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  • DOT/FAA/AR-01/40 Office of Aviation Research Washington, D.C. 20591

    Determination of Temperature/ Moisture Sensitive Composite Properties September 2001 Final Report This document is available to the U.S. public through the National Technical Information Service (NTIS), Springfield, Virginia 22161.

    U.S. Department of Transportation Federal Aviation Administration

  • NOTICE

    This document is disseminated under the sponsorship of the U.S. Department of Transportation in the interest of information exchange. The United States Government assumes no liability for the contents or use thereof. The United States Government does not endorse products or manufacturers. Trade or manufacturer's names appear herein solely because they are considered essential to the objective of this report. This document does not constitute FAA certification policy. Consult your local FAA aircraft certification office as to its use. This report is available at the Federal Aviation Administration William J. Hughes Technical Center's Full-Text Technical Reports page: actlibrary.tc.faa.gov in Adobe Acrobat portable document format (PDF).

  • Technical Report Documentation Page

    1. Report No. DOT/FAA/AR-01/40

    2. Government Accession No. 3. Recipient's Catalog No.

    5. Report Date September 2001

    4. Title and Subtitle DETERMINATION OF TEMPERATURE/MOISTURE SENSITIVE COMPOSITE PROPERTIES 6. Performing Organization Code

    7. Author(s) John S.Tomblin, Lamia Salah, Yeow C. Ng

    8. Performing Organization Report No.

    9. Performing Organization Name and Address National Institute For Aviation Research Wichita State University

    10. Work Unit No. (TRAIS)

    1845 Fairmount Wichita, KS 67260-0093

    11. Contract or Grant No. IA031

    12. Sponsoring Agency Name and Address U.S. Department of Transportation Federal Aviation Administration

    13. Type of Report and Period Covered Final Report

    Office of Aviation Research Washington, DC 20591

    14. Sponsoring Agency Code

    ACE-110 15. Supplementary Notes The Federal Aviation Administration William J. Hughes Technical Center manager was Peter Shyprykevich. 16. Abstract An investigation of the temperature and moisture sensitive composite properties was conducted. Results provide an evaluation of the degree of conservatism of the 50F margin from glass transition values commonly used to determine a material systems operational limit (MOL). A series of dynamic mechanical analysis (DMA) and static mechanical tests were performed using specimens conditioned at three relative humidity levels and tested at six different temperatures for two commonly used 270F cure prepreg systems. This report documents the results obtained from the DMA and static mechanical tests from which moisture and temperature sensitive properties can be determined. Limitations of the scope of this project are addressed as a means of providing recommendations for future research. 17. Key Words Composite materials, Temperature, Moisture, Mechanical properties, Glass transition temperature

    18. Distribution Statement This document is available to the public through the National Technical Information Service (NTIS), Springfield, Virginia 22161.

    19. Security Classif. (of this report) Unclassified

    20. Security Classif. (of this page) Unclassified

    21. No. of Pages 73

    22. Price

    Form DOT F1700.7 (8-72) Reproduction of completed page authorized

  • TABLE OF CONTENTS Page

    EXECUTIVE SUMMARY xi

    1. INTRODUCTION 1

    1.1 Purpose 1 1.2 Background 1

    2. TECHNICAL PROCEDURE 4

    3. RESULTS 5

    3.1 Zero Percent Relative Humidity 5

    3.1.1 Mechanical Test Results 5 3.1.2 DMA Test Results 11

    3.2 Sixty-Eight Percent Relative Humidity 11

    3.2.1 Mechanical Test Results 11 3.2.2 DMA Test Results 17

    3.3 Eighty-Five Percent Relative Humidity 17

    3.3.1 Mechanical Test Results 17 3.3.2 DMA Test Results 23

    3.4 Summary 23

    4. TEMPERATURE EFFECTS ON THE MECHANICAL PROPERTIES 24

    5. MOISTURE EFFECTS ON THE MECHANICAL PROPERTIES 28

    6. GLASS TRANSITION TEMPERATURE AND 50F MARGIN 36

    7. TWO-THIRD RETENTION METHOD 42

    8. CONCLUSIONS AND RECOMMENDATIONS 56

    9. REFERENCES 57

    APPENDIX ABASIC PRINCIPLES OF DYNAMIC MECHANICAL ANALYSIS

    iii

  • LIST OF FIGURES Figure Page

    1 Evaluation of the Mol Using Tg and Mechanical Data 3

    2 Variation of In-Plane Shear Strength Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (0% RH) 6

    3 Variation of Compression Strength Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (0% RH) 6

    4 Variation of Open-Hole Compression Strength Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (0% RH) 7

    5 Variation of In-Plane Shear Modulus Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (0% RH) 7

    6. Variation of Compression Modulus Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (0% RH) 8

    7 Variation of In-Plane Shear Strength Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (0% RH) 8

    8 Variation of Compression Strength Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (0% RH) 9

    9 Variation of Open-Hole Compression Strength Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (0% RH) 9

    10 Variation of In-Plane Shear Modulus Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (0% RH) 10

    11 Variation of Compression Modulus Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (0% RH) 10

    12 Variation of In-Plane Shear Strength Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (68% RH) 12

    13 Variation of Compression Strength Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (68% RH) 12

    14 Variation of Open-Hole Compression Strength Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (68% RH) 13

    15 Variation of In-Plane Shear Modulus Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (68% RH) 13

    iv

  • 16 Variation of Compression Modulus Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (68% RH) 14

    17 Variation of In-Plane Shear Strength Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (68% RH) 14

    18 Variation of Compression Strength Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (68% RH) 15

    19 Variation of Open-Hole Compression Strength Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (68% RH) 15

    20 Variation of In-Plane Shear Modulus Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (68% RH) 16

    21 Variation of Compression Modulus Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (68% RH) 16

    22 Variation of In-Plane Shear Strength Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (85% RH) 18

    23 Variation of Compression Strength Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (85% RH) 18

    24 Variation of Open-Hole Compression Strength Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (85% RH) 19

    25 Variation of In-Plane Shear Modulus Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (85% RH) 19

    26 Variation of Compression Modulus Values as a Function of Temperature for Newport 7781/NB321 Glass Fabric Material System (85% RH) 20

    27 Variation of In-Plane Shear Strength Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (85% RH) 20

    28 Variation of Compression Strength Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (85% RH) 21

    29 Variation of Open-Hole Compression Strength Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (85% RH) 21

    30 Variation of In-Plane Shear Modulus Values as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Material System (85% RH) 22

    31 Variation of Compression Modulus Values as a Function of Temperature for FiberCote E 765/T300 3KPW Material System (85% RH) 22

    v

  • 32 Variation in the Percentage of Mechanical Properties as a Function of Temperature for Newport 7781/NB321 Glass Fabric Dry Specimens 25

    33 Variation in the Percentage of Mechanical Properties as a Function of Temperature for Newport 7781/NB321 Glass Fabric Specimens Conditioned at 68% RH 25

    34 Variation in the Percentage of Mechanical Properties as a Function of Temperature for Newport 7781/NB321 Glass Fabric Specimens Conditioned at 85% RH 26

    35 Variation in the Percentage of Mechanical Properties as a Function of Temperature for FiberCote E 765/T300 3KPW Carbon Fabric Specimens Conditioned at 0% RH 26

    36 Variation in the Percentage of Mechanical Properties as a Function of Temperature f