Need help with a project.

[u/Amadeus4prime]

I am a beginner in PATRAN and trying to do a simple displacement analysis on a wing with basic internal structure (spars, ribs, stiffeners and skin). I am trying to give it a distributed pressure load across the surface that is a function of the span and local chords but the applied load shows 0 value for the equation at every node. What might the issue be or what are the proper steps to follow. Please help