Nov 6, 2021 · How should I decide the locations of these stringers within the top and bottom skins of the aircraft's wing and fuselage? P.S: I can conduct a FEA for the wing + various shapes of these stringers, but it will take too much time. I believe there exists a rule of thumb for the choice of each stringer shape depending on somethings.

Aug 24, 2021 · However still the local bending modes of the wingskin are seen where seen. So what is the appropriate spar-rib-stringer spacing and their thicknesses and the wingksin thickness so as to obtain the expected normal modes of a wing? My wing is a sweptback wing with 30deg sweep angle, taper ratio of 0.6, span of 2m, and made of NACA0012 airfoil.

May 20, 2018 · When aircraft have broken fuselages on hard landings (Boeing did it on their company 717 -formerly DC-9 - on hard landing testing and an Embraer 145 broke its back on landing in Brazil about 15 years ago - they did an excellent job keeping it out of the media) they fail in compression buckling right at that stress peak point.

May 11, 2023 · So we see shapes which have lots of discontinuities in the flange area for ease in manufacturing. My question is - is it the most ideal shape for a rib keeping manufacturing ease and stringer requirements aside? In an aircraft with carbon fibre sandwich skin, would ribs with complete flanges be more suitable? vs

Mar 2, 2016 · The main difference between the two is the way the loads are carried by the aircraft structure. The earliest aircraft had an underlying truss structure that carried the load, with fabric covering this load bearing skeleton. The outer shell carried no loads and from the structural viewpoint, was basically dead weight.

Aug 31, 2018 · When you have a thin sheet that is put under a shearing load like a spar web as shown, the sheet, being flexible, has very little resistance to bending under compression out of its surface plane (or buckling) at which point its ability to resist the shear force is lost.

Nov 10, 2017 · $\begingroup$ @mins No, that's not even close. Maybe I wasn't clear. If you scaled a standard 355mL beverage can proportionally to a cylinder of diameter equal to the fuselage of something like a B737 (imagine exactly a pop can the size of an aircraft), you would find that the pop can would have a wall thickness several times (2-4) thicker than the aircraft.

Oct 2, 2015 · In the case of pressurized aircraft, the best option structurally is to have a circular fuselage, but in order to have a useful internal space, an elliptical or 'double bubble' design is used, with an outer circular section and divided internal sections, like the A380. Source: EADS

Jan 27, 2024 · If you're going to build from carbon fibre, you generally aren't going to bother with a very "old fashioned" structural method like tube and fabric; you're going to go with the natural advantages of composite construction by building a monocoque structure with carbon cloth and roving instead of fibreglass, and if you're really smart, Graphlite pulltruded carbon rod for key …

Mar 28, 2017 · Boeing has said that the 787 is as easy to repair as traditional aluminum skin aircraft. One case in point is the Ethiopian Airlines aircraft ET-AOP damaged by fire. The procedure to fix it is to cut out the carbon fiber material and put a …