I'm trying to find the displacements of the centre of an access cover relative to the fixings around it's edge. The access cover is modelled on a FEM of the full wingbox but my problem is the deflection caused by global wing bending 'swamp' the local deflections on the access panel. How can I remove these global wing bending effects so I can find the local deflections on the access panel caused by the applied air pressures, thermal and wing bending strains?
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