alex2000junio
Student
I'm working on my final college project on composite materials and studying one of the standard models provided by NASA CRM. I'll be conducting a buckling study in FEMAP on the upper wing surface.
To do this, I first need to apply the loads. For the loads, I'm doing the following: I'll consider and calculate the trim state (calculating the lift, thrust, drag, and weight so that their sum equals zero). For the force distribution, I'll use the Stender (Schrenk) method. I only need to consider the wing loads, as the rest of the aircraft model won't be developed.
Since the focus of my work is composite materials and their behavior under buckling, I'm considering this simplification and using these loads and this distribution method. Although I have experience with simulation, I don't have it with aircraft loads, and I wanted to know if considering only these loads is a valid simplification. If not, could you please point me to the load I have to consider and maybe some bibliographical references, as I'm a bit lost.
Any help I'll appreciate!
To do this, I first need to apply the loads. For the loads, I'm doing the following: I'll consider and calculate the trim state (calculating the lift, thrust, drag, and weight so that their sum equals zero). For the force distribution, I'll use the Stender (Schrenk) method. I only need to consider the wing loads, as the rest of the aircraft model won't be developed.
Since the focus of my work is composite materials and their behavior under buckling, I'm considering this simplification and using these loads and this distribution method. Although I have experience with simulation, I don't have it with aircraft loads, and I wanted to know if considering only these loads is a valid simplification. If not, could you please point me to the load I have to consider and maybe some bibliographical references, as I'm a bit lost.
Any help I'll appreciate!