Design and Analysis of Aluminium Matrix Composite Aircraft …
59
Fig. 8 Von-misses strain
Fig. 9 Velocity contour over the wing
5 Conclusion
As per the design requirements, a wing has been modelled in CATIA. Material
properties of LM6 and fly ash has been given to it. The structural analysis and flow
analysis was carried out in ANSYS. Wing has been analysed in finite element analysis
and has been found that maximum deformation acting over the wing for the load of
20,000 N is 0.679 m. Similarly, stress and strain distribution have also been seen
in finite element analysis. It has been seen that maximum strain was found to be
0.036 m/m and maximum stress was 7.25e9 pa.
59
Fig. 8 Von-misses strain
Fig. 9 Velocity contour over the wing
5 Conclusion
As per the design requirements, a wing has been modelled in CATIA. Material
properties of LM6 and fly ash has been given to it. The structural analysis and flow
analysis was carried out in ANSYS. Wing has been analysed in finite element analysis
and has been found that maximum deformation acting over the wing for the load of
20,000 N is 0.679 m. Similarly, stress and strain distribution have also been seen
in finite element analysis. It has been seen that maximum strain was found to be
0.036 m/m and maximum stress was 7.25e9 pa.