AE 1350Topics to be StudiedImportance of Weight and IntegrityDevelopment of Aircraft StructuresEarlier Wood ConstructionsElements of Aircraft StructuresSpars and RibsStress s, Strain e and Young’s Modulus ESlide 9Some DefinitionsExample of Skin BucklingFatigueMaterialsSlide 14FAR CriteriaAE 1350Lecture Notes #12Topics to be Studied•Importance of Structural Weight and Integrity•Development of Aircraft Structures•Elements of Aircraft Structures•Importance of Fatigue•Materials•LoadsImportance of Weight and Integrity•Aircraft cost, take-off and landing distances are all directly dependent on empty weight of the aircraft.•A pound of structural weight saved is a pound of payload that can be carried.•Structures must be strong enough to either–fail safe : Will not fail during the life of the component–safe fail: If a component fails, an alternate load path must be available to carry the loads, so that no single failure will be hazardous to the aircraft/spacecraft.Development of Aircraft Structures•Early aircraft were built with light wood, tension wire, and fabric. (See figures 18-1, 18-2).•Next step was the substitution of metal for wood. Steel and aluminum were used around 1920. •External bracing and struts slowly disappeared. Drag decreased.•In earlier designs, the skin did not carry any load. Later designs relied on skins, stiffened with stiffeners or stringers to carry some of the load (Figures 18.3, 18.4)•The skin thickness varied from root to tip of a wing, to reduce the weight.•Fail safe design was achieved by using multiple spars - an I beam that runs from the root to tip of a wing.Earlier Wood ConstructionsElements of Aircraft Structures•Three common structural elements are used: skins, stiffeners, and beams.•Materials may experience both tension, and compression. Compression can cause the elements to buckle.•Structural analyses (to be covered in AE 2120, 3120, 3121, 4120) may be used to compute these loads.•Many of these calculations are automated.Spars and RibsStress , Strain  and Young’s Modulus EHere F is the force, A is the area of cross sectionYoung's Modulus for Typical Materials Material Modulus (GPa)Metals: Tungsten (W) 406 Chromium (Cr) 289Berylium (Be) 200 - 289 Nickel (Ni) 214Iron (Fe) 196 Low Alloy Steels 200 - 207Stainless Steels 190 - 200 Cast Irons 170 - 190Copper (Cu) 124 Titanium (Ti) 116Brasses and Bronzes 103 - 124 Aluminum (Al) 69Polymers: Polyimides 3 - 5 Polyesters 1 - 5Nylon 2 - 4 Polystryene 3 - 3.4Polyethylene 0.2 -0.7 Rubbers 0.01-0.1Some Definitions•Stress: Axial Force applied to an element (beam, stiffener or skin ) divided by its cross sectional area.•Strain: Linear deformation of the element divided by its original length/size.•Young’s Modulus, E: Stress/Strain•I : Moment of inertia of the cross section •A rod of length L will buckle if the critical load exceeds 2EI/L2Example of Skin BucklingFatigue•Structural fatigue occurs when an element is subjected to repeated application and removal of loads.–e.g. Wing experiencing unsteady gusts.•The number of load cycles a material can tolerate depends on the stress level (See figure 18-10).•Smaller cross sections, will have higher stresses, easily fail.•Structural analyses can identify “hot spots” where fatigue will first occur.Materials•Aluminum (80%), steel (17%) and titanium (3%) are used for load carrying elements (spars, stiffeners, skins).•Graphite and Boron composite materials are commonly used for their light weight, in non-load carrying parts- flaps, spoilers, fuel tanks, etc.•All composite aircraft are being built. See figure 18-14 that compares these different materials.•Many of these materials, and composites in particular, lose their strength at high temperatures.FAR Criteria•FAR-23 criteria (general aviation aircraft), and FAR-25 criteria (transport aircraft) require that the structure must be designed to withstand load factor “n” (n = Total Lift/Aircraft Weight) above 2.5.•Military aircraft may have to meet n above 7 or 8. •Use the formula–n = 2.1 + 24000/(W+10000)to determine the load factor the aircraft must meet. Here W is the design maximum take-off weight in