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  • 1
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    Flammability tests for Apollo command module and lunar module mockup (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The flammability test program for Apollo command module and lunar module mockups is described. The fire safety design of the modules was verified by performing deliberate ignitions at many locations while the interior atmosphere was controlled to simulate realistic flight conditions. The data obtained for each test and restrictions on various materials are discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 43-54
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Fire-resistant aircraft materials development and evaluation program (1974)
    In:  CASI
    Details
    Publication Date: 2006-05-07
    Description: The overall objectives of this program are to provide a more fire-resistant commercial aircraft interior and to improve the fuselage insulation barrier between the cabin interior and an exterior fuel fire. Significant secondary objectives are to reduce the smoke and toxic gas production of the materials and to meet the end item use requirements pertaining to wearability, color fastness, and aesthetic appeal. It is shown that the fuselage insulation materials must meet stringent requirements pertaining to acoustic attenuation, low density, and water repellency.
    Keywords: COMPOSITE MATERIALS
    Type: Chamber of Commerce Proc. of the 1st 1974 Technol. Transfer Conf.; p 445-491
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Flammability testing conducted in support of Apollo 13 (1971)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: In support of the Apollo 13 investigation of the oxygen tank failure, flame propagation rates were determined for Teflon insulation in cryogenic and ambient temperature oxygen for upward, downward, and zero g burns. The propagation rates depended heavily on configuration and varied from 4.8 to 10.9 cm/sec for upward one g burns to 0.48 cm/sec for zero g burns. In addition to the flame propagation rates, tests were conducted to determine if Teflon burning in cryogenic oxygen could ignite metals (promoted ignition) with which it came in contact. Tests conducted on various metal alloys used in the oxygen tank indicated that most of the alloys could be ignited by burning Teflon in certain configurations. After the propagation rates and promoted metal ignitions had been evaluated, a test was conducted on a quantity gauge and wire harness used in the oxygen tank to determine if flame propagation to the tank wall was possible. Propagation of the wire bundle after ignition resulted in a catastrophic failure of the test vessel in the area of the quantity gauge.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: MSC Cryog. Symp. Papers; p 455-474
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    The 737 aircraft flammability testing (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The FAA requested approximately 20 component and full-scale tests in a 737 fuselage to provide validation data or indicate changes that need to be made to a fire math model (Dayton Aircraft Cabin Fire Model) developed for the FAA. Some preliminary tests were conducted to evaluate the adequacy of planned instrumentation. The objectives of the program were met in that it was verified that propagation of a fire could be determined from the sequential response of thermocouples located on a test specimen(such as a seat), and continuous weighing of the specimen during the test was accomplished. Two differenct techniques for measuring smoke density were found to be comparable.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA. Ames Res. Center Conf. on Fire Resistant Mater. (FIREMEN); p 14-38
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Materials research for aircraft fire safety (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The thermochemical and flammability characteristics of two polymeric composites currently in use and seven others being considered for use as aircraft interior panels are described. The properties studied included: (1) limiting oxygen index of the composite constituents; (2) fire containment capability of the composite; (3) smoke evolution from the composite; (4) thermogravimetric analysis; (5) composition of the volatile products of thermal degradation; and (6) relative toxicity of the volatile products of pyrolysis. The performance of high-temperature laminating resins such as bismaleimides is compared with the performance of phenolics and epoxies. The relationship of increased fire safety with the use of polymers with high anaerobic char yield is shown. Processing parameters of the state-of-the-art and the advanced bismaleimide composites are detailed.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: Aircraft Safety and Operating Problems; p 391-422
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Seat test program (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The test program has the objectives to: (1) evaluate severity of newspaper ignition source with contemporary seats (determine weight loss, visual damage, and if ignition source is severe enough to show improvement with new material configurations); (2) compare damage with jet A-1 ignition source; and (3) determine if materials for seat tests pass FAR 25 and obtain L01. Test configurations, data acquired, material test results, seat test results, and conclusions are presented.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA. Ames Res. Center Conf. on Fire Resistant Mater.; p 13-26
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Airport flammability, full scale fire tests (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The primary objectives of the fire tests are: (1) conduct full scale test with 737 fuselages by the end of 1980; (2) demonstrate evacuation time increase to five minutes minimum; (3) show that exterior fire will not penetrate an intact cabin for five minutes; (4) show that closed cabin will not have excess smoke or temperatures above 400 F; and (5) demonstrate that fire in cabin opening will not propagate throughout cabin. The test program has three phases. A test schedule and status of required materials are presented.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA. Ames Res. Center Conf. on Fire Resistant Mater.; p 1-12
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Test results from a comparative evaluation of a condensation nuclei fire detector (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The fire/smoke alarm response of a condensation nuclei fire detector (CNFD) was compared with photoelectric and ionization detectors. Tests were conducted in a former control room 8.5 m by 8.9 with a 2.7 m ceiling. The room had air supplied from above the ceiling and under the floor with return air exiting from ceiling grills. The environment was varied from 278 to 305 K and relative humidities from 8 to 65%. Four detection zones were located in the room. Each zone contained a sampling head for the CNDF, a photodetector, and an ionization detector so that each detector system had four opportunities to alarm during tests. The particle level in the test room was also monitored during tests with a condensation nuclei particle counter. The CNFD responded to 90% of exposures to smoldering plastic and 84% of exposures to visible fire. The photoelectric response was 43 and 12.5% respectively for the same conditions. The ionization response was 9 and 48 respectively.
    Keywords: QUALITY ASSURANCE AND RELIABILITY
    Type: NASA-CR-3874 , S-543 , NAS 1.26:3874
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Full-scale flammability test data for validation of aircraft fire mathematical models (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Twenty-five large scale aircraft flammability tests were conducted in a Boeing 737 fuselage at the NASA Johnson Space Center (JSC). The objective of this test program was to provide a data base on the propagation of large scale aircraft fires to support the validation of aircraft fire mathematical models. Variables in the test program included cabin volume, amount of fuel, fuel pan area, fire location, airflow rate, and cabin materials. A number of tests were conducted with jet A-1 fuel only, while others were conducted with various Boeing 747 type cabin materials. These included urethane foam seats, passenger service units, stowage bins, and wall and ceiling panels. Two tests were also included using special urethane foam and polyimide foam seats. Tests were conducted with each cabin material individually, with various combinations of these materials, and finally, with all materials in the cabin. The data include information obtained from approximately 160 locations inside the fuselage.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA-TM-58244 , NAS 1.15:58244
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Apollo experience reports: Window contamination (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The problem of window contamination in the Apollo command module is reviewed. All five command module windows were contaminated while in earth orbit on the first three manned Apollo flights. The contamination sources were identified and eliminated. Preflight testing of lunar module windows showed that no serious contamination should occur, and this conclusion was verified in subsequent manned flights. The command module window designs and materials are described, the window contamination sources are identified, and the inflight and chemical analyses of the contamination are outlined. The corrective actions that were taken are reviewed. For the lunar module, the window design and materials and the preflight and fight evaluations are described. Window design recommendations are made.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-6721 , MSC-S-284
    Format: application/pdf
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