How to derive boundary condition for fuselage fe analysis. 1

[lingot123]

Dear Friends, I am new for aerospace structural analysis ( Like fuselage and wings).Though I am not new for finite element analysis, I am using it last from 10 years. I am doing FE analysis for fuselage, I have taken care of types of element to be used perfectly. Now how and where to apply forces and boundary condition to get the static analysis results.pls help me.

 

[amorrison]

See

thread404-188619

 

[lingot123]

Thank you very much. But I think this information is not enough,do you have some case study report?

 

[amorrison]

This may be useful for the download it contains.

thread2-217844

 

[rb1957]

a common approach is the model the fuselage, apply the internal (inertia) loads, apply the aero-loads (to the fuse and the H.Stab), and hold onto the model at the wing pick ups (just like the real 'plane).

if you've already calculated the wing interface loads, then you've got something to compare these constraint reactions to.

alternatively, you could apply a balancing set of loads and reactions to the fuselage model, and you need to constrain the 6 rigid body motions (constrain 1 node in all 6 dofs (not recommended IMHO), constrain 3 nodes with a combination of force constrinats to react the 6 dofs (ie XYZ at one, YZ at another, Z at the 3rd ... or some combination like that depending on how your nodes are positioned). the nodes should be in reasonably rigid pieces of the structure, ie not the canopy roof. you should check your output to ensure that these rigid constrinats are not reacting significant load.