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  • 1
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    Composition of Cigaret Smoke. (1949)
    American Chemical Society
    Details
    Publication Date: 1949-07-01
    Print ISSN: 0019-7866
    Electronic ISSN: 1541-5724
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Published by American Chemical Society
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  • 2
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    Effects of 50,000 h of thermal aging on graphite/epoxy and graphite/polyimide composites (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previoulsy cited in issue 13, p. 2034, Accession no. A82-30087
    Keywords: COMPOSITE MATERIALS
    Type: AIAA Journal (ISSN 0001-1452); 22; 96-102
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Effects of real-time thermal aging on graphite/polyimide composites (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As part of a program to evaluate high-temperature advanced composites for use on supersonic cruise transport aircraft, two graphite/polyimide composites have been aged at elevated temperatures for times up to 5.7 years. Work on the first, HT-S/710 graphite/polyimide, was started in 1974. Evaluation of the second polyimide, Celion 6000/LARC-160, began in 1980. Baseline properties are presented, including unnotched and notched tensile data as a function of temperature, compression, flexure, shear, and constant-amplitude fatigue data at R = 0.1 and R = -1. Tensile specimens were aged in ovens where pressure and aging temperatures were controlled for various times up to and including 50,000 hours. Changes in tensile strength were determined and plotted as a function of aging time. The HT-S/710 composite aged at 450 F and 550 F if compared to the Celion 6000/LARC-160 composite aged at 350 F and 450 F. After tensile testing, many of the thermal aging specimens were examined using a scanning electron microscope. Results of these studies are presented, and changes in properties and degradation mechanisms during high-temperature aging are discussed and illustrated using metallographic techniques.
    Keywords: COMPOSITE MATERIALS
    Type: NASA. Lewis Research Center High Temp. Polymer Matrix Composites; p 315-327
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Time-temperature-stress capabilities of composite materials for advanced supersonic technology application, phase 1 (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Implementation of metal and resin matrix composites into supersonic vehicle usage is contingent upon accelerating the demonstration of service capacity and design technology. Because of the added material complexity and lack of extensive service data, laboratory replication of the flight service will provide the most rapid method of documenting the airworthiness of advanced composite systems. A program in progress to determine the time temperature stress capabilities of several high temperature composite materials includes thermal aging, environmental aging, fatigue, creep, fracture, and tensile tests as well as real time flight simulation exposure. The program has two parts. The first includes all the material property determinations and aging and simulation exposures up through 10,000 hours. The second continues these tests up to 50,000 cumulative hours. Results are presented of the 10,000 hour phase, which has now been completed.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-159267 , GDC-MAP-80-001
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Effects of 50,000 hours of thermal aging on graphite/epoxy and graphite/polyimide composites (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Thermal effects on tensile strengths of advanced composite systems have been determined for exposure times of 100 to 50,000 hours (5.7 years). Exposures were conducted at both ambient and reduced pressures at two temperatures for each composite. At the completion of the various aging periods, specimens were removed from the specially constructed aging furnaces, visually examined, and tensile tested at elevated temperature. After tensile testing, many of the thermal aging specimens were examined using a scanning electron microscope. Results of these studies are presented, and the changes in properties and the degradation mechanisms during high-temperature aging are discussed and illustrated using metallographic techniques.
    Keywords: COMPOSITE MATERIALS
    Type: AIAA PAPER 82-0657 , In: Structures, Structural Dynamics and Materials Conference; May 10, 1982 - May 12, 1982; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Flight simulation testing of advanced composites for supersonic cruise aircraft applications (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The goal of this program is to characterize advanced composite systems before and after exposures to simulated supersonic cruise environments for real times of up to 50,000 hours. Fatigue data for specimens tested at various temperatures and stress ratios are presented. The changes in properties and the degradation mechanisms during high temperature aging are discussed and illustrated using metallographic and fractographic techniques. Initial results of long term flight simulation tests are presented and compared with wearout model predictions based on accelerated flight simulation exposures.
    Keywords: COMPOSITE MATERIALS
    Type: AIAA PAPER 77-401 , Conference on Structures, Structural Dynamics and Materials; Mar 21, 1977 - Mar 23, 1977; San Diego, CA; US|Mar 24, 1977 - Mar 25, 1977
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Flight simulation testing equipment for composite material systems (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A test program is discussed which aims at establishing the time-temperature-stress characteristics of several classes of high-temperature composite materials in order to determine their suitability for applications in supersonic cruise aircraft. Five advanced composite materials (a boron epoxy, a boron polyimide, a graphite epoxy, a graphite polyimide, and diffusion-bonded boron aluminum) are being evaluated using a flight-test simulator capable of long-term automatic testing based on random loading and realistic flight temperature profiles. The design, construction, and checkout of this simulator are described along with the digital load programmer, load magnitude controllers, the hydraulic pumping system, the heating and cooling systems, the control console, and the data recording system. Typical results for short-term tests performed at constant temperatures and accelerated load rates are presented in terms of a random-load spectrum and a wearout model.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Environmental effects on advanced composite materials; Jun 22, 1975 - Jun 27, 1975; Montreal; Canada
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Program definition and preliminary results of a long-term evaluation program of advanced composites for supersonic cruise aircraft applications (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Advanced composites will play a key role in the development of the technology required for the design and fabrication of future supersonic vehicles. A program is in progress to determine the time-temperature-stress capabilities of several high-temperature composite materials. Tests included in this study are thermal aging, ambient aging, fatigue, creep, fracture, tensile, and real-time flight-simulation exposure. The program has two parts. The first includes all the material-property determinations and aging and simulation exposures up through 10,000 h. The second continues these tests up to 50,000 cumulative h. The program is currently in the midst of the 10,000-h phase. Some of the results obtained to date and the status of the various tests are discussed.
    Keywords: COMPOSITE MATERIALS
    Type: Environmental effects on advanced composite materials; Jun 22, 1975 - Jun 27, 1975; Montreal; Canada
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Time-temperature-stress capabilities of composites for supersonic cruise aircraft applications (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A range of baseline properties was determined for representatives of 5 composite materials systems: B/Ep, Gr/Ep, B/PI, Gr/PI, and B/Al. Long-term exposures are underway in static thermal environments and in ones which simultaneously combine programmed thermal histories and mechanical loading histories. Selected results from the environmental exposure studies with emphasis placed on the 10,000-hour thermal aging data are presented. Results of residual strength determinations and changes in physcial and chemical properties during high temperature aging are discussed and illustrated using metallographic, fractographic and thermomechanical analyses. Some initial results of the long-term flight simulation tests are also included.
    Keywords: COMPOSITE MATERIALS
    Type: Proc. on the SCAR Conf., Pt. 2,; 30 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    THE ALKALINE OXIDATION OF CELLULOSE. I. MECHANISM OF THE DEGRADATIVE OXIDATION OF CELLULOSE BY HYDROGEN PEROXIDE IN PRESENCE OF ALKALI (1950)
    American Chemical Society
    Details
    Publication Date: 1950-11-01
    Print ISSN: 0022-3263
    Electronic ISSN: 1520-6904
    Topics: Chemistry and Pharmacology
    Published by American Chemical Society
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