Design the two types of wings using inventor or Nx software, with internal structure design then using Nx we try to develop the actual stress analysis on both the wings. analysis the stress concentration on each models and compare both .try to modify the internal structure to reduce the overall stress concentration .this is the actual working plan of my project
Body
Methodology
Design and comparison of wings in nx and simulation in nx compare the stress concentration of two models.
Body consist of different parts:
Explain the two different wings model, its application and some other data.
Explain the stress and other factor influences in aircraft wings.
Literature review
Explanation on the design and simulation parts
Analysis and comparison
Result &future plans its includes the stress graph & all
Design A320 & A380
For designing am going to take the airfoil coordinates of these two wings
Conclusion
Compare the stress concentration in the each model. As a bench mark I will use the previous research reports and findings. Before analysing the results I will research on the allowable stress concentration on the wings. Then benchmark these readings and discus the results.
Demonstrate how u get the dimensions of wings to draw.
Air foil coordinate values are available in the NASA database (http://airfoiltools.com/airfoil/details?airfoil=a18-il) and transferred in excel. Before that we need to find the NASA air foil coordinates for A320 and A380. Air foil design and development will carried out in the inventor software.
Sketch outline of program (project plan)
Collect the data required to design the model.
Design of wing of both A320 & A380.
Development of internal structural frame.
Analyse the structure using ANSYS or NX UNIGRAPHICS
All the boundary conditions and loading conditions are similar to the real life situations.
Compare the analysed results.
How u going to do it?
Collection of air foil coordinate values from the NASA database.
Design and simulation using inventor, NX, and ANSYS.
Result expected?
Compare the stress concentration in the each model. As a bench mark I will use the previous research reports and findings. Before analysing the results I will research on the allowable stress concentration on the wings. Then benchmark these readings and discus the results.
