Advanced General Aviation Transport Experiments

Transcription

1 Advanced General Aviation Transport Experiments B Basis Design Allowables for Epoxy Based Prepreg 3M E-Glass Fabric 7781 / SP381 AGATE-WP September 2001 J. Tomblin, J. McKenna, Y. Ng, K. S. Raju National Institute for Aviation Research Wichita State University Wichita, KS

2 TABLE OF CONTENTS 1.0 INTRODUCTION Scope Symbols Used Acronyms and Definitions References Methodology Test Matrix Environmental Conditioning Normalization Procedures Statistical Analysis Material Performance Envelope and Interpolation Interpolation Example M 7781 E-GLASS / SP381 PREPREG PROPERTIES Prepreg Documentation by Prepreg Lot Process Specification M 7781 E-GLASS / SP381 LAMINATE PROPERTIES Test Results Summary Individual Test Summaries Tension, Laminate Compression, Laminate Shear, 12 axis Shear, 13 axis Individual Test Charts Tension, Laminate Compression, Laminate Shear, 12 axis Shear, 13 axis Raw Data Raw Data Spreadsheets and Scatter Charts Representative Shear Stress-Strain Curve Statistical Results Plot by Condition Plot of Pooled Data

3 3.4 Moisture Conditioning History Charts Physical Test Results Testing and Reporting Comments

4 1.0 INTRODUCTION 1.1 Scope The Advanced General Aviation Transport Experiments (AGATE) consortium is an industry-university-government partnership initiated by NASA to create the technological basis for revitalization of the United States general aviation industry. It was founded in 1994 to develop affordable new technology as well as the industrial standards and certification methods for composite airframe, cockpit, flight systems and airspace infrastructure for Federal Aviation Regulations (FAR) Part 23 aircraft. The composite material properties contained within the document were generated under Work Package 3 : Integrated Design and Manufacturing Methods. Although AGATE was focused towards the small general aviation aircraft (Part 23), the test methods and results contained in this document are consistent with MIL-HDBK-17-1E,2D,3E - Military Handbook for Polymer Matrix Composites. All material, specimens, fixtures and test results contained within this document were traceable and conformed by the Federal Aviation Administration (FAA) as part of the AGATE effort. It should be noted that before application of the basis values presented in this document to design, demonstration of the ability to consistently produce equivalent material properties as that evaluated during this program should be substantiated through an acceptable test program. The test methods and results described in this document are intended to provide basic composite properties essential to most methods of analysis. These properties are considered to provide the initial base of the building block approach. Additional coupon level tests and subelement tests may be required to fully substantiate the full-scale design. 5

5 1.2 Symbols Used major Poisson s ratio, tension µε micro-strain E c compressive modulus, laminate E t tensile modulus, laminate su F 12 in plane shear strength su F 13 apparent interlaminar shear strength F cu compressive strength, laminate F tu tensile strength, laminate in plane shear modulus ν 12 tu G 12 s Superscripts c cu s su t tu compression compression ultimate shear shear ultimate tension tension ultimate Subscripts 12 in plane shear 13 interlaminar shear (apparent) 6

6 1.3 Acronyms and Definitions A Basis 95% lower confidence limit on the first population percentile AGATE Advanced General Aviation Transport Experiments ASTM American Society for Testing and Materials B Basis 95% lower confidence limit on the tenth population percentile C. V. coefficient of variation CTD cold temperature dry CPT cured ply thickness DMA dynamic mechanical analysis dry specimen tested with an as fabricated moisture content ETD elevated temperature dry ETW elevated temperature wet FAR Federal Aviation Regulations FAW fiber areal weight Gl/Ep Glass-Epoxy NASA National Aeronautics and Space Administration RTD room temperature dry SACMA Suppliers of Advanced Composite Materials Association SRM SACMA Recommended Method T g glass transition temperature t ply cured ply thickness wet specimen tested with an equilibrium moisture content per section

7 1.4 References ASTM Standards D Tensile Properties of Polymer Matrix Composite Materials D Shear Properties of Composite Materials by the V-Notched Beam Method D Apparent Interlaminar Shear Strength of Parallel Fiber Composites by Short Beam Method D Density and Specific Gravity (Relative Density) of Plastics by Displacement D Ignition Loss of Cured Reinforced Plastics D Void Content of Reinforced Plastics D Compressive Properties of Rigid Plastics SACMA Standards SRM 1-94 SRM 8-94 SRM Compressive Properties of Oriented Fiber-Resin Composites Short Beam Shear Strength of Oriented Fiber-Resin Composites Glass Transition Temperature (T g ) Determination by DMA of Oriented Fiber-Resin Composites Other Documents FAA Document DOT/FAA/AR-00/47: Material Qualification and Equivalency for Polymer Matrix Composite Material Systems, J.S. Tomblin, Y.C. Ng and K.S. Raju, MIL-HDBK-17 1E, 2D, 3E Military Handbook for Polymer Matrix Composites Cirrus Design Corporation: Material Properties Test Plan, February

8 1.5 Methodology Test Matrix Testing was performed according to the test methods delineated in the test matrix, with modifications as referenced in the AGATE report, Material Qualification and Equivalency for Polymer Matrix Composite Material Systems. The test matrix for properties included in this document is listed on the next page, with the following notation cited in each column: # x # where the first # represents the required number of prepreg batches, defined as: Prepreg containing 7781 E-Glass Fabric from one mill roll, impregnated with one batch of resin in one continuous manufacturing operation with traceability to all components. The second # represents the required number of replicates per prepreg batch. For example, 3 x 6 refers to three prepreg batches of material and six specimens per prepreg batch for a total requirement of 18 test specimens. 9

9 Table 1.5.1: Test Matrix and Standards Used TEST METHOD NO. OF REPLICATES PER TEST CONDITION CTD 1 RTD 2 ETW 3 ETW 4 ETD 5 Laminate Tension ASTM D Strength 1x3 5x8 5x8 3x4 3x4 Laminate Tension ASTM D Modulus, Strength and 1x3 5x3 5x3 3x2 3x2 Poisson s Ratio Laminate Compression SACMA SRM 1-94 Strength 1x6 5x11 5x11 3x6 3x4 Laminate Compression SACMA SRM 1-94 Modulus --- 1x11 1x11 3x2 3x2 In-Plane Shear Strength ASTM D x3 5x8 5x8 3x4 3x6 In-Plane Shear Modulus ASTM D and Strength 1x3 5x3 5x3 3x2 3x2 Short Beam Shear ASTM D x Fiber Volume ASTM D One sample per panel Resin Volume ASTM D One sample per panel Void Content ASTM D One sample per panel Cured Neat Resin --- Density Supplied by manufacturer for material Glass Transition Temperature SACMA SRM x5 dry, 1x5 wet Notes : 1 CTD: One prepreg lot of material tested (test temperature = -65 ± 5 o F, moisture content = as fabricated, soak time at 65 was 3 min.) 2 RTD: Three prepreg lots of material tested (test temperature = 70 ± 10 o F, moisture content = as fabricated) 3 ETW: Three prepreg lots of material tested (test temperature = 150 ± 5 o F, moisture content = equilibrium per section 1.5.2, soak time at 150 was 60 sec.) 4 ETW: Three prepreg lots of material tested (test temperature = 180 ± 5 o F, moisture content = as fabricated, soak time at 180 was 2-3 min.) 5 ETD: Three prepreg lots of material tested (test temperature = 150 ± 5 o F, moisture content = as fabricated, soak time at 150 was 2-3 min.) 10

10 1.5.2 Environmental Conditioning All wet conditioned samples were exposed to elevated temperature and humidity conditions to establish moisture saturation of the material. Specimens were exposed to 85 ± 5 % relative humidity and 145 ± 5 F until an equilibrium moisture weight gain of traveler, or witness coupons (1 x 1 x specimen thickness) was achieved. ASTM D5229 and SACMA SRM 11 were used as guidelines for environmental conditioning and moisture absorption. Effective moisture equilibrium was achieved when the average moisture content of the traveler specimen changed by less than 0.05% for two consecutive readings within a span of 7 ± 0.5 days and was expressed by: W i -W W b i - 1 < where W i = weight at current time W i-1 = weight at previous time W b = baseline weight prior to conditioning It is common to see small fluctuations in an unfitted plot of the weight gain vs. time curve. There were no fluctuations that made significant errors in results or caused rejection in the moisture equilibrium criteria. Once the traveler coupons passed the criteria for two consecutive readings, the samples were removed from the environmental chamber and placed in a sealed bag with a moist paper or cotton towel for a maximum of 14 days until mechanical testing. Strain gauged specimens were removed from the controlled environment for a maximum of 2 hours for application of gages in ambient laboratory conditions Normalization Procedures The normalization procedure attempts to reduce variability in fiber-dominated material properties by adjusting raw test values to a specified fiber volume content. Only the following properties were normalized: Laminate Tensile Strength and Modulus Laminate Compression Strength and Modulus The normalization procedure was adopted from MIL-HDBK-17-1E, section The procedure which was used to normalize the data is based on two primary assumptions: 11

11 The relationship between fiber volume fraction and ultimate laminate strength is linear over the entire range of fiber/resin ratios. (It neglects the effects of resin starvation at high fiber contents.) Fiber volume is not commonly measured for each test sample, so this method accounts for the fiber volume variation between individual test specimens by utilizing a relationship between fiber volume fraction and laminate cured ply thickness. This relationship is virtually linear in the 0.45 to 0.65 fiber volume fraction range. Additional information is detailed in FAA Document DOT/FAA/AR-00/47: Material Qualification and Equivalency for Polymer Matrix Composite Material Systems. For all normalized data contained in this document, the test values are normalized by cured ply thickness according to: where: CPT Normalized Value = Test Value CPT specimen normalizing Average Sample Thickness CPT specimen = # of plies Statistical Analysis When compared to metallic materials, fiber reinforced composite materials exhibit a high degree of material property variability. This variability is due to many factors, including but not limited to: raw material and prepreg manufacture, material handling, part fabrication techniques, ply stacking sequence, environmental conditions, and testing techniques. This inherent variability drives up the cost of composite testing and tends to render smaller data sets than those produced for metallic materials. This necessitates the usage of statistical techniques for determining reasonable design allowables for composites. The analyses and design allowable generation for both A and B basis values were performed using the procedure detailed in section 5.3 of FAA Document DOT/FAA/AR- 00/47: Material Qualification and Equivalency for Polymer Matrix Composite Material Systems. 12

12 1.5.5 Material Performance Envelope and Interpolation Using the B-basis numbers, a material performance envelope may be generated for the material system by plotting these values as a function of temperature. Figure shows an example material performance envelope using B-basis values. 120 Actual Basis Value Estimated Value 100 B-Basis Strength Values (ksi) CTD Material Performance Envelope RTD RTW ETD ETW Temperature ( o F) Figure Material performance envelope. Since each specific aircraft application of the qualified material may have different Material Operational Limits (MOL) than those tested in the material qualification (which is usually the upper limit), some applications may require a reduced MOL. In this case, simple linear interpolation may be used to obtain the corresponding basis values at the new application MOL. This interpolation may be accomplished using the following simple relationships assuming T RTD < T MOL < T ETD : For the corresponding MOL dry basis value, the interpolated basis value using the qualification data is 13

13 B MOL = B RTD ( BRTD BETD ) ( TRTD TMOL ) ( T T ) RTD ETD where B MOL = new application basis value interpolated to T MOL B RTD = basis RTD strength value B ETD = basis ETD strength value T RTD = RTD test temperature T ETD = ETD test temperature T MOL = new application MOL temperature For the corresponding MOL wet basis value, an estimated Room Temperature Wet (RTW) value must be calculated. This may be accomplished by the simple relation B RTW = B RTD ( B BETW ) ETD The interpolated wet basis value using the qualification data may then be obtained by B MOL = B RTW ( BRTW BETW )( TRTW TMOL ) ( T T ) RTW ETW where: B MOL = new application basis value interpolated to T MOL B RTW = estimated basis RTW strength value B ETW = basis ETW strength value T RTW = RTW (i.e., RTD) test temperature T ETW = ETW test temperature T MOL = new application MOL temperature These equations may also be used for interpolated mean strengths as well as A-basis values with the appropriate substitutions. It should be noted that because unforeseen material property drop-offs with respect to temperature and environment can occur, extrapolation to a higher MOL should not be attempted without additional testing and verification. In addition, the interpolation equations shown above are practical for materials obeying typical mechanical behavior. In most cases, some minimal amount of testing may also be required to verify the interpolated values. 14

14 Interpolation Example This section provides an example of linear interpolations to a specific application environment less than the tested upper material limit used in qualification. Assuming a specific application environment of 150 o F, Figure depicts the linear interpolation of the B-basis design allowable to this environment. Using the above equations along with the nominal testing temperatures (see Table 1.5.1), the interpolated basis values at 150 o F become ETD : B MOL = ksi ETW : B MOL = ksi 120 Actual Basis Value Estimated Value 100 CTD RTD B-Basis Strength Values (ksi) RTW ETD ETW Temperature ( o F) Figure Example of 150 o F interpolation for B-basis values. 15

15 2.0 3M 7781 E-GLASS / SP381 PREPREG PROPERTIES 16

16 2.1 Prepreg Documentation by Prepreg Lot Batch ID - AGATE Prepreg Documentation Prepreg Manufacturer & Product ID: 3M 7781 / SP381 Material Identification (weave, form, class, etc.): SP 381 OST FAW 38RC Impregnation Method: hot melt Prepreg Batch or Lot # 106A2 126A 7001A7 7002A7 7006A7 7007G7 7009J7 7008H7 Date of Manufacture 10/30/96 12/16/96 1/29/97 1/30/97 4/30/97 7/18/97 9/16/97 8/7/97 Expiration Date 10/30/97 12/16/97 1/29/98 1/30/98 4/30/98 7/18/98 9/16/98 8/7/98 Resin Content [%] Reinforcement Areal Weight [gsm] & Test Method Cirrus spec GEK0101 method Resin Flow [%] 23.1 N/A & Test Conditions Cirrus spec GEK0101 method Gel Time [min] & Test Conditions Cirrus spec GEK0101 method Volatile Content N/A Reinforcement Documentation Fabric Batch or Lot # Fiber/Fabric Manufacturer & Product ID: 7781 E-glass BGF 8HS Finish/Sizing Type and %: 497A ; % Nominal tow or yarn count/inch: Warp 58, Fill / / / // / / / Date of Manufacture 9/24/96 12/2/96 1/21/97 1/20/97 2/17/97 4/21/97 4/21/97 5/5/97 Average Fiber Density & Test Method Typical value = 2.60 (specific gravity) N/A by lot Matrix Documentation Resin Manufacturer & Product ID: PM / Matrix Batch or Lot # 19K6P 210M6R 97212A 97211A 7216D7 7217E7 7219J7 7218G7 Date of Manufacture 10/96 12/96 1/97 1/97 4/97 5/97 9/97 7/97 Average Neat Resin Density by Lot & Test Method Typical value = g/cc (ASTM D792) N/A by lot 17

17 2.2 Process Specification This specification does not address issues relating to safety, quality control, bagging material selection, bagging procedure, tool preparation, or equipment selection. Although these may affect overall part quality, it is the responsibility of the end user to develop procedures related to these issues in a manner that produces parts with high quality and consistency. The following oven cure procedures are excerpts from Cirrus Design Corporation GEP0001 Rev. C specification, Manufacture of Glass-Fiber Prepreg Assemblies, 260 F Cure. All test specimens were cured per this specification by Cirrus Design Corporation. However, the effects of the upper and lower limits of vacuum, temperature, cure time, heat-up rate and hold temperature on the mechanical and thermal properties have not been investigated. Prior to Cure Unitape orientation angle shall be within ±3 of the specified orientation. Before placing a bagged assembly in the oven, apply at least 22 Hg vacuum and check for bag leaks. Bag leaks greater than 3.0 Hg during 5 minutes shall be corrected. Debulk shall be performed every ten layers, or more frequently if required. Oven Cure Procedure The maximum air temperature of the oven prior to loading is 160 F. Connect the calibrated thermocouples to the parts, allowing at least one thermocouple per part. The temperature of the part must be 150 F or less before removing from the oven Cure all prepreg parts according to the following cure cycle chart. 18

18 Figure 2.1: Sample prepreg cure cycle for SP381 / 7781 E-glass. Figure courtesy of Cirrus Design Corporation. 19

19 3.0 3M 7781 E-GLASS / SP381 LAMINATE PROPERTIES Note: The mechanical properties included in this document do not represent true lamina (ply) properties due to the fabric orientation of the samples tested. Therefore, the term laminate is used throughout the document for clarity. 20

20 3.1 Test Results 21

21 3.1.1 Summary 22

22 MATERIAL: SP381/7781 E-Glass Cloth Date of fiber manufacture: 9/96-5/97 FIBER: BGF 7781 RESIN: 3M SP381 Date of resin manufacture: 10/96-7/97 PREPEG: 3M SP381/7781 E-glass Cloth; 497A finish, % sizing Date of prepeg manufacture: 10/96-8/97 T g (dry): F T g (wet): F T g METHOD: DMA(SRM 18-94) Date of composite manufacture:2/97-1/98 Date of testing: 4/97-9/98 PROCESSING: vacuum bag cure (22+ in Hg) F for min. Date of analysis: 5/98-9/98 SP381/7781 Summary LAMINATE MECHANICAL PROPERTY SUMMARY Data Reported as: Measured (Normalized by CPT = in.) CTD (-65 F) RTD ETD (180 F) ETW (150 F) ETW (180 F) B-Basis Mean A-Basis B-Basis Mean B-Basis Mean A-Basis B-Basis Mean B-Basis Mean F tu (ksi) (58.01) (64.84) (52.06) (55.65) (60.64) (50.24) (55.24) (42.65) (45.60) (49.66) (40.95) (45.02) E t (Msi) (3.59) (3.61) (3.30) (3.31) (3.29) n 12 tu F cu (ksi) (80.68) (91.58) (63.43) (68.48) (75.50) (57.25) (63.77) (48.00) (51.82) (57.14) (44.76) (49.30) E c (Msi) (3.66) (3.64) (3.54) (3.54) F 12 su (ksi) G 12 s (Msi) F13 su ** (ksi) **Apparent interlaminar shear strength 23

23 3.1.2 Individual Test Summaries 24

24 Tension, Laminate Material: 3M SP381/7781 E-glass cloth Resin content: wt.% Comp. density: g/cc Fiber volume: % Void content: % Ply thickness: in. Ply range: 11 ply Tension, Laminate Gl/Ep 3M SP381/7781 E-glass cloth [(0 f /90 f ) 2 /0 f /90 f /0 f /(90 f /0 f ) 2 ] Test method: D Modulus calculation: linear fit from µε Normalized by: in. ply thickness CTD RTD ETD ETW ETW Test Temperature [ F] Moisture Conditioning dry dry dry equilibrium equilibrium Equilibrium at T, RH as fabricated as fabricated as fabricated 145 F, 85 % 145 F, 85 % Source code LAUXXXXB LAUXXXXA LAUXXXXG LAUXXXXC LAUXXXXF Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Mean Minimum Maximum C.V.(%) F tu B-value (ksi) A-value No. Specimens No. Prepreg Lots Mean Minimum Maximum E t C.V.(%) (Msi) No. Specimens No. Prepreg Lots n 12 t Mean No. Specimens No. Prepreg Lots

25 Compression, Laminate Material: 3M SP381/7781 E-glass cloth Resin content: wt.% Comp. density: g/cc Fiber volume: % Void content: % Ply thickness: in. Ply range: ply Compression, Laminate Gl/Ep 3M SP381/7781 E-glass cloth [(0 f /90 f ) 3 /0 f /(90 f /0 f ) 3 ] Test method: SRM 1-94, D (mod) Modulus calculation: linear fit from µε Normalized by: in. ply thickness CTD RTD ETD ETW ETW Test Temperature [ F] Moisture Conditioning dry dry dry equilibrium equilibrium Equilibrium at T, RH as fabricated as fabricated as fabricated 145 F, 85 % 145 F, 85 % Source code LAKXXXXB LAKXXXXA LAKXXXXG LAKXXXXC LAKXXXXF Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Mean Minimum Maximum C.V.(%) F cu B-value (ksi) A-value No. Specimens No. Prepreg Lots Mean Minimum Maximum E c C.V.(%) (Msi) No. Specimens No. Prepreg Lots

26 Shear, 12 axis Material: 3M SP381/7781 E-glass cloth Resin content: wt.% Comp. density: g/cc Fiber volume: % Void content: % Ply thickness: in. Ply range: ply Shear, 12-axis Gl/Ep 3M SP381/7781 E-glass cloth [(0 f /90 f ) 3 /0 f /90 f /0 f /(90 f /0 f ) 3 ] Test method: D Modulus calculation: linear fit from µε Normalized by: N/A CTD RTD ETD ETW ETW Test Temperature [ F] Moisture Conditioning dry dry dry equilibrium equilibrium Equilibrium at T, RH as fabricated as fabricated as fabricated 145 F, 85 % 145 F, 85 % Source code LANXXXXB LANXXXXA LANXXXXG LANXXXXC LANXXXXF Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Mean Minimum Maximum C.V.(%) F 12 su B-value (ksi) A-value G 12 s (Msi) No. Specimens No. Prepreg Lots Mean Minimum Maximum C.V.(%) No. Specimens No. Prepreg Lots

27 Shear, 13 axis Material: 3M SP381/7781 E-glass cloth Resin content: wt.% Comp. density: g/cc Fiber volume: % Void content: % Ply thickness: in. Ply range: 14 ply Shear, 13-axis Gl/Ep 3M SP381/7781 E-glass cloth [(0 f /90 f ) 3 /(0 f ) 2 /(90 f /0 f ) 3 ] Test method: D Modulus calculation: N/A Normalized by: N/A RTD Test Temperature [ F] Moisture Conditioning Equilibrium at T, RH Source code 75 dry as fabricated LAQXXXXA Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Mean 8.36 Minimum 7.69 Maximum 8.98 C.V.(%) 4.24 F 13 su B-value 7.71 (ksi) A-value 7.24 No. Specimens No. Prepreg Lots 25 3 NOTES: These values represent the apparent interlaminar shear properties and are to be used for quality control purposes only. Do not use these values for interlaminar shear strength design values. 28

28 3.1.3 Individual Test Charts 29

29 Tension, Laminate Laminate Tension -- Normalized Strength Strength (ksi) Conditioning X Dry O Wet Temperature ( F) NOTE: The symbols represent the pooled average of all tests, and the bars represent the upper and lower limit of the data. 30

30 Compression, Laminate 120 Laminate Compression -- Normalized Strength 100 Strength (ksi) Conditioning X Dry O Wet Temperature ( F) NOTE: The symbols represent the pooled average of all tests, and the bars represent the upper and lower limit of the data. 31

31 Shear, 12 axis In-Plane Shear -- Measured Strength Strength (ksi) Conditioning O Wet X Dry Temperature ( F) NOTE: The symbols represent the pooled average of all tests, and the bars represent the upper and lower limit of the data. 32

32 Shear, 13 axis Apparent Interlaminar Shear -- Measured Strength Strength (ksi) Conditioning X Dry O Wet Temperature ( F) NOTE: The symbols represent the pooled average of all tests, and the bars represent the upper and lower limit of the data. 33

33 3.2 Raw Data Specimen Naming Convention Test coupons were identified using an eight-digit specimen code, with the significance of each digit delineated below. A representative sample ID is shown for reference purposes. L A J F 1 st Character: Fabricator L designates Cirrus 2 nd Character: Material System A designates 7781 E-glass / SP381 3 rd Character: Test Type J designates 0 Tension Strength and Modulus, other test types will be clearly labeled at the top of each sheet 4 th Character: Prepreg Batch ID See Table 2.1 for Cirrus Batch ID / Sample Batch ID correlation. 5 th Character: Panel Number The panel(s) fabricated for a specific test method. 6 th Character: Subpanel Number The sub-panel(s) cut from each panel, with subpanel numbers labeled increasing from reference edge. 7 th Character: Sample Number The sample(s) cut from each subpanel, with sample numbers labeled increasing from reference edge. 8 th Character: Test Condition A --- RTD B --- CTD C --- ETW, 150 F F --- ETW, 180 F G --- ETD, 180 F See Table for condition parameters. 34

34 3.2.1 Raw Data Spreadsheets and Scatter Charts 35

35 Laminate Tension -- (RTD) Strength & Modulus normalizing t ply [in] Specimen Batch Strength Modulus Poisson's Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Number [ksi] [Msi] Ratio Thickn. [in] Laminate [in] [ksi] [Msi] LAU2111A LAU2112A LAU2113A LAU2714A LAU2715A LAU2121A LAU2122A LAU2123A LAU2124A LAU2125A LAU2126A LAU3311A LAU3312A LAU3313A LAU3314A LAU3315A LAU3316A LAU3321A LAU3322A LAU3323A LAU3324A LAU3326A LAU4221A LAU4222A LAU4223A LAU4224A LAU4311A LAU4312A LAU4321A LAU4322A LAU4323A LAU4324A LAU4325A LAU5311A LAU5321A LAU5322A LAU5323A LAU5324A LAU5325A LAU5411A LAU5412A LAU5413A LAU5414A LAU5415A LAU6111A LAU6112A LAU6113A LAU6114A LAU6115A LAU6121A LAU6122A LAU6123A LAU6124A LAU6125A LAU6211A Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min. Value Min. Value norm Max. Value Max. Value norm Number of Spec Number of Spec. norm

36 Laminate Tension -- (RTD) Normalized Strength Pooled Average = [ksi] Pooled Standard Deviation = [ksi] Pooled Coeff. of Variation = [%] Batch # Laminate Tension Strength Strength [ksi] Laminate Tension -- (RTD) Normalized Modulus Pooled Average = [Msi] Pooled Standard Deviation = [Msi] Pooled Coeff. of Variation = [%] Batch # Laminate Tension Strength Modulus [Msi] 37

37 Laminate Tension -- (CTD) Strength & Modulus normalizing t ply [in] Specimen Batch Strength Modulus Poisson's Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Number [ksi] [Msi] Ratio Thickn. [in] Laminate [in] [ksi] [Msi] LAU2721B LAU2722B LAU2723B LAU2724B LAU2715B LAU2716B Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min. Value Min. Value norm Max.Value Max. Value norm Number of Spec Number of Spec. norm

38 Laminate Tension -- (CTD) Normalized Strength Pooled Average = [ksi] Pooled Standard Deviation = [ksi] Pooled Coeff. of Variation = [%] Batch # Laminate Tension Strength [ksi] Laminate Tension -- (CTD) Normalized Modulus Pooled Average = [Msi] Pooled Standard Deviation = [Msi] Pooled Coeff. of Variation = [%] Batch # LaminateTension Modulus [Msi] 39

39 Laminate Tension -- (ETW ) Strength & Modulus normalizing t ply [in] Specimen Batch Strength Modulus Poisson's Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Number [ksi] [Msi] Ratio Thickn. [in] Laminate [in] [ksi] [Msi] LAU2811C LAU2812C LAU2821C LAU2822C LAU2823C LAU2824C LAU2825C LAU2911C LAU2912C LAU2913C LAU2914C LAU2915C LAU2921C LAU2922C LAU2923C LAU2924C LAU2925C LAU3111C LAU311XC LAU3113C LAU3114C LAU3115C LAU3116C LAU3411C LAU3412C LAU3413C LAU3414C LAU3415C LAU4111C LAU4112C LAU4113C LAU4114C LAU4115C LAU4121C LAU4122C LAU4123C LAU4124C LAU4125C LAU4212C LAU5111C LAU5112C LAU5113C LAU5114C LAU5115C LAU5121C LAU5122C LAU5123C LAU5124C LAU5125C LAU5221C LAU7114C LAU7122C LAU7123C LAU7124C LAU7125C LAU7215C LAU7221C LAU7222C LAU7223C LAU7224C Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min. Value Min. Value norm

40 Laminate Tension -- (ETW ) Normalized Strength Pooled Average = [ksi] Pooled Standard Deviation = [ksi] Pooled Coeff. of Variation = [%] Batch # Laminate Tension Strength [ksi] Laminate Tension -- (ETW ) Normalized Modulus Pooled Average = [Msi] Pooled Standard Deviation = [Msi] Pooled Coeff. of Variation = [%] Batch # Laminate Tension Modulus [Msi] 41

41 Laminate Tension -- (ETW ) Strength & Modulus normalizing t ply [in] Specimen Batch Strength Modulus Poisson's Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Number [ksi] [Msi] Ratio Thickn. [in] Laminate [in] [ksi] [Msi] LAU6212F LAU6213F LAU6221F LAU6222F LAU6223F LAU6224F LAU7111F LAU7113F LAU7115F LAU7211F LAU7212F LAU7213F LAU8111F LAU8112F LAU8113F LAU8114F LAU8115F LAU8221F Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min. Value Min. Value norm Max. Value Max. Value norm Number of Spec Number of Spec. norm

42 Laminate Tension -- (ETW ) Normalized Strength Pooled Average = [ksi] Pooled Standard Deviation = [ksi] Pooled Coeff. of Variation = [%] Batch # Laminate Tension Strength [ksi] Batch # Laminate Tension -- (ETW ) Normalized Modulus Laminate Tension Modulus [Msi] Pooled Average = [Msi] Pooled Standard Deviation = [Msi] Pooled Coeff. of Variation = [%] 43

43 Laminate Tension -- (ETD ) Strength & Modulus normalizing t ply [in] Specimen Batch Strength Modulus Poisson's Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Number [ksi] [Msi] Ratio Thickn. [in] Laminate [in] [ksi] [Msi] LAU6411G LAU6412G LAU6413G LAU6421G LAU6422G LAU6423G LAU7111G LAU7112G LAU7113G LAU7114G LAU7115G LAU7221G LAU8121G LAU8122G LAU8123G LAU8124G LAU8211G LAU8212G Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min. Value Min. Value norm Max. Value Max. Value norm Number of Spec Number of Spec. norm

44 Laminate Tension -- (ETD ) Normalized Strength Pooled Average = [ksi] Pooled Standard Deviation = [ksi] Pooled Coeff. of Variation = [%] Batch # Laminate Tension Strength [ksi] Laminate Tension -- (ETD ) Normalized Modulus Pooled Average = [Msi] Pooled Standard Deviation = [Msi] Pooled Coeff. of Variation = [%] Batch # Laminate Tension Modulus [Msi] 45

45 Laminate Compression -- (RTD) Strength & Modulus normalizing t ply [in] Specimen Batch Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Number [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] LAK1142A LAK1143A LAK1151A LAK1152A LAK1153A LAK1154A LAK1155A LAK1111A LAK1112A LAK1113A LAK1114A LAK2111A LAK2112A LAK2113A LAK2114A LAK2115A LAK2116A LAK2117A LAK2118A LAK2119A LAK2131A LAK2132A LAL2131A LAL2132A LAL2133A LAL2134A LAL2135A LAL2136A LAL2137A LAL2138A LAL2139A LAL213AA LAL213BA LAK3141A LAK3142A LAK3143A LAK3144A LAK3145A LAK3146A LAK3147A LAK3148A LAK3149A LAK3113A LAK3114A LAK4121A LAK4122A LAK4123A LAK4124A LAK4125A LAK4126A LAK4127A LAK4128A LAK4141A LAK4142A LAK4143A LAK5211A LAK5212A LAK5213A LAK5214A LAK5215A LAK5221A LAK5222A LAK5231A LAK5232A LAK5233A LAK5234A Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min. Value Min. Value norm Max. Value Max. Value norm Number of Spec Number of Spec. norm

46 Laminate Compression -- (RTD) Normalized Strength Pooled Average = [ksi] Pooled Standard Deviation = [ksi] Pooled Coeff. of Variation = [%] Batch # Laminate Compression Strength [ksi] Laminate Compression -- (RTD) Normalized Modulus Pooled Average = [Msi] Pooled Standard Deviation = [Msi] Pooled Coeff. of Variation = [%] Batch # Laminate Compression Modulus [Msi] 47

47 Laminate Compression -- (CTD) Strength normalizing t ply [in] Specimen Batch Strength Avg. Specimen # Plies in Avg. t ply Strength norm Number Number [ksi] Thickn. [in] Laminate [in] [ksi] LAK2144B LAK2145B LAK2146B LAK2147B LAK2148B LAK2149B Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min. Value Min. Value norm Max. Value Max. Value norm Number of Spec. 6 Number of Spec. norm 6 48

48 7 Laminate Compression -- (CTD) Normalized Strength Pooled Average = [ksi] Pooled Standard Deviation = [ksi] Pooled Coeff. of Variation = [%] 6 Batch # Laminate Compression Strength [ksi] 49

49 Laminate Compression -- (ETW ) Strength & Modulus normalizing t ply [in] Specimen Batch Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Number [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] LAK1112C LAK1113C LAK1114C LAK1115C LAK1121C LAK1122C LAK1141C LAK1142C LAK1143C LAK1144C LAK1145C LAK2121C LAK2122C LAK2123C LAK2124C LAK2125C LAK2126C LAK2127C LAK2128C LAK2129C LAK212AC LAK2131C LAL2111C LAL2112C LAL2113C LAL2114C LAL2115C LAL2116C LAL2117C LAL2118C LAL2119C LAL2121C LAL2122C LAK3121C LAK3122C LAK3123C LAK3124C LAK3125C LAK3126C LAK3127C LAK3132C LAK3133C LAK3134C LAK4132C LAK4133C LAK4134C LAK4135C LAK4137C LAK4138C LAK4139C LAK4141C LAK4142C LAK4143C LAK4144C LAK5212C LAK5213C LAK5214C LAK5221C LAK5222C LAK5223C LAK5224C LAK5231C LAK5232C LAK5233C LAK5234C Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min. Value Min. Value norm Max. Value Max. Value norm Number of Spec Number of Spec. norm

50 Laminate Compression -- (ETW ) Normalized Strength Pooled Average = [ksi] Pooled Standard Deviation = [ksi] Pooled Coeff. of Variation = [%] Batch # Laminate Compression Strength [ksi] Laminate Compression -- (ETW ) Normalized Modulus Pooled Average = [Msi] Pooled Standard Deviation = [Msi] Pooled Coeff. of Variation = [%] Batch # Laminate Compression Modulus [Msi] 51

51 Laminate Compression -- (ETW ) Strength & Modulus normalizing t ply [in] Specimen Batch Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Number [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] LAK6121F LAK6122F LAK6123F LAK6124F LAK6125F LAK6126F LAK6127F LAK6128F LAK6129F LAK6139F LAL6111F LAL6112F LAK7121F LAK7122F LAK7123F LAK7124F LAK7125F LAK7131F LAK7132F LAK7133F LAK7134F LAK7135F LAL712AF LAL7123F LAK8115F LAK8116F LAK8117F LAK8118F LAK8119F LAK8136F LAK8137F LAK8138F LAL8112F LAL8113F Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min. Value Min. Value norm Max. Value Max. Value norm Number of Spec Number of Spec. norm