Design Analysis And Fabrication Of Delta Wing Amphibian UAV
International Journal of Engineering Research & Technology (IJERT)ISSN: 2278-0181Published by :http://www.ijert.orgVol. 5 Issue 04, April-2016Design Analysis and Fabrication of Delta WingAmphibian UAVG. Mari Prabu M.ES. K. AravindhkumarAssistant ProfessorDept. of Aeronautical Engg.Sri Shakthi Institute of Engineering and TechnologyCoimbatore, IndiaDept. of Aeronautical Engg.Sri Shakthi Institute of Engineering and TechnologyCoimbatore, IndiaS. JeganDept. of Aeronautical Engg.Sri Shakthi Institute of Engineering and TechnologyCoimbatore, IndiaAbstract— This project reveals the design, analysis andfabrication of delta wing amphibian, Unmanned Aerial Vehicle(UAV). The UAV is capable of both vertical takeoff and landing(VTOL), and short takeoff and landing (STOL). This UAV canbe used for both surveillance and medical emergency. Adding anadvantage to this UAV camouflage image setup is used for thebetter surveillance in air and water. Delta wing is used for theserious aerobatic motions and control ability. Design andanalysis result shows that delta wing is suitable for thisquadcopter and gives the high lift coefficient and decrease indrag. The design is done by using CATIA V5 software and theflow and structure analysis is done with help of ANSYSsoftware. The lightweight materials like aluminum, corrugatedsheet and thermocol and card board sheet is used which reducesthe weight and helps the quadcopter to float in water.Quadcopter is being used to have better fuel efficient and reducein control channel. From the calculation and testing the range isobtained to be 7miles. The maximum speed is 30m/s and theendurance is to be 1hr 30 mints.Keywords—Amphibian quadcopter;analysis; structural analysis; flight testingI.Deltawing;flowINTRODUCTIONBirds can fly in sky due to their inherent characteristics.They are the dominant in the sky. It is human characteristics todominate or rule over other. So they tried their best to fly insky from dawn of civilization. And they got it through thesuccess of Wright brothers in 1903. Subsequently manymodernization and invention had done through 19th centuryand now a day’s fly without pilot is one of the most importanttopics of study worldwide for national, international, militarypurposes under the banner of Unmanned Aerial Vehicle(UAV).Unmanned-Aerial-Vehicle (UAV) development wasinspired by the evaluation of piloted airplanes. Interest in thedesign and development of small UAVs began for more than25 years ago. Although the definition of small UAVs isarbitrary, vehicles with length less than 6m and mass less than25 kg are usually considered to be in this category. There area wide variety of UAV shapes, sizes, configurations, andcharacteristics. Historically, UAVs were simple drones(remotely piloted aircraft),but autonomous control isincreasingly being employed in UAVs. UAVs come in twovarieties: some are controlled from a remote location(which may even be many thousands of kilometers away,on another continent), and others fly autonomously basedon pre-programmed flight plans using more complexdynamic automation systems.Small unmanned air vehicles (UAVs) can be deployed atthe front lines of combat to provide situational awareness tosmall units of troops through real-time information aboutsurrounding areas. The technical challenges for small rotarywing UAV systems are numerous. High thrust-to-weightratios are necessary for the propulsion system. An endurancelong enough to perform a meaningful mission will also beimportant. A careful matching of batteries, electric motors,and rotors will be essential; and these will have to be sized tocarry the necessary payload. Incorporating a reliable semiautonomous control system in these small vehicles, so that theoperator does not have to constantly monitor theirperformance or location,II.CAD MODEL DESIGNSolid modeling is the most complicated of the CADtechnology, because it stimulates an object internally andexternally. Solid models can be sectioned to reveal theirinternal features, and they can be stress tested as if they werephysically entities in the real world.A mathematical technique for representing solid objects.Unlike wireframe and surface, modeling systems ensure thatall surfaces meet properly and that object is geometricallycorrect solid models allows for interference checking, whichtest to see if two or more objects occupy the same space.Primary use of solid modeling are for CAD, engineeringanalysis, computer graphics and animations, rapidprototyping, medical testing, product visualization andvisualization of scientific research.A numerical model describes some physical phenomenonwhich comprises equation relating the dependent and theindependent variables and the relevant parameters typically, a416IJERTV5IS040708(This work is licensed under a Creative Commons Attribution 4.0 International License.)
International Journal of Engineering Research & Technology (IJERT)ISSN: 2278-0181Published by :http://www.ijert.orgVol. 5 Issue 04, April-2016numerical model consist of different equations that govern thebehavior of the physical system, and the associated boundaryconditions.The model for the numerical method is constructed usingthe software CATIA V5CATIA V5, which stands for Computer Aided Threedimensional Interactive Application, is the most powerful andwidely used CAD software of its kind in the world. CATIAV5 was created by Dassault System.Using the CATIA V5 software, constructed a solidquadcopter and the isometric view and the dimension of thequadcopter used are given:Now the below figure 2 reveals the detail design of theentire quadcopter. Which was designed by using CATIA V5and the tool used is generative sheet metal.TABLE 1: DIMENSIONS OF THE QUADCOPTERNo. of aluminum rodsArm lengthArm height4450mm12mmArm breath12mmArm thickness2mmArm angle90 degNo. of base plate2Base plate120mm x120mmBox thickness5mmArm cover length350mmArm cover height35mmArm cover breath35mmArm cover thickness5mmFIG 2: DETAIL DESIGN OF QUADCOPTERIII. FLOW ANALYSISAfter completing the design the next step is analysis. Theprocess of analysis starts with the meshing. Meshing is theprocess of sub dividing a structure into a convenient numberof smaller elements (mesh density)A question that frequently arises in computational fluidanalysis, how fines should the element mesh in order toobtain reasonably good result?” unfortunately, no one cangive you a definite answer to this question; you must resolvethis issue yourself.IV.BASE FRAME DESIGN OF THE QUADCOPTER:The below mentioned figure 1 shows the base framedesign of the quadcopter this designed is chosen for thestructural analysis of the quadcopter.MESH OF QUADCOPTER SURFACE BODYTABLE 2: MESH DETAILSMesh typeTriangular prism meshNo. of nodesN0. Of elementsNo. of facesMesh metric32484173574321759Skewness(0.8575451)A triangular prism mesh is used for this quadcopter toget the convenient values. Mesh view of the quadcopter isgiven below;FIG 1: FRAME DESIGN OF THE QUADCOPTERThe above figure 1 shows the base frame design of thequadcopter in which the wing structure with boat shape andother electronics item will be attached to it.FIG 3: MESH VIEW OF QUADCOPTER SURFACE417IJERTV5IS040708(This work is licensed under a Creative Commons Attribution 4.0 International License.)
International Journal of Engineering Research & Technology (IJERT)ISSN: 2278-0181Published by :http://www.ijert.orgVol. 5 Issue 04, April-2016After completing the CAD modeling, the next step is theanalysis of quadcopter. Before to start with fluent, it isnecessary to know if the meshed geometry is correct, so ischecked. To ensue with, we are to define the model, material,operating condition and boundary condition. Models are to beset in order to define the continuity, momentum, energyequations are dealt with our study, if the flow is viscous etc.We have chosen coupled solver, 2d implicit, absolute velocityformulation, cell based gradient option, superficial velocityporous formulation. As our flow is dealt with continuity,momentum, energy equation so is necessary to check themup. The material is selected as air and the density as ideal gasto make the solution simpler. Under the solve command thecontrol is initialization of value is compute from the inlet. Itis also necessary to select the appropriate approximationrequired in the residual command under monitor and check inplot to visualize the progress of iteration. Once everyparameter is described the iteration is performed till the valuegets converged to required approximation. The figure can beplotted between position in x-axis and any other function iny-axis from plot command. In the velocity magnitude,velocity vector, static pressure, quadcopter surface velocityhas been chosen. The three basic equations are:Continuity Equation: ρ/ t .(ρV) 0Momentum Equation: .(ρuV) - p/ x .(ρvV) - p/ y .(ρwV) - p/ zEnergy Equations: . [ρ(e v 2/2)v] - .(ρv)V.STRUCTURAL ANALYSISAfter completing the flow analysis using the ANSYSfluent software, now the structure analysis is also dose withsame ANSYS (static structural). The structural analysis isnothing but it is about to analysis of the materialcharacteristics. Such as stress, strain, load distribution anddeformation of the structure.In this structure analysis we calculated the followingmaterial properties for our quadcopter aluminum frame. Thematerials properties are: Total displacement Normal stress Normal strainThe following steps are carried out for our structural analysis: Applying the material property Meshing Load conditions Result by contourFIG 3: MESH VIEW OF QUADCOPTER BASE FRAMEVII. RESULT AND DISCUSSIONA. Flow analysisFrom the analysis of this quadcopter, it is clearlyvisualized the pressure and velocity distribution during theflow. We have obtained the co-efficient of lift and dragvalues from the iterations.TABLE 4: BOUNDARY CONDITIONSPARAMETERSValueInlet Velocity30m/sHydraulic diameter0.45mTurbulence intensity2.14 %Inlet static pressure1 barPRESSURE DISTRIBUTION OVER THE SURFACE.VI. MESH OF QUADCOPTER BASE FRAMETABLE 3: MESH DETAILSMesh typeTriangular prism meshNo of nodesNo of elements456817684SmoothingFineMeshFineFIG 4: STATIC PRESSURE CONTOUR PLOTS418IJERTV5IS040708(This work is licensed under a Creative Commons Attribution 4.0 International License.)
International Journal of Engineering Research & Technology (IJERT)ISSN: 2278-0181Published by :http://www.ijert.orgVol. 5 Issue 04, April-2016Firstly, we have done the flow analysis with zero degreeof angle of attack. Since our delta wing, which we have usedhere is static one.The pressure distribution over the surface. The inletpressure is given as the atmospheric pressure over the surfaceand the pressure flow is evenlly distributed over the surface.From the contour plots we can understand that the pressurestarts to decrease from the leading edge of the surface, it alsoindicates that the increase in velocity.F kuThe results are solved from the above equations and theresults are taken as the contour plots.TOTAL DISPLACEMENT OF BASE FRAMEVELOCITY DISTRIBUTION OVER THE SURFACEFIG 6: TOTAL LOAD DISTRIBUTION FOR STATIC STRUCTUREThe maximum total load distribution over the surface ateach end points of the frame. This picture also reveals theselected load is suitable for the designed frame and the load isacting very low at the fixed point. So this frame is suitable forthe selected thrust.FIG 5: VELOCITY CONTOURS OVER THE SURFACEELASTIC STRAIN OVER THE FRAMEThe velocity contour over the surface from the, figure itreveals that the velocity is maintained constant over thesurface. And the velocity is slightly increased over the midsurface of the wing. Since the velocity is increased over thesurface this model can be used for flying.TABLE 5: RESULT FOR FLOW ANALYSISPARAMETERSVALUEStatic Pressure over the surface101323 PaMaximum VelocityCo-efficient of liftCo-efficient of drag3.09e 01m/s1.4510e-026.0698e-03B Structural analysisAfter meshing the loading conditions are given to theselected frames. The loads are given in opposite to Xdirection at each ends points and the load is given as thethrust load. The load value is given as -1.5 which will givethe total displacement of the structure and also the normalstress and strain.The following equation is solved for the structuralanalysis for the structure. And the total load distribution,normal stress and strain for the given loading conditions. TheFinite element method is used for solving the structuralproblems.FIG 7: NORMAL ELASTIC STRAIN OVER THE FRAME419IJERTV5IS040708(This work is licensed under a Creative Commons Attribution 4.0 International License.)
International Journal of Engineering Research & Technology (IJERT)ISSN: 2278-0181Published by :http://www.ijert.orgVol. 5 Issue 04, April-2016ELASTIC STRESS OVER THE FRAMEFIG 9: PRE-FINAL ASSEMBLYThe metal frame construction with all the electronicscomponents attached to it.FIG 8: ELASTIC STRESS OVER THE SURFACEFrom the figures 7 and 8 it shoe the normal elastic stressand strain for the given loading conditions. From the aboveobtained result we can find that the designed structure issuitable for the loading conditions.FINAL ASSEMBLYTABLE 6: RESULT FOR STRUCTURAL ANALYSISPARAMETERSVALUESMaximum total deformation dueto the effect of the liftMaximum Normal elastic stressMaximum Normal elastic strain0.00001519 m6.4965e-05m/m5.24259e-05m/mVIII. FABRICATION PROCESSFabrication work started with the metal frameconstruction and mathematical analysis. All the electroniccontrols and the wing construction will be attached to themetal frame. For the construction of metal frame the materialis selected according to the estimated weight and total size ofthe model.Material used:1. Aluminum rod (frame)2. Aluminum sheet (base frame)3. Coharated sheet (wing section)4. Cardboard sheet (base plate)FIG 10: FINAL ASSEMBLY WITH CAMOUFLAUGE SETUP.IX. CONCLUSIONBy performance analysis from the both the softwareanalysis of the designed model and the test flight from thefabricated model the results are obtained and the performanceresults are calculated both by numerically and analytically theresults obtained are showing the positive for the use of thefabricated model. The flow analysis result shows the increasein velocity and decrease in velocity and also the proper valueof lift and drag. On the other hand we also done the structureanalysis for the frame here we obtained the values ofstructural properties of the frame such as maximum total loaddisplacement, normal elastic stress and normal elastic strainare calculated. Then the fabricated model is tested both on theair and water the altitude is maintained above 1000m and420IJERTV5IS040708(This work is licensed under a Creative Commons Attribution 4.0 International License.)
International Journal of Engineering Research & Technology (IJERT)ISSN: 2278-0181Published by :http://www.ijert.orgVol. 5 Issue 04, April-2016efficiency for the flight time is about 1hr: 30 mints and thetotal speed of the model in air is 30m/s and in the water is1m/s. these are results which we obtained from the softwareanalysis and the experimental work. From this we concludethat this can implemented as an real one for both the defenseand the social as an surveillance and medical emergency.ACKNOWLEDGEMENTThe authors acknowledge the valuable suggestion fromthe faculty of aeronautical engg., Sri Shakthi Institute ofEngineering and Technology.REFERENCE[1][2]DoD. Unmanned Systems Integrated Roadmap - FY 2009-2034,April 2008.Vargas-Clara A, Redkar S. Dynamics and Control of a Stop RotorUnmanned Aerial Vehicle, International Journal of Electrical andComputer Engineering (IJECE), 2013; 2(5): 597-608.[3]Yanhui G, Qiangui X, Shousong H, Xiao J. Flight Control SystemSimulation Platform for UAV Based on Integrating Simulink WithState flow, TELKOMNIKA Indonesian Journal of ElectricalEngineering, 2012; 10(5): 985-999.[4] Frederick-RecascinoC.New Uses for UAVs, Strata – Report onResearch, Embry-Riddle Aeronautical University, 2006.[5] Watts AC, Ambrosia VG, Hinkley EA. Unmanned Aircraft Systemsin Remote Sensing and Scientific Research: Classification andConsiderations of Use, Remote Sensing,2012; 4: 1671-1692.[6] Cox TH, Nagy CJ, Skoog MA, Somers MA. Civil UAV CapabilityAssessment, NASA Report, Dec 2004.[7] Wise J. Civilian UAVs: No Pilot, No Problem, Popular Mechanics,Oct 2009.[8] Rango A et al. Using Unmanned Vehicles for Rangelands: CurrentApplications and Future Potentials,” Environmental Practice, 2006;8: 159-169.[9] Wyllie D. Police UAVs – Nearly Limitless Potential, Police One,May 2012.[10] McKay J. Sacramento Police Unmanned Aerial Vehicle ProgramGaining Altitude, Government Technology Magazine, Sept 2007.421IJERTV5IS040708(This work is licensed under a Creative Commons Attribution 4.0 International License.)
Design Analysis and Fabrication of Delta Wing Amphibian UAV G. Mari Prabu M.E Assistant Professor Dept. of Aeronautical Engg. Sri Shakthi Institute of Engineering and Technology Coimbatore, India S. K. Aravindhkumar Dept. of Aeronautical Engg. Sri Shakthi Institute of Engineering and Technology Coimbatore, India S. Jegan Dept. of Aeronautical Engg.
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