Hello to everybody,
I need to calculate the internal loads, on several wing sections, arising during a flexible aircraft model landing simulation.
I've used the durability plugin to generate a .mdf file after the landing simulation, and, subsequently, I've run a restart simulation in Nastran (sol 112) . In order to retrieve the internal loads, I've defined a set of grids (AECOMP card), which define the downstream structure portion, and a reference monitor point (MONPNT1 card), where the resultant (integrated) bending an torsion moments acting on the structure portion are evaluated . The request to output the internal loads has been specified in the case control section of the restart file (MONITOR(IMAG)=ALL).
The monitor point technique has been adopted to evaluate the internal loads, since the FE model is a dynamic model where the stiffness and the mass properties have been defined by means of matrices (DMIG), instead of conventional elements…
Unfortunately I don't find any output in the f06 (and no specific error/warning message)...I've tried to insert the AECOMP, MONPNT1 cards, alternatively, in the original Nastran file (the one used to generate the .mnf and the .master files), or in the restart file, but the results don't change...
On the contrary, I’ve tried to output the acceleration in some structure grids (specifying the XYPUNCH ACCE RESP card in the case control), and it works: only the integrated loads seem to be a problem to retrieve…
Anyone can help me?
Thank you very much in advance,
Francesco
