Aircraft Under Floor Structure

Aircraft structures being extremely flexible are prone to distortion under load.

Aircraft under floor structure. In this construction method strength and rigidity are obtained by joining tubing steel or aluminum to produce a series of triangular shapes called trusses. Design analysis and optimization of fuselage floor beam. The aluminium structure of the aircraft is used as a ground path for electrical devices. Simulation of helicopter under floor structure impact on water article in international journal of crashworthiness 6 3 425 443 january 2001 with 43 reads how we measure reads.

As an undergraduate studying aerospace engineering i have to say this blog is a great resource for gaining extra history and. 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. 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.

Structural elements such as pyramid frustums and reinforcements are arranged on the beams. 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 major structural components refer to the primary structure of an aircraft. It can lead to complete structural damage.

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. Ideally wood used in aircraft structures should have a moisture content between 10 and 12 percent. 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. Airplane airplane materials and construction.

A history of aircraft structures from the early beginnings of wire and brace structures to semi monocoque and modern sandwich construction. I am going to do an intensive research on load transfer structure using aircraft structure from engineering book and i am going to explain. For reasons of availability low weight and prior manufacturing experience most early aircraft were of wood and fabric construction. Wood structures are made strong enough to offset this loss but the extra beef means a weight penalty.