Dummy

Part-A:
1. You are presented with a section of fuselage comprising of Aluminium alloy beams. The main beam shows signs of stress due to bending. Your team deduced that from the position of the section at the scene and the fuselage outer skin being intact it was not caused by the impact. Your remit it to determine the magnitude and distribution of the bending moments and stress for the beam. The design confirms for your calculations it can be considered as a “ Simply Supported Beam “
Your results will be used by colleagues to compare against the design requirements which included a FoS.
The Beam section is 10 Metres in length. With a UDL of 2.5 kNm and its maximum design loading of 8kN is located centrally as a point load where it acts as a part support for the main wing spar.
Your brief is to produce the calculations and diagrams to illustrate your findings when...