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POST IMPACTED STRENGTH ANALYSIS OFFIBRE METAL LAMINATES( REVIEW – 3)

C.SETHUMAHADEVANM.E (AERO) P.T2013657013

GUIDEDr.B.T.N. Sridhar Professor & Head

Department of Aerospace Engineering

MIT Campus ,Anna University ,Chennai -44

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AIM AND OBJECTIVE

• Aircraft structures are more prone to impact damages. Impact damage on aircraftstructures can be caused by low- and high-velocity sources such as runawaydebris, hail, bird strikes, engine debris, collisions between service cars, and cargo.

• To overcome the above, this experiment’s objective is to characterize the impactproperties of the FML used for aircraft structures.

.

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PRACTICAL RELEVANCE

Weight reduction and improved damage tolerance characteristics were the

prime drivers to develop new family of materials for the aerospace/aeronauticalindustry. Aiming this objective, a new lightweight Fiber/Metal Laminate (FML) has

been developed. The combination of metal and polymer composite laminates can

create a synergistic effect on many properties. The mechanical properties of FML

shows improvements over the properties of both aluminum alloys and composite

materials individually. Due to their excellent properties, FML are being used as

fuselage skin structures of the next generation commercial aircrafts

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The moisture absorption in FML composites is slower when compared with

polymer composites, even under the relatively harsh conditions, due to the barrier

of the aluminum outer layers. Due to this favorable atmosphere, recently big

companies such as EMBRAER, Aerospatiale, Boeing, Airbus, and so one, starting

to work with this kind of materials as an alternative to save money and to guarantee

the security of their aircrafts.

Cont ..

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RESULTS PLOT

IMPACT

Load Vs TimeEnergy Vs TimeDeformation Vs Time

FLEXURAL(3 Point Bending)

Stress Vs Strain

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FACILITIES AVAILABLE

oven

UTM (Instron 3367)IIT (Instrument Impact Test )

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OVEN

Maximum Temperature :400 ° CVolume: 500 ltr Resolution : ± 5 ° c

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UNIVERSAL TESTING MACHINE

Instron Model : 3367

Load Capacity :30 KN

Test typeTensileFlexural :3 point -4 point

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INSTRUMENT IMPACT TEST

Drop height Range (mm) 30 to 1100

Mass Range (kg) 2 to 70

Speed range (m/s) 0.75 to 4.6

Maximum speed withadditional system (option)(m/s)

24

Energy Range (J) 0.6 to 775

Maximum energy withadditional energy system(option) (J)

1800

Test Temperature RT to 150°C

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SELECTION OF LAMINATE

Fibre Metal laminates

GLARE ARALL(GLAss Reinfored Epoxy) (Aramid Fiber /Aluminum)

GLARE Advantage• Better damage tolerance behavior (especially impact and metal fatigue as the

elastic strain is larger than other metal material it can consume more impactenergy. It is dented easier but has a higher penetration resistance )

• Better corrosion resistance.• Better fire resistance.• Lower specific weight .

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STANDARD GLARE GRADE

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FABRICATION OF GLARE

A . Surface pre-treatment of aluminium Sheet .

B. Hand lay-up

C . Cutting the Specimen as per ASTM Standard

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SURFACE TREAMENT

Types of surface treatments1. Mechanical2. Chemical

3. Electromechanical4. Coupling agent5. Dry surface treatment

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SURFACE PRE-TREATMENT OF ALUMINIUM

As per ASTM D 2651 Surface Prepartaion of metal surface for Adhesive BondingAluminium Alloy

1. Sulfuric acidSodium Dichromate

2. Etch (sulfuric Acid/Sulfate)

Sulfuric AcidFerric sulfate

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SULPHURIC ACID – SODIUM DICHROMATE

SOLUTION COMPOSITION:Distilled water (70% by weight of total solution)Concentrated Sulphuric acid (H 2SO 4) – lab grade (27 % by weight of total solution)Sodium dichromate Na 2Cr 2O7 -(3% by weight of total solution)

1. Clean the sheets using with banyan cloth.2. Emery the bonding surface of the sheet using 100 grit size emery sheets to get mat

finishing.3. Ensure the surface is free from contamination and dust particles.4. Pour the distilled water (70% by weight of total solution) into the tray.

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Cont…

5. Ensure the level of water is maintained 10mm above the skin sheet.6. Mix the sodium dichromate (3% by weight of total solution) thoroughly with the distilled

water.7. Slowly pour the Concentrated Sulphuric Acid (27% by weight of total solution) inside the

tray uniformly over the total surface of the solution.8. Place the thermometer at one corner of the tray to monitor the temperature of the

solution.9. Record the time at which the bath reaches 70 ⁰ C.10. Place the aluminum skin sheets slowly one by one inside the bath and keep it for

30± 5min.

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Cont …

1. Clean another tray with IPA.2. Fill the tray with distilled water for cleaning the etched sheets.3. Take out the etched sheets after 30 ± 5 min from the bath one by one and place them

inside the cleaning tray.4. Clean the skin surface using banyan cloth.5. Shift the skin sheets to another cleaning tray filled with distilled water for further

cleaning.6. cleaned sheets in hot distilled running water (temp.70 ± 5⁰ C).

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FIBRE ORIENATION&HAND LAYUP

1. Cross ply (0 ° /90 ° )2. Araldite AW 106 with hardener 956 by 1:1 ratio (adhesive)3. EPOXY LY 556 with hardener araldite it 951 by the ratio of

10:1.(resin)

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CROSS PLY

Al 2024-T3

Al 2024 T36 layer Fibre

0

90

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FIBRE METAL LAMINATE

250 X250 mm

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FLEXURAL TEST (3 POINT BENDING)

As per ASTM Standard D790Span length: 110mmWidth : 25 mmThickness : 3 mmCross Head moment : 1 mm/min

MaxiLoad (KN)

MaxDisplacement (mm)

MaxStrain

Modules(Mpa)

0.1586 20.29 144.2 27990

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TENSILE TEST

Max Load (KN) MaxDisplacement(mm)

Max Strain Modules (Mpa)

7.200 3.359 0.031 7953

ASTM D 3039Gauge length :120 mmGrip distance :80mmCross head moment : 0.5 mm/min

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Peak Force (N) Total Energy (J) Total Deformation (mm)

3177.555 27.159 17.570

IMPACT TEST

Standard followed ASTM D 5628 FDStriker Velocity : 6 m/sTotal mass :1.92kgTup Diameter (mm) : Ø12.7 Hemispherical

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REFERENCE

1. Botelho, Edson Cocchieri, Silva, Rogério Almeida, Pardini, Luiz Cláudio, & Rezende,Mirabel Cerqueira. (2006). A review on the development and properties of continuousfiber/epoxy/aluminum hybrid composites for aircraft structures. Materials Research ,9 (3), 247-256,http://dx.doi.org/10.1590/S1516-14392006000300002

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3. M. Sadighi, R.C. Alderliesten, R. Benedictus, Impact resistance of fiber-metallaminates: A review, International Journal of Impact Engineering, Volume 49, November

2012, Pages 77-90, ISSN 0734-743X, http://dx.doi.org/10.1016/j.ijimpeng.2012.05.006.

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5. Roman Starikov, Assessment of impact response of fiber metal laminates,

International Journal of Impact Engineering, Volume 59, September 2013, Pages 38-45, ISSN 0734-743X, http://dx.doi.org/10.1016/j.ijimpeng.2013.02.008 .6. Qi Chen, Zhidong Guan, Zengshan Li, Zhaojie Ji, Yue Zhuo, Experimentalinvestigation on impact performances of GLARE laminates, Chinese Journal of Aeronautics, Available online 29 August 2015, ISSN 1000-9361,http://dx.doi.org/10.1016/j.cja.2015.07.002 .7. J. Bieniaś , P. Jakubczak, B. Surowska, K. Dragan, Low-energy impact behaviour anddamage characterization of carbon fibre reinforced polymer and aluminium hybridlaminates, Archives of Civil and Mechanical Engineering, Volume 15, Issue 4,September 2015, Pages 925-932, ISSN 1644-9665,http://dx.doi.org/10.1016/j.acme.2014.09.007 .

8. Guo-Cai Yu, Lin-Zhi Wu, Li Ma, Jian Xiong, Low velocity impact of carbon fiberaluminum laminates, Composite Structures, Volume 119, January 2015, Pages 757-766, ISSN 0263-8223, http://dx.doi.org/10.1016/j.compstruct.2014.09.054

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Thank you