Boeing Gang Plank Modeling The panels are 72 inches long by 14 inches wide constructed with 1.88 inch commercial grade aluminum honeycomb core with 3/8 inch cell and .0025 inch faced with 5052-H32 aluminum sheet of .040 inch thickness. The panel is capped on all sides with edge stiffening beams of 2 x 1.5 x .0625 wall aluminum channel. The panel was analyzed in two ways to determine deflections and stresses. The first method used a finite difference model of a flat plate to determine deflections. Symmetry in geometry and loading allowed one quarter of the plate to be analyzed using 20 node points. The mathematical basis for this analysis is taken from "S. Timoshenko, Theory of Plates and Shells." The second method utilizes classical beam theory for the determination of stresses in the faces and core. Loading Initially, a line load of 400 lbs. was applied to the center of the span using both analysis methods. Next, a 2000 lb. line load was applied to the finite difference model. Finally, the beam model was used to determine the load required to produce failure of the panel. Summary The 400 lb. live load predicts a maxium deflection in the neighborhood of 0.200 inch. This is within the 0.25 inch requirement from Boeing. The safety factor for yielding failure of the faces is 5.54. The 2000 lb. load predicts a maximum deflection of approximately 1.0 inch. Yield failure of the faces is predicted under a load of 2300 lbs. This is beyond the 2000 lb. required by Boeing. This analysis predicts that the panel will perform within the parameters set by the customer. If you have any questions, feel free to contact us. return to top

Paneltec                                          1218 Commerce Court                                    Lafayette, Colorado 80026-9536                                                303.664.1420                                                800.466.3914                                             fax: 303.664.1430                                     email: info@Panelteccorp.com

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