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Park Aerospace E-765 T700 Uni Tape

Park’s E-765 is a toughened 270°F cure epoxy prepreg system designed to replace 350°F cure systems in many aircraft structural applications. Park’s E-765-3K-PW, -6K-5HS and 7781 materials are AGATE approved. FAA-approved, B-Basis design allowable databases for AGATE materials are available upon request. Park has also developed AGATE approved material and process specifications which are also available upon request.

Polymer Name: Epoxy Resins & Compounds

Functions: Prepreg

Reinforcement Material: Carbon Fibers, Glass Fibers

Processing Methods: Compression Molding, Out of Autoclave Prepreg, Prepreg Processing, Vacuum Bagging

End Uses: Bulkheads, Doors, Fairings, Fuselage, Radomes, Wing Box, Wing Ribs, Wing Skins

Technical Data Sheet
  • TypeDocument Name
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Knowde Enhanced TDS

Identification & Functionality

Chemical Family

Epoxy & Epoxy Derivatives

Polymer Name

Epoxy Resins & Compounds

Reinforcement Material

Carbon Fibers,

Glass Fibers

Composite Materials Functions

Prepreg

Technologies

Composite Materials

Product Families

Composite Materials — Prepregs & Molding Compounds

Thermoset Prepregs

Features & Benefits

Materials Features

Tacky

Key Features & Benefits
  • Designed to replace first generation 350°F (176°C) cure systems
  • Wide cure temperature process window of 260°F to 350°F (lower cures are possible depending on the application)
  • Exhibits low void content, e.g., <2% after oven/vacuum cure.
  • Excellent fiber property translation.
  • 180°F Wet service temperature after ~270°F cure
  • Good tack and drape characteristics after 30 days at room temperature.
Product Forms
  • Available on a wide variety of reinforcements including fiberglass and carbon
  • Various Fabrics per customer requirements (e.g., plain, harness and twill weaves)
  • Unitape and glass broad goods up to 60 inches wide
  • Compatible with autoclave, vacuum bag/oven or press cure processes

Applications & Uses

Markets

Automotive & Transportation,

Building & Construction

Applications

Automotive & Transportation — Automotive

Exterior & Body,

Interior

Building & Construction — Building Materials

Interior Fixtures

Automotive & Transportation — Transportation

Aerospace & Aviation

Composites End Use

Bulkheads,

Doors,

Fairings,

Fuselage,

Radomes,

Wing Box,

Wing Ribs,

Wing Skins

Composites Processing Methods

Compression Molding,

Out of Autoclave Prepreg,

Prepreg Processing,

Vacuum Bagging

Autoclave/ Cure Cycle
  • Apply 24”Hg vacuum (minimum) for a minimum of 1 hour before cure
  • Apply 40 -100 psi autoclave pressure, vent vacuum when pressure reaches 15 – 20 psi
  • Ramp product temp to 270-280°F at 1 – 5° F (0.05 – 3°C)/min
  • For Laminates > 0.125” thick, hold at 180°F for 60 minutes
  • Hold product at 270-280°F for 110-130 minutes
  • Cool to 150°F at 3 – 10°F/min prior to releasing autoclave pressure
Applications / Qualifications
  • Primary Aircraft Structures
  • Fuselage
  • Wing
  • Control Surfaces
  • Secondary Aircraft Structures
  • Fairings
  • Doors
  • Radomes
  • Bulkheads
Vacuum/Oven Cure Cycle
  • Apply 25”Hg vacuum (minimum) for a minimum of 1 hour before cure
  • Ramp product temp to 270-280°F at 1 – 5° F (0.05 – 3°C)/min
  • For laminates > 0.125” thick, hold at 180°F for 60 minutes
  • Hold product at 270-280°F for 110-130 minutes
  • Cool to 150°F at 3 – 10°F/min
Thick Laminate Cure Cycle
  • Slower ramp rate and multiple dwell times below 190°F are critical to remove excess energy from the system and avoid dangerous exotherms.
  • Contact your Park representative to discuss specific part process requirements to optimize processing of E-765.
  • Failure to properly control the exotherm can lead to a potential safety hazard and/or degradation of final material performance.

Properties

Physical Properties
ValueUnitsTest Method / Conditions
Fabric Area Weight 150gsm-
Resin Solids35±3%-
Volatile Contentmax. 1%-
Flow (275°F / 15psi)18±6%-
TackMedium--
Tg (dry, by DMA, onset storage mod)150° C / 300°F--
Gel time (275°F)2 - 6minutes-
Cure per ply thickness 0.0056in-
Dielectric Constant4.5Dk-
Loss Tangent 0.02Df-
Flatwise Tensile Strength1000 psi-ASTM-C-297
Cure TypeVacuum/Oven--
Mechanical Properties
ValueUnitsTest Method / Conditions
Climbing Drum Peel4in lb/3 inASTM-D-1781
Tensile Strength - Dry (65°F)370KsiASTM-D-3039-95
Tensile Strength - Dry (70°F) 370KsiASTM-D-3039-95
Tensile Strength - Dry (180°F)349KsiASTM-D-3039-95
Tensile Strength - Wet (180°F) 333KsiASTM-D-3039-95
Tensile Modulus - Dry (65°F) 18.8MsiASTM-D-3039-95
Tensile Modulus - Dry (70°F) 18.7MsiASTM-D-3039-95
Tensile Modulus - Dry (180°F)18.2MsiASTM-D-3039-95
Tensile Modulus - Wet (180°F) 18.6MsiASTM-D-3039-95
Compressive Strength - Dry (65°F) 211KsiSACMA 1-94
Compressive Strength - Dry (70°F)180KsiSACMA 1-94
Compressive Strength - Dry (180°F) 177KsiSACMA 1-94
Compressive Strength - Wet (180°F) 107KsiSACMA 1-94
Compressive Modulus - Dry (65°F) 17.9MsiSACMA 1-94
Compressive Modulus - Dry (70°F )18.1MsiSACMA 1-94
Compressive Modulus - Dry (180°F )18.4MsiSACMA 1-94
Compressive Modulus - Wet (180°F )18MsiSACMA 1-94
Short Beam Shear - Dry (65°F)17KsiASTM-D-2344
Short Beam Shear - Dry (70°F)13KsiASTM-D-2344
Short Beam Shear - Dry (180°F)9KsiASTM-D-2344
Short Beam Shear - Wet (180°F)6KsiASTM-D-2344
In-plane Shear Strength, V-notched - Dry (65°F)26KsiASTM-D-5379-93
In-plane Shear Strength, V-notched - Dry (70°F)20KsiASTM-D-5379-93
In-plane Shear Strength, V-notched - Dry (180°F)16KsiASTM-D-5379-93
In-plane Shear Strength, V-notched - Wet (180°F)11KsiASTM-D-5379-93
Electrical Properties
ValueUnitsTest Method / Conditions
Frequency9.375GHz-

Regulatory & Compliance

Quality Standards

Advanced General Aviation Transport Experiments (AGTE) Approved,

Federal Aviation Administration (FAA) Approved