Aircraft Under Floor Structure

A history of aircraft structures from the early beginnings of wire and brace structures to semi monocoque and modern sandwich construction.

Aircraft under floor structure.

Aircraft structures being extremely flexible are prone to distortion under load. Structural elements such as pyramid frustums and reinforcements are arranged on the beams. When these loads are caused by aerodynamic forces which themselves depend on the geometry of the structure and the orientation of the various structural components to the. I am going to do an intensive research on load transfer structure using aircraft structure from engineering book and i am going to explain.

Wood structures are made strong enough to offset this loss but the extra beef means a weight penalty. So components are attached to the structure with bonding straps to ensure that components are have the same electrical potential and that a low resistance path is available for current. A subfloor structure of an aircraft airframe particularly of a helicopter includes longitudinal beams and crossbeams that intersect each other and are interconnected to form a grid that is fixedly attached to the floor and the bottom skin of the aircraft fuselage. If the primary structure fails the aircraft won t be capable of flying anymore.

The major structural components refer to the primary structure of an aircraft. Airplane airplane materials and construction. Design analysis and optimization of fuselage floor beam. Wood is also subject to attack by fungus minute plants that grow and feed on wood cells when the wood s moisture content rises above 20 percent.

It can lead to complete structural damage. At the lower speeds then obtainable streamlining was not a primary consideration and many wires struts braces and other devices were used to provide the necessary structural strength. The construction of aircraft fuselages evolved from the early wood truss structural arrangements to monocoque shell structures to the current semi monocoque shell structures. For reasons of availability low weight and prior manufacturing experience most early aircraft were of wood and fabric construction.

The optimized floor beam model is then statically analyzed to find the maximum stress von mises stress maximum von mises stress is below the allowable or yield stress 200mpa and hence the designed optimized cfrp. Megson in aircraft structures for engineering students fifth edition 2013. Ideally wood used in aircraft structures should have a moisture content between 10 and 12 percent. In this construction method strength and rigidity are obtained by joining tubing steel or aluminum to produce a series of triangular shapes called trusses.