Mechanical Engineer, Aerospace, Finite Element Analysis, Stress

MOHSIN KHAN

**-*-***/*&C/***, Salva Residency, Amba Gardens, Mehdipatnam, Hyderabad-500028, Telangana, India,

Contact: +919*********

Email: ************@*****.***

PROFILE

I am a post-graduate with a master’s degree with a specialization in Aerospace Engineering, with a keen interest in the design and stress analysis of aircraft primary and secondary structures, where I can contribute towards upcoming technology, innovations and, manage key projects that impact the organization as well as broaden my scope of learning.

SUMMARY OF EXPERIENCE

Computation of section properties using hand calculations i.e., Moment of Inertia (I) or Second moment of area.

Good level of understanding of the pure bending theory and Euler’s theory of column buckling.

I have knowledge of aircraft primary and secondary structures such as skin-stringer panels, design of shear fitting or lug sizing, pin-sizing, secondary bracket, sizing of ribs and spars, structural joints.

Understanding of the fastener checks such as bolt shear, bolt tension failure, plate tension, plate bearing and bolt pull-through.

Hands on experience of the classical-hand calculations for the aircraft skin-stringer panel analysis, lug sizing, secondary bracket and the bolt group analysis as per the global industry methods and standards.

I have understanding of the intact load and fail safe conditions for a lug design using design and limit loads respectively (as per FAR regulations).

I am aware of the global industrial methods and standards such as Michael Niu, Roark’s Formula for stress and strain, ESDU Methods and MMPDS.

Understanding of the conceptual study of the vertical tail to rear fuselage interface.

I have a good experience and understanding of the Finite Element Methods such as linear analysis and buckling analysis.

Very good understanding of the best practices and standards of Finite Element Analysis such as Quality Assurance of the Finite element model i.e., free edge checks, coincident nodes, element connectivity, element quality aspects etc.

I have a good awareness of the MSC Patran element library such CROD, CBEAM, CBAR, CBUSH, SHELL, PLATE, 0D, MPCs, RBE, QUAD, TET, HEX, as well as enforced displacements using SPCD.

Good exposure to the design life cycle of the aircraft structures.

I have good knowledge of aircraft metallic and composite materials and properties.

Awareness of the design processes involved in the composite construction.

I have knowledge of ply stacking sequence guidelines, composite material properties and allowable, composite failure theories such as Hill’s theory, Hoffman’s theory, Tsai-Wu theory and the Yamada-Sun Failure criteria.

Hands on experience of the composite stacking sequence and analysis using finite element method.

I have exposure to aircraft interior structures and interface loads such as stowage unit, galleys.

EDUCATION

MSc. Aerospace Engineering -University of Hertfordshire (Jan 2016-Feb 2018) - Hatfield, United Kingdom.

B.E Mechanical Engineering -Osmania University (Oct 2010 – Oct 2014) – Hyderabad, India.

TRAININGS AND CERTIFICATIONS

Core Design Engineering course – A school of Industry Oriented Engineering & Solutions.

Structural Certification of Aircraft Composite Interiors – High Peak Courses.

Actively participated in the webinar on Metal Matrix Composites and Applications conducted by MAFTREE.

Presented a seminar on Composite materials and their applications.

Actively participated in the webinar on Buckling of Flat plates and Stiffened Panels conducted by MAFTREE.

PROJECTS

Sizing of Skin-Stringer panel as per global industry methods and standards ESDU 81047

The aim of the project was to evaluate the buckling phenomenon due to uni-axial, bi-axial, shear and combined loads.

Extraction of loads from the GFEM acting on the specified panel using sub-modelling technique.

Creation of input deck for the Finite Element Analysis of the Panel using PATRAN-NASTRAN.

Post-processing and interpretation of the results obtained, and updating of the skin-stringer parameters accordingly to improve the stability of the panel in buckling.

Application of the updated results obtained back into the GFEM.

Design of Shear Fitting

The aim of the project was to design a shear fitting to attach the Vertical Tail to fuselage interface.

Extraction of the in-plane loads (X and Z forces) from the GFEM.

Sizing of the lug using industry approved method ESDU 91008 to satisfy the failure criteria.

Finite Element Analysis of the fitting using 2D and 3D idealization in MSC PATRAN-NASTRAN.

Calculation of Reserve Factor/ Margin of Safety, as well as performing fastener checks.

Interpretation of the post-processing results for any improvements in the design.

Bolt group Analysis of structural joints

The aim of the project was to design a lap-joint subjected to axial loads on one end.

Creation of model with and without 2D offset.

Creation of the input deck for the Finite Element Analysis of the Lap-joint.

Post-processing and interpretation of the bushing forces acting at the joints.

Fatigue Analysis of Heavy-Duty Connecting Rod (Forged Steel and Aluminium Alloy 7475).

The aim of the project was to analyse the heavy-duty connecting rod and compare the results of forged steel and aluminium alloy 7475.

Modelled a Connecting rod used in an Ashok Leyland Heavy Duty Truck by reverse engineering process using CATIA.

Structural analysis was performed to validate the strength of the connecting rod using ANSYS.

SKILLS

1.MSC PATRAN-NASTRAN

Linear static Analysis.

Buckling Analysis.

Element Library and quality aspects.

Meshing – Iso and Paver

Quality checks and assurance.

Creation of analysis deck.

2.CATIA

Sketching – creation of sketch geometry, sketch constraints, sketch tools,

Part creation – base feature, create pad, pocket, holes, fillet, chamfers

Drafting – new drawing, create views, create dimensions and annotations, additional views.

3.Microsoft Office

Excel (Styles, Templates, Tables, Version Control).

Word (Report writing)

PowerPoint (Presentation)

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