ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
  • 1
    facet.materialart.
    Unknown
    Progressive Damage Analysis of Laminated Composite (PDALC)-A Computational Model Implemented in the NASA COMET Finite Element Code (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method for analysis of progressive failure in the Computational Structural Mechanics Testbed is presented in this report. The relationship employed in this analysis describes the matrix crack damage and fiber fracture via kinematics-based volume-averaged variables. Damage accumulation during monotonic and cyclic loads is predicted by damage evolution laws for tensile load conditions. The implementation of this damage model required the development of two testbed processors. While this report concentrates on the theory and usage of these processors, a complete list of all testbed processors and inputs that are required for this analysis are included. Sample calculations for laminates subjected to monotonic and cyclic loads were performed to illustrate the damage accumulation, stress redistribution, and changes to the global response that occur during the load history. Residual strength predictions made with this information compared favorably with experimental measurements.
    Keywords: Structural Mechanics
    Type: NASA-TM-4724 , NAS 1.15:4724 , L-17545
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    Analytical Methodology for Predicting the Onset of Widespread Fatigue Damage in Fuselage Structure (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: NASA has developed a comprehensive analytical methodology for predicting the onset of widespread fatigue damage in fuselage structure. The determination of the number of flights and operational hours of aircraft service life that are related to the onset of widespread fatigue damage includes analyses for crack initiation, fatigue crack growth, and residual strength. Therefore, the computational capability required to predict analytically the onset of widespread fatigue damage must be able to represent a wide range of crack sizes from the material (microscale) level to the global structural-scale level. NASA studies indicate that the fatigue crack behavior in aircraft structure can be represented conveniently by the following three analysis scales: small three-dimensional cracks at the microscale level, through-the-thickness two-dimensional cracks at the local structural level, and long cracks at the global structural level. The computational requirements for each of these three analysis scales are described in this paper.
    Keywords: Structural Mechanics
    Type: NASA-TM-110293 , NAS 1.15:110293
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    Unknown
    An Assessment of the State-of-the-Art in the Design and Manufacturing of Large Composite Structures for Aerospace Vehicles (2001)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: An assessment of the State-of-the-Art in the design and manufacturing of large composite structures has been conducted. The focus of the assessment is large structural components in commercial and military aircraft. Applications of composites are reviewed for commercial transport aircraft, general aviation aircraft, rotorcraft, and military aircraft.
    Keywords: Structural Mechanics
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 4
    facet.materialart.
    Unknown
    The Second Joint NASA/FAA/DOD Conference on Aging Aircraft (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The purpose of the Conference was to bring together world leaders in aviation safety research, aircraft design and manufacturing, fleet operation and aviation maintenance to disseminate information on current practices and advanced technologies that will assure the continued airworthiness of the aging aircraft in the military and commercial fleets. The Conference included reviews of current industry practices, assessments of future technology requirements, and status of aviation safety research. The Conference provided an opportunity for interactions among the key personnel in the research and technology development community, the original equipment manufacturers, commercial airline operators, military fleet operators, aviation maintenance, and aircraft certification and regulatory authorities. Conference participation was unrestricted and open to the international aviation community.
    Keywords: Structural Mechanics
    Type: NASA/CP-1999-208982/PT1 , L-17819A , NAS 1.55:208982/PT1 , The Second Joint NASA/FAA/DOD Conference on Aging Aircraft; NASA/CP-1999-208982/PT1|Aging Aircraft; Aug 31, 1998 - Sep 03, 1998; Williamsburg, VA; United States
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 5
    facet.materialart.
    Unknown
    The Second Joint NASA/FAA/DoD Conference on Aging Aircraft (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The purpose of the Conference was to bring together world leaders in aviation safety research, aircraft design and manufacturing, fleet operation and aviation maintenance to disseminate information on current practices and advanced technologies that will assure the continued airworthiness of the aging aircraft in the military and commercial fleets. The Conference included reviews of current industry practices, assessments of future technology requirements, and status of aviation safety research. The Conference provided an opportunity for interactions among the key personnel in the research and technology development community, the original equipment manufacturers, commercial airline operators, military fleet operators, aviation maintenance, and aircraft certification and regulatory authorities. Conference participation was unrestricted and open to the international aviation community. Appendix B contains the name and addresses of the 623 participants in the Conference.
    Keywords: Structural Mechanics
    Type: NASA/CP-1999-208982/PT2 , L-17819B , NAS 1.55:208982/PT2 , Aging Aircraft; Aug 31, 1998 - Sep 03, 1998; Williamsburg, VA; United States|The Second Joint NASA/FAA/DoD Conference on Aging Aircraft; NASA/CP-1999-208982/PT2
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 6
    facet.materialart.
    Unknown
    Implementation Plan for the NASA Center of Excellence for Structures and Materials (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: This report presents the implementation plans of the Center of Excellence (COE) for Structures and Materials. The plan documented herein is the result of an Agencywide planning activity led by the Office of the Center of Excellence for Structures and Materials at Langley Research Center (LaRC). The COE Leadership Team, with a representative from each NASA Field Center, was established to assist LaRC in fulfilling the responsibilities of the COE. The Leadership Team developed the plan presented in this report.
    Keywords: Structural Mechanics
    Type: NASA/TM-1998-208714 , NAS 1.15:208714 , L-17754
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 7
    facet.materialart.
    Unknown
    Orbiter LH2 Feedline Flowliner Cracking Problem (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: In May of 2002, three cracks were found in the downstream flowliner at the gimbal joint in the LH2 feedline at the interface with the Low Pressure Fuel Turbopump (LPFP) of Space Shuttle Main Engine (SSME) #1 of Orbiter OV-104. Subsequent inspections of the feedline flowliners in the other orbiters revealed the existence of 8 additional cracks. No cracks were found in the LO2 feedline flowliners. A solution to the cracking problem was developed and implemented on all orbiters. The solution included weld repair of all detectable cracks and the polishing of all slot edges to remove manufacturing discrepancies that could initiate new cracks. Using the results of a fracture mechanics analysis with a scatter factor of 4 on the predicted fatigue life, the orbiters were cleared for return to flight with a one-flight rationale requiring inspections after each flight. OV-104 flew mission STS-112 and OV-105 flew mission STS-113. The post-flight inspections did not find any cracks in the repaired flowliners. At the request of the Orbiter Program, the NESC conducted an assessment of the Orbiter LH2 Feedline Flowliner cracking problem with a team of subject matter experts from throughout NASA.
    Keywords: Structural Mechanics
    Type: NASA/TM-2005-213787/Version-1.0 , L-19148/Version-1.0 , NESC-RP-04-11/04-004-E/Version-1.0
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...