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Subject: seeking job in finite element analysis (ansys)

Date: 10/25/02 at 9:41 AM
Posted by: M.Karthick
E-mail: karthiaero@rediffmail.com
Message Posted:

NAME:

M.KARTHICK

DATE OF BIRTH :

03JULY1981

SEX :

MALE

ADDRESS :

73/15C1,M.S.BHAVANAM
AYYALURROAD,ERIYODU
DINDIGUL- 624702


QUALIFICATIONS :

S.S.L.C
John Paul High School, Dindigul
State Board 89.4

Diploma In Tool Engineering
Institute Of Tool Engineering
State Board 84.16

B.E (Aeronautical)
Park College Of Engg & Tech, Coimbatore
Bharathiar University 75.45

.
ELECTIVES CHOSEN :

1.FINITE ELEMENT METHODS
IN AEROSPACE STRUCTURERS
2.VIBRATION& AEROELASITY
3. FATIGUE&FRACTURE MECHANICS
4.EXPERIMENTAL STRESS ANALYSIS

PROJECT TITLE :

FINITE ELEMENT FLUTTER ANALYSIS
OF AIRCRAFT WING USING ANSYS

LANGAUGES KNOWN :

TAMIL, ENGLISH

EXTRA CURRICLAR ACTIVITIES :

GAMES

COMPUTER PROFICIENCY :

AUTOCADD, 3DMAX, C++
ANSYS
STRUCTURAL :
STATIC ANALYSIS
MODAL ANALYSIS
HARMONIC ANALYSIS
TRANSIENT ANALYSIS
SPECTRUM ANALYSIS
CFD.

DECLARATION
I here by given above information are true to my best knowledge

PLACE:
DATE: SIGNATURE


PROJECT ABSTRACT


One of the problems limiting the aircraft performance, especially that of combat aircraft are aero elastic instabilities such as wing divergence and flutter. Of these two, flutter is more severe since modern combat aircraft usually have swept back wings. Our project aim is to determine the reaction forces and moments at the wing fuselage intersection when the classical bending-torsion flutter occurs. Using ANSYS-FLOTRAN package the analysis of 2-dimensional airfoil section such as “test case and naca-0009” sections under the incompressible flow, which holds good agreement results. After the validation of Computational Fluid Dynamics (CFD) results the analysis is switched over to compressible flow on 2-dimensional typical section of aircraft wing at the flutter speed. From that the unsteady lift forces and moments were calculated per unit span.

Using ANSYS-STRUCTURAL, In modal analysis the frequency of free vibration of flexure and torsion modes were calculated (these two modes of combined vibration prevails the flutter). In harmonic analysis, the lift force and moment are applied to vibrate the wing at flutter conditions and flutter frequency was found. In transient analysis, the displacement along the lateral and longitudinal axes was found. In spectrum analysis for the flutter frequency and displacements the reaction forces and moments at fixed support (wing-fuselage intersection) were found.



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