bonded repair of composite airframe laminate and sandwich ... · bonded repair of composite...
TRANSCRIPT
![Page 1: Bonded Repair of Composite Airframe Laminate and Sandwich ... · Bonded Repair of Composite Airframe Laminate and Sandwich Structures John Tomblin, PhD ... “Adam Aircraft ... ¾Bonded](https://reader031.vdocuments.site/reader031/viewer/2022021610/5b86e8db7f8b9a2e3a8df031/html5/thumbnails/1.jpg)
June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Bonded Repair of Composite Airframe Bonded Repair of Composite Airframe Laminate and Sandwich StructuresLaminate and Sandwich Structures
John Tomblin, PhDJohn Tomblin, PhDExecutive Director, NIARExecutive Director, NIAR
Lamia SalahLamia SalahSr. Research Engineer, NIARSr. Research Engineer, NIAR
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2June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
FAA Sponsored Project Information
Principal Investigators & ResearchersDr. John Tomblin, Wichita State UniversityLamia Salah, Wichita State UniversityMike Borgman, Spirit Aerosystems
FAA Technical MonitorCurtis Davies, Lin Pham
Other FAA Personnel InvolvedLarry Ilcewicz, Peter Sheprykevich
Industry ParticipationMike Borgman, Spirit AerosystemsMike Mott, Hawker BeechcraftPierre Harter and Amador Motos, “Adam Aircraft”
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3June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Objective
To investigate different variables on the performance of repairs applied to solid laminates and sandwich structures
To generate baseline repair data (static and fatigue) for both laminate/ sandwich configurations using OEM/ Factory but also field repairsTo evaluate the strength/ durability of poorly bonded and/or contaminated repairs that passed NDI (Laminate)To evaluate the damage tolerance of repairs subjected to BVID inflicted at three different locations on the repair (Laminate)To evaluate the strength of repairs improperly curedTo provide recommendations pertaining to process improvement to ensure repair bond repeatability and structural integrity
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4June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Laminate Repair Coupon Configuration
Parent
Repair
Parent
Repair
Fiberglass Tabs
Adhesive LayerMetalbond 1515or FM300-2
Fiberglass Tabs
Parent Toray T800/3900 graphiteepoxy
Single scarf joint, 4”wide to isolate the variables investigated
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5June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology OEM Repair Material Evaluation
To generate baseline repair data with the parent material used as the repair material (OEM repair), 96 coupons used for the investigation
STATIC FATIGUEPanel # Thickness (in) E (Msi) Scarf Rate RTA RTA
10 6 31 7.2 20 6 3
0.1332 30 3 310 6 3
2 9.1 20 6 330 3 310 6 3
3 7.7 20 6 30.2368 30 3 3
10 6 34 8.8 20 6 3
30 3 3
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6June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology OEM Repair Material Evaluation
Failure Loads, normalized vs. Scarf Rates (Panels 1 & 2)
0
20
40
60
80
100
120
0 10 20 30 40
Scarf Rates
Failu
re L
oads
, Nor
mal
ized
%
Panel 1, E=7.2Msi, RTAPanel 2, E=9.1Msi, RTA
100% corresponds to the failure load of the -30 repairsincreased load carrying capability with increased repair size
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7June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology OEM Repair Material Evaluation
100% corresponds to the failure load of the -30 repairsincreased load carrying capability with increased repair size
Failure Loads, Normalized vs. Scarf Rates (Panels 3 & 4)
0
20
40
60
80
100
120
0 10 20 30 40
Scarf Rates
Failu
re L
oads
, Nor
mal
ized
%
Panel 3, E=7.7Msi, RTAPanel 4, E=8.8Msi, RTA
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8June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology OEM Repair Material Evaluation
100% corresponds to the failure load of the -30 repairsStatic/ Residual Strength vs. Scarf Rates (Panel 1)
0
20
40
60
80
100
120
0 10 20 30 40
Scarf Rates
Failu
re L
oads
, Nor
mal
ized
(100
%)
Panel 1, E=7.2Msi, RTAPanel 1, E=7.2Msi, RTF
20% strength degradation
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9June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology OEM Repair Material Evaluation
Load Versus Strain (1-1-30-RTA vs 1-1-30-RTF)
0
10000
20000
30000
40000
50000
60000
0 2000 4000 6000 8000 10000
Microstrain
Load
(lb
s)
Far-Field GageFar Field gage after Fatigue
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10June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology OEM Repair Material Evaluation
Bonded Repair performance is dependent on repair processesOverall increased static performance with increased repair sizeStiffer panels tend to have a lower strength capability than panels with lower stiffness (more pronounced poisson’s effects)All -20 and -30 repairs survived 165000 cycles of fatigue at 3000 microstraindemonstrating acceptability of these repairs at that strain levelThe thin panels residual strength after fatigue was 20% lower than their ultimate static strength capability due to a change in compliance/ stiffness after fatigue (adhesive plastic deformation)
Adhesive LayerMetalbond 1515
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11June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology Field Repair Material Evaluation
To generate baseline repair data for a candidate field repair material (ACG T800/ MTM45-1, 250°F vacuum cure system), 72 coupons used for this investigation (scarf rates correspond to 5.7°, 2.86° and 1.98°)
STATIC FATIGUEPanel # T (in) E (Msi) Scarf Rate RTA RTA
10 3 31 7.2 20 3 3
0.1332 30 3 310 3 3
2 9.1 20 3 330 3 310 3 3
3 7.7 20 3 30.2368 30 3 3
10 3 34 8.8 20 3 3
30 3 3
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12June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology Field Repair Material Evaluation
Scarf Machining Scarfed Panels
Repair Implementation
Adhesive LayerFM300-2
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13June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology Field Repair Material Evaluation
Repair Implementation
Tabbed PanelMechanical Testing
Repair Bagging
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14June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology Field Repair Material Evaluation
ACG 2-1-10-RTA ACG 2-1-10-RTF 4-2-20-RTA
Process yielded repairs with various levels of porosity as illustrated by the C-Scan imagesPossible source of variability in the mechanical data
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15June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
ResultsField Repair Material Evaluation
ARAMISa non-contact optical 3-D deformation measuring system that uses two high resolution cameras to monitor strain concentrations in a test article
the test article is sprayed with a random pattern prior to loading
measurements are taken at different load levels,
changes in displacements and rotations between stages are recorded, from which strains can be calculated
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16June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
ResultsField Repair Material Evaluation
0
10000
20000
30000
40000
50000
60000
70000
80000
0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000
Strain (microstrain)
Load
(lbs
)
Strain Gauge 1Strain Gauge 2Strain Gauge 3Strain Gauge 4Strain Gauge 5Strain Gauge 6
ACG-4-2-20-RTA-03
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17June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Results-StaticField Repair Material Evaluation
100% represents the failure load of the baseline repairs (parent material same as repair material)At least 80% “baseline repair performance” was restored at room temperature
Field Repair Material Performance
0
20
40
60
80
100
120
10 20 30Scarf Ratio
Nor
mal
ized
Fai
lure
Loa
d (%
)
18-7.2-RTABaseline Repair System Performance
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18June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Results-StaticField Repair Material Evaluation
At least 98% “baseline repair performance” was restored at room temperature
Field Repair Material Performance
0
20
40
60
80
100
120
140
10 20 30Scarf Ratio
Nor
mal
ized
Fai
lure
Loa
d (%
)
18-9.1-RTA
Baseline Material Performance
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19June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Results-StaticField Repair Material Evaluation
At least 90% “baseline repair performance” was restored at room temperature
Field Repair Material Performance
0
20
40
60
80
100
120
10 20 30Scarf Ratio
Nor
mal
ized
Fai
lure
Loa
d (%
)
32-7.7-RTABaseline Material Performance
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20June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Results-StaticField Repair Material Evaluation
At least 89% “baseline repair performance” was restored at room temperature
Field Repair Material Performance
0
20
40
60
80
100
120
10 20 30Scarf Ratio
Nor
mal
ized
Fai
lure
Loa
d (%
)
32-8.8-RTABaseline Material Performance
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21June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology - Field Repair Material Evaluation- Summary
Field repair material cured at 250°F under vacuumAt least 89% of RTA baseline joint strength was restored for most casesA few low data points (porosity, process variability)A higher strength knockdown with respect to baseline repair material performance was observed for CTD and ETW specimensThe thicker specimens 32 ply and 48 ply repairs survived 3DSO in fatigue for all RTD specimensFor the 18 ply repairs, the -30 all survived 3DSO (165000) in fatigue at RTA
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22June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology Effects of Contamination
The quality of training and experience of repair technicians is directly associated with the technician’s successful implementation of a repairProcess deviation directly affects the strength of the repair
0
20
40
60
80
100
120
Failu
re L
oad
(%)
4"diameter hole
CACRC Picture Frame Shear Elements
undamaged
Airline Depot # 1 Airline Depot # 2 Airline Depot # 3
Boeing prepregrepair
prepreg repair
wet lay-up repair
prepreg repair
wet lay-up repair
wet lay-up repair
prepreg repair
Airline Depot # 4
prepreg repair
wet lay-up repair
BVID
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23June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology Effects of Contamination
To evaluate the strength of contaminated repairs applied to laminate configurations. Five different contaminants are considered: Hydraulic oil (skydrol), jet fuel (JP8), paint stripper, water and perspiration. The effects of each one of the contaminants is being evaluated according to the proposed test matrix. A total of 168 contaminated coupons are being used for this evaluation.
Contamination Test Matrix (Laminate)
TestModulus scarf rate Condition
7.7 10 RTA 3 3 3 3 3 3 3 3 3 3 3 3 3 320 RTA 3 3 3 3 3 3 3 3 3 3 3 3 3 3
8.8 10 RTA 3 3 3 3 3 3 3 3 3 3 3 3 3 320 RTA 3 3 3 3 3 3 3 3 3 3 3 3 3 3
ContaminationSkydrol Jet Fuel Paint Stripper Water
75% 50% 25% 0%
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24June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Contaminant Minimum Soak Time
Jet Fuel, JP8 30 daysPaint Stripper 6 daysSkydrol 30 daysWater 30 days
After saturation, coupons have been dried to achieve saturation levels of 0%,25%,50%, 75% and 100%
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
0 10 20 30 40 50 60 70 80
Time (days)
% W
eigh
t Gai
n (T
otal
)SPR
Methodology Effects of Contamination
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25June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Exposure to Water and Skydrol
Methodology Effects of Contamination
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26June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology Effects of Contamination
% Saturation Versus Time (160F Vacuum Drying, 32 ply laminate)
0%
25%
50%
75%
100%
0 5 10 15 20 25 30 35 40 45
Period (days)
% S
atur
atio
n
Traveler Average0.73 day
4.73 days
18 days
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27June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology Effects of Contamination
Surface Analysis: Dr Stevenson/ Irish Alcalen
Surface Free Energy Measurements on Contaminated Surfaces Prior to Repair
-5
5
15
25
35
45
55
65
SH PS JF PR WA75 WA50 WA 25
Contaminating Agent
Surf
ace
Free
Ene
rgy
(mN
/m)
Good Surface for Bonding
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28June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Repair after ContaminantExposure
Adhesive Application
Individual Ply Location Marking
Repair Lay-up/ Thermocouple InstallationRepair Bagging
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29June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
TTU Non-Destructive Inspection
Jet Fuel Contaminated Panel Skydrol Contaminated Panel
Water Contaminated Panel
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30June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Contamination ResultsMax Strength degradation 14%
Strength Performance of Coupons Exposed to Perspiration as the Contaminant
0.0
20.0
40.0
60.0
80.0
100.0
120.0
140.0
7.7-C
-PR-10
-1-RTA
7.7-C
-PR-10
-2-RTA
7.7-C
-PR-20
-1-RTA
7.7-C
-PR-20
-2-RTA
% B
asel
ine
Stre
ngth
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31June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Contamination Results
Max Strength degradation 30%
Strength Performance of Coupons Exposed to WA (75% saturation) as the Contaminant
0
20
40
60
80
100
120
7.7-C
-WA-75
-10-1-
RTA
7.7-C
-WA-75
-10-2-
RTA
7.7-C
-WA-75
-20-1-
RTA
7.7-C
-WA-75
-20-2-
RTA
% B
asel
ine
Stre
ngth
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32June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Contamination Results
Max Strength degradation 27%
Strength Performance of Coupons Exposed to WA (0% moisture after full saturation) as the Contaminant
0
20
40
60
80
100
120
8.8-C
-WA-0-
10-1-
RTA
8.8-C
-WA-0-
10-2-
RTA
8.8-C
-WA-0-
20-1-
RTA
8.8-C
-WA-0-
20-2-
RTA
% B
asel
ine
Stre
ngth
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33June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Static data showed a lower strength performance for all panels contaminated with PR, WA75%, WA 50%, WA 25%, WA 0%RTA Static data showed minor strength degradation for panels contaminated with JF, SH and PS Need fatigue data to confirm results
Methodology Effects of Contamination
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34June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology – Damage Effects
To evaluate the strength, durability and damage tolerance of repairs applied to laminate structures. 144 Coupons of different thicknesses and stiffnesses are being considered and are being impacted in three different locations: at the center of the repair scarf and at the edge of the scarf.
Parent Panel Rep
air P
anel
Parent Panel Repair Panel
Parent Panel Rep
air P
anel
Parent Panel Repair Panel
Parent Panel R
epai
r Pan
el
Parent Panel Repair Panel
Parent Panel R
epai
r Pan
el
Parent Panel Repair Panel
Parent Panel R
epai
r Pan
el
Parent Panel Repair Panel
Parent Panel Rep
air P
anel
Parent Panel Repair Panel
Parent Panel Rep
air P
anel
Parent Panel Repair Panel
Parent Panel Rep
air P
anel
Parent Panel Repair Panel
Center Impact
Tip of the scarf TNTip of the scarf far side TF
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35June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology – Damage Effects
18 ply configurationsImpact Energy Level 200 in-lbsDepth: 0.01”
TestPlies Modulus scarf rate Condition TN TF CN
10 RTA 3 3 37.2 RTF 3 3 3
20 RTA 3 3 318 RTF 3 3 3
10 RTA 3 3 39.1 RTF 3 3 3
20 RTA 3 3 3RTF 3 3 3
10 RTA 3 3 37.2 RTF 3 3 3
20 RTA 3 3 348 RTF 3 3 3
10 RTA 3 3 39.1 RTF 3 3 3
20 RTA 3 3 3RTF 3 3 3
Impact Site
48 ply configurationsImpact Energy Level 400 in-lbsDepth: 0.01”
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36June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
10941-18-7.2-20-CN-180W-1 10941-18-7.2-20-CN-180W-2 10941-18-7.2-20-CN-180W-3
Methodology – Damage Effects
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37June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology – Damage EffectsResults
Failure Load, Normalized, as a Function of Damage Location
0
20
40
60
80
100
120
Tip Near Tip Far Center
Damage Location
Ulti
mat
e Lo
ad (%
)
18ply-7.2-10-RTA
Baseline Undamaged Panels
47% baseline residual strength
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38June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology – Damage EffectsResults
Max Strength Degradation 9%
Failure Load, Normalized as a Function of Damage Location
0
20
40
60
80
100
120
Tip Near Tip Far Center
Damage Location
Ulti
mat
e Lo
ad (%
)
18ply-7.2-20-RTA
Baseline Undamaged Panels
91% baseline residual strength
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39June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Failure Load, Normalized as a Function of Damage Location
0
20
40
60
80
100
120
Tip Near Tip Far Center
Damage Location
Failu
re L
oad
(%)
48ply-9.1-10-RTA
Baseline Undamaged Panels
Methodology – Damage EffectsResults
44% baseline residual strength
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40June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology – Damage EffectsResults
Max Strength Degradation 3%
Failure Load, Normalized as a Function of Damage Location
0
20
40
60
80
100
120
Tip Near Tip Far Center
Damage Location
Failu
re L
oad
(%)
48ply-9.1-20-RTABaseline Undamaged
97% baseline residual strength
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41June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology Damage Effects Summary
Strength degradation is proportional to damage areaCoupons impacted at the center of the repair, had the largest damage area and the lowest static strength The performance of coupons impacted at the edge of the repair was comparable to that of baseline repaired undamaged couponsThe residual strength is also dependent on the “residual” bond area. The largest repairs are more “damage tolerant” than smaller repairs
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42June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
MethodologySandwich Repair Evaluation
To evaluate the strength and durability of OEM vs field repairs. Scarf repairs are considered for this investigation.
2-D Taper Sand Region (0.5" overlap)
Exposed Core (3" diameter)
46.00
11.50
5.00 4.007.00
Synspand
Repair Configuration Core Cell Size Repair Material Repair Type Scarf Overlap (in) Static (RTA)
N/A Open-Hole N/A 3
Toray T700/2510 PW Baseline UndamagedPrepreg N/A 6
CACRC Wet Lay-Up Flush Scarf RepairRepair 0.5 6
CACRC Wet Lay-Up Flush Scarf RepairRepair Undercure 0.5 6
CACRC Wet Lay-Up Flush Scarf RepairRepair Overcure 0.5 6
1/82-D Compression
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43June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
MethodologySandwich Repair Evaluation
To evaluate the strength and durability of OEM vs field repairs.
Screening Panels yielded acceptable Failures
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44June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
Methodology-Sandwich Repair using CACRC method
Epocast 52A/B, TENEX FABRIC
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45June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
MethodologyCure Cycle Deviation Evaluation
Cure Cycle Deviation Investigation
0
20
40
60
80
100
120
Baseline Open-Hole CACRC-WetLay-Up
IC Overcure Undercure
% U
ndam
aged
Str
engt
h
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46June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
MethodologySandwich Repair Evaluation
Wet lay-up repair specimen
Tested Specimen
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47June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
MethodologySandwich Repair Evaluation
Undercure (UC), Overcure (OC), Interrupted Cure (IC) panels all had lower strength capability than repaired panels cured following the OEM recommended cycle
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48June 18th, 2008 The Joint Advanced Materials and Structures Center of Excellence
A look Forward/ Benefits to Aviation
To generate repair data for OEM/ factory materials that can be used to demonstrate acceptability of alternate materials to use for repair when the parent material is not available or cannot be used for repair
To generate data that correlates contamination and process parameter deviation to the performance of bonded repairs
To provide information on repair damage tolerance depending on damage location
To identify the crucial steps in bonded repair
To develop rigorous repeatable repair processes that ensure structural integrity of bonded repairs
To gain confidence in bonded structural repairs