AEROPLANE STRUCTURE

The goal of aeroplane design and construction is to obtain maximum efficiency, combined with adequate strength. Excess strength requires excess weight and therefore lowers the efficiency of the aeroplane by reducing its speed and the amount of useful load it can carry.

The required structural strength is based on the aeroplane's use. An aeroplane which is to be used only for normal flying is not expected to be subjected to the excessive strains of aerobatic manoeuvres and therefore will not need to be as strong as an aeroplane intended for aerobatic flight or other special purposes involving severe in-flight stresses. Information about limitations of each aeroplane is made available to the pilot through markings on instruments, signs on the instrument panels, operating limitations attached to airworthiness certificates, or aeroplane flight manuals carried in the aeroplane.

Aeroplane strength is measured basically by the total load which the wings are capable for carrying without permanent damage. The load imposed upon the wings depends very largely upon the type of flight in which the aeroplane is engaged. The wing must support not only the weight of the aeroplane but also the additional loads imposed during manoeuvres such as turns and pullouts from dives. Turbulence also imposes additional loads.