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  • 1
    Publication Date: 2015-06-17
    Description: The Lepsy fault of the northern Tien Shan, SE Kazakhstan, extends E-W 120 km from the high mountains of the Dzhungarian Ala-tau, a sub-range of the northern Tien Shan, into the low-lying Kazakh platform. It is an example of an active structure that connects a more rapidly deforming mountain region with an apparently stable continental region (SCR), and follows a known Palaeozoic structure. Field-based and satellite observations reveal a ~10 m vertical offset exceptionally preserved along the entire length of the fault. Geomorphic analysis and age control from radiocarbon and optically stimulated luminescence (OSL) dating methods indicate that the scarp formed in the Holocene and was generated by at least two substantial earthquakes. The most recent event, dated to some time after ~400 years BP, is likely to have ruptured the entire 120 km fault length in a Mw 7.5{8.2 earthquake. The Lepsy fault kinematics were characterised using digital elevation models and high-resolution satellite imagery, which indicate that the predominant sense of motion is reverse right-lateral with a fault strike, dip and slip vector azimuth of ~110°, 50°S and 317{343 respectively, which is consistent with predominant N-S shortening related to the India-Eurasia collision. In light of these observations, and because the activity of the Lepsy fault would have been hard to ascertain if it had not ruptured in the recent past, we note that the absence of known active faults within low-relief and low strain-rate continental interiors does not always imply an absence of seismic hazard.
    Print ISSN: 0148-0227
    Topics: Geosciences , Physics
    Published by Wiley on behalf of American Geophysical Union (AGU).
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  • 2
    Publication Date: 2019-07-12
    Description: As part of a program examining a composite payload adaptor fitting (PAF) for NASAs Space Launch System (SLS), a repair study of impact damage and misdrilled holes was undertaken. At the beginning of this repair study, the PAF was baselined as a honeycomb sandwich structure with eight-ply quasi-isotropic, carbon-fiber-reinforced epoxy facesheets. Although the baseline configuration could change, the repair program presented herein is generic enough in nature such that it will apply to most sandwich configurations. The vast majority of loads experienced by this structure will be in-plane compression; thus, this repair study concentrates on the in-plane compression strength of representative sandwich structure specimens. The PAF is a truncated cone with a minimum diameter of about 170 inches at the top and a maximum diameter of about 335 inches at the bottom. While the launch vehicle hardware should be protected throughout its life on the ground, rogue events (or misdrilled holes) are still a possibility. This study is not meant to address large scale damage or damage to the part other than in the acreage (the uniform portion of the structure that does not consist of joints or other detailed areas), but address the most probable type of damages (small impacts and misdrilled holes) in the vast majority of the structure (the acreage).
    Keywords: Composite Materials; Structural Mechanics
    Type: NASA/TM-2018-219866 , M18-6927 , M-1470
    Format: application/pdf
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  • 3
    Publication Date: 2019-07-12
    Description: Reducing risk for utilizing honeycomb sandwich structure for the Space Launch System payload adapter fitting includes determining what parameters need to be tested for damage tolerance to ensure a safe structure. Specimen size and boundary conditions are the most practical parameters to use in damage tolerance inspection. The effect of impact over core splices and foreign object debris between the facesheet and core is assessed. Effects of enhanced damage tolerance by applying an outer layer of carbon fiber woven cloth is examined. A simple repair technique for barely visible impact damage that restores all compression strength is presented.
    Keywords: Composite Materials
    Type: NASA/TM-2018-219849 , M-1452
    Format: application/pdf
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  • 4
    Publication Date: 2019-07-12
    Description: The Composites for Exploration Upper Stage (CEUS) was a 3-year, level III project within the Technology Demonstration Missions program of the NASA Space Technology Mission Directorate. Studies have shown that composites provide important programmatic enhancements, including reduced weight to increase capability and accelerated expansion of exploration and science mission objectives. The CEUS project was focused on technologies that best advanced innovation, infusion, and broad applications for the inclusion of composites on future large human-rated launch vehicles and spacecraft. The benefits included near- and far-term opportunities for infusion (NASA, industry/commercial, Department of Defense), demonstrated critical technologies and technically implementable evolvable innovations, and sustained Agency experience. The initial scope of the project was to advance technologies for large composite structures applicable to the Space Launch System (SLS) Exploration Upper Stage (EUS) by focusing on the affordability and technical performance of the EUS forward and aft skirts. The project was tasked to develop and demonstrate critical composite technologies with a focus on full-scale materials, design, manufacturing, and test using NASA in-house capabilities. This would have demonstrated a major advancement in confidence and matured the large-scale composite technology to a Technology Readiness Level 6. This project would, therefore, have bridged the gap for providing composite application to SLS upgrades, enabling future exploration missions.
    Keywords: Engineering (General); Spacecraft Design, Testing and Performance
    Type: NASA/TM-2016-219433 , M-1422 , MSFC-E-DAA-TN33615
    Format: application/pdf
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