PASSANGER AIRCRAFT

http://www.1001crash.com/index-page-composite-lg-2.html

PASSANGER AIRCRAFTNO NAME OF PART MATERIAL

USEDPROPERTIES REASON

1. FUSELAGE AlMgSiCu (AA6013) T6

WeldableIncreased Yield Strength Reduced Fatigue Crack Growth Rate Higher Toughness Lower Density

Weight Reduction ,High value of specific Strength

2. RUDDER, WINGS,AILERONS, TAIL CONE, FLAP TRACK PANEL , LANDING GEAR DOORS , WING RIBS , CENTER WING BOX , ENGINE COWLINGS , REAR PRESSURE BULK HEAD

Carbon fiber–reinforced polymer

strength and rigidityhigh initial strength-to-weight ratio

extremely light and rigidlighter and stronger than their metal counterparts

3. HORIZONTAL AND VERTICAL STABILIZER

Aluminium 7075 T6

density of 2.810 g/cm³Utm 74,000–78,000 psiyield strength of at least 63,000–69,000 psi

Highly Stress Structure

4. FLOOR PANELS , FUEL TANKS

S-2 Glass fiber Softening point: 1056°C (1932°F) , Annealing point: 816°C (1500°F) , Strain point: 766°C (1410°F)

Greater fiber tensile strength and stability at elevated temperatures in thermoset and thermoplastic applications

5. Engine Titanium , Inconel 65

high strength, stiffness, toughness, low density, and good corrosion resistance

high strength-to-weight ratio.

6. Wind Shield PLEXIGLAS®

GS 241UV transmittance less than 1 %,high optical standards

Better Visibility and Toughness

MILIATRY AIRCRAFT

http://www.tejas.gov.in/

MILITARY AIRCRAFTSR. NO.

NAME OF PART MATERIAL USED PROPERTIES Reason

1. Leading and Trailing edge S – 2 Glass Fiber high strength, modulus and durability under conditions of extreme temperature of corrosive environments

For radar absorption

2. Wing , Fuselage and Tail skin AS4/3501 – 06 Carbon -Epoxy

Density 1.265 gm/cc Tg dry 6 hr 350°F (177°C) cure 410°F (210°C) Tg wet 6 hr 350°F (177°C) cure 304°F (151°C) Tensile strength 6.6 ksi Tensile modulus 0.615 msi

Considering Higher Tensile Strength ,

Test result on Cessna 180Result : 3.8 KsiF.O.S.– 1.73

3. Engine Bay Region BMI RM 3010 Cured Resin Density 1.25 g/cc Glass Transition Tg (G’) 72 hr, 180⁰F immersion Dry: 534⁰F Wet: 485⁰F Resin Flex Strength 18 ksi Resin Flex Modulus 665 ksi Resin Flex Strain to Failure 2.5%

High Temperature Resistance

4. Fuel Tank , Frame , Walls RTM method Inner liner of synthetic rubber or rubber-coated fabric,• Ballistic nylon barrier,• Sealant, and• a Retainer of woven nylon cord.

• Lightweight Bladder,• Self-Sealing, and• Crash Resistant.

Fuel Resistance , High Pressure Sustain in Speed, Crash Resistance

5. Nose Fibre GlassE – Glass ,S - Glass

high strength, modulus and durability under conditions of extreme temperature of corrosive environments

performance over narrow frequency bands, high-quality RF performance

http://www.faqs.org/patents/app/20140197280

 Unmanned Aerial Vehicle

 Unmanned Aerial VehicleSR. NO.

NAME OF PART MATERIAL USED Reason

UAV Types Target and decoy - providing ground and aerial gunnery a target that simulates an enemy aircraft or missileReconnaissance - providing battlefield intelligenceCombat - providing attack capability for high-risk missions (see Unmanned Combat Air Vehicle)Research and development - used to further develop UAV technologies to be integrated into field deployed UAV aircraftCivil and Commercial UAVs - UAVs specifically designed for civil and commercial applications.

1 Body / Frame , Wings Wood , Form , Plastic , Aluminium , G10 , Carbon Fibre , Carbon Fiber Skin ,

Depends Upon Size and Design

HELICOPTER

https://commons.wikimedia.org/wiki/File:Merlin_Airframe_Material.jpg

HELICOPTERSR. NO.

NAME OF PART MATERIAL USED PROPERTIES REASON

1. ROTOR BLADE Sandwich Design with GFRP , CFRP , FORM , GREEN NOMEX HONEYCOMB CORE , SS EROTION SHEILD , WOVEN GLASS OUTER SHIELD

ductile, relatively soft and with quite a high plasticity

To provide high stiffness under rotation tip velocity of 200m/s and Flipping also in Environmental condition such humidity and temperature , it provide better vibration characteristics of blade

2 Airframes, empennage CFRP Sandwich panels ductile, relatively soft and with quite a high plasticity

Light Weight

3. Nose, Exhaust, Wind Shield Kevlar 49 / epoxy Nomex/Polycarbonate

High modulus / High Temp Resistance , Density – 1.44 g/cc , UTS – 3000MPA , Tensile Modulus – 112 GPA ,

For better visualization and bullet proof , Ultra High Temperature

4. Cabin Weldalite 049 /Alloy 2090 /Alloy 2091 / Alloy 8090 Alloy Frames

Higher stiffness , Superior fatigue crack growth resistance , Reduced ductility

For Minimizing Vibration And Damping

5. Tail Boom Weldalite 049 /Alloy 2090 /Alloy 2091 / Alloy 8090 Alloy Frames

Higher stiffness , Superior fatigue crack growth resistance , Reduced ductility

To resist exhaust impingement temps and reduce empty weight fraction

GLIDER

https://en.wikipedia.org/wiki/Glider_(aircraft)

GLIDER SR. NO.

NAME OF PART MATERIAL USED SPECIFIC USE

1. Frame, Wing Span Basla Wood ,A Grain ,B Grain ,C Grain

Making Light Weight

2. Frame Cover Thin sheet of Basla or Thick Plastic Film

Providing bending and torsional strength , Desired airfoil shape

3. Core Dow Styrofoam High load 60 insulation

For good Compressive strength

4. Skin  fibreglass cloth , carbon-fiber cloth

Aerodynamic Shape

HOT AIR BALOON

https://en.wikipedia.org/wiki/Hot_air_balloon

HOT AIR BALOON

SR. NO.

NAME OF PART MATERIAL USED PROPERTIES Reason

1. Balloon Envelope , Gores , Parachute Valve

Nylon / Polyester / Nomex (Near Gas Burner )

Polyester good aging resistance at high temperaturesNylon superior elasticity, stronger rip resistance and the durability, UV stability, colour brilliance, fungus resistance or dirt resistance

No UV Radiation when heated

2. Wicker Basket woven from Kooboo and Palambang cane , Aluminium

extremely sturdy, flexible and relatively lightweight

Light weight Constraint

SUPER SONIC AND HYPERSONIC AIRCRAFT

https://en.wikipedia.org/wiki/Supersonic_speedhttp://seit.unsw.adfa.edu.au/ojs/index.php/Hypersonics/article/viewFile/21/12

HYPERSONIC AIRCRAFTSR. NO.

NAME OF PART MATERIAL USED PROPERTIES SPECIFIC USE

1. Inward Turning Inlet of Scam Jet Engine

TZM Molybdenum 0.50% Titanium, 0.08% Zirconium and 0.02% Carbon with the balance Molybdenum

 high strength/high temperature applications, especially above 2000°F

2. truss structures Rene 41 super alloy temperature strength up to 980C

Heat Absorption

3. Body Parts Titanium-Aluminium alloy

above 650C, the alloy has a high solubility with oxygen

Weight Reduction

4. thermal protection systems Hafnium Diboride and Zirconium Diboride

high melting point of approximately 3200Coxidation resistance at temperatures up to 2000C

For Protection of system under high temperature

5. Complex Body Structure Carbon/Silicon Carbide ceramic matrix composite

constant strength to weight ratio up to 1600C

Design Complex body parts

6. Nose TAZ-8A Cermet minute oxidation build up of 1.8 milligrams per square centimetre of alloy when exposed to 1900 F

Nose cone

7. Propulsion System Titanium Metal Matrix Composite

withstanding thousands of hours of cyclic loading in an oxidative environment

Propulsion temperature up to 3000C

SUMMARY

• Composite parts used for aircraft applications are defined by – Material, process, and manufacturing specifications. – Material allowable (engineering definition).

• All of these have a basis in regulatory requirements.Most efficient use of advanced composites in aircraft Most efficient use of advanced composites in aircraft structure is in applications with – Highly loaded parts with thick gages. – High fatigue loads (fuselage and wing structure, etc). – Areas susceptible to corrosion (fuselage, etc). – Critical weight reduction (empennage wings fuselage etc) Critical weight reduction (empennage, wings, fuselage, etc).

• Use must be justified by weighing benefits against costs.

References:

• PASSANGER AIRCRAFT

FUSELAGE :-

http://www.mat.ethz.ch/news_events/archive/materialsday/matday01/pdf/TempusMD.pdf http://www.wiley-vch.de/books/sample/3527313605_c01.pdf http://www.aluminiumleader.com/en/around/transport/aircraft

RUDDER, WINGS,AILERONS, TAIL CONE, FLAP TRACK PANEL , LANDING GEAR DOORS , WING RIBS , CENTER WING BOX , ENGINE COWLINGS , REAR PRESSURE BULK HEAD :-

http://www.ndt.net/article/aero2010/papers/tu1a4.pdf https://en.wikipedia.org/wiki/Carbon-fiber-reinforced_polymer#Properties http://www.carbonfiber.gr.jp/english/field/craft.html http://www.ndt.net/article/ecndt98/aero/015/015.htm http://www.carbonfiber.gr.jp/english/field/craft.html http://www.tapplastics.com/product_info/why_use_carbon_fiber

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References:

STABILIZER:-

http://www.ijirset.com/upload/2014/april/15_Static.pdf http://asm.matweb.com/search/SpecificMaterial.asp?bassnum=MA7075T6 https://en.wikipedia.org/wiki/7075_aluminium_alloy

FLOOR PANELS , FUEL TANKS :-

http://www.agy.com/wp-content/uploads/2014/03/449_S-2-Aerospace.pdf http://www.scielo.br/scielo.php?pid=S1516-14392013000500024&script=sci_arttext

ENGINE:-

http://www.iom3.org/materials-world-magazine/feature/2013/may/09/materials-through-ages-materials-aeroplane-engines

http://link.springer.com/article/10.1007/BF00136790

WINDSHIELD :- http://www.plexiglas.de/product/plexiglas/en/products/solid-sheets/aircraft-materials/pages/default.aspx

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• MILITARY AIRCRAFT:

LEADING AND TRAILING EDGE:-

http://www.agy.com/wp-content/uploads/2014/03/Mechanical_Properties_of_Polymeric_Composites-Technical.pdf

https://books.google.co.in/books?id=5SPAIKFmFjcC&pg=PA436&lpg=PA436&dq=military+aircraft+fix+trailing+edge+material&source=bl&ots=KFJouzrSu2&sig=-I1-1urQCQW261f6vrZdZi3eXCE&hl=en&sa=X&ved=0CB4Q6AEwAGoVChMI1oytiaatxwIVynKOCh3DWw_C#v=onepage&q=military%20aircraft%20fix%20trailing%20edge%20material&f=false

WING , FUSELAGE AND TAIL SKIN :-

http://www.hexcel.com/Resources/DataSheets/Prepreg-Data-Sheets/3501-6_eu.pdf https://books.google.co.in/books?

id=JLogBQAAQBAJ&pg=PA237&lpg=PA237&dq=FATIGUE+VALUE+RECOMMENDED+ON+AIRCRAFT+WING&source=bl&ots=V6h63OkUQJ&sig=B9s8vYxrS2tqavmmLqAFTRPILtA&hl=en&sa=X&ved=0CC4Q6AEwA2oVChMI79GTtK-txwIVRAiOCh0i8wnZ#v=onepage&q=FATIGUE%20VALUE%20RECOMMENDED%20ON%20AIRCRAFT%20WING&f=false

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References:

Engine Bay Region :-

http://www.compositesworld.com/articles/resin-infused-ms-21-wings-and-wingbox

FUEL TANK , FRAME , WALLS :-

http://www.ffcfuelcells.com/aircraftfueltanks1.asp

NOSE :-

http://www.azom.com/article.aspx?ArticleID=12107 http://www.selkirk-aviation.com/nosebowls.html

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References:

• UNMANNED AERIAL VEHICLE

BODY / FRAME , WINGS

http://www.robotshop.com/blog/en/make-uav-lesson-2-platform-14448 http://www.theuav.com/

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References:

• HELICOPTER

http://classroom.materials.ac.uk/caseRoto.php https://books.google.co.in/books?

id=e1id9bKG100C&pg=PA31&lpg=PA31&dq=kevlar+nomex+for+helicopter+nose&source=bl&ots=Vi4de1JRzJ&sig=qdYKggCcYRO68mX9xXTPowt2-74&hl=en&sa=X&ved=0CDUQ6AEwA2oVChMIi4Lvru6txwIVwxqOCh3NUQF2#v=onepage&q=kevlar%20nomex%20for%20helicopter%20nose&f=false

http://www.ncn-uk.co.uk/uploads/michael%20Overd.pdf http://esaform2008.insa-lyon.fr/proceedings/MS12/p_Du_473.pdf http://www.metalwebnews.com/howto/alloys/alloys.pdf

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References:

References:

• GLIDER

http://www.modelaviation.com/freeflightmaterials

• HOT AIR BALOON

http://www.schroederballon.de/en/dates-impressions/schroeder-news/nylon-or-polyester.html \ http://www.eballoon.org/balloon/basket.html http://www.eballoon.org/balloon/how-it-works.html

• SUPER SONIC AND HYPERSONIC AIRCRAFT

http://seit.unsw.adfa.edu.au/ojs/index.php/Hypersonics/article/viewFile/21/12

LESSON LEARNT

• Able to know what design approach should be made for selection of material• Understood the requirement of specific material for specific application• Learned about the how important is case study for using specific material • Able to understand about the Composite sandwich , how they are useful in different loading , force

and thermal situation.• Able to understand what are the constraint for selection of material . i.e. Cost , Manufacturing ,

Availability etc.• Learned about different parts of aviation i.e. Aircraft parts , Hot air balloon parts.• Learned about new material.