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  • 1
    facet.materialart.
    Unknown
    Reference Material Kydex(registered trademark)-100 Test Data Message for Flammability Testing (2003)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The Marshall Space Flight Center (MSFC) Materials and Processes Technical Information System (MAPTIS) database contains, as an engineering resource, a large amount of material test data carefully obtained and recorded over a number of years. Flammability test data obtained using Test 1 of NASA-STD-6001 is a significant component of this database. NASA-STD-6001 recommends that Kydex 100 be used as a reference material for testing certification and for comparison between test facilities in the round-robin certification testing that occurs every 2 years. As a result of these regular activities, a large volume of test data is recorded within the MAPTIS database. The activity described in this technical report was undertaken to mine the database, recover flammability (Test 1) Kydex 100 data, and review the lessons learned from analysis of these data.
    Keywords: Composite Materials
    Type: 5th Conference on Aerospace Materials, Processes, and Environmental Technology; NASA/CP-2003-212931
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Orbital flight test shuttle external tank aerothermal flight evaluation, volume 2 (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This 3-volume report discusses the evaluation of aerothermal flight measurements made on the orbital flight test Space Shuttle External Tanks (ETs). Six ETs were instrumented to measure various quantities during flight; including heat transfer, pressure, and structural temperature. The flight data was reduced and analyzed against math models established from an extensive wind tunnel data base and empirical heat-transfer relationships. This analysis has supported the validity of the current aeroheating methodology and existing data base; and, has also identified some problem areas which require methodology modifications. Volume 1 is the Executive Summary. This is volume 2, containing Appendix A (Aerothermal Comparisons), and Appendix B (Flight-Derived h sub i/h sub u vs. M sub inf. Plots). Volume 3 contains Appendix C (Comparison of Interference Factors between OFT Flight, Prediction and 1H-97A Data), Appendix D (Freestream Stanton Number and Reynolds Number Correlation for Flight and Tunnel Data), and Appendix E (Flight-Derived h sub i/h sub u Tables).
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-179075 , NAS 1.26:179075 , RTR-041-02-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
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    Orbital flight test shuttle external tank aerothermal flight evaluation, volume 1 (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This 3-volume report discusses the evaluation of aerothermal flight measurements made on the orbital flight test Space Shuttle External Tanks (ETs). Six ETs were instrumented to measure various quantities during flight; including heat transfer, pressure, and structural temperature. The flight data was reduced and analyzed against math models established from an extensive wind tunnel data base and empirical heat-transfer relationships. This analysis has supported the validity of the current aeroheating methodology and existing data base; and, has also identified some problem areas which require methodology modifications. This is Volume 1, an Executive Summary. Volume 2 contains Appendices A (Aerothermal Comparisons) and B (Flight Derived h sub 1/h sub u vs. M sub inf. Plots), and Volume 3 contains Appendix C (Comparison of Interference Factors among OFT Flight, Prediction and 1H-97A Data), Appendix D (Freestream Stanton Number and Reynolds Number Correlation for Flight and Tunnel Data), and Appendix E (Flight-Derived h sub i/h sub u Tables).
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-179074 , NAS 1.26:179074 , RTR-041-02-VOL-1
    Format: application/pdf
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  • 4
    facet.materialart.
    Unknown
    Orbital flight test shuttle external tank aerothermal flight evaluation, volume 3 (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This 3-volume report discusses the evaluation of aerothermal flight measurements made on the orbital flight test Space Shuttle External Tanks (ETs). Six ETs were instrumented to measure various quantities during flight; including heat transfer, pressure, and structural temperature. The flight data was reduced and analyzed against math models established from an extensive wind tunnel data base and empirical heat-transfer relationships. This analysis has supported the validity of the current aeroheating methodology and existing data base; and, has also identified some problem areas which require methodology modifications. Volume 1 is the Executive Summary. Volume 2 contains Appendix A (Aerothermal Comparisons), and Appendix B (Flight-Derived h sub 1/h sub u vs. M sub inf. Plots). This is Volume 3, containing Appendix C (Comparison of Interference Factors between OFT Flight, Prediction and 1H-97A Data), Appendix D (Freestream Stanton Number and Reynolds Number Correlation for Flight and Tunnel Data), and Appendix E (Flight-Derived h sub i/h sub u Tables).
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-179076 , NAS 1.26:179076 , RTR-041-02-VOL-3
    Format: application/pdf
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  • 5
    facet.materialart.
    Unknown
    Remtech SSME nozzle design TPS (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Thermal damage to the Space Shuttle Main Engine (SSME) aft manifold Thermal Protection System (TPS) has been observed for flights STS-8 through STS-13. This damaged area is located on the ME2 and ME3 and extends over a region of approximately one square foot. Total failure or burn-through of the TPS could lead to severe thermal damage of the SSME manifold and loss of an engine nozzle necessitating nozzle replacement causing significant schedule delays and cost increases. Thermal damage to the manifold can be defined as a situation where the manifold temperature becomes greater than 1300 F; thereby causing loss of heat treatment in the nozzle. Results of Orbiter/nozzle wind tunnel tests and Hot Gas Facility tests of the TPS are presented. Aerothermal and thermal analysis models for the SSME aft manifold are discussed along with the flight predictions, design trajectory and design environment. Finally, the TPS design concept and TPS thermal response are addressed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-192516 , NAS 1.26:192516 , RTR-113-03
    Format: application/pdf
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  • 6
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    Upward Flammability Testing: A Probabilistic Measurement (2003)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Examination of NASA-STD-6001 Test 1 data suggests burn length outcome for a given environment has a large statistical variation from run to run. Large data sets show that burn length data form cumulative probability distribution curves, which describe a material's characteristic to burn in a specific environment, suggesting that the current practice of testing three samples at specific conditions is inadequate. Sufficient testing can establish material characteristics probability curves to provide the probability that a material will sustain a burn length of at least 15.24 cm (6.0 in.) or will sustain burning until all material is consumed. A simple pasdfail criterion may not be possible or practical. Future application of flammability data for some material classes may require the engineer to assess risk based on the probability of an occurrence and the probable outcome with different materials as characterized with cumulative burn length distributions for specific use conditions.
    Keywords: Statistics and Probability
    Type: Tenth International Symposium on Flammability and Sensitivity of Materials in Oxygen-Enriched Atmospheres; Nov 10, 2003 - Nov 14, 2003; Brisbane; Australia
    Format: text
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  • 7
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    Potential of Organic Matrix Composites for Liquid Oxygen Tank (2005)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Composite materials are being considered for the tankage of cryogenic propellants in access to space because of potentially lower structural weights. A major hurdle for composites is an inherent concern about the safety of using flammable structural materials in contact with liquid and gaseous oxygen. A hazards analysis approach addresses a series of specific concerns that must be addressed based upon test data. Under the 2nd Generation Reusable Launch Vehicle contracts, testing was begun for a variety of organic matrix composite materials both to aid in the selection of materials and to provide needed test data to support hazards analyses. The work has continued at NASA MSFC and the NASA WSTF to provide information on the potential for using composite materials in oxygen systems. Appropriate methods for oxygen compatibility testing of structural materials and data for a range of composite materials from impact, friction, flammability and electrostatic discharge testing are presented. Remaining concerns and conclusions about composite tank structures, and recommendations for additional testing are discussed. Requirements for system specific hazards analysis are identified.
    Keywords: Composite Materials
    Type: 2005 National Space and Missile Materials Symposium; Jun 27, 2005 - Jul 01, 2005; Summerlin, NV; United States
    Format: text
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  • 8
    facet.materialart.
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    Oxygen Compatibility Testing of Composite Materials (2006)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Composite materials offer significant weight-saving potential for aerospace applications in propellant and oxidizer tanks. This application for oxygen tanks presents the challenge of being oxygen compatible in addition to complying with the other required material characteristics. This effort reports on the testing procedures and data obtained in examining and selecting potential composite materials for oxygen tank usage. Impact testing of composites has shown that most of these materials initiate a combustion event when impacted at 72 ft-lbf in the presence of liquid oxygen, though testing has also shown substantial variability in reaction sensitivities to impact. Data for screening of 14 potential composites using the Bruceton method is given herein and shows that the 50-percent reaction frequencies range from 17 to 67 ft-lbf. The pressure and temperature rises for several composite materials were recorded to compare the energy releases as functions of the combustion reactions with their respective reaction probabilities. The test data presented are primarily for a test pressure of 300 psia in liquid oxygen. The impact screening process is compared with oxygen index and autogenous ignition test data for both the composite and the basic resin. The usefulness of these supplemental tests in helping select the most oxygen compatible materials is explored. The propensity for mechanical impact ignition of the composite compared with the resin alone is also examined. Since an ignition-free composite material at the peak impact energy of 72 ft-lbf has not been identified, composite reactivity must be characterized over the impact energy level and operating pressure ranges to provide data for hazard analyses in selecting the best potential material for liquid tank usage.
    Keywords: Composite Materials
    Type: 2006 National Space and Missile Materials Symposium; Jun 26, 2006 - Jun 30, 2006; Orlando, FL; United States
    Format: text
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  • 9
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    Mechanical Impact Testing: A Statistical Measurement (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In the decades since the 1950s, when NASA first developed mechanical impact testing of materials, researchers have continued efforts to gain a better understanding of the chemical, mechanical, and thermodynamic nature of the phenomenon. The impact mechanism is a real combustion ignition mechanism that needs understanding in the design of an oxygen system. The use of test data from this test method has been questioned due to lack of a clear method of application of the data and variability found between tests, material batches, and facilities. This effort explores a large database that has accumulated over a number of years and explores its overall nature. Moreover, testing was performed to determine the statistical nature of the test procedure to help establish sample size guidelines for material characterization. The current method of determining a pass/fail criterion based on either light emission or sound report or material charring is questioned.
    Keywords: Mechanical Engineering
    Type: ASTM International 11th International Symposium on Flammability and Sensitivity of Materials in Oxygen-Enriched Atmospheres; Oct 18, 2006 - Oct 20, 2006; Washington, DC; United States
    Format: application/pdf
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  • 10
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    Heated Promoted Combustion-Initial Test Results (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The purpose of the STD 6001 test 17 is to determine the flammability of materials in GOX at ambient temperature and at use pressure. The purpose of the new Heated Promoted combustion test is to determine the flammability of material in GOX at use temperature and pressure. The objective is to present the new heated promoted combustion method and show initial data and trends for three representative metals.
    Keywords: Spacecraft Propulsion and Power
    Type: National Space and Missile Materials Symposium; Jun 27, 2005 - Jul 01, 2005; Summerlin, NV; United States
    Format: application/pdf
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