Shear and Bending Moment Diagram for Wing Spar
I am trying to analyze the stresses experienced by a tube that is used to carry loads from a UAV’s wings to the fuselage. This tube is permanently fastened to the fuselage and is inserted into the aircraft wing which has an opposing tube of slightly greater diameter inside, forming a tight concentric fit (other internal wing structure not shown).
I have the Nx, Ny, Nz shear loads (units of lbs) and the Mx, My, Mz bending loads (ft-lbs) that were generated at different station line intervals from the root of the wing all the way to the tip at 25% chord, which is roughly where my tube sits.
I understand a wing spar pretty much mimics a beam problem, but the part that’s tripping me up is that the structure I am interested in analyzing is only the tube coming from the fuselage (black), but the loads of the entire wing are experienced by this tube. How do I collect all these loads on the section of the tube that is concentric with the wing? I believe from there I can do a standard shear and bending diagram to look at the internal stresses.
Looking forward to your insight!
