and Lower Jurassic strata. During Plio-Pleistocene, glacial erosion removed additional Mesozoic and Cenozoic strata. This basin is regarded as a frontier salt province. A small hydrocarbon discovery (Pandora well) in the southwestern part of the basin points to the presence several functioning petroleum systems. The primary play type is related to salt traps below overhangs. Such structures are however, very difficult to image with conventional seismic techniques due to i) generation of multiples from sea floor and top of shallow salt bodies and ii) seismic shadow zones within the salt (possibly resulting from shale and carbonate stringers) which cause severe diffractions so that prospective areas adjacent to the salt remain elusive. Arctic exploration is expensive and the ability to focus on the highest potential targets is essential. A unique solution to this challenging subsurface Arctic environment was developed by integrating petroleum system modeling with full azimuth broadband seismic acquisition and processing. This integrated approach allows intelligent location of seismic surveys over structures which have the maximum chance of success of hydrocarbon charge. Petroleum system modeling was conducted for four seismic sections. Salt was reconstructed according to the diapiric evolution presented in Nilsen et al. (1995) and Koyi et al. (1995). Episodes of major erosion were assigned to Tertiary (tectonic) and Pleistocene (glacial). The models have been thermally calibrated. Consideration of Pleistocene glacial/interglacial cycles was required for thermal calibration as well as to better understand and predict the hydrocarbon phase behavior. References: Koyi, H., Talbot, C.J., Tørudbakken, B.O., 1993, Salt diapirs of the southwest Nordkapp Basin: analogue modelling, Tectonophysics, Volume 228, Issues 3-4, Pages 167-187. Nilsen, K.T., Vendeville, B.C., Johansen, J.-T., 1995, Influence of regional tectonics on halokinesis in the Nordkapp Basin, Barents Sea. In: Jackson, M.P.A., Roberts, D.G., Snelson, S. (eds), Salt tectonics, a global perspective, AAPG Memoir 65, 413-436.

  20. New Sections and Fossils From the Southern Bighorn Basin, Wyoming Document Faunal Turnover During the PETM

    NASA Astrophysics Data System (ADS)

    Bloch, J. I.; Boyer, D. M.; Strait, S. G.; Wing, S. L.

    2004-12-01

    Though earliest Eocene (Wa-0) mammals are known from the southern Bighorn Basin, late Paleocene mammals are not. Recent discovery of latest Paleocene mammals in section with new Wa-0 faunas and floras at Cabin Fork allows for the first studies of terrestrial biotic change across the Paleocene-Eocene boundary interval outside of the northern Bighorn Basin. A differential GPS was used to map the area and provide a framework for high-resolution biostratigraphy. Least squares interpolation of bedding planes from points marking outcrop of beds reveals high r2 coefficients (0.97-0.98). This indicates that small scale folding is minimal and bed traces are smoothly planar. Beds in the study area strike N-NW (355° ) and dip shallowly W-SW (<1.0° ). Smaller scale undulations are present: to the NE beds strike NW and dip to the SW (342° /1.0° ) whereas those to the SW strike NE and dip NW (5° /1.0° ). Shallow dips allow us to approximate stratigraphic thickness with elevation. Paleocene mammals, including diagnostic Clarkforkian land-mammal age indicators, Aletodon gunnelli, Apheliscus nitidus, and Haplomylus simpsoni, were found in a ferruginous, grit-pebble conglomerate at the base of a channel sand at the top of the Fort Union Fm. The fossiliferous horizon is extensive and has produced over 200 specimens from more than 60 sites for which positions have been determined with sub-meter accuracy. Absence of Plesiadapis cookei and Hyracotherium spp., together with high relative abundance of Phenacodus and Ectocion, indicate this fauna is latest Clarkforkian (Phenacodus-Ectocion Range Zone, Cf-3). Earliest Eocene mammals, including diagnostic Wa-0 taxa Arfia junnei, Copecion davisi, Hyracotherium sandrae, and Diacodexis ilicis, are represented by more than 233 specimens from 70 sites at three levels in the lowest Willwood Formation. The lowest fossils come from paleosols and claygall accumulations in stringer sands approximately 3 meters above the top of the channel sand that is the top of the Fort Union Formation, and 8 meters above the Clarkforkian localities. The second level is a fossiliferous paleosol 6-8 meters above the top of the channel sand. The third level is a paleosol fossil accumulation approximately 22 meters above the top of the channel sand and 15 meters below a large and persistent red paleosol informally called ?Big Red.? In the Cabin Fork area, Big Red produces mammal fossils, including Cardiolophus, that have been used to define the succeeding Wa-1 faunal zone (although some Wa-0 taxa have been recovered from Big Red approximately 6 km to the east). The Wa-0 interval in the Cabin Fork area is 38-40 meters thick and bounded by distinct Cf-3 and Wa-1 faunas. Preliminary analyses of fossils from the Cabin Fork section show that the faunal shift marking the PETM was very similar to that seen in the northern Bighorn Basin. This suggests that previously documented differences between Wa-0 mammalian faunas in the southern and northern Bighorn Basin, including the absence of certain diagnostic Wa-0 taxa in the south, may reflect local sampling variation or artifacts rather than regional variation in faunal composition.

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