Design Engineer Aircraft
Resume:
SANJEEVI KARTHIK NARAYANAN
AEROSPACE STRESS ENGINEER - RESUME
EXPERIENCE SUMMARY
• Having a total of 5 years and 10 months (onsite & offshore) experience in Structural Analysis of Aircraft Components.
• Worked at customer location (Bombardier, USA) for 1 year and 6 months in MRB Stress Support (Concessions).
• Experienced in static and fatigue analysis of Bombardier BA Global 7500 Wing components
(Both Metallic and Composite structures) for EIS and Flight Test phase.
• Good theoretical knowledge on Aircraft Structures, Strength of Materials, Mechanics of Materials, Finite Element Analysis and Composite Materials.
• Ability to perform static analysis using classical hand calculations by building templates.
• Experience in the use of FEA modelling techniques for loads extraction, linear static analysis and fatigue analysis.
• Proficiency with CAE software’s like MSC Nastran/ Patran, HyperMesh, ANSYS and CAD software CATIA V5.
• Familiar with the use of MMPDS and familiar with Bruhn, Niu and Peterson stress books for stress methodologies.
• Excellent skills in writing technical reports (Stress Dossier) as per the Certification Standards.
• Good organizational, written, oral communication skills, highly articulate, adaptability to situations, self-confidence, demonstrating exceptional relationship building, quick learner with good decision making, analytical and interpersonal skills.
ACADEMIC PROFILE:
M.Tech in Aeronautical Engineering (2012-2014) with Distinction (CGPA – 9.49) from Hindustan Institute of Technology and Science (Hindustan University, Chennai, Tamil Nadu, India) Bachelor of Engineering in Aeronautical Engineering (2008-2012) with CGPA - 8.73 from Nehru Institute of Engineering and Technology, Coimbatore (Affiliated to Anna University, Chennai, Tamil Nadu, India)
ACADEMIC PROJECTS
• Completed project on “Bearing Bypass Analysis of Bolted Composite Joints” TECHNICAL SKILLS
CAE Packages : MSC Nastran/Patran, HyperMesh, ANSYS CAD Packages : CATIA V5
Platform : Windows 98/2000/XP/VISTA/07/08/10
Other Packages : MS Office 2019 and earlier
SANJEEVI KARTHIK NARAYANAN
WORK EXPERIENCE
Name of company : CYIENT Limited, Hyderabad
Period : October 2014 – August 2020
Title/Designation : Senior Design Engineer.
EXPERIENCE DETAILS
Projects undertaken in chronological order:
1. Fatigue Analysis of Bombardier Global 7500 Aircraft Inboard and Outboard Flap Client : Triumph Aero structures - Vought Aircraft Division, USA Software used : Nastran/Patran, HyperMesh, CATIA, Golihat Description:
• The scope of the program is to provide the detail fatigue analysis of various flap components such as spars, tracks, ribs, skin and fittings.
Responsibilities:
• Identification of critical location of various flap components such as spars, tracks, ribs, skin for fatigue analysis.
• Fatigue analysis of airload ribs, track ribs and flap tracks.
• Extraction of loads for analysis & calculation of GFI using Golihat.
• FEM modeling of track ribs using HyperMesh & Patran (Meshed the components using 1D, 2D & 3D elements).
• Linear static analysis of flap tracks & track rib using Nastran.
• Report generation for flap tracks, skin, spar, fitting, airload rib and track rib. 2. Fatigue Analysis of Bombardier Global 7500 Aircraft Wing Under Slat Surface Client : Triumph Aero structures - Vought Aircraft Division, USA Software used : Nastran/Patran, HyperMesh, CATIA, Golihat Description:
• The scope of the program is to provide the detail fatigue analysis at cutout and joint locations of skin, spar joints and ribs.
Responsibilities:
• Identification of critical location for wing components such as spars, ribs and skin for fatigue analysis.
• Fatigue analysis of skin, rib cutout and joint locations using Max Principal method and End load methodology.
• Extraction of loads for analysis & calculation of GFI using Golihat.
• FEM modeling of skin and rib assembly using HyperMesh & Patran.
• Linear static analysis of skin and Rib assembly using Nastran.
• Report generation for skin cutout, rib cutout, skin to spar joint and rib to spar joint locations. SANJEEVI KARTHIK NARAYANAN
3. Bombardier Global 7500 Aircraft Inboard Flap Design Client : Triumph Aero structures - Vought Aircraft Division, USA Software used : Nastran/Patran, HyperMesh, CATIA, Slim tool Description:
• The scope of the program is to provide the analysis and design of inboard flap for Bombardier Global 7500 series aircraft from conceptual stage until parts release. static, fatigue and fail-safe analysis was performed for flap structure.
• Structural requirements include strength and stability criteria.
• Analysis and stress substantiation were to be provided for various flap components such as spars, tracks, ribs, skin and fittings.
Responsibilities:
• Static analysis of aft Tracks.
• Analysis for strength and stability for Aft Tracks using hand calculations and DFEM Analysis using HyperMesh and Nastran/Patran. Section strength and stability checks were evaluated to arrive at margins.
• Report generation for Aft tracks.
4. Residual strength analysis of Bombardier Global 7500 Aircraft Inboard & outboard Flap Client : Triumph Aero structures - Vought Aircraft Division, USA Software used : Nastran/Patran, HyperMesh, CATIA, Slim tool Description:
• The scope of the program is to provide the residual strength analysis of inboard flap for Bombardier Global 7500 series aircraft flap structure after bird strike.
• Analysis and stress substantiation were to be provided for various flap components such as spars, tracks, ribs, skin and fittings.
Responsibilities:
• Static analysis & sizing of rib, spar & skin.
• Extraction of free body loads for analysis using Nastran/Patran & slim tool.
• Analysis for strength and stability for rib, spar & skin using hand calculations. Section strength and stability checks were evaluated to arrive at margins.
• Fastener analysis at rib to spar, rib to skin & spar to skin joint locations.
• Report generation for rib, spar & skin analysis. SANJEEVI KARTHIK NARAYANAN
5. Assembly Pre-Planning for Bombardier and Embrarer Structural Parts Client : Triumph Aero structures - Vought Aircraft Division, USA Software used : CATIA V5, ENOVIA PLM, MES
Description:
• The scope of the project is to create FAI pre-plan operation instruction sheets for assembly of leading edge, trailing edge, front center spar, rear center spar, lower skin, upper skin, wing box and wing joints of wing assembly for Bombardier Global 7500 aircraft and fuselage components of Embraer EA190 aircraft.
• All assembly parameters related to locating, fastening, drilling and sealant applications at assembly level are planned.
• FAI preplanning provides assembly requirements of the customer as per AS9102 aerospace standard.
Responsibilities:
• Preparation of pre-plan operation instruction sheets for assembly of leading edge, trailing edge, front center spar, rear center spar, lower skin, upper skin, wing box, wing joints of the wing structure and fuselage structure.
• Referring to the applicable Bombardier standards as per customer requirements
• Creating AS9102 Forms, bubble drawing and FAIM loader
• Coordination with the onsite coordinator and customer to ensure best in quality pre-plan and operation instruction results for submission
• Performing the quality check and maintain team quality metrics in E3
• Prepare weekly reports and project highlights including forecast for upcoming week(s) 6. MRB Stress Support (Concessions) for Bombardier Global 7500 Aircraft Client : Bombardier, USA
Software used : Nastran/Patran, HyperMesh, CATIA V5 Description:
• The scope of this project is to analyse the damaged metallic and composite components of Bombardier Global 7500 aircraft wing components (wing root to wing tip) and to prepare a concession report for the same.
Responsibilities:
• Analysing the components that were damaged during manufacturing or during the flight to ensure that the component is safe to use it back in the aircraft.
• The damaged components are re assessed to ensure that they can be able to withstand the loads even after the damage.
• Analysing concessions such as the gap, dent, tool mark, crack, undersize thickness and hole oversizing in the fastener regions.
• Preparing concession report for the damaged component compared with the undamaged component. SANJEEVI KARTHIK NARAYANAN
PROFESSIONAL ACHIEVEMENTS:
• Awarded “TEAM OF THE MONTH” in April month 2015 for successful fatigue analysis of Inboard Flap for Bombardier Global series.
• Awarded “TEAM OF THE MONTH” in July month 2015 for outstanding contribution towards completion of Stress Reports for BA wing program.
• Awarded “TEAM OF THE MONTH” in July month 2016 for successful residual strength analysis after bird strike of Inboard & outboard flap for Bombardier Global series.
• Awarded “TEAM OF THE MONTH” in July month 2017 for Receiving Good Comments from Bombardier.
• Awarded “ASSOCIATE OF THE MONTH” in December month 2016 for providing valuable support in Meshing of IBF & OBF Components.
• “MOST VALUED PERFORMER BRONZE AWARD” in February month 2020 for my contribution on MRB Stress Support.
PERSONAL PROFILE
Date of Birth : 16-12-1990
Sex : Male
Marital Status : Single
Nationality : Indian
Permanent address : F1 Sabari Flats,
124\54 North mada Street,
Vadapalani
Chennai - 600026
Tamil Nadu
Contact No : +91-837*******
Personal Email ID : ***************@*****.***
I do hereby confirm that the information given in this form is true to the best of my knowledge and belief. Date: Sanjeevi Karthik N
Contact this candidate