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  • 1
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    Advanced X-Ray Inspection of Reinforced Carbon Composite Materials on the Orbiter Leading Edge Structural Subsystem (LESS) (2004)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The post return-to-flight (RTF) inspection methodology for the Orbiter Leading Edge Structural Subsystem (LESS) is currently being defined. Numerous NDT modalities and techniques are being explored to perform the flight-to-flight inspections of the reinforced carbon/carbon (RCC) composite material for impact damage, general loss of mass in the bulk layers, or other anomalous conditions that would pose risk to safe return upon re-entry. It is possible to have an impact upon ascent that is not visually observable on the surface, yet causes internal damage. Radiographic testing may be a useful NDT technique for such occurrences. The authors have performed radiographic tests on full-sized mock samples of LESS hardware with embedded image quality phantoms. Digitized radiographic film, computed radiography and flat panel digital real-time radiography was acquired using a GE Eresco 200 x-ray tube, and Se-75 and Yb-169 radioisotopes.
    Schlagwort(e): Composite Materials
    Materialart: JSC-CN-8726 , NDT 2004 Conference and Exhibition; Sep 14, 2004 - Sep 16, 2004; Torquay; United Kingdom
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 2
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    Friction Stir Welding Development at National Aeronautics and Space Administration-Marshall Space Flight Center (2001)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-18
    Beschreibung: This paper presents an over-view of friction stir welding (FSW) process development and applications at Marshall Space Flight Center (MSFC). FSW process development started as a laboratory curiosity but soon found support from many users. The FSW process advanced very quickly and has found many applications both within and outside the aerospace industry. It is currently being adapted for joining key elements of the Space Shuttle External Tank for improved producibility and reliability. FSW process modeling is done to better understand and improve the process. Special tools have been developed to weld variable thickness materials including very thin and very thick materials. FSW is now being applied to higher temperature materials such as copper and to advanced materials such as metal matrix composites. FSW technology is being successfully transferred from MSFC laboratory to shop floors of many commercial companies.
    Schlagwort(e): Mechanical Engineering
    Materialart: TMS Conference; Nov 01, 2001; Indianapolis, IN; United States
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 3
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    Thermal Conductivity of EB-PVD Thermal Barrier Coatings Evaluated by a Steady-State Laser Heat Flux Technique (2000)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The thermal conductivity of electron beam-physical vapor deposited (EB-PVD) Zr02-8wt%Y2O3 thermal barrier coatings was determined by a steady-state heat flux laser technique. Thermal conductivity change kinetics of the EB-PVD ceramic coatings were also obtained in real time, at high temperatures, under the laser high heat flux, long term test conditions. The thermal conductivity increase due to micro-pore sintering and the decrease due to coating micro-delaminations in the EB-PVD coatings were evaluated for grooved and non-grooved EB-PVD coating systems under isothermal and thermal cycling conditions. The coating failure modes under the high heat flux test conditions were also investigated. The test technique provides a viable means for obtaining coating thermal conductivity data for use in design, development, and life prediction for engine applications.
    Schlagwort(e): Composite Materials
    Materialart: NASA/TM-2000-210238 , E-12357 , NAS 1.15:210238 , Metallurgical Coatings and Thin Films; Apr 10, 2000 - Apr 14, 2000; San Diego, CA; United States
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 4
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    Advanced Layered Composite Polylaminate Electroactive Actuator and Sensor (2000)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-10
    Beschreibung: The present invention relates to the mounting of pre-stressed electroactive material in such a manner that large displacement actuators or sensors result. The invention comprises mounting the pre-stressed electroactive material to a support layer. This combination of a pre-stressed electroactive material and support layer may in turn be attached to a mounting surface. The pre-stressed electroactive material may be a ferroelectric, pyroelectric, piezoelectric, or magnetostrictive material. The size, stiffness, mass, and material of the support layer is selected to result in the electroactive device having dynamic response properties, environmental capability characteristics, and the required resilience optimized for a given application. The capacity to connect the support layer to a surface expands the arenas in which the prestressed electroactive device may be used. Application for which the invention may be used include actuators, sensors, or as a component in a pumps, switches, relays, pressure transducers and acoustic devices.
    Schlagwort(e): Composite Materials
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 5
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    Friction Stir Welding Development at NASA-Marshall Space Flight Center (2001)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper presents an overview of friction stir welding (FSW) process development and applications at Marshall Space Flight Center (MSFC). FSW process development started as a laboratory curiosity but soon found support from many users. The FSW process advanced very quickly and has found many applications both within and outside the aerospace industry. It is currently being adapted for joining key elements of the Space Shuttle External Tank for improved producibility and reliability. FSW process modeling is done to better understand and improve the process. Special tools have been developed to weld variable thickness materials including thin and thick materials. FSW is now being applied to higher temperature materials such as copper and to advanced materials such as metal matrix composites. FSW technology is being successfully transferred from MSFC laboratory to shop floors of many commercial companies.
    Schlagwort(e): Mechanical Engineering
    Materialart: TMS Special Publication on Friction Stir Welding; Jan 01, 2001; Warrendale, PA; United States
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 6
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    Overview of NASA's UEET Program (2002)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-03
    Beschreibung: This paper presents a general overview of NASA's Ultra Efficient Engine Technology (UEET) Program. The program's vision is to develop and hand off revolutionary turbine engine propulsion technologies that will enable future generation vehicles over a wide range of flight speeds. The specific goals include: 1) Perform propulsion technologies to enable increases in system efficiency and, therefore, fuel burn reductions of up to 15% (equivalent reductions in CO2); and 2) Provide combustor technologies (configuration and materials) which will enable reductions in Landing/Take-off (LTO) NOx of 70% relative to 1996 ICAO standards.
    Schlagwort(e): Mechanical Engineering
    Materialart: 2001 NASA Seal/Secondary Air System Workshop; Volume 1; 53-67; NASA/CP-2002-211911/VOL1
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 7
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    Overview of NASA Glenn Seal Development Program (2001)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-03
    Beschreibung: NASA Glenn hosted the Seals/Secondary Air System Workshop on October 25-26, 2000. Each year NASA and our industry and university partners share their respective seal technology developments. We use these workshops as a technical forum to exchange recent advancements and 'lessons-learned' in advancing seal technology and solving problems of common interest. As in the past we are publishing two volumes. Volume I will be publicly available and individual papers will be made available online through the web page address listed at the end of this chapter.
    Schlagwort(e): Mechanical Engineering
    Materialart: 2000 NASA Seal/Secondary Air System Workshop; Volume 1; 1-21; NASA/CP-2001-211208/VOL1
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 8
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    1999 NASA Seal/Secondary Air System Workshop (2000)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: NASA Glenn hosted the Seals/Secondary Air System Workshop on October 2829, 1999. Each year NASA and our industry and university partners share their respective seal technology development. We use these workshops as a technical forum to exchange recent advancements and "lessons-learned" in advancing seal technology and solving problems of common interest. As in the past we are publishing two volumes. Volume 1 will be publicly available and will be made available on-line through the web page address listed at the end of this chapter. Volume 2 will be restricted under International Traffic and Arms Regulations (I.T.A.R.) In this conference participants gained an appreciation of NASA's new Ultra Efficient Engine Technology (UEET) program and how this program will be partnering with ongoing DOE -industrial power production and DOD- military aircraft engine programs. In addition to gaining a deeper understanding into sealing advancements and challenges that lie ahead, participants gained new working and personal relationships with the attendees. When the seals and secondary fluid management program was initiated, the emphasis was on rocket engines with spinoffs to gas turbines. Today, the opposite is true and we are, again building our involvement in the rocket engine and space vehicle demonstration programs.
    Schlagwort(e): Mechanical Engineering
    Materialart: 1999 NASA Seal/Secondary Air System Workshop; Volume 1; 1-17; NASA/CP-2000-210472/VOL1
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 9
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    Unbekannt
    Continued Evaluation of The Hybrid Floating Brush Seal (HFBS) (2000)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The objective of this presentation is to increase thrust to weight ratio, decrease specific fuel consumption, and to eliminate wear of sealing components.
    Schlagwort(e): Mechanical Engineering
    Materialart: 1999 NASA Seal/Secondary Air System Workshop; Volume 1; 365-394; NASA/CP-2000-210472/VOL1
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 10
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    Unshrouded Centrifugal Turbopump Impeller Design Methodology (2001)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Turbopump weight continues to be a dominant parameter in the trade space for reduction of engine weight. Space Shuttle Main Engine weight distribution indicates that the turbomachinery make up approximately 30% of the total engine weight. Weight reduction can be achieved through the reduction of envelope of the turbopump. Reduction in envelope relates to an increase in turbopump speed and an increase in impeller head coefficient. Speed can be increased until suction performance limits are achieved on the pump or due to alternate constraints the turbine or bearings limit speed. Once the speed of the turbopump is set the impeller tip speed sets the minimum head coefficient of the machine. To reduce impeller diameter the head coefficient must be increased. A significant limitation with increasing head coefficient is that the slope of the head-flow characteristic is affected and this can limit engine throttling range. Unshrouded impellers offer a design option for increased turbopump speed without increasing the impeller head coefficient. However, there are several issues with regard to using an unshrouded impeller: there is a pump performance penalty due to the front open face recirculation flow, there is a potential pump axial thrust problem from the unbalanced front open face and the back shroud face, and since test data is very limited for this configuration, there is uncertainty in the magnitude and phase of the rotordynamic forces due to the front impeller passage. The purpose of the paper is to discuss the design of an unshrouded impeller and to examine the hydrodynamic performance, axial thrust, and rotordynamic performance. The design methodology will also be discussed. This work will help provide some guidelines for unshrouded impeller design.
    Schlagwort(e): Mechanical Engineering
    Materialart: The Tenth Thermal and Fluids Analysis Workshop; NASA/CP-2001-211141
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
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