Aircraft Forward Section Floor Structure

When subjected to a structural load at its far unsupported end the cantilever carries the load.

Aircraft forward section floor structure.

A structure constructed on a coast as part of a coastal defense system or to protect an anchorage from the effects of weather and longshore drift. 14 cfr subpart c section 25 561. The athwartship structure consists of transverse frames and floors. Many manufacturers consider the center line of the aircraft to be a zero station.

Aircraft fuselages consist of thin sheets of material stiffened by large numbers of longitudinal stringers together with transverse frames. International journal of aerospace and mechanical engineering volume 2 no 6 december 2015. Looking at the image above let us say the pilots are able to land this aircraft with wheels up in an emergency situation. Aircraft structure and also replace the current aluminium c56 floor beam by future cfrp floor beam in order to obtain better performance as well as to reduces the weight of the aircraft structure.

The floors run outboard from the keel to the turn of the bilge where the bottom turns upward. They land it on its belly and on a stretch of flat land can be a body of water as well. Load supporting aircraft flooring systems preferably are provided with a longitudinally separated series of transverse bridges having an upper doubler flange which defines latitudinally separated upper openings and a latitudinally separated series of beams which include an upper flange and. Structures systems and methods provide a load bearing aircraft flooring within an aircraft s fuselage.

Like other structural elements a cantilever can be formed as a beam plate truss or slab. Various numbering systems are used to facilitate the location of specific wing frames fuselage bulkheads or any other structural members on an aircraft. This is where they are attached. A structure built on the forecastle of a ship intended to divert water away from the forward superstructure or gun mounts.

To locate structures to the right or left of the center line of an aircraft a similar method is employed. Generally they carry bending moments shear forces and torsional loads which induce axial stresses in the stringers and skin together with shear stresses in the skin. Manufacturers use some system of station marking. The optimized floor beam model is then statically analyzed to find the maximum stress von mises stress.

Megson in aircraft structures for engineering students fifth edition 2013. Ultimate loads 9 0g fwd inertia load factor. Loss of structural integrity during flight can be caused by. An integrated floor for an aircraft fuselage includes a composite panel forming a floor surface and composite beams bonded to the floor panel.

The beams extend longitudinally within the fuselage and support the floor.