Dipl.-Ing. Sudharshan Vankamamidi

 3D Printing brackets (Fire Bottles Cradle A350-900) optimization and justification, Static, Buckling and wind milling  Major Repair of Vertical Tail Strike on Section16-18 A350-900. DFEM check and validation, Plain Strength Check, Damage Tolerance, Fasteners bearing check, buckling analysis and preparing Stress dossier as per FAR-JAR and EASA standards. Software: ISAMI, ISSY, Nastran, Patran, Hyper Mesh and Catia-V5, Trend, PDM Link, Python.

 Stress justification for Cargo Door surround shear plates Section16-18 A350-1000.DFEM check and validation, Transverse Damage Tol-erance, Edge Damage Tolerance, Corin Analysis, Filled Hole Analy-sis Composite / Metallic, Inter Rivet buckling, Strength check , Free Flange Damage Tolerance and Buckling Analysis and preparing the RF summary Software: ISAMI, Nastran, Patran, Hyper mesh and Catia-V5, PDM Link, Trend

Strength, Thermal, Durability, Vibration and Frequency Response analysis of steering knuckle, Pipe support for steam boiler, Ignition switch of bike. Pretension, Nonlinear Contacts using Abaqus and Hyper mesh. Head impact on instrumental panel, Bus role over analysis using LSDYNA. Meshing with Ansa, Hyper mesh (sheet metal, plastic and HEXA meshing).

Performing Concessions (Repairs and Solutions) for section 16-18 and 13- 14 primary structures. Preparing Stress and Fatigue justification in accordance to A350-XWB requirements. Expertise in modeling and validate DFEM (Detailed Finite Element Model) using condensation and integration methods as per Airbus and PAG standards. Modification of existing DFEM as per new repair proposals, validating DFEM with GFEM and creating a new. Software: ISAMI, Patran/Nastran, Hyper Mesh, Optistrut, ISSY and Catia V5.

 Worked on technology road map project to ascertain a highly automated precise process to replace existing production (VARTM) for the manufacturing of wind turbines nacelle covers.  In the preliminary design phase minimum thickness of the skin GFRP, layer orientations are calculated and bench marked for the critical load cases.

 A380 primary and secondary structures concession – Studying and justifying the non-conformities of A380 primary structures which include aluminum and GLARE structures.  Technical, in-service and airworthiness assessment of the received concession in accordance with A380 SRM and HSB methods used for static and fatigue strength

Role & Achievement: • Creating a material database for composites (using LS-DYNA 971) documenting different material cards suitable for Monolithic Skins and Foams with different failure criteria’s • To perform static and dynamic analysis of various automobile components using HYPERMESH 8.0 and LS-DYNA 971 • Tolerances stack up analysis for combustion chamber volume of six cylinder engine using Catia V5 and 3DCS Stand alone version • Tolerances stack up analysis of roof rack to meet the allowed assemb

Role & Achievement: • Building up a numerical model using LSDYNA 971 • Analytically determined residual strength in the composite/ sandwich panel after impact • Investigating the failure propagations for various impact velocities • Using contact algorithms to determine delamination failure between the lay-ups • Performed Software validation by comparing experimental and simulation results (Source: Airbus) Software: LSDYNA971, LSPREPOST

Advanced methods using CAD, Structural Analysis,Composites