CURRICULUM VITAE
Personal Information
Name
Narasimha Prasad
Qualification
Masters in Machine Design
Nationality
Indian
Visa status
Valid Blue Card (aufenthaltserlaubnis)
EU Workpermit
Current location
Hamburg, Germany
Designation
Senior Stress Engineer
acqw54@r.postjobfree.com
Mobile
Personal background
Key competence
Employee in business unit Aviation Stress Engineer
Career level: Advanced
6 years’ experience in the area Stress Analysis
Preferred location /mobility: flexible
Availability: short term/as agreed
Experience in Stress analysis(CAE/FEM)
Gas Turbine Engine/Nacelles/Turbine Blades, Mechanical Structures.
Commercial as well as business jets
Tool knowledge: Patran/ Nastran, Ansys/ Workbench, Hypermesh, ISAMI, Catia V5, MS Excel, Ansys,
F&DT
Calculations: Linear, Nonlinear, Contacts,Buckling, Vibration,Steady State Thermal, Dynamic studies and Static studies for both metallic and composite structures.
Skills
Tool Skills
NASTRAN
6 Years
Advanced
PATRAN
6 Years
Advanced
HYPERMESH
6 Years
Advanced
CATIA V5
1 Year
Good
Airbus collection programs
3 Years
Good
ANSYS/Workbench
6 Year
Advanced
ISAMI
3 Year
Good
MS –Office
6 Years
Advanced
Language Skills
English
Fluent
German
Basic
Professional Experience
Project – 1
Title
Structural analysis and Sizing of Nacelle Metallic and Composite components
Customer
Bombardier and Mitsubishi
Company
Goodrich
Industry
Aerospace
Role in Project
Senior Stress Analyst
Description
To carry out the design and sizing of the metallic components of the Nacelles-C-series and MRJ. The various metallic components to be designed include the Drag link, Drag link fitting, Upper bumper, Lower bumper, Thrust Reverser Actuation Systems and brackets including the joint analysis. The component needs to be understood and hand calculation methods are to be defined using suitable Bruhn and Niu references. These components are analyzed for 3 load cases which include ultimate, failure and LCF load cases and sizing is carried out to determine the optimum working solution in terms of weight and design. A detailed stress dossier report was prepared after reaching every Maturity describing the critical Margin of safety and the critical locations calculated for all the components.
Responsibilities:
Meshing the components and creating the metallic structure for Nacelle components using MSC PATRAN .
Creation of fastener by using CBUSH Element in MSC PATRAN .
Carrying out the quality checks .
Understanding the load cases .
Define the calculation method that is required to carry out the sizing work using methods such as, Bruhn, Niu standards .
Size the component in line with the design to obtain the best result in terms of weight and optimum performance of the components .
Carryout weekly meeting with the customer to discuss the work that was carried out in the whole week .
Composite blocker door analysis.
Interact with the design team so as to understand the design limitation in order to optimize the component in all aspects .
Carry out the static analysis and joint analysis for all components for all possible failure modes .
To determine the Margin of safety for all failure modes .
Preparation of Stress Dossier report after each maturity level .
Tools
MSC NASTRAN
MSC PATRAN
CATIA V5
Project – 2
Title
Structural Design and analysis of Gas turbine blades and components.,
Duration
2 years
Customer
Rolls Royce and Honeywell
Company
Honeywell
Industry
Aerospace
Role in Project
Senior Stress Analyst
Description
Objection is to perform Aero-engines - rotors, blades and blade locking mechanism,structural design, product development, simulation of turbo machinery, aero engine, structural analysis (stress analysis, vibrations, Fatigue (LCF, HCF), over-speed, and burst margin), safety evaluation of gas turbine blades and rotors at Aero Engine unit. Structural Assessment of Bladed disk and blisk of first stage compressor Aero-engine. Strength and safety evaluation of bladed disk and blisk for structural integrity. Design modifications on bladed disk (topological optimization) to develop blisk
Responsibilities:
Performed various analysis such as linear, non-linear, dynamics, fatigue…etc for rotating components in various projects.
Hand calculations of blade force measurement using in-house design tools.
Blade frequency measurement using in-house tools.
Mathematical modeling of rotating disc using CAE, validated the results with tests.
Effect of taper twist, caster, camber on blade frequency using CAE tools.
Effect of tip rubbing gas turbine blade during over speeding.
Stress Analysis of Gas Turbine Blade for “Safe Life Design”.
Frequency evaluation through Campbell and SAFE diagram.
LCF and HCF analysis of Bladed disk and blisk ( Lifing ).
Disk stress evaluation for over-speed and burst margin limits employing Hallian approach
Tools
Ansys Workbench
Ansys
MS office
Project – 3
Title
Nonlinear contact analysis of MIXER for BR700NG Gas Turbine engine (Ansys )
Duration
Since 01/ 2014- 2015
Customer
Rolls Royce
Company
Altran
Industry
Aerospace
Role in Project
Senior Stress Analyst
Description
Objective was to perform structural static analysis ( nonlinear contact analysis) for Mixer body of BR725 and BR700NG,establish the contacts for the modal at different locations such as finger fairing, mixer body, intermediated ring, LPT fairing, baffle and the brackets.Thermal steady state analysis before the static analysis with contact boundary conditions such as bonded contacts and frictional contacts at the main mixer body.Harmonic analysis for HCF.Elastic plastic analysis for the Mixer body location
Responsibilities:
Extraction of geometric model from UG into Ansys workbench.
Preparing the model according to the requirement of the analysis .
Establishing bonded and frictionless contacts at different locations of the model.
Meshing the model.
Perform thermal analysis according to necessary thermal boundary conditions from Aerodynamics.
After performing thermal analysis, static contact nonlinear problem is to be solved using Ansys Workbench solver
Post processing the model for von Mises and Principal stresses at different locations of the model.
Modal analysis at the end to know the frequencies.
Dynamic analysis involves, modal and harmonic analysis .
HCF is determined using modal stresses and the frequencies from the modal analysis.
Performing harmonic analysis for HCF calculation
Goodman calculation for mean stress effect
Presentations and calculations for design review
If there is plastic behavior at some location of the contact then bilinear material properties are applied to run elastic plastic analysis.
LCF is performed for 6505 load case and knowing the life of the component.
Report preparation for the complete analysis as the design approval
Tools
Ansys Workbench 14.0
MS office
Project – 4
Title
Structural Analysis of Boeing 787 Fuel Shutoff Module (FSM)
Duration
1 year
Customer
Boeing
Company
Goodrich
Industry
Aerospace
Role in Project
Stress Analyst
Description
Objective was to perform structural analysis of Fuel Shutoff Module for critical load cases like emergency landing loads. Hand calculations are performed to check the strength of the critical section, strength of the fastener attachments, lug analysis and fatigue analysis for the FSM and its components. Modal analysis was performed to determine critical frequencies and random vibration analysis for average stresses useful in determining life using Miners rule. A detailed structural report was prepared calculating margin of safety for all the attachments.
Responsibilities:
Geometry extraction of the component using CATIA V5 .
Meshing the model using HYPERMESH/ ANSYS .
Few of the components were modelled as point mass and connected by MPC’S .
Understanding and applying load cases and properties .
Mounting foot analysis which has the attachment similar to a lug .
Bolt group analysis at the attachment location using MS excels .
Modal analysis, random vibration analysis using ANSYS
Fatigue analysis for the estimation of life .
Sectional analysis for theoretical validation against FE static stress analysis .
Results extraction from ANSYS.
Static analysis using hand calculation to determine the Margin of safety for all critical loads such as 4g, 10g, 9g, 3g, and 2g .
Preperation of Structural Report .
Tools
ANSYS
HYPERMESH
CATIA V5
Project – 5
Title
Structural Stability Analysis of Reduction Gear Box (Submarine)
Duration
03/ 2009 – 09/ 2009
Customer
Rolls Royce
Industry
Gas Turbine
Role in Project
Stress Analyst
Description
Objective was to perform structural static analysis of reduction gear box for critical load cases like thrust loads and static loads. Simple static stress analysis for finding out displacements at bearing location and Von Misses stress at critical location. Hand calculations are performed to check the stiffness of radial and axial bearings the Reduction Gear Box. A detailed structural report was prepared calculating stiffness’s of the bearing and reserve factors for all the bearings.
Responsibilities:
Extraction of the geometric model using CATIA V5.
Meshing the model using HYPERMESH/ MSC PATRAN.
Understanding and applying load cases and properties.
Assigning proper material properties for the metallic components.
Results extraction from MSC PATRAN & MSC NASTRAN.
Determining bearing stiffness using hand calculation and reserve factors for all critical loads.
Stress analysis using FEM and hand calculation was performed.
Load check and validation were part of hand calculation.
Vibration analysis for the rigid body mode calculation.
Structural stability report generation.
Tools
MSC NASTRAN
MSC PATRAN
HYPERMESH
CATIA V5
Project – 6
Title
A350-1000 Side Shell Fuselage (Composite)
Duration
Since 01/ 2015
Customer
Airbus
Customer
Altran
Industry
Aerospace
Role in Project
Senior Stress Analyst
Description
Objective was to perform structural static analysis for Side Shell Fuselage composing of frames, skins, A bracket and B bracket. Initially load comparison is made with A350-900, if the loads are similar then the brackets with frame location are passed by comparison. For brackets with new interface loads and new design complete DFEM analysis is performed by taking the section of the model at frame and bracket location. Loads are extracted from the fastner locations after performing Composite static analysis using NASTRAN PATRAN . The extracted loads are input into ISAMI for calculation for RF of bearing and bearing bypass at the fastener hole location
Responsibilities:
Comparison of loads from VPM at different IP locations and numbers.
Finding the location of brackets using Trent.
IP’s which are having higher loads are considered for Static FE analysis.
Model is cut in CATIA at the frame location of IP bracket.
This model is imported in Patran using Step file.
The model is meshed, proper boundary conditions and material properties are given at each location.
Frames,Skins are of composites and the brackets are metallic, the iteraction is with cbush and the RBE’s .
Load is applied at lug hole location of B bracket.
Fastener forces are extracted using RPT files.
The forces from FE analysis will be the input for Filled hole analysis in ISAMI.
RF summary sheet is prepared after performing Filled Hole Analysis
Tools
Nastran/Patran
ISAMI
MS office
Project - 7
Title
A380 SRM Section 13 and Section 18
Duration
Since 07/ 2014
Customer
PAG
Company
Altran
Industry
Aerospace
Role in Project
Senior Stress Analyst
Description
Objective was to create Service Repair Manual for A380 aircraft.
This report presents the allowable damages due to dents in the fuselage skin panels of the A380-800e Section 13 Forward Fuselage. The forces, the skin thickness and the geometrical data are based on the certification stress reports for the fuselage skin panels including frames and stringers..
This justification refers to the original skin thickness. Additional damages are not taken into account. In affected area the skin is free of cracks. The inner sub-structure is free of cracks and free of severe bending damage, adjacent fasteners are not affected. There is no oil canning effect investigated.
Responsibilities:
Calculation Section 13 Dents Fulfilling Form and Nearness Criteria
Calculation of Frames for all the Section 13
Calculation of Crash Load Cases
Geometric Data and Strength Characteristic
Sizing and Typical Selected Load Cases
Specific Post-Processing Hypotheses, Methods and Tools
FEM Detailed Description
SCHADI and SPADI with ISSY
Tools
Nastran/Patran
ISSY
MS office
Project – 9
Title
A350-900 BCD lining (Composite)
Duration
Since 08/ 2013
Customer
Airbus
Customer
Altran
Industry
Aerospace
Role in Project
Senior Stress Analyst
Description
Objective was to perform structural and stability static analysis for BCD lining composing of frames, skins .FE analysis is performed on the BCD lining made of CFRP material, fasteners are modeled using cbush at the bolt hole locations, forces at bolt hole locations are extracted for filled hole analysis using ISAMI, frame beams are checked for panel, web, flange and inter rivet buckling analysis is performed for stability check .
Responsibilities:
Load precedence check .
FE modeling using Patran for BCD lining and beams of the frame.
Material property and CFRP assignment for the shell elements
Orientation of material and assigning proper ply thickness according to the
Airbus guideline
The model is meshed, proper boundary conditions and material properties are given at each location.
Displacement and rigid elements are used at the bolt hole and clamping locations.
Pressure load is applied on the outer skin location
SOL101 is run for the FE analysis
SSOL105 for the stability check of frames.
OR buckling panel analysis is performed with ISAMI
Shell forces and moments are extracted from FE
Fastener forces are extracted using RPT files.
The forces from FE analysis will be the input for Filled hole analysis in ISAMI.
Corin analysis is performed at the L angle locations.
Fatigue and Damage Tolerance (F&DT) analysis is perfomed with ISAMI.
RF summary sheet is prepared after performing Filled Hole Analysis and Corin analysis.
Tools
Nastran/Patran
ISAMI
MS office
Project – 10
Title
Static stress analysis of brackets and connectors for A350-900 FTI fuselage sections
Duration
Since 08/ 2012
Customer
Airbus Hamburg
Company
Altran
Industry
Aerospace
Role in Project
Senior Stress Analyst
Description
To carry out static stress analysis for flight test installation in section 15 of fuselage having brackets, connectors and ramps.Indentifying optimum weight of the bracket, ramps with electrical harnesses using Catia, in order to maintain below the range of weight mentioned in the legacy document. Fixing optimum weight as the reference and pass components by the measument of weight itself, else a static analysis is conducted for RF checks. A calculation sheet for the FE analysis has to be prepared as the documentation. Hand calculation is performed for quick checks of ramps and brackets static strength.
Responsibilities:
Meshing the components and creating the metallic FE structure for FTI brackets using MSC PATRAN .
Creation of fastener by using CBUSH Element in MSC PATRAN .
Carrying out the quality checks .
Understanding the loads acting on the bracket.
Calculation is done using Airbus methods.
Carryout weekly meeting with the customer .
Interact with the design team so as to understand the design limitation.
Carry out the static analysis and joint analysis of components for possible failure modes .
To establish the Reserve factor for failure modes .
Preparation of calculation sheet at the final level of stress analysis .
Tools
MSC NASTRAN
MSC PATRAN
CATIA V5
ISAMI
Project – 11
Title
Perform static analysis on Airbus A400 Ribs for all components in the Section
Duration
10/ 2010 - 05/ 2011
Customer
Airbus
Company
Atkins
Industry
Aerospace
Role in Project
Stress Analyst
Description
To carry out the buckling analysis, static stress analysis on various components in Section. The various components to be analyzed include panels, stiffeners, castellation, rib feet, rib to spar joint, rib to cover, castellation joints and fasteners. All the geometric parameters need to be extracted from CATIA V5 and the analysis to be carried out using RAMSAS. These components are analyzed for different load cases. A detailed stress dossier report was prepared after reaching every stage describing the critical Reserve factor and the critical locations calculated for all the components. The project is executed in various stages for Panels, Stiffeners and joint analysis.
Responsibilities:
Extracting the geometric parameters using CATIA V5.
Updating the obtained values in the VBA-Excel provided from the client.
Validating the obtained results using RAMSAS.
Stress Dossier report preperation.
Tools
Airbus Collection Programme
MSC PATRAN
CATIA V5
Project – 12
Title
Airbus A320 Sharklet Pylon Reinforcement Static analysis using FEM and theoretical validation
Duration
06/ 2010 – 09/ 2010
Customer
Airbus
Company
Atkins
Industry
Aerospace
Role in Project
Stress Analyst
Description
To carry out the investigation on A320 Sharklet Pylon Reinforcement attachment and determine the behavior due to Gust loads and compare them so as to check whether internal loads created due to gust loads in the original model are representative or not and to conclude whether the analysis level of the detailed FEM is sufficient enough to reproduce the gust loading. Loads and boundary condition is to be applied as per the requirement and FE stress analysis is carried out and justification report was prepared along with theoretical hand calculation.
Preparing the way forward document and have customer approval.
Meshing the model using MSC PATRAN.
Updating the material properties for the component.
Applying the loads and boundary condition.
Extract the reaction loads and determine load distribution for generated FE model .
Fastener analysis at various location of the reinforcement .
Prepare investigation report concluding the summary of comparison .
Tools
MSC NASTRAN
MSC PATRAN
Project – 13
Title
Static analysis of Airbus A320/A321 Sharklet Fixed Leading Edge and Fixed Trailing Edge of a Wing Structure
Duration
10/ 2009 – 05/ 2010
Customer
Airbus
Company
Atkins
Industry
Aerospace
Role in Project
Stress Analyst
Description
Objective was to validate the existing design of FTE and FLE under limit and ultimate load cases. Margin of safety calculations are carried out for all load cases and are reported. All calculations are carried out using theoretical and empirical relations with assumptions. Preparing the excedance check for the established reserve factors.
Responsibilities:
Understanding load cases and properties.
Involved in carrying out assumptions.
Carry out the hand calculations to determine the reserve factor using Classical methods.
Report generation .
Tools
MSC PATRAN
CATIA V5
Professional Education
2008
Master in Machine Design, Vishweshwariah Technological University, Bangalore