Team members:

1. Alok Kumar Sahoo

2. Kshitij

3. Arpit

Introduction:

We all have always wonder atleast once that how do aircrafts fly and wish if we would have been able to fly. But to fly the most important factor is wings, a lot of studies are carried out before it can used in an aircraft, which can not only fly but fly efficiently. Our main in this project is is to determine the dynamic characteristics of aircraft wing such as natural frequency and mode shapes. For this we have performed Modal Analysis using Ansys.

 

What exactly is modal analysis?

Modal Analysis is the understanding of how a structure or system naturally vibrates or moves when subjected to external forces or disturbances. By identifying these natural frequencies and mode shapes, engineers can assess the stability, response, and performance of the structure or system, and optimize its design to meet desired criteria such as reducing vibrations or improving structural integrity.

 

Softwares used:

1. Fusion

2. Ansys

 

Theoretical Learning:

There can be a number of aircraft geometries but in our case we used trapezoidal shaped aircraft wing. And for airfoil we've used NACA 2424, these characteristics are the aircraft wing of X-47B unmanned combat air vehicle (UCAV). 

Now for calculations we've used taper's ratio as 0.45 for optimal conditions and used aspect ratio as 3.26.

 

 

 

 

 

 

 

 

 

 

 

Now, using the assumed values of taper's ratio and aspect ratio we've calculated the geometric dimensions of the aircraft wing that is to be used for designing purposes.

We assumed Cr as 1 and got  Ct as 0.45 from the above formula and observations, then we got b/2 or wing's length as 1.181m.

This was the theoretical learning required for basic designing of an aircraft wing.

Procedure:

The whole procedure of the project has been divided into two parts:

1. Designing of Aircraft wing

       2. Modal analysis of Aircraft wing 

 1. Designing of the wing:

        For the designing of our wing we have used Fusion. So, as we are using NACA for our reference, we've downloaded the dat file of NACA 2424          airfoil and as per the calculations taking trapezoidal wing as a reference the wing length came outto be 1.181m. using these two data we've created the basic geometry of the aircraft wing, then solid wing like structure we've created using loft tool. Spars are added using loft and for ribs first we've created different surfaces all across the wing using pattern feature. Ribs are modified by creating shells cutting sections in the body and then used surface loft and patch for planes previously created.

Step by step guide attached be

 

 

2. Modal Analysis of wing:

First we've imported the cad file for wing from Fusion to Ansys to perform Modal analysis. But before importing cad file to Ansys we did pre analysis on Fusion's simulation workspace to avoid any error while importing. The material that we used is Aluminium. Then we've imported to Ansys Mechanical and then the meshing(edge sizing is done at the wing ends to create a uniform mesh). Now, fixed supports were created at the root chord of wing and 6 different studies were created for 6 different mode shapes. Now we ran modal analysis on the wing and got the results, which is attached below.

Step wise guide is given below:

 

 

 

 

Results:

So, after running Modal anlysis of NACA 2424 on Ansys we got the following results.

 

 

 

 

 

 

 

 

 

 

And the mode shapes corresponding to respective frequency given below.

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Google meet link for the project: Click here!

References: