1.2 in market of engineering applications, the

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2       Problem statement             Recently, sandwich compositestructures are widely used in aerospace, marine and automative applications.The significant of using honeycomb sandwich panels because their highlyefficient in stiffness-to-weight situations, strength-to-weight-ratios andenergy absorptions capabillties (J.R Vinson 1999). As an increasing the demandin market of engineering applications, the implementation of additivemanufacturing (AM) in fabrication sandwich composite is significant due to thelow cost in manufacturing, easy to shape any profile shape, flexibility inmanufacture and fast fabrication part in manufacture.

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             For cost in manufacturing, usingsubtactive method can exposed a lot of material that need to be removed andmostly this material cannot be recycled. Waste material occured when cores aremachined from large and flat sheet. From this factor, it can exposed to thehigh cost of sandwich panel.

This is proven when the component of wing mass isestimated about 30% and 70% comes from the cost (Pollardet al. 2017). In aerospacefields,the components often have complex geometries because aerospaceapplications usually require components with integrated functions.

A largevolume envelope-to-volume ratio, as in thin-walled structures, combustionchambers or turbine blade  the tool pathplanning algorithm very complicated, time consuming, and material-consuming byconventional computer numerical control (CNC) machining. By implementation ofAM, capability for freeform fabrication makes it very suitable for these kindof aerospace components.              Traditional corematerials like foam and Nomex honeycomb are milled using a tool path programand CNC equipment to sculpt the desired shape take 18 days and $27,000 to builda first article using traditional methods.

Using FDM, it can produce a firstarticle in roughly 6 days and at a cost of about $13,000.   (Jolie et al.,2017) evidenceexists in the aerospace industry which has reported a 70–85% reduction in manhours due to the implementation of automated composite tape layers wings andother internal features without degrading the composite core’s structuralintegrity. Producing these features with conventional core materials andfabrication methods is difficult or impossible due to the complex geometriesinvolved. The wind turbine blades will employ a sandwich structure instead ofthe more traditional skin-over-rib design used by most turbine blademanufacturers. Using FDM and a high modulus material like Polycarbonate, netshaped cores can be fabricated with the shear and compression strength neededto withstand the temperatures and pressures               In fabrication sandwich structure the commonfailure mode in sandwich composite structure which is compression areinvestigate.To test behavior of compression sandwich composite structure, thereare two types of test need to carried out such as flatwise and in-panel compression test. This test will be conducted using ASTM C365 M-05 and ASTM C364-16.

  1.3       Objectives To investigate the relation 3D printed honeycomb sandwich compositestructure   materials against compressionbehaviour of sandwich composite structure.      1.3.1       Toinvestigate the varying thickness of hexagonal honeycomb core using flatwisecompression test with ASTM C365 M-05  1.3.2       Toinvestigate the varying thickness of hexagonal honeycomb core using in-panelcompression test with ASTM C364-16 respectively.

  1.4       Scopes of research              This study review the effect ofcompression behaviour of sandwich composite structure subjected to flatwisecompression and inplane compression loading. The hexagonal honeycomb core aredesigned using 3D CAD software then fabricated with additive manufacturingtechnique.

  Fused deposition modeling, FDM-01(Mankati Fullscale XT Plus)  are used in fabrication core structure. The typeof material used for this machine is polylactic acid (PLA) while sandwichcomposite structure with honeycomb core were manufactured by using ply flaxfiber for the facesheet. Types of flax fiber used in this fabrication is (2´2twill)  in 400g/m2. Adhesive material used to honeycomb core are epoxy resin andvacuum bagging process. Flatwise and inplane compressive test were investigatedto evaluate the compression behaviour of sandwich structure with ASTM C365 M-05and ASTM C364-16. The various of failure modes were discussed based on the testresults.   1.5       Organization of report This study isorganized into the following chapters:Chapter 1:Introduction             Explain about the introduction ofthe present work.

This chapter will be divided into several subtopics ofresearch backgrounds, problem statement, objectives, scopes and organization ofreport. Chapter 2:Literature review            Literature review on the currentfabrication sandwich composite structure and methods along with an overview ofthe previous process. This chapter also exposed to the compression test forsandwich composite structure and their finding during the experiment. Theoverall thesis organization for manufactured sandwich composite stucture usingadditive manufacturing, FDM, and investigation on compression behavior within varyingthickness.

 Chapter 3:Methodology             Provides the details about thematerial that were used and geometries properties of the honeycomb core, facesheets . Compression test, flatwise and in plane compression test wereperformed to investigate the compression behaviour between sandwich strcturedesign parameters.  Chapter 4:Result             Explain the result and discussion.The result ontained throughout the experiment will be compared with thefindings o present research and result will be discuss throughly.

 Chapter 5:Conclusion Work             The conlcusions of this researchwork are discussed along with the recommendations for future work.  

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