An Analytical-Based Lightning-Induced Damage Model for an Aircraft Wing Exposed to Pressure Loading of Lightning

Algorithm 1

The pseudocode for application of DTM ( is a tolerance value, BC: boundary condition).

Step 1. Read the data

Step 2. Compute coefficeints a, b, c, d.

Step 3. Set

    For

       Compute

       Compute

    End

    For

       Compute BC1

       Compute BC2

       Compute BC3

    End

Step 4. Solve the following system of equations:

Step 5. Check the convergence of the solution of the system given in Step 4.

 where the jth estimated vibration frequency corresponding to n,

  the jth estimated vibration frequency corresponding to n − 1.

 If iterative refinement is needed, go back to Step 5.

Step 6. Select the real parts of the vibration frequencies obtained in Step 5 as the resulting vibration frequencies.

Step 7. Compute the vibration mode shapes and by using inverse transformation functions.